[Title 40 CFR ]
[Code of Federal Regulations (annual edition) - July 1, 2012 Edition]
[From the U.S. Government Printing Office]
[[Page i]]
Title 40
Protection of Environment
________________________
Part 60 (Appendices)
Revised as of July 1, 20122
Containing a codification of documents of general
applicability and future effect
As of July 1, 2012
Published by the Office of the Federal Register
National Archives and Records Administration as a
Special Edition of the Federal Register
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Table of Contents
Page
Explanation................................................. v
Title 40:
Chapter I--Environmental Protection Agency
(Continued) 3
Finding Aids:
Table of CFR Titles and Chapters........................ 757
Alphabetical List of Agencies Appearing in the CFR...... 777
List of CFR Sections Affected........................... 787
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Cite this Code: CFR
To cite the regulations in
this volume use title,
part and appendix letter.
Thus, 40 CFR 60,
appendices refers to title
40, part 60, appendix A.
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EXPLANATION
The Code of Federal Regulations is a codification of the general and
permanent rules published in the Federal Register by the Executive
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parts covering specific regulatory areas.
Each volume of the Code is revised at least once each calendar year
and issued on a quarterly basis approximately as follows:
Title 1 through Title 16.................................as of January 1
Title 17 through Title 27..................................as of April 1
Title 28 through Title 41...................................as of July 1
Title 42 through Title 50................................as of October 1
The appropriate revision date is printed on the cover of each
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collection request.
[[Page vi]]
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What is a proper incorporation by reference? The Director of the
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(b) The matter incorporated is in fact available to the extent
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(c) The incorporating document is drafted and submitted for
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Office of the Federal Register.
July 1, 2012.
[[Page ix]]
THIS TITLE
Title 40--Protection of Environment is composed of thirty-four
volumes. The parts in these volumes are arranged in the following order:
Parts 1-49, parts 50-51, part 52 (52.01-52.1018), part 52 (52.1019-
52.2019), part 52 (52.2020-end of part 52), parts 53-59, part 60 (60.1-
end of part 60, sections), part 60 (Appendices), parts 61-62, part 63
(63.1-63.599), part 63 (63.600-63.1199), part 63 (63.1200-63.1439), part
63 (63.1440-63.6175), part 63 (63.6580-63.8830), part 63 (63.8980-end of
part 63) parts 64-71, parts 72-80, parts 81-84, part 85-Sec. 86.599-99,
part 86 (86.600-1-end of part 86), parts 87-95, parts 96-99, parts 100-
135, parts 136-149, parts 150-189, parts 190-259, parts 260-265, parts
266-299, parts 300-399, parts 400-424, parts 425-699, parts 700-789,
parts 790-999, and part 1000 to end. The contents of these volumes
represent all current regulations codified under this title of the CFR
as of July 1, 2012.
Chapter I--Environmental Protection Agency appears in all thirty-
four volumes. Regulations issued by the Council on Environmental
Quality, including an Index to Parts 1500 through 1508, appear in the
volume containing part 1000 to end. The OMB control numbers for title 40
appear in Sec. 9.1 of this chapter.
For this volume, Jonn V. Lilyea was Chief Editor. The Code of
Federal Regulations publication program is under the direction of
Michael L. White, assisted by Ann Worley.
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TITLE 40--PROTECTION OF ENVIRONMENT
(This book contains part 60, appendices)
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Part
chapter i--Environmental Protection Agency (Continued)...... 60
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CHAPTER I--ENVIRONMENTAL PROTECTION AGENCY (CONTINUED)
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Editorial Note: Nomenclature changes to chapter I appear at 65 FR
47324, 47325, Aug. 2, 2000.
SUBCHAPTER C--AIR PROGRAMS (CONTINUED)
Part Page
60 Part 60--Standards of performance for new
stationary sources (continued).......... 5
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SUBCHAPTER C_AIR PROGRAMS (CONTINUED)
PART 60_STANDARDS OF PERFORMANCE FOR NEW STATIONARY SOURCES (CONTINUED)--Table
of Contents
Appendix A-1 to Part 60--Test Methods 1 through 2F
Appendix A-2 to Part 60--Test Methods 2G through 3C
Appendix A-3 to Part 60--Test Methods 4 through 5I
Appendix A-4 to Part 60--Test Methods 6 through 10B
Appendix A-5 to Part 60--Test Methods 11 through 15A
Appendix A-6 to Part 60--Test Methods 16 through 18
Appendix A-7 to Part 60--Test Methods 19 through 25E
Appendix A-8 to Part 60--Test Methods 26 through 29
Appendix B to Part 60--Performance Specifications
Appendix C to Part 60--Determination of Emission Rate Change
Appendix D to Part 60--Required Emission Inventory Information
Appendix E to Part 60 [Reserved]
Appendix F to Part 60--Quality Assurance Procedures
Appendix G to Part 60--Provisions for an Alternative Method of
Demonstrating Compliance with 40 CFR 60.43 for the Newton
Power Station of Central Illinois Public Service Company
Appendix H to Part 60 [Reserved]
Appendix I to Part 60--Removable Label and Owner's Manual
Authority: 42 U.S.C. 7401-7601.
Source: 36 FR 24877, Dec. 23, 1971, unless otherwise noted.
Sec. Appendix A-1 to Part 60--Test Methods 1 through 2F
Method 1--Sample and velocity traverses for stationary sources
Method 1A--Sample and velocity traverses for stationary sources with
small stacks or ducts
Method 2--Determination of stack gas velocity and volumetric flow rate
(Type S pitot tube)
Method 2A--Direct measurement of gas volume through pipes and small
ducts
Method 2B--Determination of exhaust gas volume flow rate from gasoline
vapor incinerators
Method 2C--Determination of gas velocity and volumetric flow rate in
small stacks or ducts (standard pitot tube)
Method 2D--Measurement of gas volume flow rates in small pipes and ducts
Method 2E--Determination of landfill gas production flow rate
Method 2F--Determination of Stack Gas Velocity and Volumetric Flow Rate
With Three-Dimensional Probes
The test methods in this appendix are referred to in Sec. 60.8
(Performance Tests) and Sec. 60.11 (Compliance With Standards and
Maintenance Requirements) of 40 CFR part 60, subpart A (General
Provisions). Specific uses of these test methods are described in the
standards of performance contained in the subparts, beginning with
Subpart D.
Within each standard of performance, a section title ``Test Methods
and Procedures'' is provided to: (1) Identify the test methods to be
used as reference methods to the facility subject to the respective
standard and (2) identify any special instructions or conditions to be
followed when applying a method to the respective facility. Such
instructions (for example, establish sampling rates, volumes, or
temperatures) are to be used either in addition to, or as a substitute
for procedures in a test method. Similarly, for sources subject to
emission monitoring requirements, specific instructions pertaining to
any use of a test method as a reference method are provided in the
subpart or in Appendix B.
Inclusion of methods in this appendix is not intended as an
endorsement or denial of their applicability to sources that are not
subject to standards of performance. The methods are potentially
applicable to other sources; however, applicability should be confirmed
by careful and appropriate evaluation of the conditions prevalent at
such sources.
The approach followed in the formulation of the test methods
involves specifications for equipment, procedures, and performance. In
concept, a performance specification approach would be preferable in all
methods because this allows the greatest flexibility to the user. In
practice, however, this approach is impractical in most cases because
performance specifications cannot be established. Most of the methods
described herein, therefore, involve specific equipment specifications
and procedures, and only a few methods in this appendix rely on
performance criteria.
Minor changes in the test methods should not necessarily affect the
validity of the results and it is recognized that alternative and
equivalent methods exist. Section 60.8 provides authority for the
Administrator to specify or approve (1) equivalent methods, (2)
alternative methods, and (3) minor changes in the methodology of the
test methods. It
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should be clearly understood that unless otherwise identified all such
methods and changes must have prior approval of the Administrator. An
owner employing such methods or deviations from the test methods without
obtaining prior approval does so at the risk of subsequent disapproval
and retesting with approved methods.
Within the test methods, certain specific equipment or procedures
are recognized as being acceptable or potentially acceptable and are
specifically identified in the methods. The items identified as
acceptable options may be used without approval but must be identified
in the test report. The potentially approvable options are cited as
``subject to the approval of the Administrator'' or as ``or
equivalent.'' Such potentially approvable techniques or alternatives may
be used at the discretion of the owner without prior approval. However,
detailed descriptions for applying these potentially approvable
techniques or alternatives are not provided in the test methods. Also,
the potentially approvable options are not necessarily acceptable in all
applications. Therefore, an owner electing to use such potentially
approvable techniques or alternatives is responsible for: (1) assuring
that the techniques or alternatives are in fact applicable and are
properly executed; (2) including a written description of the
alternative method in the test report (the written method must be clear
and must be capable of being performed without additional instruction,
and the degree of detail should be similar to the detail contained in
the test methods); and (3) providing any rationale or supporting data
necessary to show the validity of the alternative in the particular
application. Failure to meet these requirements can result in the
Administrator's disapproval of the alternative.
Method 1--Sample and Velocity Traverses for Stationary Sources
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material is incorporated by reference from other
methods in this part. Therefore, to obtain reliable results, persons
using this method should have a thorough knowledge of at least the
following additional test method: Method 2.
1.0 Scope and Application
1.1 Measured Parameters. The purpose of the method is to provide
guidance for the selection of sampling ports and traverse points at
which sampling for air pollutants will be performed pursuant to
regulations set forth in this part. Two procedures are presented: a
simplified procedure, and an alternative procedure (see Section 11.5).
The magnitude of cyclonic flow of effluent gas in a stack or duct is the
only parameter quantitatively measured in the simplified procedure.
1.2 Applicability. This method is applicable to gas streams flowing
in ducts, stacks, and flues. This method cannot be used when: (1) the
flow is cyclonic or swirling; or (2) a stack is smaller than 0.30 meter
(12 in.) in diameter, or 0.071 m\2\ (113 in.\2\) in cross-sectional
area. The simplified procedure cannot be used when the measurement site
is less than two stack or duct diameters downstream or less than a half
diameter upstream from a flow disturbance.
1.3 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
Note: The requirements of this method must be considered before
construction of a new facility from which emissions are to be measured;
failure to do so may require subsequent alterations to the stack or
deviation from the standard procedure. Cases involving variants are
subject to approval by the Administrator.
2.0 Summary of Method
2.1 This method is designed to aid in the representative measurement
of pollutant emissions and/or total volumetric flow rate from a
stationary source. A measurement site where the effluent stream is
flowing in a known direction is selected, and the cross-section of the
stack is divided into a number of equal areas. Traverse points are then
located within each of these equal areas.
3.0 Definitions [Reserved]
4.0 Interferences [Reserved]
5.0 Safety
5.1 Disclaimer. This method may involve hazardous materials,
operations, and equipment. This test method may not address all of the
safety problems associated with its use. It is the responsibility of the
user of this test method to establish appropriate safety and health
practices and determine the applicability of regulatory limitations
prior to performing this test method.
6.0 Equipment and Supplies.
6.1 Apparatus. The apparatus described below is required only when
utilizing the alternative site selection procedure described in Section
11.5 of this method.
6.1.1 Directional Probe. Any directional probe, such as United
Sensor Type DA Three-Dimensional Directional Probe, capable of measuring
both the pitch and yaw angles of gas flows is acceptable. Before using
the probe, assign an identification number to the directional probe, and
permanently mark or engrave the number on the body of the probe. The
pressure holes of directional
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probes are susceptible to plugging when used in particulate-laden gas
streams. Therefore, a procedure for cleaning the pressure holes by
``back-purging'' with pressurized air is required.
6.1.2 Differential Pressure Gauges. Inclined manometers, U-tube
manometers, or other differential pressure gauges (e.g., magnehelic
gauges) that meet the specifications described in Method 2, Section 6.2.
Note: If the differential pressure gauge produces both negative and
positive readings, then both negative and positive pressure readings
shall be calibrated at a minimum of three points as specified in Method
2, Section 6.2.
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection, Preservation, Storage, and Transport [Reserved]
9.0 Quality Control [Reserved]
10.0 Calibration and Standardization [Reserved]
11.0 Procedure
11.1 Selection of Measurement Site.
11.1.1 Sampling and/or velocity measurements are performed at a site
located at least eight stack or duct diameters downstream and two
diameters upstream from any flow disturbance such as a bend, expansion,
or contraction in the stack, or from a visible flame. If necessary, an
alternative location may be selected, at a position at least two stack
or duct diameters downstream and a half diameter upstream from any flow
disturbance.
11.1.2 An alternative procedure is available for determining the
acceptability of a measurement location not meeting the criteria above.
This procedure described in Section 11.5 allows for the determination of
gas flow angles at the sampling points and comparison of the measured
results with acceptability criteria.
11.2 Determining the Number of Traverse Points.
11.2.1 Particulate Traverses.
11.2.1.1 When the eight- and two-diameter criterion can be met, the
minimum number of traverse points shall be: (1) twelve, for circular or
rectangular stacks with diameters (or equivalent diameters) greater than
0.61 meter (24 in.); (2) eight, for circular stacks with diameters
between 0.30 and 0.61 meter (12 and 24 in.); and (3) nine, for
rectangular stacks with equivalent diameters between 0.30 and 0.61 meter
(12 and 24 in.).
11.2.1.2 When the eight- and two-diameter criterion cannot be met,
the minimum number of traverse points is determined from Figure 1-1.
Before referring to the figure, however, determine the istances from the
measurement site to the nearest upstream and downstream disturbances,
and divide each distance by the stack diameter or equivalent diameter,
to determine the distance in terms of the number of duct diameters.
Then, determine from Figure 1-1 the minimum number of traverse points
that corresponds: (1) to the number of duct diameters upstream; and (2)
to the number of diameters downstream. Select the higher of the two
minimum numbers of traverse points, or a greater value, so that for
circular stacks the number is a multiple of 4, and for rectangular
stacks, the number is one of those shown in Table 1-1.
11.2.2 Velocity (Non-Particulate) Traverses. When velocity or
volumetric flow rate is to be determined (but not particulate matter),
the same procedure as that used for particulate traverses (Section
11.2.1) is followed, except that Figure 1-2 may be used instead of
Figure 1-1.
11.3 Cross-Sectional Layout and Location of Traverse Points.
11.3.1 Circular Stacks.
11.3.1.1 Locate the traverse points on two perpendicular diameters
according to Table 1-2 and the example shown in Figure 1-3. Any equation
(see examples in References 2 and 3 in Section 16.0) that gives the same
values as those in Table 1-2 may be used in lieu of Table 1-2.
11.3.1.2 For particulate traverses, one of the diameters must
coincide with the plane containing the greatest expected concentration
variation (e.g., after bends); one diameter shall be congruent to the
direction of the bend. This requirement becomes less critical as the
distance from the disturbance increases; therefore, other diameter
locations may be used, subject to the approval of the Administrator.
11.3.1.3 In addition, for elliptical stacks having unequal
perpendicular diameters, separate traverse points shall be calculated
and located along each diameter. To determine the cross-sectional area
of the elliptical stack, use the following equation:
Square Area=D1 x D2 x 0.7854
Where: D1=Stack diameter 1
D2=Stack diameter 2
11.3.1.4 In addition, for stacks having diameters greater than 0.61
m (24 in.), no traverse points shall be within 2.5 centimeters (1.00
in.) of the stack walls; and for stack diameters equal to or less than
0.61 m (24 in.), no traverse points shall be located within 1.3 cm (0.50
in.) of the stack walls. To meet these criteria, observe the procedures
given below.
11.3.2 Stacks With Diameters Greater Than 0.61 m (24 in.).
11.3.2.1 When any of the traverse points as located in Section
11.3.1 fall within 2.5 cm (1.0 in.) of the stack walls, relocate them
away from the stack walls to: (1) a distance of 2.5 cm (1.0 in.); or (2)
a distance equal to
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the nozzle inside diameter, whichever is larger. These relocated
traverse points (on each end of a diameter) shall be the ``adjusted''
traverse points.
11.3.2.2 Whenever two successive traverse points are combined to
form a single adjusted traverse point, treat the adjusted point as two
separate traverse points, both in the sampling and/or velocity
measurement procedure, and in recording of the data.
11.3.3 Stacks With Diameters Equal To or Less Than 0.61 m (24 in.).
Follow the procedure in Section 11.3.1.1, noting only that any
``adjusted'' points should be relocated away from the stack walls to:
(1) a distance of 1.3 cm (0.50 in.); or (2) a distance equal to the
nozzle inside diameter, whichever is larger.
11.3.4 Rectangular Stacks.
11.3.4.1 Determine the number of traverse points as explained in
Sections 11.1 and 11.2 of this method. From Table 1-1, determine the
grid configuration. Divide the stack cross-section into as many equal
rectangular elemental areas as traverse points, and then locate a
traverse point at the centroid of each equal area according to the
example in Figure 1-4.
11.3.4.2 To use more than the minimum number of traverse points,
expand the ``minimum number of traverse points'' matrix (see Table 1-1)
by adding the extra traverse points along one or the other or both legs
of the matrix; the final matrix need not be balanced. For example, if a
4 x 3 ``minimum number of points'' matrix were expanded to 36 points,
the final matrix could be 9 x 4 or 12 x 3, and would not necessarily
have to be 6 x 6. After constructing the final matrix, divide the stack
cross-section into as many equal rectangular, elemental areas as
traverse points, and locate a traverse point at the centroid of each
equal area.
11.3.4.3 The situation of traverse points being too close to the
stack walls is not expected to arise with rectangular stacks. If this
problem should ever arise, the Administrator must be contacted for
resolution of the matter.
11.4 Verification of Absence of Cyclonic Flow.
11.4.1 In most stationary sources, the direction of stack gas flow
is essentially parallel to the stack walls. However, cyclonic flow may
exist (1) after such devices as cyclones and inertial demisters
following venturi scrubbers, or (2) in stacks having tangential inlets
or other duct configurations which tend to induce swirling; in these
instances, the presence or absence of cyclonic flow at the sampling
location must be determined. The following techniques are acceptable for
this determination.
11.4.2 Level and zero the manometer. Connect a Type S pitot tube to
the manometer and leak-check system. Position the Type S pitot tube at
each traverse point, in succession, so that the planes of the face
openings of the pitot tube are perpendicular to the stack cross-
sectional plane; when the Type S pitot tube is in this position, it is
at ``0[deg] reference.'' Note the differential pressure ([Delta]p)
reading at each traverse point. If a null (zero) pitot reading is
obtained at 0[deg] reference at a given traverse point, an acceptable
flow condition exists at that point. If the pitot reading is not zero at
0[deg] reference, rotate the pitot tube (up to 90[deg] yaw angle), until a null reading is obtained.
Carefully determine and record the value of the rotation angle ([alpha])
to the nearest degree. After the null technique has been applied at each
traverse point, calculate the average of the absolute values of [alpha];
assign [alpha] values of 0[deg] to those points for which no rotation
was required, and include these in the overall average. If the average
value of [alpha] is greater than 20[deg], the overall flow condition in
the stack is unacceptable, and alternative methodology, subject to the
approval of the Administrator, must be used to perform accurate sample
and velocity traverses.
11.5 The alternative site selection procedure may be used to
determine the rotation angles in lieu of the procedure outlined in
Section 11.4.
11.5.1 Alternative Measurement Site Selection Procedure. This
alternative applies to sources where measurement locations are less than
2 equivalent or duct diameters downstream or less than one-half duct
diameter upstream from a flow disturbance. The alternative should be
limited to ducts larger than 24 in. in diameter where blockage and wall
effects are minimal. A directional flow-sensing probe is used to measure
pitch and yaw angles of the gas flow at 40 or more traverse points; the
resultant angle is calculated and compared with acceptable criteria for
mean and standard deviation.
Note: Both the pitch and yaw angles are measured from a line passing
through the traverse point and parallel to the stack axis. The pitch
angle is the angle of the gas flow component in the plane that INCLUDES
the traverse line and is parallel to the stack axis. The yaw angle is
the angle of the gas flow component in the plane PERPENDICULAR to the
traverse line at the traverse point and is measured from the line
passing through the traverse point and parallel to the stack axis.
11.5.2 Traverse Points. Use a minimum of 40 traverse points for
circular ducts and 42 points for rectangular ducts for the gas flow
angle determinations. Follow the procedure outlined in Section 11.3 and
Table 1-1 or 1-2 for the location and layout of the traverse points. If
the measurement location is determined to be acceptable according to the
criteria in this alternative procedure, use the same traverse point
number and locations for sampling and velocity measurements.
11.5.3 Measurement Procedure.
[[Page 9]]
11.5.3.1 Prepare the directional probe and differential pressure
gauges as recommended by the manufacturer. Capillary tubing or surge
tanks may be used to dampen pressure fluctuations. It is recommended,
but not required, that a pretest leak check be conducted. To perform a
leak check, pressurize or use suction on the impact opening until a
reading of at least 7.6 cm (3 in.) H2O registers on the
differential pressure gauge, then plug the impact opening. The pressure
of a leak-free system will remain stable for at least 15 seconds.
11.5.3.2 Level and zero the manometers. Since the manometer level
and zero may drift because of vibrations and temperature changes,
periodically check the level and zero during the traverse.
11.5.3.3 Position the probe at the appropriate locations in the gas
stream, and rotate until zero deflection is indicated for the yaw angle
pressure gauge. Determine and record the yaw angle. Record the pressure
gauge readings for the pitch angle, and determine the pitch angle from
the calibration curve. Repeat this procedure for each traverse point.
Complete a ``back-purge'' of the pressure lines and the impact openings
prior to measurements of each traverse point.
11.5.3.4 A post-test check as described in Section 11.5.3.1 is
required. If the criteria for a leak-free system are not met, repair the
equipment, and repeat the flow angle measurements.
11.5.4 Calibration. Use a flow system as described in Sections
10.1.2.1 and 10.1.2.2 of Method 2. In addition, the flow system shall
have the capacity to generate two test-section velocities: one between
365 and 730 m/min (1,200 and 2,400 ft/min) and one between 730 and 1,100
m/min (2,400 and 3,600 ft/min).
11.5.4.1 Cut two entry ports in the test section. The axes through
the entry ports shall be perpendicular to each other and intersect in
the centroid of the test section. The ports should be elongated slots
parallel to the axis of the test section and of sufficient length to
allow measurement of pitch angles while maintaining the pitot head
position at the test-section centroid. To facilitate alignment of the
directional probe during calibration, the test section should be
constructed of plexiglass or some other transparent material. All
calibration measurements should be made at the same point in the test
section, preferably at the centroid of the test section.
11.5.4.2 To ensure that the gas flow is parallel to the central axis
of the test section, follow the procedure outlined in Section 11.4 for
cyclonic flow determination to measure the gas flow angles at the
centroid of the test section from two test ports located 90[deg] apart.
The gas flow angle measured in each port must be 2[deg] of 0[deg]. Straightening vanes should be
installed, if necessary, to meet this criterion.
11.5.4.3 Pitch Angle Calibration. Perform a calibration traverse
according to the manufacturer's recommended protocol in 5[deg]
increments for angles from -60[deg] to +60[deg] at one velocity in each
of the two ranges specified above. Average the pressure ratio values
obtained for each angle in the two flow ranges, and plot a calibration
curve with the average values of the pressure ratio (or other suitable
measurement factor as recommended by the manufacturer) versus the pitch
angle. Draw a smooth line through the data points. Plot also the data
values for each traverse point. Determine the differences between the
measured data values and the angle from the calibration curve at the
same pressure ratio. The difference at each comparison must be within
2[deg] for angles between 0[deg] and 40[deg] and within 3[deg] for
angles between 40[deg] and 60[deg].
11.5.4.4 Yaw Angle Calibration. Mark the three-dimensional probe to
allow the determination of the yaw position of the probe. This is
usually a line extending the length of the probe and aligned with the
impact opening. To determine the accuracy of measurements of the yaw
angle, only the zero or null position need be calibrated as follows:
Place the directional probe in the test section, and rotate the probe
until the zero position is found. With a protractor or other angle
measuring device, measure the angle indicated by the yaw angle indicator
on the three-dimensional probe. This should be within 2[deg] of 0[deg].
Repeat this measurement for any other points along the length of the
pitot where yaw angle measurements could be read in order to account for
variations in the pitot markings used to indicate pitot head positions.
12.0 Data Analysis and Calculations
12.1 Nomenclature.
L=length.
n=total number of traverse points.
Pi=pitch angle at traverse point i, degree.
Ravg=average resultant angle, degree.
Ri=resultant angle at traverse point i, degree.
Sd=standard deviation, degree.
W=width.
Yi=yaw angle at traverse point i, degree.
12.2 For a rectangular cross section, an equivalent diameter
(De) shall be calculated using the following equation, to
determine the upstream and downstream distances:
[GRAPHIC] [TIFF OMITTED] TR17OC00.037
12.3 If use of the alternative site selection procedure (Section
11.5 of this method) is required, perform the following calculations
using the equations below: the resultant angle at each traverse point,
the average resultant angle, and the standard deviation. Complete the
calculations retaining at least
[[Page 10]]
one extra significant figure beyond that of the acquired data. Round the
values after the final calculations.
12.3.1 Calculate the resultant angle at each traverse point:
[GRAPHIC] [TIFF OMITTED] TR17OC00.038
12.3.2 Calculate the average resultant for the measurements:
[GRAPHIC] [TIFF OMITTED] TR17OC00.039
12.3.3 Calculate the standard deviations:
[GRAPHIC] [TIFF OMITTED] TR17OC00.040
12.3.4 Acceptability Criteria. The measurement location is
acceptable if Ravg <= 20[deg] and Sd <= 10[deg].
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
1. Determining Dust Concentration in a Gas Stream, ASME Performance
Test Code No. 27. New York. 1957.
2. DeVorkin, Howard, et al. Air Pollution Source Testing Manual. Air
Pollution Control District. Los Angeles, CA. November 1963.
3. Methods for Determining of Velocity, Volume, Dust and Mist
Content of Gases. Western Precipitation Division of Joy Manufacturing
Co. Los Angeles, CA. Bulletin WP-50. 1968.
4. Standard Method for Sampling Stacks for Particulate Matter. In:
1971 Book of ASTM Standards, Part 23. ASTM Designation D 2928-71.
Philadelphia, PA. 1971.
5. Hanson, H.A., et al. Particulate Sampling Strategies for Large
Power Plants Including Nonuniform Flow. USEPA, ORD, ESRL, Research
Triangle Park, NC. EPA-600/2-76-170. June 1976.
6. Entropy Environmentalists, Inc. Determination of the Optimum
Number of Sampling Points: An Analysis of Method 1 Criteria.
Environmental Protection Agency. Research Triangle Park, NC. EPA
Contract No. 68-01-3172, Task 7.
7. Hanson, H.A., R.J. Davini, J.K. Morgan, and A.A. Iversen.
Particulate Sampling Strategies for Large Power Plants Including
Nonuniform Flow. USEPA, Research Triangle Park, NC. Publication No. EPA-
600/2-76-170. June 1976. 350 pp.
8. Brooks, E.F., and R.L. Williams. Flow and Gas Sampling Manual.
U.S. Environmental Protection Agency. Research Triangle Park, NC.
Publication No. EPA-600/2-76-203. July 1976. 93 pp.
9. Entropy Environmentalists, Inc. Traverse Point Study. EPA
Contract No. 68-02-3172. June 1977. 19 pp.
10. Brown, J. and K. Yu. Test Report: Particulate Sampling Strategy
in Circular Ducts. Emission Measurement Branch. U.S. Environmental
Protection Agency, Research Triangle Park, NC 27711. July 31, 1980. 12
pp.
11. Hawksley, P.G.W., S. Badzioch, and J.H. Blackett. Measurement of
Solids in Flue Gases. Leatherhead, England, The British Coal Utilisation
Research Association. 1961. pp. 129-133.
12. Knapp, K.T. The Number of Sampling Points Needed for
Representative Source Sampling. In: Proceedings of the Fourth National
Conference on Energy and Environment. Theodore, L. et al. (ed). Dayton,
Dayton Section of the American Institute of Chemical Engineers. October
3-7, 1976. pp. 563-568.
13. Smith, W.S. and D.J. Grove. A Proposed Extension of EPA Method 1
Criteria. Pollution Engineering. XV (8):36-37. August 1983.
14. Gerhart, P.M. and M.J. Dorsey. Investigation of Field Test
Procedures for Large Fans. University of Akron. Akron, OH. (EPRI
Contract CS-1651). Final Report (RP-1649-5). December 1980.
15. Smith, W.S. and D.J. Grove. A New Look at Isokinetic Sampling--
Theory and Applications. Source Evaluation Society Newsletter. VIII
(3):19-24. August 1983.
17.0 Tables, Diagrams, Flowcharts, and Validation Data
[[Page 11]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.041
Table 1-1 Cross-Section Layout for Rectangular Stacks
------------------------------------------------------------------------
Number of tranverse points layout Matrix
------------------------------------------------------------------------
9...................................... 3x3
12..................................... 4x3
16..................................... 4x4
20..................................... 5x4
25..................................... 5x5
30..................................... 6x5
36..................................... 6x6
42..................................... 7x6
49..................................... 7x7
------------------------------------------------------------------------
[[Page 12]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.042
Table 1-2--Location of Traverse Points in Circular Stacks
[Percent of stack diameter from inside wall to tranverse point]
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of traverse points on a diameter
Traverse point number on a diameter -----------------------------------------------------------------------------------------------
2 4 6 8 10 12 14 16 18 20 22 24
--------------------------------------------------------------------------------------------------------------------------------------------------------
1....................................................... 14.6 6.7 4.4 3.2 2.6 2.1 1.8 1.6 1.4 1.3 1.1 1.1
2....................................................... 85.4 25.0 14.6 10.5 8.2 6.7 5.7 4.9 4.4 3.9 3.5 3.2
3....................................................... ...... 75.0 29.6 19.4 14.6 11.8 9.9 8.5 7.5 6.7 6.0 5.5
4....................................................... ...... 93.3 70.4 32.3 22.6 17.7 14.6 12.5 10.9 9.7 8.7 7.9
5....................................................... ...... ...... 85.4 67.7 34.2 25.0 20.1 16.9 14.6 12.9 11.6 10.5
[[Page 13]]
6....................................................... ...... ...... 95.6 80.6 65.8 35.6 26.9 22.0 18.8 16.5 14.6 13.2
7....................................................... ...... ...... ...... 89.5 77.4 64.4 36.6 28.3 23.6 20.4 18.0 16.1
8....................................................... ...... ...... ...... 96.8 85.4 75.0 63.4 37.5 29.6 25.0 21.8 19.4
9....................................................... ...... ...... ...... ...... 91.8 82.3 73.1 62.5 38.2 30.6 26.2 23.0
10...................................................... ...... ...... ...... ...... 97.4 88.2 79.9 71.7 61.8 38.8 31.5 27.2
11...................................................... ...... ...... ...... ...... ...... 93.3 85.4 78.0 70.4 61.2 39.3 32.3
12...................................................... ...... ...... ...... ...... ...... 97.9 90.1 83.1 76.4 69.4 60.7 39.8
13...................................................... ...... ...... ...... ...... ...... ...... 94.3 87.5 81.2 75.0 68.5 60.2
14...................................................... ...... ...... ...... ...... ...... ...... 98.2 91.5 85.4 79.6 73.8 67.7
15...................................................... ...... ...... ...... ...... ...... ...... ...... 95.1 89.1 83.5 78.2 72.8
16...................................................... ...... ...... ...... ...... ...... ...... ...... 98.4 92.5 87.1 82.0 77.0
17...................................................... ...... ...... ...... ...... ...... ...... ...... ...... 95.6 90.3 85.4 80.6
18...................................................... ...... ...... ...... ...... ...... ...... ...... ...... 98.6 93.3 88.4 83.9
19...................................................... ...... ...... ...... ...... ...... ...... ...... ...... ...... 96.1 91.3 86.8
20...................................................... ...... ...... ...... ...... ...... ...... ...... ...... ...... 98.7 94.0 89.5
21...................................................... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... 96.5 92.1
22...................................................... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... 98.9 94.5
23...................................................... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... 96.8
24...................................................... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... 99.9
--------------------------------------------------------------------------------------------------------------------------------------------------------
[GRAPHIC] [TIFF OMITTED] TR17OC00.043
Method 1A--Sample and Velocity Traverses for Stationary Sources With
Small Stacks or Ducts
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material is incorporated by reference from other
methods in this part. Therefore, to obtain reliable results, persons
using this method should have a thorough knowledge of at least the
following additional test method: Method 1.
1.0 Scope and Application
1.1 Measured Parameters. The purpose of the method is to provide
guidance for the selection of sampling ports and traverse points at
which sampling for air pollutants will be performed pursuant to
regulations set forth in this part.
1.2 Applicability. The applicability and principle of this method
are identical to Method 1, except its applicability is limited to stacks
or ducts. This method is applicable to flowing gas streams in ducts,
stacks, and flues of less than about 0.30 meter (12 in.) in diameter, or
0.071 m\2\ (113 in.\2\) in cross-sectional area, but equal to or greater
than about 0.10 meter (4 in.) in diameter, or 0.0081 m\2\ (12.57 in.\2\)
in cross-sectional area. This method cannot be used when the flow is
cyclonic or swirling.
1.3 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
[[Page 14]]
2.0 Summary of Method
2.1 The method is designed to aid in the representative measurement
of pollutant emissions and/or total volumetric flow rate from a
stationary source. A measurement site or a pair of measurement sites
where the effluent stream is flowing in a known direction is (are)
selected. The cross-section of the stack is divided into a number of
equal areas. Traverse points are then located within each of these equal
areas.
2.2 In these small diameter stacks or ducts, the conventional Method
5 stack assembly (consisting of a Type S pitot tube attached to a
sampling probe, equipped with a nozzle and thermocouple) blocks a
significant portion of the cross-section of the duct and causes
inaccurate measurements. Therefore, for particulate matter (PM) sampling
in small stacks or ducts, the gas velocity is measured using a standard
pitot tube downstream of the actual emission sampling site. The straight
run of duct between the PM sampling and velocity measurement sites
allows the flow profile, temporarily disturbed by the presence of the
sampling probe, to redevelop and stabilize.
3.0 Definitions [Reserved]
4.0 Interferences [Reserved]
5.0 Safety
5.1 Disclaimer. This method may involve hazardous materials,
operations, and equipment. This test method may not address all of the
safety problems associated with its use. It is the responsibility of the
user of this test method to establish appropriate safety and health
practices and determine the applicability of regulatory limitations
prior to performing this test method.
6.0 Equipment and Supplies [Reserved]
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection, Preservation, Storage, and Transport [Reserved]
9.0 Quality Control [Reserved]
10.0 Calibration and Standardization [Reserved]
11.0 Procedure
11.1 Selection of Measurement Site.
11.1.1 Particulate Measurements--Steady or Unsteady Flow. Select a
particulate measurement site located preferably at least eight
equivalent stack or duct diameters downstream and 10 equivalent
diameters upstream from any flow disturbances such as bends, expansions,
or contractions in the stack, or from a visible flame. Next, locate the
velocity measurement site eight equivalent diameters downstream of the
particulate measurement site (see Figure 1A-1). If such locations are
not available, select an alternative particulate measurement location at
least two equivalent stack or duct diameters downstream and two and one-
half diameters upstream from any flow disturbance. Then, locate the
velocity measurement site two equivalent diameters downstream from the
particulate measurement site. (See Section 12.2 of Method 1 for
calculating equivalent diameters for a rectangular cross-section.)
11.1.2 PM Sampling (Steady Flow) or Velocity (Steady or Unsteady
Flow) Measurements. For PM sampling when the volumetric flow rate in a
duct is constant with respect to time, Section 11.1.1 of Method 1 may be
followed, with the PM sampling and velocity measurement performed at one
location. To demonstrate that the flow rate is constant (within 10
percent) when PM measurements are made, perform complete velocity
traverses before and after the PM sampling run, and calculate the
deviation of the flow rate derived after the PM sampling run from the
one derived before the PM sampling run. The PM sampling run is
acceptable if the deviation does not exceed 10 percent.
11.2 Determining the Number of Traverse Points.
11.2.1 Particulate Measurements (Steady or Unsteady Flow). Use
Figure 1-1 of Method 1 to determine the number of traverse points to use
at both the velocity measurement and PM sampling locations. Before
referring to the figure, however, determine the distances between both
the velocity measurement and PM sampling sites to the nearest upstream
and downstream disturbances. Then divide each distance by the stack
diameter or equivalent diameter to express the distances in terms of the
number of duct diameters. Then, determine the number of traverse points
from Figure 1-1 of Method 1 corresponding to each of these four
distances. Choose the highest of the four numbers of traverse points (or
a greater number) so that, for circular ducts the number is a multiple
of four; and for rectangular ducts, the number is one of those shown in
Table 1-1 of Method 1. When the optimum duct diameter location criteria
can be satisfied, the minimum number of traverse points required is
eight for circular ducts and nine for rectangular ducts.
11.2.2 PM Sampling (Steady Flow) or only Velocity (Non-Particulate)
Measurements. Use Figure 1-2 of Method 1 to determine number of traverse
points, following the same procedure used for PM sampling as described
in Section 11.2.1 of Method 1. When the optimum duct diameter location
criteria can be satisfied, the minimum number of traverse points
required is eight for circular ducts and nine for rectangular ducts.
[[Page 15]]
11.3 Cross-sectional Layout, Location of Traverse Points, and
Verification of the Absence of Cyclonic Flow. Same as Method 1, Sections
11.3 and 11.4, respectively.
12.0 Data Analysis and Calculations [Reserved]
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
Same as Method 1, Section 16.0, References 1 through 6, with the
addition of the following:
1. Vollaro, Robert F. Recommended Procedure for Sample Traverses in
Ducts Smaller Than 12 Inches in Diameter. U.S. Environmental Protection
Agency, Emission Measurement Branch, Research Triangle Park, North
Carolina. January 1977.
17.0 Tables, Diagrams, Flowcharts, and Validation Data
[GRAPHIC] [TIFF OMITTED] TR17OC00.044
Method 2--Determination of Stack Gas Velocity and Volumetric Flow Rate
(Type S Pitot Tube)
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material is incorporated by reference from other
methods in this part. Therefore, to obtain reliable results, persons
using this method should have a thorough knowledge of at least the
following additional test method: Method 1.
1.0 Scope and Application.
1.1 This method is applicable for the determination of the average
velocity and the volumetric flow rate of a gas stream.
1.2 This method is not applicable at measurement sites that fail to
meet the criteria of Method 1, Section 11.1. Also, the method cannot be
used for direct measurement in cyclonic or swirling gas streams; Section
11.4 of Method 1 shows how to determine cyclonic or swirling flow
conditions. When unacceptable conditions exist, alternative procedures,
subject to the approval of the Administrator, must be employed to
produce accurate flow rate determinations. Examples of such alternative
procedures are: (1) to install straightening vanes; (2) to calculate the
total volumetric flow rate stoichiometrically, or (3) to move to another
measurement site at which the flow is acceptable.
1.3 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method.
2.1 The average gas velocity in a stack is determined from the gas
density and from measurement of the average velocity head with a Type S
(Stausscheibe or reverse type) pitot tube.
[[Page 16]]
3.0 Definitions [Reserved]
4.0 Interferences [Reserved]
5.0 Safety
5.1 Disclaimer. This method may involve hazardous materials,
operations, and equipment. This test method may not address all of the
safety problems associated with its use. It is the responsibility of the
user of this test method to establish appropriate safety and health
practices and determine the applicability of regulatory limitations
prior to performing this test method.
6.0 Equipment and Supplies
Specifications for the apparatus are given below. Any other
apparatus that has been demonstrated (subject to approval of the
Administrator) to be capable of meeting the specifications will be
considered acceptable.
6.1 Type S Pitot Tube.
6.1.1 Pitot tube made of metal tubing (e.g., stainless steel) as
shown in Figure 2-1. It is recommended that the external tubing diameter
(dimension Dt, Figure 2-2b) be between 0.48 and 0.95 cm (\3/
16\ and \3/8\ inch). There shall be an equal distance from the base of
each leg of the pitot tube to its face-opening plane (dimensions
PA and PB, Figure 2-2b); it is recommended that
this distance be between 1.05 and 1.50 times the external tubing
diameter. The face openings of the pitot tube shall, preferably, be
aligned as shown in Figure 2-2; however, slight misalignments of the
openings are permissible (see Figure 2-3).
6.1.2 The Type S pitot tube shall have a known coefficient,
determined as outlined in Section 10.0. An identification number shall
be assigned to the pitot tube; this number shall be permanently marked
or engraved on the body of the tube. A standard pitot tube may be used
instead of a Type S, provided that it meets the specifications of
Sections 6.7 and 10.2. Note, however, that the static and impact
pressure holes of standard pitot tubes are susceptible to plugging in
particulate-laden gas streams. Therefore, whenever a standard pitot tube
is used to perform a traverse, adequate proof must be furnished that the
openings of the pitot tube have not plugged up during the traverse
period. This can be accomplished by comparing the velocity head
([Delta]p) measurement recorded at a selected traverse point (readable
[Delta]p value) with a second [Delta]p measurement recorded after ``back
purging'' with pressurized air to clean the impact and static holes of
the standard pitot tube. If the before and after [Delta]p measurements
are within 5 percent, then the traverse data are acceptable. Otherwise,
the data should be rejected and the traverse measurements redone. Note
that the selected traverse point should be one that demonstrates a
readable [Delta]p value. If ``back purging'' at regular intervals is
part of a routine procedure, then comparative [Delta]p measurements
shall be conducted as above for the last two traverse points that
exhibit suitable [Delta]p measurements.
6.2 Differential Pressure Gauge. An inclined manometer or equivalent
device. Most sampling trains are equipped with a 10 in. (water column)
inclined-vertical manometer, having 0.01 in. H20 divisions on
the 0 to 1 in. inclined scale, and 0.1 in. H20 divisions on
the 1 to 10 in. vertical scale. This type of manometer (or other gauge
of equivalent sensitivity) is satisfactory for the measurement of
[Delta]p values as low as 1.27 mm (0.05 in.) H20. However, a
differential pressure gauge of greater sensitivity shall be used
(subject to the approval of the Administrator), if any of the following
is found to be true: (1) the arithmetic average of all [Delta]p readings
at the traverse points in the stack is less than 1.27 mm (0.05 in.)
H20; (2) for traverses of 12 or more points, more than 10
percent of the individual [Delta]p readings are below 1.27 mm (0.05 in.)
H20; or (3) for traverses of fewer than 12 points, more than
one [Delta]p reading is below 1.27 mm (0.05 in.) H20.
Reference 18 (see Section 17.0) describes commercially available
instrumentation for the measurement of low-range gas velocities.
6.2.1 As an alternative to criteria (1) through (3) above, Equation
2-1 (Section 12.2) may be used to determine the necessity of using a
more sensitive differential pressure gauge. If T is greater than 1.05,
the velocity head data are unacceptable and a more sensitive
differential pressure gauge must be used.
Note: If differential pressure gauges other than inclined manometers
are used (e.g., magnehelic gauges), their calibration must be checked
after each test series. To check the calibration of a differential
pressure gauge, compare [Delta]p readings of the gauge with those of a
gauge-oil manometer at a minimum of three points, approximately
representing the range of [Delta]p values in the stack. If, at each
point, the values of [Delta]p as read by the differential pressure gauge
and gauge-oil manometer agree to within 5 percent, the differential
pressure gauge shall be considered to be in proper calibration.
Otherwise, the test series shall either be voided, or procedures to
adjust the measured [Delta]p values and final results shall be used,
subject to the approval of the Administrator.
6.3 Temperature Sensor. A thermocouple, liquid-filled bulb
thermometer, bimetallic thermometer, mercury-in-glass thermometer, or
other gauge capable of measuring temperatures to within 1.5 percent of
the minimum absolute stack temperature. The temperature sensor shall be
attached to the pitot tube such that the sensor tip does not touch any
metal; the gauge shall be in an interference-free arrangement with
respect to the pitot tube face openings (see Figure 2-1 and Figure 2-4).
Alternative positions may
[[Page 17]]
be used if the pitot tube-temperature gauge system is calibrated
according to the procedure of Section 10.0. Provided that a difference
of not more than 1 percent in the average velocity measurement is
introduced, the temperature gauge need not be attached to the pitot
tube. This alternative is subject to the approval of the Administrator.
6.4 Pressure Probe and Gauge. A piezometer tube and mercury- or
water-filled U-tube manometer capable of measuring stack pressure to
within 2.5 mm (0.1 in.) Hg. The static tap of a standard type pitot tube
or one leg of a Type S pitot tube with the face opening planes
positioned parallel to the gas flow may also be used as the pressure
probe.
6.5 Barometer. A mercury, aneroid, or other barometer capable of
measuring atmospheric pressure to within 2.54 mm (0.1 in.) Hg.
Note: The barometric pressure reading may be obtained from a nearby
National Weather Service station. In this case, the station value (which
is the absolute barometric pressure) shall be requested and an
adjustment for elevation differences between the weather station and
sampling point shall be made at a rate of minus 2.5 mm (0.1 in.) Hg per
30 m (100 ft) elevation increase or plus 2.5 mm (0.1 in.) Hg per 30 m
(100 ft.) for elevation decrease.
6.6 Gas Density Determination Equipment. Method 3 equipment, if
needed (see Section 8.6), to determine the stack gas dry molecular
weight, and Method 4 (reference method) or Method 5 equipment for
moisture content determination. Other methods may be used subject to
approval of the Administrator.
6.7 Calibration Pitot Tube. When calibration of the Type S pitot
tube is necessary (see Section 10.1), a standard pitot tube shall be
used for a reference. The standard pitot tube shall, preferably, have a
known coefficient, obtained either (1) directly from the National
Institute of Standards and Technology (NIST), Gaithersburg MD 20899,
(301) 975-2002, or (2) by calibration against another standard pitot
tube with an NIST-traceable coefficient. Alternatively, a standard pitot
tube designed according to the criteria given in Sections 6.7.1 through
6.7.5 below and illustrated in Figure 2-5 (see also References 7, 8, and
17 in Section 17.0) may be used. Pitot tubes designed according to these
specifications will have baseline coefficients of 0.99 0.01.
6.7.1 Standard Pitot Design.
6.7.1.1 Hemispherical (shown in Figure 2-5), ellipsoidal, or conical
tip.
6.7.1.2 A minimum of six diameters straight run (based upon D, the
external diameter of the tube) between the tip and the static pressure
holes.
6.7.1.3 A minimum of eight diameters straight run between the static
pressure holes and the centerline of the external tube, following the
90[deg] bend.
6.7.1.4 Static pressure holes of equal size (approximately 0.1 D),
equally spaced in a piezometer ring configuration.
6.7.1.5 90[deg] bend, with curved or mitered junction.
6.8 Differential Pressure Gauge for Type S Pitot Tube Calibration.
An inclined manometer or equivalent. If the single-velocity calibration
technique is employed (see Section 10.1.2.3), the calibration
differential pressure gauge shall be readable to the nearest 0.127 mm
(0.005 in.) H20. For multivelocity calibrations, the gauge
shall be readable to the nearest 0.127 mm (0.005 in.) H20 for
[Delta]p values between 1.27 and 25.4 mm (0.05 and 1.00 in.)
H20, and to the nearest 1.27 mm (0.05 in.) H20 for
[Delta]p values above 25.4 mm (1.00 in.) H20. A special, more
sensitive gauge will be required to read [Delta]p values below 1.27 mm
(0.05 in.) H20 (see Reference 18 in Section 16.0).
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection and Analysis
8.1 Set up the apparatus as shown in Figure 2-1. Capillary tubing or
surge tanks installed between the manometer and pitot tube may be used
to dampen [Delta]p fluctuations. It is recommended, but not required,
that a pretest leak-check be conducted as follows: (1) blow through the
pitot impact opening until at least 7.6 cm (3.0 in.) H20
velocity head registers on the manometer; then, close off the impact
opening. The pressure shall remain stable for at least 15 seconds; (2)
do the same for the static pressure side, except using suction to obtain
the minimum of 7.6 cm (3.0 in.) H20. Other leak-check
procedures, subject to the approval of the Administrator, may be used.
8.2 Level and zero the manometer. Because the manometer level and
zero may drift due to vibrations and temperature changes, make periodic
checks during the traverse (at least once per hour). Record all
necessary data on a form similar to that shown in Figure 2-6.
8.3 Measure the velocity head and temperature at the traverse points
specified by Method 1. Ensure that the proper differential pressure
gauge is being used for the range of [Delta]p values encountered (see
Section 6.2). If it is necessary to change to a more sensitive gauge, do
so, and remeasure the [Delta]p and temperature readings at each traverse
point. Conduct a post-test leak-check (mandatory), as described in
Section 8.1 above, to validate the traverse run.
8.4 Measure the static pressure in the stack. One reading is usually
adequate.
8.5 Determine the atmospheric pressure.
8.6 Determine the stack gas dry molecular weight. For combustion
processes or processes that emit essentially CO2,
O2, CO, and N2, use Method 3. For processes
emitting
[[Page 18]]
essentially air, an analysis need not be conducted; use a dry molecular
weight of 29.0. For other processes, other methods, subject to the
approval of the Administrator, must be used.
8.7 Obtain the moisture content from Method 4 (reference method, or
equivalent) or from Method 5.
8.8 Determine the cross-sectional area of the stack or duct at the
sampling location. Whenever possible, physically measure the stack
dimensions rather than using blueprints. Do not assume that stack
diameters are equal. Measure each diameter distance to verify its
dimensions.
9.0 Quality Control
------------------------------------------------------------------------
Quality control
Section measure Effect
------------------------------------------------------------------------
10.1-10.4..................... Sampling Ensure accurate
equipment measurement of stack
calibration. gas flow rate,
sample volume.
------------------------------------------------------------------------
10.0 Calibration and Standardization
10.1 Type S Pitot Tube. Before its initial use, carefully examine
the Type S pitot tube top, side, and end views to verify that the face
openings of the tube are aligned within the specifications illustrated
in Figures 2-2 and 2-3. The pitot tube shall not be used if it fails to
meet these alignment specifications. After verifying the face opening
alignment, measure and record the following dimensions of the pitot
tube: (a) the external tubing diameter (dimension Dt, Figure
2-2b); and (b) the base-to-opening plane distances (dimensions
PA and PB, Figure 2-2b). If Dt is
between 0.48 and 0.95 cm \3/16\ and \3/8\ in.), and if PA and
PB are equal and between 1.05 and 1.50 Dt, there
are two possible options: (1) the pitot tube may be calibrated according
to the procedure outlined in Sections 10.1.2 through 10.1.5, or (2) a
baseline (isolated tube) coefficient value of 0.84 may be assigned to
the pitot tube. Note, however, that if the pitot tube is part of an
assembly, calibration may still be required, despite knowledge of the
baseline coefficient value (see Section 10.1.1). If Dt,
PA, and PB are outside the specified limits, the
pitot tube must be calibrated as outlined in Sections 10.1.2 through
10.1.5.
10.1.1 Type S Pitot Tube Assemblies. During sample and velocity
traverses, the isolated Type S pitot tube is not always used; in many
instances, the pitot tube is used in combination with other source-
sampling components (e.g., thermocouple, sampling probe, nozzle) as part
of an ``assembly.'' The presence of other sampling components can
sometimes affect the baseline value of the Type S pitot tube coefficient
(Reference 9 in Section 17.0); therefore, an assigned (or otherwise
known) baseline coefficient value may or may not be valid for a given
assembly. The baseline and assembly coefficient values will be identical
only when the relative placement of the components in the assembly is
such that aerodynamic interference effects are eliminated. Figures 2-4,
2-7, and 2-8 illustrate interference-free component arrangements for
Type S pitot tubes having external tubing diameters between 0.48 and
0.95 cm (\3/16\ and \3/8\ in.). Type S pitot tube assemblies that fail
to meet any or all of the specifications of Figures 2-4, 2-7, and 2-8
shall be calibrated according to the procedure outlined in Sections
10.1.2 through 10.1.5, and prior to calibration, the values of the
intercomponent spacings (pitot-nozzle, pitot-thermocouple, pitot-probe
sheath) shall be measured and recorded.
Note: Do not use a Type S pitot tube assembly that is constructed
such that the impact pressure opening plane of the pitot tube is below
the entry plane of the nozzle (see Figure 2-6B).
10.1.2 Calibration Setup. If the Type S pitot tube is to be
calibrated, one leg of the tube shall be permanently marked A, and the
other, B. Calibration shall be performed in a flow system having the
following essential design features:
10.1.2.1 The flowing gas stream must be confined to a duct of
definite cross-sectional area, either circular or rectangular. For
circular cross sections, the minimum duct diameter shall be 30.48 cm (12
in.); for rectangular cross sections, the width (shorter side) shall be
at least 25.4 cm (10 in.).
10.1.2.2 The cross-sectional area of the calibration duct must be
constant over a distance of 10 or more duct diameters. For a rectangular
cross section, use an equivalent diameter, calculated according to
Equation 2-2 (see Section 12.3), to determine the number of duct
diameters. To ensure the presence of stable, fully developed flow
patterns at the calibration site, or ``test section,'' the site must be
located at least eight diameters downstream and two diameters upstream
from the nearest disturbances.
Note: The eight- and two-diameter criteria are not absolute; other
test section locations may be used (subject to approval of the
Administrator), provided that the flow at the test site has been
demonstrated to be or found stable and parallel to the duct axis.
10.1.2.3 The flow system shall have the capacity to generate a test-
section velocity around 910 m/min (3,000 ft/min). This velocity must be
constant with time to guarantee steady flow during calibration. Note
that Type S pitot tube coefficients obtained by
[[Page 19]]
single-velocity calibration at 910 m/min (3,000 ft/min) will generally
be valid to 3 percent for the measurement of
velocities above 300 m/min (1,000 ft/min) and to 6
percent for the measurement of velocities between 180 and 300 m/min (600
and 1,000 ft/min). If a more precise correlation between the pitot tube
coefficient, (Cp), and velocity is desired, the flow system
should have the capacity to generate at least four distinct, time-
invariant test-section velocities covering the velocity range from 180
to 1,500 m/min (600 to 5,000 ft/min), and calibration data shall be
taken at regular velocity intervals over this range (see References 9
and 14 in Section 17.0 for details).
10.1.2.4 Two entry ports, one for each of the standard and Type S
pitot tubes, shall be cut in the test section. The standard pitot entry
port shall be located slightly downstream of the Type S port, so that
the standard and Type S impact openings will lie in the same cross-
sectional plane during calibration. To facilitate alignment of the pitot
tubes during calibration, it is advisable that the test section be
constructed of Plexiglas \TM\ or some other transparent material.
10.1.3 Calibration Procedure. Note that this procedure is a general
one and must not be used without first referring to the special
considerations presented in Section 10.1.5. Note also that this
procedure applies only to single-velocity calibration. To obtain
calibration data for the A and B sides of the Type S pitot tube, proceed
as follows:
10.1.3.1 Make sure that the manometer is properly filled and that
the oil is free from contamination and is of the proper density. Inspect
and leak-check all pitot lines; repair or replace if necessary.
10.1.3.2 Level and zero the manometer. Switch on the fan, and allow
the flow to stabilize. Seal the Type S pitot tube entry port.
10.1.3.3 Ensure that the manometer is level and zeroed. Position the
standard pitot tube at the calibration point (determined as outlined in
Section 10.1.5.1), and align the tube so that its tip is pointed
directly into the flow. Particular care should be taken in aligning the
tube to avoid yaw and pitch angles. Make sure that the entry port
surrounding the tube is properly sealed.
10.1.3.4 Read [Delta]pstd, and record its value in a data
table similar to the one shown in Figure 2-9. Remove the standard pitot
tube from the duct, and disconnect it from the manometer. Seal the
standard entry port.
10.1.3.5 Connect the Type S pitot tube to the manometer and leak-
check. Open the Type S tube entry port. Check the manometer level and
zero. Insert and align the Type S pitot tube so that its A side impact
opening is at the same point as was the standard pitot tube and is
pointed directly into the flow. Make sure that the entry port
surrounding the tube is properly sealed.
10.1.3.6 Read [Delta]ps, and enter its value in the data
table. Remove the Type S pitot tube from the duct, and disconnect it
from the manometer.
10.1.3.7 Repeat Steps 10.1.3.3 through 10.1.3.6 until three pairs of
[Delta]p readings have been obtained for the A side of the Type S pitot
tube.
10.1.3.8 Repeat Steps 10.1.3.3 through 10.1.3.7 for the B side of
the Type S pitot tube.
10.1.3.9 Perform calculations as described in Section 12.4. Use the
Type S pitot tube only if the values of [sigma]A and
[sigma]B are less than or equal to 0.01 and if the absolute
value of the difference between Cp(A) and Cp(B) is
0.01 or less.
10.1.4 Special Considerations.
10.1.4.1 Selection of Calibration Point.
10.1.4.1.1 When an isolated Type S pitot tube is calibrated, select
a calibration point at or near the center of the duct, and follow the
procedures outlined in Section 10.1.3. The Type S pitot coefficients
measured or calculated, (i.e., Cp(A) and Cp(B))
will be valid, so long as either: (1) the isolated pitot tube is used;
or (2) the pitot tube is used with other components (nozzle,
thermocouple, sample probe) in an arrangement that is free from
aerodynamic interference effects (see Figures 2-4, 2-7, and 2-8).
10.1.4.1.2 For Type S pitot tube-thermocouple combinations (without
probe assembly), select a calibration point at or near the center of the
duct, and follow the procedures outlined in Section 10.1.3. The
coefficients so obtained will be valid so long as the pitot tube-
thermocouple combination is used by itself or with other components in
an interference-free arrangement (Figures 2-4, 2-7, and 2-8).
10.1.4.1.3 For Type S pitot tube combinations with complete probe
assemblies, the calibration point should be located at or near the
center of the duct; however, insertion of a probe sheath into a small
duct may cause significant cross-sectional area interference and
blockage and yield incorrect coefficient values (Reference 9 in Section
17.0). Therefore, to minimize the blockage effect, the calibration point
may be a few inches off-center if necessary. The actual blockage effect
will be negligible when the theoretical blockage, as determined by a
projected-area model of the probe sheath, is 2 percent or less of the
duct cross-sectional area for assemblies without external sheaths
(Figure 2-10a), and 3 percent or less for assemblies with external
sheaths (Figure 2-10b).
10.1.4.2 For those probe assemblies in which pitot tube-nozzle
interference is a factor (i.e., those in which the pitot-nozzle
separation distance fails to meet the specifications illustrated in
Figure 2-7A), the value of Cp(s) depends upon the amount of
free space between the tube and nozzle and, therefore,
[[Page 20]]
is a function of nozzle size. In these instances, separate calibrations
shall be performed with each of the commonly used nozzle sizes in place.
Note that the single-velocity calibration technique is acceptable for
this purpose, even though the larger nozzle sizes (0.635 cm
or \1/4\ in.) are not ordinarily used for isokinetic sampling at
velocities around 910 m/min (3,000 ft/min), which is the calibration
velocity. Note also that it is not necessary to draw an isokinetic
sample during calibration (see Reference 19 in Section 17.0).
10.1.4.3 For a probe assembly constructed such that its pitot tube
is always used in the same orientation, only one side of the pitot tube
need be calibrated (the side which will face the flow). The pitot tube
must still meet the alignment specifications of Figure 2-2 or 2-3,
however, and must have an average deviation ([sigma]) value of 0.01 or
less (see Section 10.1.4.4).
10.1.5 Field Use and Recalibration.
10.1.5.1 Field Use.
10.1.5.1.1 When a Type S pitot tube (isolated or in an assembly) is
used in the field, the appropriate coefficient value (whether assigned
or obtained by calibration) shall be used to perform velocity
calculations. For calibrated Type S pitot tubes, the A side coefficient
shall be used when the A side of the tube faces the flow, and the B side
coefficient shall be used when the B side faces the flow. Alternatively,
the arithmetic average of the A and B side coefficient values may be
used, irrespective of which side faces the flow.
10.1.5.1.2 When a probe assembly is used to sample a small duct,
30.5 to 91.4 cm (12 to 36 in.) in diameter, the probe sheath sometimes
blocks a significant part of the duct cross-section, causing a reduction
in the effective value of Cp(s). Consult Reference 9 (see
Section 17.0) for details. Conventional pitot-sampling probe assemblies
are not recommended for use in ducts having inside diameters smaller
than 30.5 cm (12 in.) (see Reference 16 in Section 17.0).
10.1.5.2 Recalibration.
10.1.5.2.1 Isolated Pitot Tubes. After each field use, the pitot
tube shall be carefully reexamined in top, side, and end views. If the
pitot face openings are still aligned within the specifications
illustrated in Figure 2-2 and Figure 2-3, it can be assumed that the
baseline coefficient of the pitot tube has not changed. If, however, the
tube has been damaged to the extent that it no longer meets the
specifications of Figure 2-2 and Figure 2-3, the damage shall either be
repaired to restore proper alignment of the face openings, or the tube
shall be discarded.
10.1.5.2.2 Pitot Tube Assemblies. After each field use, check the
face opening alignment of the pitot tube, as in Section 10.1.5.2.1.
Also, remeasure the intercomponent spacings of the assembly. If the
intercomponent spacings have not changed and the face opening alignment
is acceptable, it can be assumed that the coefficient of the assembly
has not changed. If the face opening alignment is no longer within the
specifications of Figure 2-2 and Figure 2-3, either repair the damage or
replace the pitot tube (calibrating the new assembly, if necessary). If
the intercomponent spacings have changed, restore the original spacings,
or recalibrate the assembly.
10.2 Standard Pitot Tube (if applicable). If a standard pitot tube
is used for the velocity traverse, the tube shall be constructed
according to the criteria of Section 6.7 and shall be assigned a
baseline coefficient value of 0.99. If the standard pitot tube is used
as part of an assembly, the tube shall be in an interference-free
arrangement (subject to the approval of the Administrator).
10.3 Temperature Sensors.
10.3.1 After each field use, calibrate dial thermometers, liquid-
filled bulb thermometers, thermocouple-potentiometer systems, and other
sensors at a temperature within 10 percent of the average absolute stack
temperature. For temperatures up to 405 [deg]C (761 [deg]F), use an ASTM
mercury-in-glass reference thermometer, or equivalent, as a reference.
Alternatively, either a reference thermocouple and potentiometer
(calibrated against NIST standards) or thermometric fixed points (e.g.,
ice bath and boiling water, corrected for barometric pressure) may be
used. For temperatures above 405 [deg]C (761 [deg]F), use a reference
thermocouple-potentiometer system calibrated against NIST standards or
an alternative reference, subject to the approval of the Administrator.
10.3.2 The temperature data recorded in the field shall be
considered valid. If, during calibration, the absolute temperature
measured with the sensor being calibrated and the reference sensor agree
within 1.5 percent, the temperature data taken in the field shall be
considered valid. Otherwise, the pollutant emission test shall either be
considered invalid or adjustments (if appropriate) of the test results
shall be made, subject to the approval of the Administrator.
10.4 Barometer. Calibrate the barometer used against a mercury
barometer.
11.0 Analytical Procedure
Sample collection and analysis are concurrent for this method (see
Section 8.0).
12.0 Data Analysis and Calculations
Carry out calculations, retaining at least one extra significant
figure beyond that of the acquired data. Round off figures after final
calculation.
12.1 Nomenclature.
A=Cross-sectional area of stack, m\2\ (ft\2\).
Bws=Water vapor in the gas stream (from Method 4 (reference
method) or Method 5), proportion by volume.
[[Page 21]]
Cp=Pitot tube coefficient, dimensionless.
Cp(s)=Type S pitot tube coefficient, dimensionless.
Cp(std)=Standard pitot tube coefficient; use 0.99 if the
coefficient is unknown and the tube is designed according to the
criteria of Sections 6.7.1 to 6.7.5 of this method.
De=Equivalent diameter.
K=0.127 mm H2O (metric units). 0.005 in. H2O
(English units).
Kp=Velocity equation constant.
L=Length.
Md=Molecular weight of stack gas, dry basis (see Section
8.6), g/g-mole (lb/lb-mole).
Ms=Molecular weight of stack gas, wet basis, g/g-mole (lb/lb-
mole).
n=Total number of traverse points.
Pbar=Barometric pressure at measurement site, mm Hg (in. Hg).
Pg=Stack static pressure, mm Hg (in. Hg).
Ps=Absolute stack pressure (Pbar + Pg),
mm Hg (in. Hg),
Pstd=Standard absolute pressure, 760 mm Hg (29.92 in. Hg).
Qsd=Dry volumetric stack gas flow rate corrected to standard
conditions, dscm/hr (dscf/hr).
T=Sensitivity factor for differential pressure gauges.
Ts=Stack temperature, [deg]C (( [deg]deg;F).
Ts(abs)=Absolute stack temperature, [deg]K ([deg]R).
=273 + Ts for metric units,
=460 + Ts for English units.
Tstd=Standard absolute temperature, 293 [deg]K (528 [deg]R).
Vs=Average stack gas velocity, m/sec (ft/sec).
W=Width.
[Delta]p=Velocity head of stack gas, mm H2O (in.
H20).
[Delta]pi=Individual velocity head reading at traverse point
``i'', mm (in.) H2O.
[Delta]pstd=Velocity head measured by the standard pitot
tube, cm (in.) H2O.
[Delta]ps=Velocity head measured by the Type S pitot tube, cm
(in.) H2O.
3600=Conversion Factor, sec/hr.
18.0=Molecular weight of water, g/g-mole (lb/lb-mole).
12.2 Calculate T as follows:
[GRAPHIC] [TIFF OMITTED] TR17OC00.045
12.3 Calculate De as follows:
[GRAPHIC] [TIFF OMITTED] TR17OC00.046
12.4 Calibration of Type S Pitot Tube.
12.4.1 For each of the six pairs of [Delta]p readings (i.e., three
from side A and three from side B) obtained in Section 10.1.3, calculate
the value of the Type S pitot tube coefficient according to Equation 2-
3:
[GRAPHIC] [TIFF OMITTED] TR17OC00.047
12.4.2 Calculate Cp(A), the mean A-side coefficient, and
Cp(B), the mean B-side coefficient. Calculate the difference
between these two average values.
12.4.3 Calculate the deviation of each of the three A-side values of
Cp(s) from Cp(A), and the deviation of each of the
three B-side values of Cp(s) from Cp(B), using
Equation 2-4:
[GRAPHIC] [TIFF OMITTED] TR17OC00.048
12.4.4 Calculate [sigma] the average deviation from the mean, for
both the A and B sides of the pitot tube. Use Equation 2-5:
[GRAPHIC] [TIFF OMITTED] TR17OC00.049
12.5 Molecular Weight of Stack Gas.
[GRAPHIC] [TIFF OMITTED] TR17OC00.050
12.6 Average Stack Gas Velocity.
[GRAPHIC] [TIFF OMITTED] TR17OC00.051
[[Page 22]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.052
[GRAPHIC] [TIFF OMITTED] TR17OC00.053
12.7 Average Stack Gas Dry Volumetric Flow Rate.
[GRAPHIC] [TIFF OMITTED] TR17OC00.054
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
1. Mark, L.S. Mechanical Engineers' Handbook. New York. McGraw-Hill
Book Co., Inc. 1951.
2. Perry, J.H., ed. Chemical Engineers' Handbook. New York. McGraw-
Hill Book Co., Inc. 1960.
3. Shigehara, R.T., W.F. Todd, and W.S. Smith. Significance of
Errors in Stack Sampling Measurements. U.S. Environmental Protection
Agency, Research Triangle Park, N.C. (Presented at the Annual Meeting of
the Air Pollution Control Association, St. Louis, MO., June 14-19,
1970).
4. Standard Method for Sampling Stacks for Particulate Matter. In:
1971 Book of ASTM Standards, Part 23. Philadelphia, PA. 1971. ASTM
Designation D 2928-71.
5. Vennard, J.K. Elementary Fluid Mechanics. New York. John Wiley
and Sons, Inc. 1947.
6. Fluid Meters--Their Theory and Application. American Society of
Mechanical Engineers, New York, N.Y. 1959.
7. ASHRAE Handbook of Fundamentals. 1972. p. 208.
8. Annual Book of ASTM Standards, Part 26. 1974. p. 648.
9. Vollaro, R.F. Guidelines for Type S Pitot Tube Calibration. U.S.
Environmental Protection Agency, Research Triangle Park, N.C. (Presented
at 1st Annual Meeting, Source Evaluation Society, Dayton, OH, September
18, 1975.)
10. Vollaro, R.F. A Type S Pitot Tube Calibration Study. U.S.
Environmental Protection Agency, Emission Measurement Branch, Research
Triangle Park, N.C. July 1974.
11. Vollaro, R.F. The Effects of Impact Opening Misalignment on the
Value of the Type S Pitot Tube Coefficient. U.S. Environmental
Protection Agency, Emission Measurement Branch, Research Triangle Park,
NC. October 1976.
12. Vollaro, R.F. Establishment of a Baseline Coefficient Value for
Properly Constructed Type S Pitot Tubes. U.S. Environmental Protection
Agency, Emission Measurement Branch, Research Triangle Park, NC.
November 1976.
13. Vollaro, R.F. An Evaluation of Single-Velocity Calibration
Technique as a Means of Determining Type S Pitot Tube Coefficients. U.S.
Environmental Protection Agency, Emission Measurement Branch, Research
Triangle Park, NC. August 1975.
14. Vollaro, R.F. The Use of Type S Pitot Tubes for the Measurement
of Low Velocities. U.S. Environmental Protection Agency, Emission
Measurement Branch, Research Triangle Park, NC. November 1976.
15. Smith, Marvin L. Velocity Calibration of EPA Type Source
Sampling Probe. United Technologies Corporation, Pratt and Whitney
Aircraft Division, East Hartford, CT. 1975.
16. Vollaro, R.F. Recommended Procedure for Sample Traverses in
Ducts Smaller than 12 Inches in Diameter. U.S. Environmental Protection
Agency, Emission Measurement Branch, Research Triangle Park, NC.
November 1976.
17. Ower, E. and R.C. Pankhurst. The Measurement of Air Flow, 4th
Ed. London, Pergamon Press. 1966.
[[Page 23]]
18. Vollaro, R.F. A Survey of Commercially Available Instrumentation
for the Measurement of Low-Range Gas Velocities. U.S. Environmental
Protection Agency, Emission Measurement Branch, Research Triangle Park,
NC. November 1976. (Unpublished Paper).
19. Gnyp, A.W., et al. An Experimental Investigation of the Effect
of Pitot Tube-Sampling Probe Configurations on the Magnitude of the S
Type Pitot Tube Coefficient for Commercially Available Source Sampling
Probes. Prepared by the University of Windsor for the Ministry of the
Environment, Toronto, Canada. February 1975.
17.0 Tables, Diagrams, Flowcharts, and Validation Data
[GRAPHIC] [TIFF OMITTED] TR17OC00.055
[[Page 24]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.056
[[Page 25]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.057
[[Page 26]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.058
[GRAPHIC] [TIFF OMITTED] TR17OC00.059
PLANT___________________________________________________________________
DATE____________________________________________________________________
[[Page 27]]
RUN NO._________________________________________________________________
STACK DIA. OR DIMENSIONS, m (in.)_______________________________________
BAROMETRIC PRESS., mm Hg (in. Hg)_______________________________________
CROSS SECTIONAL AREA, m\2\ (ft\2\)______________________________________
OPERATORS_______________________________________________________________
PITOT TUBE I.D. NO._____________________________________________________
AVG. COEFFICIENT, Cp =__________________________________________________
LAST DATE CALIBRATED____________________________________________________
------------------------------------------------------------------------
-------------------------------------------------------------------------
------------------------------------------------------------------------
SCHEMATIC OF STACK CROSS SECTION
--------------------------------------------------------------------------------------------------------------------------------------------------------
Stack temperature
Vel. Hd., [Delta]p mm -----------------------------------------------
Traverse Pt. No. (in.) H2O Ts, [deg]C (( Pg mm Hg (in. Hg) ([Delta]p)\1/2\
[deg]deg;F) Ts, [deg]K ([deg]R)
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average(1)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Figure 2-6. Velocity Traverse Data
[[Page 28]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.060
[GRAPHIC] [TIFF OMITTED] TR17OC00.061
PITOT TUBE IDENTIFICATION NUMBER:_______________________________________
DATE:___________________________________________________________________
CALIBRATED BY:__________________________________________________________
``A'' Side Calibration
----------------------------------------------------------------------------------------------------------------
[Delta]Pstd cm H2O [Delta]P(s) cm H2O Deviation Cp(s)--
Run No. (in H2O) (in H2O) Cp(s) Cp(A)
----------------------------------------------------------------------------------------------------------------
1
----------------------------------------------------------------------------------------------------------------
2
----------------------------------------------------------------------------------------------------------------
3
----------------------------------------------------------------------------------------------------------------
[[Page 29]]
Cp, avg
(SIDE A)
----------------------------------------------------------------------------------------------------------------
``B'' Side Calibration
----------------------------------------------------------------------------------------------------------------
[Delta]Pstd cm H2O [Delta]P(s) cm H2O Deviation Cp(s)--
Run No. (in H2O) (in H2O) Cp(s) Cp(B)
----------------------------------------------------------------------------------------------------------------
1
----------------------------------------------------------------------------------------------------------------
2
----------------------------------------------------------------------------------------------------------------
3
----------------------------------------------------------------------------------------------------------------
Cp, avg
(SIDE B)
----------------------------------------------------------------------------------------------------------------
[GRAPHIC] [TIFF OMITTED] TR17OC00.062
[Cp, avg (side A)--Cp, avg (side B)]*
*Must be less than or equal to 0.01
Figure 2-9. Pitot Tube Calibration Data
[[Page 30]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.063
Method 2A--Direct Measurement of Gas Volume Through Pipes and Small
Ducts
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material is incorporated by reference from other
methods in this part. Therefore, to obtain reliable results, persons
using this method should have a thorough knowledge of at least the
following additional test methods: Method 1, Method 2.
1.0 Scope and Application
1.1 This method is applicable for the determination of gas flow
rates in pipes and small ducts, either in-line or at exhaust positions,
within the temperature range of 0 to 50 [deg]C (32 to 122 [deg]F).
1.2 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method
2.1 A gas volume meter is used to measure gas volume directly.
Temperature and pressure measurements are made to allow correction of
the volume to standard conditions.
3.0 Definitions [Reserved]
4.0 Interferences [Reserved]
5.0 Safety
5.1 Disclaimer. This method may involve hazardous materials,
operations, and equipment. This test method may not address all of the
safety problems associated with its use. It is the responsibility of the
user of this test method to establish appropriate safety
[[Page 31]]
and health practices and determine the applicability of regulatory
limitations prior to performing this test method.
6.0 Equipment and Supplies
Specifications for the apparatus are given below. Any other
apparatus that has been demonstrated (subject to approval of the
Administrator) to be capable of meeting the specifications will be
considered acceptable.
6.1 Gas Volume Meter. A positive displacement meter, turbine meter,
or other direct measuring device capable of measuring volume to within 2
percent. The meter shall be equipped with a temperature sensor (accurate
to within 2 percent of the minimum absolute
temperature) and a pressure gauge (accurate to within 2.5 mm Hg). The manufacturer's recommended capacity of
the meter shall be sufficient for the expected maximum and minimum flow
rates for the sampling conditions. Temperature, pressure, corrosive
characteristics, and pipe size are factors necessary to consider in
selecting a suitable gas meter.
6.2 Barometer. A mercury, aneroid, or other barometer capable of
measuring atmospheric pressure to within 2.5 mm
Hg.
Note: In many cases, the barometric reading may be obtained from a
nearby National Weather Service station, in which case the station value
(which is the absolute barometric pressure) shall be requested and an
adjustment for elevation differences between the weather station and
sampling point shall be applied at a rate of minus 2.5 mm (0.1 in.) Hg
per 30 m (100 ft) elevation increase or vice versa for elevation
decrease.
6.3 Stopwatch. Capable of measurement to within 1 second.
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection and Analysis
8.1 Installation. As there are numerous types of pipes and small
ducts that may be subject to volume measurement, it would be difficult
to describe all possible installation schemes. In general, flange
fittings should be used for all connections wherever possible. Gaskets
or other seal materials should be used to assure leak-tight connections.
The volume meter should be located so as to avoid severe vibrations and
other factors that may affect the meter calibration.
8.2 Leak Test.
8.2.1 A volume meter installed at a location under positive pressure
may be leak-checked at the meter connections by using a liquid leak
detector solution containing a surfactant. Apply a small amount of the
solution to the connections. If a leak exists, bubbles will form, and
the leak must be corrected.
8.2.2 A volume meter installed at a location under negative pressure
is very difficult to test for leaks without blocking flow at the inlet
of the line and watching for meter movement. If this procedure is not
possible, visually check all connections to assure leak-tight seals.
8.3 Volume Measurement.
8.3.1 For sources with continuous, steady emission flow rates,
record the initial meter volume reading, meter temperature(s), meter
pressure, and start the stopwatch. Throughout the test period, record
the meter temperatures and pressures so that average values can be
determined. At the end of the test, stop the timer, and record the
elapsed time, the final volume reading, meter temperature, and pressure.
Record the barometric pressure at the beginning and end of the test run.
Record the data on a table similar to that shown in Figure 2A-1.
8.3.2 For sources with noncontinuous, non-steady emission flow
rates, use the procedure in Section 8.3.1 with the addition of the
following: Record all the meter parameters and the start and stop times
corresponding to each process cyclical or noncontinuous event.
9.0 Quality Control
------------------------------------------------------------------------
Quality control
Section measure Effect
------------------------------------------------------------------------
10.1-10.4..................... Sampling Ensure accurate
equipment measurement of stack
calibration. gas flow rate,
sample volume.
------------------------------------------------------------------------
10.0 Calibration and Standardization
10.1 Volume Meter.
10.1.1 The volume meter is calibrated against a standard reference
meter prior to its initial use in the field. The reference meter is a
spirometer or liquid displacement meter with a capacity consistent with
that of the test meter.
10.1.2 Alternatively, a calibrated, standard pitot may be used as
the reference meter in conjunction with a wind tunnel assembly. Attach
the test meter to the wind tunnel so that the total flow passes through
the test meter. For each calibration run, conduct a 4-point traverse
along one stack diameter at a position at least eight diameters of
straight tunnel downstream and two diameters upstream of any bend,
inlet, or air mover. Determine the traverse point locations as specified
in Method 1. Calculate the reference volume using the velocity values
following the procedure in Method 2, the wind tunnel cross-sectional
area, and the run time.
[[Page 32]]
10.1.3 Set up the test meter in a configuration similar to that used
in the field installation (i.e., in relation to the flow moving device).
Connect the temperature sensor and pressure gauge as they are to be used
in the field. Connect the reference meter at the inlet of the flow line,
if appropriate for the meter, and begin gas flow through the system to
condition the meters. During this conditioning operation, check the
system for leaks.
10.1.4 The calibration shall be performed during at least three
different flow rates. The calibration flow rates shall be about 0.3,
0.6, and 0.9 times the rated maximum flow rate of the test meter.
10.1.5 For each calibration run, the data to be collected include:
reference meter initial and final volume readings, the test meter
initial and final volume reading, meter average temperature and
pressure, barometric pressure, and run time. Repeat the runs at each
flow rate at least three times.
10.1.6 Calculate the test meter calibration coefficient as indicated
in Section 12.2.
10.1.7 Compare the three Ym values at each of the flow
rates tested and determine the maximum and minimum values. The
difference between the maximum and minimum values at each flow rate
should be no greater than 0.030. Extra runs may be required to complete
this requirement. If this specification cannot be met in six successive
runs, the test meter is not suitable for use. In addition, the meter
coefficients should be between 0.95 and 1.05. If these specifications
are met at all the flow rates, average all the Ym values from
runs meeting the specifications to obtain an average meter calibration
coefficient, Ym.
10.1.8 The procedure above shall be performed at least once for each
volume meter. Thereafter, an abbreviated calibration check shall be
completed following each field test. The calibration of the volume meter
shall be checked with the meter pressure set at the average value
encountered during the field test. Three calibration checks (runs) shall
be performed using this average flow rate value. Calculate the average
value of the calibration factor. If the calibration has changed by more
than 5 percent, recalibrate the meter over the full range of flow as
described above.
Note: If the volume meter calibration coefficient values obtained
before and after a test series differ by more than 5 percent, the test
series shall either be voided, or calculations for the test series shall
be performed using whichever meter coefficient value (i.e., before or
after) gives the greater value of pollutant emission rate.
10.2 Temperature Sensor. After each test series, check the
temperature sensor at ambient temperature. Use an American Society for
Testing and Materials (ASTM) mercury-in-glass reference thermometer, or
equivalent, as a reference. If the sensor being checked agrees within 2
percent (absolute temperature) of the reference, the temperature data
collected in the field shall be considered valid. Otherwise, the test
data shall be considered invalid or adjustments of the results shall be
made, subject to the approval of the Administrator.
10.3 Barometer. Calibrate the barometer used against a mercury
barometer prior to the field test.
11.0 Analytical Procedure
Sample collection and analysis are concurrent for this method (see
Section 8.0).
12.0 Data Analysis and Calculations
Carry out calculations, retaining at least one extra decimal figure
beyond that of the acquired data. Round off figures after final
calculation.
12.1 Nomenclature.
f=Final reading.
i=Initial reading.
Pbar=Barometric pressure, mm Hg.
Pg=Average static pressure in volume meter, mm Hg.
Qs=Gas flow rate, m\3\/min, standard conditions.
s=Standard conditions, 20 [deg]C and 760 mm Hg.
Tr=Reference meter average temperature, [deg]K ([deg]R).
Tm=Test meter average temperature, [deg]K ([deg]R).
Vr=Reference meter volume reading, m\3\.
Vm=Test meter volume reading, m\3\.
Ym=Test meter calibration coefficient, dimensionless.
[thetas]=Elapsed test period time, min.
12.2 Test Meter Calibration Coefficient.
[GRAPHIC] [TIFF OMITTED] TR17OC00.064
12.3 Volume.
[[Page 33]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.065
12.4 Gas Flow Rate.
[GRAPHIC] [TIFF OMITTED] TR17OC00.066
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
1. Rom, Jerome J. Maintenance, Calibration, and Operation of
Isokinetic Source Sampling Equipment. U.S. Environmental Protection
Agency, Research Triangle Park, NC. Publication No. APTD-0576. March
1972.
2. Wortman, Martin, R. Vollaro, and P.R. Westlin. Dry Gas Volume
Meter Calibrations. Source Evaluation Society Newsletter. Vol. 2, No. 2.
May 1977.
3. Westlin, P.R., and R.T. Shigehara. Procedure for Calibrating and
Using Dry Gas Volume Meters as Calibration Standards. Source Evaluation
Society Newsletter. Vol. 3, No. 1. February 1978.
17.0 Tables, Diagrams, Flowcharts, and Validation Data [Reserved]
Method 2B--Determination of Exhaust Gas Volume Flow Rate From Gasoline
Vapor Incinerators
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling and analytical)
essential to its performance. Some material is incorporated by reference
from other methods in this part. Therefore, to obtain reliable results,
persons using this method should also have a thorough knowledge of at
least the following additional test methods: Method 1, Method 2, Method
2A, Method 10, Method 25A, Method 25B.
1.0 Scope and Application
1.1 This method is applicable for the determination of exhaust
volume flow rate from incinerators that process gasoline vapors
consisting primarily of alkanes, alkenes, and/or arenes (aromatic
hydrocarbons). It is assumed that the amount of auxiliary fuel is
negligible.
1.2 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method
2.1 Organic carbon concentration and volume flow rate are measured
at the incinerator inlet using either Method 25A or Method 25B and
Method 2A, respectively. Organic carbon, carbon dioxide
(CO2), and carbon monoxide (CO) concentrations are measured
at the outlet using either Method 25A or Method 25B and Method 10,
respectively. The ratio of total carbon at the incinerator inlet and
outlet is multiplied by the inlet volume to determine the exhaust volume
flow rate.
3.0 Definitions
Same as Section 3.0 of Method 10 and Method 25A.
4.0 Interferences
Same as Section 4.0 of Method 10.
5.0 Safety
5.1 This method may involve hazardous materials, operations, and
equipment. This test method may not address all of the safety problems
associated with its use. It is the responsibility of the user of this
test method to establish appropriate safety and health practices and
determine the applicability of regulatory limitations prior to
performing this test method.
6.0 Equipment and Supplies
Same as Section 6.0 of Method 2A, Method 10, and Method 25A and/or
Method 25B as applicable, with the addition of the following:
6.1 This analyzer must meet the specifications set forth in Section
6.1.2 of Method 10, except that the span shall be 15 percent
CO2 by volume.
7.0 Reagents and Standards
Same as Section 7.0 of Method 10 and Method 25A, with the following
addition and exceptions:
7.1 Carbon Dioxide Analyzer Calibration. CO2 gases
meeting the specifications set forth in Section 7 of Method 6C are
required.
7.2 Hydrocarbon Analyzer Calibration. Methane shall not be used as a
calibration gas when performing this method.
7.3 Fuel Gas. If Method 25B is used to measure the organic carbon
concentrations at both the inlet and exhaust, no fuel gas is required.
[[Page 34]]
8.0 Sample Collection and Analysis
8.1 Pre-test Procedures. Perform all pre-test procedures (e.g.,
system performance checks, leak checks) necessary to determine gas
volume flow rate and organic carbon concentration in the vapor line to
the incinerator inlet and to determine organic carbon, carbon monoxide,
and carbon dioxide concentrations at the incinerator exhaust, as
outlined in Method 2A, Method 10, and Method 25A and/or Method 25B as
applicable.
8.2 Sampling. At the beginning of the test period, record the
initial parameters for the inlet volume meter according to the
procedures in Method 2A and mark all of the recorder strip charts to
indicate the start of the test. Conduct sampling and analysis as
outlined in Method 2A, Method 10, and Method 25A and/or Method 25B as
applicable. Continue recording inlet organic and exhaust CO2,
CO, and organic concentrations throughout the test. During periods of
process interruption and halting of gas flow, stop the timer and mark
the recorder strip charts so that data from this interruption are not
included in the calculations. At the end of the test period, record the
final parameters for the inlet volume meter and mark the end on all of
the recorder strip charts.
8.3 Post-test Procedures. Perform all post-test procedures (e.g.,
drift tests, leak checks), as outlined in Method 2A, Method 10, and
Method 25A and/or Method 25B as applicable.
9.0 Quality Control
Same as Section 9.0 of Method 2A, Method 10, and Method 25A.
10.0 Calibration and Standardization
Same as Section 10.0 of Method 2A, Method 10, and Method 25A.
Note: If a manifold system is used for the exhaust analyzers, all
the analyzers and sample pumps must be operating when the analyzer
calibrations are performed.
10.1 If an analyzer output does not meet the specifications of the
method, invalidate the test data for the period. Alternatively,
calculate the exhaust volume results using initial calibration data and
using final calibration data and report both resulting volumes. Then,
for emissions calculations, use the volume measurement resulting in the
greatest emission rate or concentration.
11.0 Analytical Procedure
Sample collection and analysis are concurrent for this method (see
Section 8.0).
12.0 Data Analysis and Calculations
Carry out the calculations, retaining at least one extra decimal
figure beyond that of the acquired data. Round off figures after the
final calculation.
12.1 Nomenclature.
Coe=Mean carbon monoxide concentration in system exhaust,
ppm.
(CO2)2=Ambient carbon dioxide concentration, ppm
(if not measured during the test period, may be assumed to equal 300
ppm).
(CO2)e=Mean carbon dioxide concentration in system
exhaust, ppm.
HCe=Mean organic concentration in system exhaust as defined
by the calibration gas, ppm.
Hci=Mean organic concentration in system inlet as defined by
the calibration gas, ppm.
Ke=Hydrocarbon calibration gas factor for the exhaust
hydrocarbon analyzer, unitless [equal to the number of carbon atoms per
molecule of the gas used to calibrate the analyzer (2 for ethane, 3 for
propane, etc.)].
Ki=Hydrocarbon calibration gas factor for the inlet
hydrocarbon analyzer, unitless.
Ves=Exhaust gas volume, m\3\.
Vis=Inlet gas volume, m\3\.
Qes=Exhaust gas volume flow rate, m\3\/min.
Qis=Inlet gas volume flow rate, m\3\/min.
[thetas]=Sample run time, min.
s=Standard conditions: 20 [deg]C, 760 mm Hg.
12.2 Concentrations. Determine mean concentrations of inlet
organics, outlet CO2, outlet CO, and outlet organics
according to the procedures in the respective methods and the analyzers'
calibration curves, and for the time intervals specified in the
applicable regulations.
12.3 Exhaust Gas Volume. Calculate the exhaust gas volume as
follows:
[GRAPHIC] [TIFF OMITTED] TR17OC00.067
12.4 Exhaust Gas Volume Flow Rate. Calculate the exhaust gas volume
flow rate as follows:
[GRAPHIC] [TIFF OMITTED] TR17OC00.210
[[Page 35]]
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
Same as Section 16.0 of Method 2A, Method 10, and Method 25A.
17.0 Tables, Diagrams, Flowcharts, and Validation Data [Reserved]
Method 2C--Determination of Gas Velocity and Volumetric Flow Rate in
Small Stacks or Ducts (Standard Pitot Tube)
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material is incorporated by reference from other
methods in this part. Therefore, to obtain reliable results, persons
using this method should also have a thorough knowledge of at least the
following additional test methods: Method 1, Method 2.
1.0 Scope and Application
1.1 This method is applicable for the determination of average
velocity and volumetric flow rate of gas streams in small stacks or
ducts. Limits on the applicability of this method are identical to those
set forth in Method 2, Section 1.0, except that this method is limited
to stationary source stacks or ducts less than about 0.30 meter (12 in.)
in diameter, or 0.071 m\2\ (113 in.\2\) in cross-sectional area, but
equal to or greater than about 0.10 meter (4 in.) in diameter, or 0.0081
m\2\ (12.57 in.\2\) in cross-sectional area.
1.2 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method
2.1 The average gas velocity in a stack or duct is determined from
the gas density and from measurement of velocity heads with a standard
pitot tube.
3.0 Definitions [Reserved]
4.0 Interferences [Reserved]
5.0 Safety
5.1 This method may involve hazardous materials, operations, and
equipment. This test method may not address all of the safety problems
associated with its use. It is the responsibility of the user of this
test method to establish appropriate safety and health practices and
determine the applicability of regulatory limitations prior to
performing this test method.
6.0 Equipment and Supplies
Same as Method 2, Section 6.0, with the exception of the following:
6.1 Standard Pitot Tube (instead of Type S). A standard pitot tube
which meets the specifications of Section 6.7 of Method 2. Use a
coefficient of 0.99 unless it is calibrated against another standard
pitot tube with a NIST-traceable coefficient (see Section 10.2 of Method
2).
6.2 Alternative Pitot Tube. A modified hemispherical-nosed pitot
tube (see Figure 2C-1), which features a shortened stem and enlarged
impact and static pressure holes. Use a coefficient of 0.99 unless it is
calibrated as mentioned in Section 6.1 above. This pitot tube is useful
in particulate liquid droplet-laden gas streams when a ``back purge'' is
ineffective.
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection and Analysis
8.1 Follow the general procedures in Section 8.0 of Method 2, except
conduct the measurements at the traverse points specified in Method 1A.
The static and impact pressure holes of standard pitot tubes are
susceptible to plugging in particulate-laden gas streams. Therefore,
adequate proof that the openings of the pitot tube have not plugged
during the traverse period must be furnished; this can be done by taking
the velocity head ([Delta]p) heading at the final traverse point,
cleaning out the impact and static holes of the standard pitot tube by
``back-purging'' with pressurized air, and then taking another [Delta]p
reading. If the [Delta]p readings made before and after the air purge
are the same (within 5 percent) the traverse is
acceptable. Otherwise, reject the run. Note that if the [Delta]p at the
final traverse point is unsuitably low, another point may be selected.
If ``back purging'' at regular intervals is part of the procedure, then
take comparative [Delta]p readings, as above, for the last two back
purges at which suitably high [Delta]p readings are observed.
9.0 Quality Control
------------------------------------------------------------------------
Quality control
Section measure Effect
------------------------------------------------------------------------
10.0.......................... Sampling Ensure accurate
equipment measurement of stack
calibration. gas velocity head.
------------------------------------------------------------------------
[[Page 36]]
10.0 Calibration and Standardization
Same as Method 2, Sections 10.2 through 10.4.
11.0 Analytical Procedure
Sample collection and analysis are concurrent for this method (see
Section 8.0).
12.0 Calculations and Data Analysis
Same as Method 2, Section 12.0.
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
Same as Method 2, Section 16.0.
17.0 Tables, Diagrams, Flowcharts, and Validation Data
[GRAPHIC] [TIFF OMITTED] TR17OC00.068
Method 2D--Measurement of Gas Volume Flow Rates in Small Pipes and Ducts
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material is incorporated by reference from other
methods in this part. Therefore, to obtain reliable results, persons
using this method should also have a thorough knowledge of at least the
following additional test methods: Method 1, Method 2, and Method 2A.
1.0 Scope and Application
1.1 This method is applicable for the determination of the
volumetric flow rates of gas streams in small pipes and ducts. It can be
applied to intermittent or variable gas flows only with particular
caution.
1.2 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method
2.1 All the gas flow in the pipe or duct is directed through a
rotameter, orifice plate or similar device to measure flow rate or
pressure drop. The device has been previously calibrated in a manner
that insures its proper calibration for the gas being measured. Absolute
temperature and pressure measurements are made to allow correction of
volumetric flow rates to standard conditions.
3.0 Definitions [Reserved]
4.0 Interferences [Reserved]
5.0 Safety
5.1 This method may involve hazardous materials, operations, and
equipment. This test method may not address all of the safety problems
associated with its use. It is the responsibility of the user of this
test method to establish appropriate safety and health practices and
determine the applicability of regulatory limitations prior to
performing this test method.
[[Page 37]]
6.0 Equipment and Supplies
Specifications for the apparatus are given below. Any other
apparatus that has been demonstrated (subject to approval of the
Administrator) to be capable of meeting the specifications will be
considered acceptable.
6.1 Gas Metering Rate or Flow Element Device. A rotameter, orifice
plate, or other volume rate or pressure drop measuring device capable of
measuring the stack flow rate to within 5 percent.
The metering device shall be equipped with a temperature gauge accurate
to within 2 percent of the minimum absolute stack
temperature and a pressure gauge (accurate to within 5 mm Hg). The capacity of the metering device shall be
sufficient for the expected maximum and minimum flow rates at the stack
gas conditions. The magnitude and variability of stack gas flow rate,
molecular weight, temperature, pressure, dewpoint, and corrosive
characteristics, and pipe or duct size are factors to consider in
choosing a suitable metering device.
6.2 Barometer. Same as Method 2, Section 6.5.
6.3 Stopwatch. Capable of measurement to within 1 second.
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection and Analysis
8.1 Installation and Leak Check. Same as Method 2A, Sections 8.1 and
8.2, respectively.
8.2 Volume Rate Measurement.
8.2.1 Continuous, Steady Flow. At least once an hour, record the
metering device flow rate or pressure drop reading, and the metering
device temperature and pressure. Make a minimum of 12 equally spaced
readings of each parameter during the test period. Record the barometric
pressure at the beginning and end of the test period. Record the data on
a table similar to that shown in Figure 2D-1.
8.2.2 Noncontinuous and Nonsteady Flow. Use volume rate devices with
particular caution. Calibration will be affected by variation in stack
gas temperature, pressure and molecular weight. Use the procedure in
Section 8.2.1 with the addition of the following: Record all the
metering device parameters on a time interval frequency sufficient to
adequately profile each process cyclical or noncontinuous event. A
multichannel continuous recorder may be used.
9.0 Quality Control
------------------------------------------------------------------------
Quality control
Section measure Effect
------------------------------------------------------------------------
10.0.......................... Sampling Ensure accurate
equipment measurement of stack
calibration. gas flow rate or
sample volume.
------------------------------------------------------------------------
10.0 Calibration and Standardization
Same as Method 2A, Section 10.0, with the following exception:
10.1 Gas Metering Device. Same as Method 2A, Section 10.1, except
calibrate the metering device with the principle stack gas to be
measured (examples: air, nitrogen) against a standard reference meter. A
calibrated dry gas meter is an acceptable reference meter. Ideally,
calibrate the metering device in the field with the actual gas to be
metered. For metering devices that have a volume rate readout, calculate
the test metering device calibration coefficient, Ym, for
each run shown in Equation 2D-2 Section 12.3.
10.2 For metering devices that do not have a volume rate readout,
refer to the manufacturer's instructions to calculate the Vm2
corresponding to each Vr.
10.3 Temperature Gauge. Use the procedure and specifications in
Method 2A, Section 10.2. Perform the calibration at a temperature that
approximates field test conditions.
10.4 Barometer. Calibrate the barometer to be used in the field test
with a mercury barometer prior to the field test.
11.0 Analytical Procedure.
Sample collection and analysis are concurrent for this method (see
Section 8.0).
12.0 Data Analysis and Calculations
12.1 Nomenclature.
Pbar=Barometric pressure, mm Hg (in. Hg).
Pm=Test meter average static pressure, mm Hg (in. Hg).
Qr=Reference meter volume flow rate reading, m\3\/min (ft\3\/
min).
Qm=Test meter volume flow rate reading, m\3\/min (ft\3\/min).
Tr=Absolute reference meter average temperature, [deg]K
([deg]R).
Tm=Absolute test meter average temperature, [deg]K ([deg]R).
Kl=0.3855 [deg]K/mm Hg for metric units,=17.65 [deg]R/in. Hg
for English units.
12.2 Gas Flow Rate.
[GRAPHIC] [TIFF OMITTED] TR17OC00.069
12.3 Test Meter Device Calibration Coefficient. Calculation for
testing metering device calibration coefficient, Ym.
[[Page 38]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.070
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
1. Spink, L.K. Principles and Practice of Flowmeter Engineering. The
Foxboro Company. Foxboro, MA. 1967.
2. Benedict, R.P. Fundamentals of Temperature, Pressure, and Flow
Measurements. John Wiley & Sons, Inc. New York, NY. 1969.
3. Orifice Metering of Natural Gas. American Gas Association.
Arlington, VA. Report No. 3. March 1978. 88 pp.
17.0 Tables, Diagrams, Flowcharts, and Validation Data
Plant___________________________________________________________________
Date____________________________________________________________________
Run No._________________________________________________________________
Sample location_________________________________________________________
Barometric pressure (mm Hg):
Start___________________________________________________________________
Finish__________________________________________________________________
Operators_______________________________________________________________
Metering device No._____________________________________________________
Calibration coefficient_________________________________________________
Calibration gas_________________________________________________________
Date to recalibrate_____________________________________________________
----------------------------------------------------------------------------------------------------------------
Temperature
Time Flow rate reading Static Pressure ---------------------------------------
[mm Hg (in. Hg)] [deg]C ([deg]F) [deg]K ([deg]R)
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Average
----------------------------------------------------------------------------------------------------------------
Figure 2D-1. Volume Flow Rate Measurement Data
Method 2E--Determination of Landfill Gas Production Flow Rate
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling and analytical)
essential to its performance. Some material is incorporated by reference
from other methods in this part. Therefore, to obtain reliable results,
persons using this method should also have a thorough knowledge of at
least the following additional test methods: Methods 2 and 3C.
1.0 Scope and Application
1.1 Applicability. This method applies to the measurement of
landfill gas (LFG) production flow rate from municipal solid waste
landfills and is used to calculate the flow rate of nonmethane organic
compounds (NMOC) from landfills.
1.2 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method
2.1 Extraction wells are installed either in a cluster of three or
at five dispersed locations in the landfill. A blower is used to extract
LFG from the landfill. LFG composition, landfill pressures, and orifice
pressure differentials from the wells are measured and the landfill gas
production flow rate is calculated.
[[Page 39]]
3.0 Definitions [Reserved]
4.0 Interferences [Reserved]
5.0 Safety
5.1 Since this method is complex, only experienced personnel should
perform the test. Landfill gas contains methane, therefore explosive
mixtures may exist at or near the landfill. It is advisable to take
appropriate safety precautions when testing landfills, such as
refraining from smoking and installing explosion-proof equipment.
6.0 Equipment and Supplies
6.1 Well Drilling Rig. Capable of boring a 0.61 m (24 in.) diameter
hole into the landfill to a minimum of 75 percent of the landfill depth.
The depth of the well shall not extend to the bottom of the landfill or
the liquid level.
6.2 Gravel. No fines. Gravel diameter should be appreciably larger
than perforations stated in Sections 6.10 and 8.2.
6.3 Bentonite.
6.4 Backfill Material. Clay, soil, and sandy loam have been found to
be acceptable.
6.5 Extraction Well Pipe. Minimum diameter of 3 in., constructed of
polyvinyl chloride (PVC), high density polyethylene (HDPE), fiberglass,
stainless steel, or other suitable nonporous material capable of
transporting landfill gas.
6.6 Above Ground Well Assembly. Valve capable of adjusting gas flow,
such as a gate, ball, or butterfly valve; sampling ports at the well
head and outlet; and a flow measuring device, such as an in-line orifice
meter or pitot tube. A schematic of the aboveground well head assembly
is shown in Figure 2E-1.
6.7 Cap. Constructed of PVC or HDPE.
6.8 Header Piping. Constructed of PVC or HDPE.
6.9 Auger. Capable of boring a 0.15-to 0.23-m (6-to 9-in.) diameter
hole to a depth equal to the top of the perforated section of the
extraction well, for pressure probe installation.
6.10 Pressure Probe. Constructed of PVC or stainless steel (316),
0.025-m (1-in.). Schedule 40 pipe. Perforate the bottom two-thirds. A
minimum requirement for perforations is slots or holes with an open area
equivalent to four 0.006-m (\1/4\-in.) diameter holes spaced 90[deg]
apart every 0.15 m (6 in.).
6.11 Blower and Flare Assembly. Explosion-proof blower, capable of
extracting LFG at a flow rate of 8.5 m\3\/min (300 ft\3\/min), a water
knockout, and flare or incinerator.
6.12 Standard Pitot Tube and Differential Pressure Gauge for Flow
Rate Calibration with Standard Pitot. Same as Method 2, Sections 6.7 and
6.8.
6.13 Orifice Meter. Orifice plate, pressure tabs, and pressure
measuring device to measure the LFG flow rate.
6.14 Barometer. Same as Method 4, Section 6.1.5.
6.15 Differential Pressure Gauge. Water-filled U-tube manometer or
equivalent, capable of measuring within 0.02 mm Hg (0.01 in.
H2O), for measuring the pressure of the pressure probes.
7.0 Reagents and Standards. Not Applicable
8.0 Sample Collection, Preservation, Storage, and Transport
8.1 Placement of Extraction Wells. The landfill owner or operator
may install a single cluster of three extraction wells in a test area or
space five equal-volume wells over the landfill. The cluster wells are
recommended but may be used only if the composition, age of the refuse,
and the landfill depth of the test area can be determined.
8.1.1 Cluster Wells. Consult landfill site records for the age of
the refuse, depth, and composition of various sections of the landfill.
Select an area near the perimeter of the landfill with a depth equal to
or greater than the average depth of the landfill and with the average
age of the refuse between 2 and 10 years old. Avoid areas known to
contain nondecomposable materials, such as concrete and asbestos. Locate
the cluster wells as shown in Figure 2E-2.
8.1.1.1 The age of the refuse in a test area will not be uniform, so
calculate a weighted average age of the refuse as shown in Section 12.2.
8.1.2 Equal Volume Wells. Divide the sections of the landfill that
are at least 2 years old into five areas representing equal volumes.
Locate an extraction well near the center of each area.
8.2 Installation of Extraction Wells. Use a well drilling rig to dig
a 0.6 m (24 in.) diameter hole in the landfill to a minimum of 75
percent of the landfill depth, not to extend to the bottom of the
landfill or the liquid level. Perforate the bottom two thirds of the
extraction well pipe. A minimum requirement for perforations is holes or
slots with an open area equivalent to 0.01-m (0.5-in.) diameter holes
spaced 90[deg] apart every 0.1 to 0.2 m (4 to 8 in.). Place the
extraction well in the center of the hole and backfill with gravel to a
level 0.30 m (1 ft) above the perforated section. Add a layer of
backfill material 1.2 m (4 ft) thick. Add a layer of bentonite 0.9 m (3
ft) thick, and backfill the remainder of the hole with cover material or
material equal in permeability to the existing cover material. The
specifications for extraction well installation are shown in Figure 2E-
3.
8.3 Pressure Probes. Shallow pressure probes are used in the check
for infiltration of air into the landfill, and deep pressure probes are
use to determine the radius of influence. Locate pressure probes along
three radial arms approximately 120[deg] apart at distances of 3, 15,
30, and 45 m (10, 50, 100, and
[[Page 40]]
150 ft) from the extraction well. The tester has the option of locating
additional pressure probes at distances every 15 m (50 feet) beyond 45 m
(150 ft). Example placements of probes are shown in Figure 2E-4. The 15-
, 30-, and 45-m, (50-, 100-, and 150-ft) probes from each well, and any
additional probes located along the three radial arms (deep probes),
shall extend to a depth equal to the top of the perforated section of
the extraction wells. All other probes (shallow probes) shall extend to
a depth equal to half the depth of the deep probes.
8.3.1 Use an auger to dig a hole, 0.15- to 0.23-m (6-to 9-in.) in
diameter, for each pressure probe. Perforate the bottom two thirds of
the pressure probe. A minimum requirement for perforations is holes or
slots with an open area equivalent to four 0.006-m (0.25-in.) diameter
holes spaced 90[deg] apart every 0.15 m (6 in.). Place the pressure
probe in the center of the hole and backfill with gravel to a level 0.30
m (1 ft) above the perforated section. Add a layer of backfill material
at least 1.2 m (4 ft) thick. Add a layer of bentonite at least 0.3 m (1
ft) thick, and backfill the remainder of the hole with cover material or
material equal in permeability to the existing cover material. The
specifications for pressure probe installation are shown in Figure 2E-5.
8.4 LFG Flow Rate Measurement. Place the flow measurement device,
such as an orifice meter, as shown in Figure 2E-1. Attach the wells to
the blower and flare assembly. The individual wells may be ducted to a
common header so that a single blower, flare assembly, and flow meter
may be used. Use the procedures in Section 10.1 to calibrate the flow
meter.
8.5 Leak-Check. A leak-check of the above ground system is required
for accurate flow rate measurements and for safety. Sample LFG at the
well head sample port and at the outlet sample port. Use Method 3C to
determine nitrogen (N2) concentrations. Determine the
difference between the well head and outlet N2 concentrations
using the formula in Section 12.3. The system passes the leak-check if
the difference is less than 10,000 ppmv.
8.6 Static Testing. Close the control valves on the well heads
during static testing. Measure the gauge pressure (Pg) at
each deep pressure probe and the barometric pressure (Pbar)
every 8 hours (hr) for 3 days. Convert the gauge pressure of each deep
pressure probe to absolute pressure using the equation in Section 12.4.
Record as Pi (initial absolute pressure).
8.6.1 For each probe, average all of the 8-hr deep pressure probe
readings (Pi) and record as Pia (average absolute
pressure). Pia is used in Section 8.7.5 to determine the
maximum radius of influence.
8.6.2 Measure the static flow rate of each well once during static
testing.
8.7 Short-Term Testing. The purpose of short-term testing is to
determine the maximum vacuum that can be applied to the wells without
infiltration of ambient air into the landfill. The short-term testing is
performed on one well at a time. Burn all LFG with a flare or
incinerator.
8.7.1 Use the blower to extract LFG from a single well at a rate at
least twice the static flow rate of the respective well measured in
Section 8.6.2. If using a single blower and flare assembly and a common
header system, close the control valve on the wells not being measured.
Allow 24 hr for the system to stabilize at this flow rate.
8.7.2 Test for infiltration of air into the landfill by measuring
the gauge pressures of the shallow pressure probes and using Method 3C
to determine the LFG N2 concentration. If the LFG
N2 concentration is less than 5 percent and all of the
shallow probes have a positive gauge pressure, increase the blower
vacuum by 3.7 mm Hg (2 in. H2O), wait 24 hr, and repeat the
tests for infiltration. Continue the above steps of increasing blower
vacuum by 3.7 mm Hg (2 in. H2O), waiting 24 hr, and testing
for infiltration until the concentration of N2 exceeds 5
percent or any of the shallow probes have a negative gauge pressure.
When this occurs,reduce the blower vacuum to the maximum setting at
which the N2 concentration was less than 5 percent and the
gauge pressures of the shallow probes are positive.
8.7.3 At this blower vacuum, measure atmospheric pressure
(Pbar) every 8 hr for 24 hr, and record the LFG flow rate
(Qs) and the probe gauge pressures (Pf) for all of
the probes. Convert the gauge pressures of the deep probes to absolute
pressures for each 8-hr reading at Qs as shown in Section
12.4.
8.7.4 For each probe, average the 8-hr deep pressure probe absolute
pressure readings and record as Pfa (the final average
absolute pressure).
8.7.5 For each probe, compare the initial average pressure
(Pia) from Section 8.6.1 to the final average pressure
(Pfa). Determine the furthermost point from the well head
along each radial arm where Pfa <= Pia. This
distance is the maximum radius of influence (Rm), which is
the distance from the well affected by the vacuum. Average these values
to determine the average maximum radius of influence (Rma).
8.7.6 Calculate the depth (Dst) affected by the
extraction well during the short term test as shown in Section 12.6. If
the computed value of Dst exceeds the depth of the landfill,
set Dst equal to the landfill depth.
8.7.7 Calculate the void volume (V) for the extraction well as shown
in Section 12.7.
8.7.8 Repeat the procedures in Section 8.7 for each well.
8.8 Calculate the total void volume of the test wells
(Vv) by summing the void volumes (V) of each well.
[[Page 41]]
8.9 Long-Term Testing. The purpose of long-term testing is to
extract two void volumes of LFG from the extraction wells. Use the
blower to extract LFG from the wells. If a single Blower and flare
assembly and common header system are used, open all control valves and
set the blower vacuum equal to the highest stabilized blower vacuum
demonstrated by any individual well in Section 8.7. Every 8 hr, sample
the LFG from the well head sample port, measure the gauge pressures of
the shallow pressure probes, the blower vacuum, the LFG flow rate, and
use the criteria for infiltration in Section 8.7.2 and Method 3C to test
for infiltration. If infiltration is detected, do not reduce the blower
vacuum, instead reduce the LFG flow rate from the well by adjusting the
control valve on the well head. Adjust each affected well individually.
Continue until the equivalent of two total void volumes (Vv)
have been extracted, or until Vt=2Vv.
8.9.1 Calculate Vt, the total volume of LFG extracted
from the wells, as shown in Section 12.8.
8.9.2 Record the final stabilized flow rate as Qf and the
gauge pressure for each deep probe. If, during the long term testing,
the flow rate does not stabilize, calculate Qf by averaging
the last 10 recorded flow rates.
8.9.3 For each deep probe, convert each gauge pressure to absolute
pressure as in Section 12.4. Average these values and record as
Psa. For each probe, compare Pia to
Psa. Determine the furthermost point from the well head along
each radial arm where Psa <= Pia. This distance is
the stabilized radius of influence. Average these values to determine
the average stabilized radius of influence (Rsa).
8.10 Determine the NMOC mass emission rate using the procedures in
Section 12.9 through 12.15.
9.0 Quality Control
9.1 Miscellaneous Quality Control Measures.
------------------------------------------------------------------------
Quality control
Section measure Effect
------------------------------------------------------------------------
10.1.......................... LFG flow rate Ensures accurate
meter measurement of LFG
calibration. flow rate and sample
volume
------------------------------------------------------------------------
10.0 Calibration and Standardization
10.1 LFG Flow Rate Meter (Orifice) Calibration Procedure. Locate a
standard pitot tube in line with an orifice meter. Use the procedures in
Section 8, 12.5, 12.6, and 12.7 of Method 2 to determine the average dry
gas volumetric flow rate for at least five flow rates that bracket the
expected LFG flow rates, except in Section 8.1, use a standard pitot
tube rather than a Type S pitot tube. Method 3C may be used to determine
the dry molecular weight. It may be necessary to calibrate more than one
orifice meter in order to bracket the LFG flow rates. Construct a
calibration curve by plotting the pressure drops across the orifice
meter for each flow rate versus the average dry gas volumetric flow rate
in m\3\/min of the gas.
11.0 Procedures [Reserved]
12.0 Data Analysis and Calculations
12.1 Nomenclature.
A=Age of landfill, yr.
Aavg=Average age of the refuse tested, yr.
Ai=Age of refuse in the ith fraction, yr.
Ar=Acceptance rate, Mg/yr.
CNMOC=NMOC concentration, ppmv as hexane
(CNMOC=Ct/6).
Co=Concentration of N2 at the outlet, ppmv.
Ct=NMOC concentration, ppmv (carbon equivalent) from Method
25C.
Cw=Concentration of N2 at the wellhead, ppmv.
D=Depth affected by the test wells, m.
Dst=Depth affected by the test wells in the short-term test,
m.
e=Base number for natural logarithms (2.718).
f=Fraction of decomposable refuse in the landfill.
fi=Fraction of the refuse in the ith section.
k=Landfill gas generation constant, yr-1.
Lo=Methane generation potential, m\3\/Mg.
Lo'=Revised methane generation potential to account for the
amount of nondecomposable material in the landfill, m\3\/Mg.
Mi=Mass of refuse in the ith section, Mg.
Mr=Mass of decomposable refuse affected by the test well, Mg.
Pbar=Atmospheric pressure, mm Hg.
Pf=Final absolute pressure of the deep pressure probes during
short-term testing, mm Hg.
Pfa=Average final absolute pressure of the deep pressure
probes during short-term testing, mm Hg.
Pgf=final gauge pressure of the deep pressure probes, mm Hg.
Pgi=Initial gauge pressure of the deep pressure probes, mm
Hg.
Pi=Initial absolute pressure of the deep pressure probes
during static testing, mm Hg.
Pia=Average initial absolute pressure of the deep pressure
probes during static testing, mm Hg.
Ps=Final absolute pressure of the deep pressure probes during
long-term testing, mm Hg.
[[Page 42]]
Psa=Average final absolute pressure of the deep pressure
probes during long-term testing, mm Hg.
Qf=Final stabilized flow rate, m\3\/min.
Qi=LFG flow rate measured at orifice meter during the ith
interval, m\3\/min.
Qs=Maximum LFG flow rate at each well determined by short-
term test, m\3\/min.
Qt=NMOC mass emission rate, m\3\/min.
Rm=Maximum radius of influence, m.
Rma=Average maximum radius of influence, m.
Rs=Stabilized radius of influence for an individual well, m.
Rsa=Average stabilized radius of influence, m.
ti=Age of section i, yr.
tt=Total time of long-term testing, yr.
tvi=Time of the ith interval (usually 8), hr.
V=Void volume of test well, m\3\.
Vr=Volume of refuse affected by the test well, m\3\.
Vt=Total volume of refuse affected by the long-term testing,
m\3\.
Vv=Total void volume affected by test wells, m\3\.
WD=Well depth, m.
[rho]=Refuse density, Mg/m\3\ (Assume 0.64 Mg/m\3\ if data are
unavailable).
12.2 Use the following equation to calculate a weighted average age
of landfill refuse.
[GRAPHIC] [TIFF OMITTED] TR17OC00.071
12.3 Use the following equation to determine the difference in
N2 concentrations (ppmv) at the well head and outlet
location.
[GRAPHIC] [TIFF OMITTED] TR17OC00.072
12.4 Use the following equation to convert the gauge pressure
(Pg) of each initial deep pressure probe to absolute pressure
(Pi).
[GRAPHIC] [TIFF OMITTED] TR17OC00.073
12.5 Use the following equation to convert the gauge pressures of
the deep probes to absolute pressures for each 8-hr reading at
Qs.
[GRAPHIC] [TIFF OMITTED] TR17OC00.074
12.6 Use the following equation to calculate the depth
(Dst) affected by the extraction well during the short-term
test.
[GRAPHIC] [TIFF OMITTED] TR17OC00.075
12.7 Use the following equation to calculate the void volume for the
extraction well (V).
[GRAPHIC] [TIFF OMITTED] TR17OC00.076
12.8 Use the following equation to calculate Vt, the
total volume of LFG extracted from the wells.
[GRAPHIC] [TIFF OMITTED] TR17OC00.077
12.9 Use the following equation to calculate the depth affected by
the test well. If using cluster wells, use the average depth of the
wells for WD. If the value of D is greater than the depth of the
landfill, set D equal to the landfill depth.
[GRAPHIC] [TIFF OMITTED] TR17OC00.078
12.10 Use the following equation to calculate the volume of refuse
affected by the test well.
[GRAPHIC] [TIFF OMITTED] TR17OC00.079
12.11 Use the following equation to calculate the mass affected by
the test well.
[GRAPHIC] [TIFF OMITTED] TR17OC00.080
12.12 Modify Lo to account for the nondecomposable refuse
in the landfill.
[GRAPHIC] [TIFF OMITTED] TR17OC00.081
12.13 In the following equation, solve for k (landfill gas
generation constant) by iteration. A suggested procedure is to select a
value for k, calculate the left side of the equation, and if not equal
to zero, select another value for k. Continue this process until the
left hand side of the equation equals zero, 0.001.
[GRAPHIC] [TIFF OMITTED] TR17OC00.082
12.14 Use the following equation to determine landfill NMOC mass
emission rate if the yearly acceptance rate of refuse has been
consistent (10 percent) over the life of the landfill.
[GRAPHIC] [TIFF OMITTED] TR17OC00.083
12.15 Use the following equation to determine landfill NMOC mass
emission rate if the acceptance rate has not been consistent over the
life of the landfill.
[[Page 43]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.084
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
1. Same as Method 2, Appendix A, 40 CFR Part 60.
2. Emcon Associates, Methane Generation and Recovery from Landfills.
Ann Arbor Science, 1982.
3. The Johns Hopkins University, Brown Station Road Landfill Gas
Resource Assessment, Volume 1: Field Testing and Gas Recovery
Projections. Laurel, Maryland: October 1982.
4. Mandeville and Associates, Procedure Manual for Landfill Gases
Emission Testing.
5. Letter and attachments from Briggum, S., Waste Management of
North America, to Thorneloe, S., EPA. Response to July 28, 1988 request
for additional information. August 18, 1988.
6. Letter and attachments from Briggum, S., Waste Management of
North America, to Wyatt, S., EPA. Response to December 7, 1988 request
for additional information. January 16, 1989.
17.0 Tables, Diagrams, Flowcharts, and Validation Data
[[Page 44]]
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[GRAPHIC] [TIFF OMITTED] TR17OC00.086
[[Page 46]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.087
[[Page 47]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.088
[[Page 48]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.089
Method 2F--Determination of Stack Gas Velocity And Volumetric Flow Rate
With Three-Dimensional Probes
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material has been incorporated from other methods in
this part. Therefore, to obtain reliable results, those using this
method should have a thorough knowledge of at least the following
additional test methods: Methods 1, 2, 3 or 3A, and 4.
1.0 Scope and Application
1.1 This method is applicable for the determination of yaw angle, pitch
angle, axial velocity and the volumetric flow rate of a gas
[[Page 49]]
stream in a stack or duct using a three-dimensional (3-D) probe. This
method may be used only when the average stack or duct gas velocity is
greater than or equal to 20 ft/sec. When the above condition cannot be
met, alternative procedures, approved by the Administrator, U.S.
Environmental Protection Agency, shall be used to make accurate flow
rate determinations.
2.0 Summary of Method
2.1 A 3-D probe is used to determine the velocity pressure and the
yaw and pitch angles of the flow velocity vector in a stack or duct. The
method determines the yaw angle directly by rotating the probe to null
the pressure across a pair of symmetrically placed ports on the probe
head. The pitch angle is calculated using probe-specific calibration
curves. From these values and a determination of the stack gas density,
the average axial velocity of the stack gas is calculated. The average
gas volumetric flow rate in the stack or duct is then determined from
the average axial velocity.
3.0 Definitions
3.1. Angle-measuring Device Rotational Offset (RADO). The rotational
position of an angle-measuring device relative to the reference scribe
line, as determined during the pre-test rotational position check
described in section 8.3.
3.2 Axial Velocity. The velocity vector parallel to the axis of the
stack or duct that accounts for the yaw and pitch angle components of
gas flow. The term ``axial'' is used herein to indicate that the
velocity and volumetric flow rate results account for the measured yaw
and pitch components of flow at each measurement point.
3.3 Calibration Pitot Tube. The standard (Prandtl type) pitot tube
used as a reference when calibrating a 3-D probe under this method.
3.4 Field Test. A set of measurements conducted at a specific unit
or exhaust stack/duct to satisfy the applicable regulation (e.g., a
three-run boiler performance test, a single-or multiple-load nine-run
relative accuracy test).
3.5 Full Scale of Pressure-measuring Device. Full scale refers to
the upper limit of the measurement range displayed by the device. For
bi-directional pressure gauges, full scale includes the entire pressure
range from the lowest negative value to the highest positive value on
the pressure scale.
3.6 Main probe. Refers to the probe head and that section of probe
sheath directly attached to the probe head. The main probe sheath is
distinguished from probe extensions, which are sections of sheath added
onto the main probe to extend its reach.
3.7 ``May,'' ``Must,'' ``Shall,'' ``Should,'' and the imperative
form of verbs.
3.7.1 ``May'' is used to indicate that a provision of this method is
optional.
3.7.2 ``Must,'' ``Shall,'' and the imperative form of verbs (such as
``record'' or ``enter'') are used to indicate that a provision of this
method is mandatory.
3.7.3 ``Should'' is used to indicate that a provision of this method
is not mandatory, but is highly recommended as good practice.
3.8 Method 1. Refers to 40 CFR part 60, appendix A, ``Method 1--
Sample and velocity traverses for stationary sources.''
3.9 Method 2. Refers to 40 CFR part 60, appendix A, ``Method 2--
Determination of stack gas velocity and volumetric flow rate (Type S
pitot tube).''
3.10 Method 2G. Refers to 40 CFR part 60, appendix A, ``Method 2G--
Determination of stack gas velocity and volumetric flow rate with two-
dimensional probes.''
3.11 Nominal Velocity. Refers to a wind tunnel velocity setting that
approximates the actual wind tunnel velocity to within 1.5 m/sec (5 ft/sec).
3.12 Pitch Angle. The angle between the axis of the stack or duct
and the pitch component of flow, i.e., the component of the total
velocity vector in a plane defined by the traverse line and the axis of
the stack or duct. (Figure 2F-1 illustrates the ``pitch plane.'') From
the standpoint of a tester facing a test port in a vertical stack, the
pitch component of flow is the vector of flow moving from the center of
the stack toward or away from that test port. The pitch angle is the
angle described by this pitch component of flow and the vertical axis of
the stack.
3.13 Readability. For the purposes of this method, readability for
an analog measurement device is one half of the smallest scale division.
For a digital measurement device, it is the number of decimals displayed
by the device.
3.14 Reference Scribe Line. A line permanently inscribed on the main
probe sheath (in accordance with section 6.1.6.1) to serve as a
reference mark for determining yaw angles.
3.15 Reference Scribe Line Rotational Offset (RSLO). The
rotational position of a probe's reference scribe line relative to the
probe's yaw-null position, as determined during the yaw angle
calibration described in section 10.5.
3.16 Response Time. The time required for the measurement system to
fully respond to a change from zero differential pressure and ambient
temperature to the stable stack or duct pressure and temperature
readings at a traverse point.
3.17 Tested Probe. A 3-D probe that is being calibrated.
3.18 Three-dimensional (3-D) Probe. A directional probe used to
determine the velocity pressure and yaw and pitch angles in a flowing
gas stream.
[[Page 50]]
3.19 Traverse Line. A diameter or axis extending across a stack or
duct on which measurements of differential pressure and flow angles are
made.
3.20 Wind Tunnel Calibration Location. A point, line, area, or
volume within the wind tunnel test section at, along, or within which
probes are calibrated. At a particular wind tunnel velocity setting, the
average velocity pressures at specified points at, along, or within the
calibration location shall vary by no more than 2 percent or 0.3 mm
H2O (0.01 in. H2O), whichever is less restrictive,
from the average velocity pressure at the calibration pitot tube
location. Air flow at this location shall be axial, i.e., yaw and pitch
angles within 3[deg]. Compliance with these flow
criteria shall be demonstrated by performing the procedures prescribed
in sections 10.1.1 and 10.1.2. For circular tunnels, no part of the
calibration location may be closer to the tunnel wall than 10.2 cm (4
in.) or 25 percent of the tunnel diameter, whichever is farther from the
wall. For elliptical or rectangular tunnels, no part of the calibration
location may be closer to the tunnel wall than 10.2 cm (4 in.) or 25
percent of the applicable cross-sectional axis, whichever is farther
from the wall.
3.21 Wind Tunnel with Documented Axial Flow. A wind tunnel facility
documented as meeting the provisions of sections 10.1.1 (velocity
pressure cross-check) and 10.1.2 (axial flow verification) using the
procedures described in these sections or alternative procedures
determined to be technically equivalent.
3.22 Yaw Angle. The angle between the axis of the stack or duct and
the yaw component of flow, i.e., the component of the total velocity
vector in a plane perpendicular to the traverse line at a particular
traverse point. (Figure 2F-1 illustrates the ``yaw plane.'') From the
standpoint of a tester facing a test port in a vertical stack, the yaw
component of flow is the vector of flow moving to the left or right from
the center of the stack as viewed by the tester. (This is sometimes
referred to as ``vortex flow,'' i.e., flow around the centerline of a
stack or duct.) The yaw angle is the angle described by this yaw
component of flow and the vertical axis of the stack. The algebraic sign
convention is illustrated in Figure 2F-2.
3.23 Yaw Nulling. A procedure in which a probe is rotated about its
axis in a stack or duct until a zero differential pressure reading
(``yaw null'') is obtained. When a 3-D probe is yaw-nulled, its impact
pressure port (P1) faces directly into the direction of flow
in the stack or duct and the differential pressure between pressure
ports P2 and P3 is zero.
4.0 Interferences [Reserved]
5.0 Safety
5.1 This test method may involve hazardous operations and the use of
hazardous materials or equipment. This method does not purport to
address all of the safety problems associated with its use. It is the
responsibility of the user to establish and implement appropriate safety
and health practices and to determine the applicability of regulatory
limitations before using this test method.
6.0 Equipment and Supplies
6.1 Three-dimensional Probes. The 3-D probes as specified in
subsections 6.1.1 through 6.1.3 below qualify for use based on
comprehensive wind tunnel and field studies involving both inter-and
intra-probe comparisons by multiple test teams. Other types of probes
shall not be used unless approved by the Administrator. Each 3-D probe
shall have a unique identification number or code permanently marked on
the main probe sheath. The minimum recommended diameter of the sensing
head of any probe used under this method is 2.5 cm (1 in.). Each probe
shall be calibrated prior to use according to the procedures in section
10. Manufacturer-supplied calibration data shall be used as example
information only, except when the manufacturer calibrates the 3-D probe
as specified in section 10 and provides complete documentation.
6.1.1 Five-hole prism-shaped probe. This type of probe consists of
five pressure taps in the flat facets of a prism-shaped sensing head.
The pressure taps are numbered 1 through 5, with the pressures measured
at each hole referred to as P1, P2, P3,
P4, and P5, respectively. Figure 2F-3 is an
illustration of the placement of pressure taps on a commonly available
five-hole prism-shaped probe, the 2.5-cm (1-in.) DAT probe. (Note:
Mention of trade names or specific products does not constitute
endorsement by the U.S. Environmental Protection Agency.) The numbering
arrangement for the prism-shaped sensing head presented in Figure 2F-3
shall be followed for correct operation of the probe. A brief
description of the probe measurements involved is as follows: the
differential pressure P2-P3 is used to yaw null
the probe and determine the yaw angle; the differential pressure
P4-P5 is a function of pitch angle; and the
differential pressure P1-P2 is a function of total
velocity.
6.1.2 Five-hole spherical probe. This type of probe consists of five
pressure taps in a spherical sensing head. As with the prism-shaped
probe, the pressure taps are numbered 1 through 5, with the pressures
measured at each hole referred to as P1, P2,
P3, P4, and P5, respectively. However,
the P4 and P5 pressure taps are in the reverse
location
[[Page 51]]
from their respective positions on the prism-shaped probe head. The
differential pressure P2-P3 is used to yaw null
the probe and determine the yaw angle; the differential pressure
P4-P5 is a function of pitch angle; and the
differential pressure P1-P2 is a function of total
velocity. A diagram of a typical spherical probe sensing head is
presented in Figure 2F-4. Typical probe dimensions are indicated in the
illustration.
6.1.3 A manual 3-D probe refers to a five-hole prism-shaped or
spherical probe that is positioned at individual traverse points and yaw
nulled manually by an operator. An automated 3-D probe refers to a
system that uses a computer-controlled motorized mechanism to position
the five-hole prism-shaped or spherical head at individual traverse
points and perform yaw angle determinations.
6.1.4 Other three-dimensional probes. [Reserved]
6.1.5 Probe sheath. The probe shaft shall include an outer sheath
to: (1) provide a surface for inscribing a permanent reference scribe
line, (2) accommodate attachment of an angle-measuring device to the
probe shaft, and (3) facilitate precise rotational movement of the probe
for determining yaw angles. The sheath shall be rigidly attached to the
probe assembly and shall enclose all pressure lines from the probe head
to the farthest position away from the probe head where an angle-
measuring device may be attached during use in the field. The sheath of
the fully assembled probe shall be sufficiently rigid and straight at
all rotational positions such that, when one end of the probe shaft is
held in a horizontal position, the fully extended probe meets the
horizontal straightness specifications indicated in section 8.2 below.
6.1.6 Scribe lines.
6.1.6.1 Reference scribe line. A permanent line, no greater than 1.6
mm (1/16 in.) in width, shall be inscribed on each manual probe that
will be used to determine yaw angles of flow. This line shall be placed
on the main probe sheath in accordance with the procedures described in
section 10.4 and is used as a reference position for installation of the
yaw angle-measuring device on the probe. At the discretion of the
tester, the scribe line may be a single line segment placed at a
particular position on the probe sheath (e.g., near the probe head),
multiple line segments placed at various locations along the length of
the probe sheath (e.g., at every position where a yaw angle-measuring
device may be mounted), or a single continuous line extending along the
full length of the probe sheath.
6.1.6.2 Scribe line on probe extensions. A permanent line may also
be inscribed on any probe extension that will be attached to the main
probe in performing field testing. This allows a yaw angle-measuring
device mounted on the extension to be readily aligned with the reference
scribe line on the main probe sheath.
6.1.6.3 Alignment specifications. This specification shall be met
separately, using the procedures in section 10.4.1, on the main probe
and on each probe extension. The rotational position of the scribe line
or scribe line segments on the main probe or any probe extension must
not vary by more than 2[deg]. That is, the difference between the
minimum and maximum of all of the rotational angles that are measured
along the full length of the main probe or the probe extension must not
exceed 2[deg].
6.1.7 Probe and system characteristics to ensure horizontal
stability.
6.1.7.1 For manual probes, it is recommended that the effective
length of the probe (coupled with a probe extension, if necessary) be at
least 0.9 m (3 ft.) longer than the farthest traverse point mark on the
probe shaft away from the probe head. The operator should maintain the
probe's horizontal stability when it is fully inserted into the stack or
duct. If a shorter probe is used, the probe should be inserted through a
bushing sleeve, similar to the one shown in Figure 2F-5, that is
installed on the test port; such a bushing shall fit snugly around the
probe and be secured to the stack or duct entry port in such a manner as
to maintain the probe's horizontal stability when fully inserted into
the stack or duct.
6.1.7.2 An automated system that includes an external probe casing
with a transport system shall have a mechanism for maintaining
horizontal stability comparable to that obtained by manual probes
following the provisions of this method. The automated probe assembly
shall also be constructed to maintain the alignment and position of the
pressure ports during sampling at each traverse point. The design of the
probe casing and transport system shall allow the probe to be removed
from the stack or duct and checked through direct physical measurement
for angular position and insertion depth.
6.1.8 The tubing that is used to connect the probe and the pressure-
measuring device should have an inside diameter of at least 3.2 mm (1/8
in.), to reduce the time required for pressure equilibration, and should
be as short as practicable.
6.2 Yaw Angle-measuring Device. One of the following devices shall
be used for measurement of the yaw angle of flow.
6.2.1 Digital inclinometer. This refers to a digital device capable
of measuring and displaying the rotational position of the probe to
within 1[deg]. The device shall be able to be
locked into position on the probe sheath or probe extension, so that it
indicates the probe's rotational position throughout the test. A
rotational position collar block that can be attached to the probe
sheath (similar
[[Page 52]]
to the collar shown in Figure 2F-6) may be required to lock the digital
inclinometer into position on the probe sheath.
6.2.2 Protractor wheel and pointer assembly. This apparatus, similar
to that shown in Figure 2F-7, consists of the following components.
6.2.2.1 A protractor wheel that can be attached to a port opening
and set in a fixed rotational position to indicate the yaw angle
position of the probe's scribe line relative to the longitudinal axis of
the stack or duct. The protractor wheel must have a measurement ring on
its face that is no less than 17.8 cm (7 in.) in diameter, shall be able
to be rotated to any angle and then locked into position on the stack or
duct port, and shall indicate angles to a resolution of 1[deg].
6.2.2.2 A pointer assembly that includes an indicator needle mounted
on a collar that can slide over the probe sheath and be locked into a
fixed rotational position on the probe sheath. The pointer needle shall
be of sufficient length, rigidity, and sharpness to allow the tester to
determine the probe's angular position to within 1[deg] from the
markings on the protractor wheel. Corresponding to the position of the
pointer, the collar must have a scribe line to be used in aligning the
pointer with the scribe line on the probe sheath.
6.2.3 Other yaw angle-measuring devices. Other angle-measuring
devices with a manufacturer's specified precision of 1[deg] or better
may be used, if approved by the Administrator.
6.3 Probe Supports and Stabilization Devices. When probes are used
for determining flow angles, the probe head should be kept in a stable
horizontal position. For probes longer than 3.0 m (10 ft.), the section
of the probe that extends outside the test port shall be secured. Three
alternative devices are suggested for maintaining the horizontal
position and stability of the probe shaft during flow angle
determinations and velocity pressure measurements: (1) Monorails
installed above each port, (2) probe stands on which the probe shaft may
be rested, or (3) bushing sleeves of sufficient length secured to the
test ports to maintain probes in a horizontal position. Comparable
provisions shall be made to ensure that automated systems maintain the
horizontal position of the probe in the stack or duct. The physical
characteristics of each test platform may dictate the most suitable type
of stabilization device. Thus, the choice of a specific stabilization
device is left to the judgment of the testers.
6.4 Differential Pressure Gauges. The pressure ([Delta]P) measuring
devices used during wind tunnel calibrations and field testing shall be
either electronic manometers (e.g., pressure transducers), fluid
manometers, or mechanical pressure gauges (e.g.,
Magnehelic[Delta] gauges). Use of electronic manometers is
recommended. Under low velocity conditions, use of electronic manometers
may be necessary to obtain acceptable measurements.
6.4.1 Differential pressure-measuring device. This refers to a
device capable of measuring pressure differentials and having a
readability of 1 percent of full scale. The device
shall be capable of accurately measuring the maximum expected pressure
differential. Such devices are used to determine the following pressure
measurements: velocity pressure, static pressure, yaw-null pressure, and
pitch-angle pressure. For an inclined-vertical manometer, the
readability specification of 1 percent shall be
met separately using the respective full-scale upper limits of the
inclined and vertical portions of the scales. To the extent practicable,
the device shall be selected such that most of the pressure readings are
between 10 and 90 percent of the device's full-scale measurement range
(as defined in section 3.5). Typical velocity pressure (P1-
P2) ranges for both the prism-shaped probe and the spherical
probe are 0 to 1.3 cm H2O (0 to 0.5 in. H2O), 0 to
5.1 cm H2O (0 to 2 in. H2O), and 0 to 12.7 cm
H2O (0 to 5 in. H2O). The pitch angle
(P4-P5) pressure range is typically -6.4 to +6.4
mm H2O (-0.25 to +0.25 in. H2O) or -12.7 to +12.7
mm H2O (-0.5 to +0.5 in. H2O) for the prism-shaped
probe, and -12.7 to +12.7 mm H2O (-0.5 to +0.5 in.
H2O) or -5.1 to +5.1 cm H2O (-2 to +2 in.
H2O) for the spherical probe. The pressure range for the yaw
null (P2-P3) readings is typically -12.7 to +12.7
mm H2O (-0.5 to +0.5 in. H2O) for both probe
types. In addition, pressure-measuring devices should be selected such
that the zero does not drift by more than 5 percent of the average
expected pressure readings to be encountered during the field test. This
is particularly important under low pressure conditions.
6.4.2 Gauge used for yaw nulling. The differential pressure-
measuring device chosen for yaw nulling the probe during the wind tunnel
calibrations and field testing shall be bi-directional, i.e., capable of
reading both positive and negative differential pressures. If a
mechanical, bi-directional pressure gauge is chosen, it shall have a
full-scale range no greater than 2.6 cm H2O (1 in.
H2O) [i.e., -1.3 to +1.3 cm H2O (-0.5 in. to +0.5
in.)].
6.4.3 Devices for calibrating differential pressure-measuring
devices. A precision manometer (e.g., a U-tube, inclined, or inclined-
vertical manometer, or micromanometer) or NIST (National Institute of
Standards and Technology) traceable pressure source shall be used for
calibrating differential pressure-measuring devices. The device shall be
maintained under laboratory conditions or in a similar protected
environment (e.g., a climate-controlled trailer). It shall not be used
in field tests. The precision manometer shall have a scale gradation of
0.3 mm H2O (0.01 in. H2O), or less, in the range
of 0 to 5.1 cm H2O (0 to 2 in. H2O) and 2.5 mm
H2O (0.1 in. H2O),
[[Page 53]]
or less, in the range of 5.1 to 25.4 cm H2O (2 to 10 in.
H2O). The manometer shall have manufacturer's documentation
that it meets an accuracy specification of at least 0.5 percent of full
scale. The NIST-traceable pressure source shall be recertified annually.
6.4.4 Devices used for post-test calibration check. A precision
manometer meeting the specifications in section 6.4.3, a pressure-
measuring device or pressure source with a documented calibration
traceable to NIST, or an equivalent device approved by the Administrator
shall be used for the post-test calibration check. The pressure-
measuring device shall have a readability equivalent to or greater than
the tested device. The pressure source shall be capable of generating
pressures between 50 and 90 percent of the range of the tested device
and known to within 1 percent of the full scale of
the tested device. The pressure source shall be recertified annually.
6.5 Data Display and Capture Devices. Electronic manometers (if
used) shall be coupled with a data display device (such as a digital
panel meter, personal computer display, or strip chart) that allows the
tester to observe and validate the pressure measurements taken during
testing. They shall also be connected to a data recorder (such as a data
logger or a personal computer with data capture software) that has the
ability to compute and retain the appropriate average value at each
traverse point, identified by collection time and traverse point.
6.6 Temperature Gauges. For field tests, a thermocouple or
resistance temperature detector (RTD) capable of measuring temperature
to within 3 [deg]C (5
[deg]F) of the stack or duct temperature shall be used. The thermocouple
shall be attached to the probe such that the sensor tip does not touch
any metal and is located on the opposite side of the probe head from the
pressure ports so as not to interfere with the gas flow around the probe
head. The position of the thermocouple relative to the pressure port
face openings shall be in the same configuration as used for the probe
calibrations in the wind tunnel. Temperature gauges used for wind tunnel
calibrations shall be capable of measuring temperature to within 0.6 [deg]C (1 [deg]F) of the
temperature of the flowing gas stream in the wind tunnel.
6.7 Stack or Duct Static Pressure Measurement. The pressure-
measuring device used with the probe shall be as specified in section
6.4 of this method. The static tap of a standard (Prandtl type) pitot
tube or one leg of a Type S pitot tube with the face opening planes
positioned parallel to the gas flow may be used for this measurement.
Also acceptable is the pressure differential reading of P1-
Pbar from a five-hole prism-shaped probe (e.g., Type DA or
DAT probe) with the P1 pressure port face opening positioned
parallel to the gas flow in the same manner as the Type S probe.
However, the spherical probe, as specified in section 6.1.2, is unable
to provide this measurement and shall not be used to take static
pressure measurements. Static pressure measurement is further described
in section 8.11.
6.8 Barometer. Same as Method 2, section 2.5.
6.9 Gas Density Determination Equipment. Method 3 or 3A shall be
used to determine the dry molecular weight of the stack gas. Method 4
shall be used for moisture content determination and computation of
stack gas wet molecular weight. Other methods may be used, if approved
by the Administrator.
6.10 Calibration Pitot Tube. Same as Method 2, section 2.7.
6.11 Wind Tunnel for Probe Calibration. Wind tunnels used to
calibrate velocity probes must meet the following design specifications.
6.11.1 Test section cross-sectional area. The flowing gas stream
shall be confined within a circular, rectangular, or elliptical duct.
The cross-sectional area of the tunnel must be large enough to ensure
fully developed flow in the presence of both the calibration pitot tube
and the tested probe. The calibration site, or ``test section,'' of the
wind tunnel shall have a minimum diameter of 30.5 cm (12 in.) for
circular or elliptical duct cross-sections or a minimum width of 30.5 cm
(12 in.) on the shorter side for rectangular cross-sections. Wind
tunnels shall meet the probe blockage provisions of this section and the
qualification requirements prescribed in section 10.1. The projected
area of the portion of the probe head, shaft, and attached devices
inside the wind tunnel during calibration shall represent no more than 4
percent of the cross-sectional area of the tunnel. The projected area
shall include the combined area of the calibration pitot tube and the
tested probe if both probes are placed simultaneously in the same cross-
sectional plane in the wind tunnel, or the larger projected area of the
two probes if they are placed alternately in the wind tunnel.
6.11.2 Velocity range and stability. The wind tunnel should be
capable of maintaining velocities between 6.1 m/sec and 30.5 m/sec (20
ft/sec and 100 ft/sec). The wind tunnel shall produce fully developed
flow patterns that are stable and parallel to the axis of the duct in
the test section.
6.11.3 Flow profile at the calibration location. The wind tunnel
shall provide axial flow within the test section calibration location
(as defined in section 3.20). Yaw and pitch angles in the calibration
location shall be within 3[deg] of 0[deg]. The
procedure for determining that this requirement has been met is
described in section 10.1.2.
6.11.4 Entry ports in the wind tunnel test section.
[[Page 54]]
6.11.4.1 Port for tested probe. A port shall be constructed for the
tested probe. The port should have an elongated slot parallel to the
axis of the duct at the test section. The elongated slot should be of
sufficient length to allow attaining all the pitch angles at which the
probe will be calibrated for use in the field. To facilitate alignment
of the probe during calibration, the test section should include a
window constructed of a transparent material to allow the tested probe
to be viewed. This port shall be located to allow the head of the tested
probe to be positioned within the calibration location (as defined in
section 3.20) at all pitch angle settings.
6.11.4.2 Port for verification of axial flow. Depending on the
equipment selected to conduct the axial flow verification prescribed in
section 10.1.2, a second port, located 90[deg] from the entry port for
the tested probe, may be needed to allow verification that the gas flow
is parallel to the central axis of the test section. This port should be
located and constructed so as to allow one of the probes described in
section 10.1.2.2 to access the same test point(s) that are accessible
from the port described in section 6.11.4.1.
6.11.4.3 Port for calibration pitot tube. The calibration pitot tube
shall be used in the port for the tested probe or a separate entry port.
In either case, all measurements with the calibration pitot tube shall
be made at the same point within the wind tunnel over the course of a
probe calibration. The measurement point for the calibration pitot tube
shall meet the same specifications for distance from the wall and for
axial flow as described in section 3.20 for the wind tunnel calibration
location.
6.11.5 Pitch angle protractor plate. A protractor plate shall be
attached directly under the port used with the tested probe and set in a
fixed position to indicate the pitch angle position of the probe
relative to the longitudinal axis of the wind tunnel duct (similar to
Figure 2F-8). The protractor plate shall indicate angles in 5[deg]
increments with a minimum resolution of 2[deg].
The tested probe shall be able to be locked into position at the desired
pitch angle delineated on the protractor. The probe head position shall
be maintained within the calibration location (as defined in section
3.20) in the test section of the wind tunnel during all tests across the
range of pitch angles.
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection and Analysis
8.1 Equipment Inspection and Set-Up
8.1.1 All probes, differential pressure-measuring devices, yaw
angle-measuring devices, thermocouples, and barometers shall have a
current, valid calibration before being used in a field test. (See
sections 10.3.3, 10.3.4, and 10.5 through10.10 for the applicable
calibration requirements.)
8.1.2 Before each field use of a 3-D probe, perform a visual
inspection to verify the physical condition of the probe head according
to the procedures in section 10.2. Record the inspection results on a
form similar to Table 2F-1. If there is visible damage to the 3-D probe,
the probe shall not be used until it is recalibrated.
8.1.3 After verifying that the physical condition of the probe head
is acceptable, set up the apparatus using lengths of flexible tubing
that are as short as practicable. Surge tanks installed between the
probe and pressure-measuring device may be used to dampen pressure
fluctuations provided that an adequate measurement response time (see
section 8.8) is maintained.
8.2 Horizontal Straightness Check. A horizontal straightness check
shall be performed before the start of each field test, except as
otherwise specified in this section. Secure the fully assembled probe
(including the probe head and all probe shaft extensions) in a
horizontal position using a stationary support at a point along the
probe shaft approximating the location of the stack or duct entry port
when the probe is sampling at the farthest traverse point from the stack
or duct wall. The probe shall be rotated to detect bends. Use an angle-
measuring device or trigonometry to determine the bend or sag between
the probe head and the secured end. (See Figure 2F-9.) Probes that are
bent or sag by more than 5[deg] shall not be used. Although this check
does not apply when the probe is used for a vertical traverse, care
should be taken to avoid the use of bent probes when conducting vertical
traverses. If the probe is constructed of a rigid steel material and
consists of a main probe without probe extensions, this check need only
be performed before the initial field use of the probe, when the probe
is recalibrated, when a change is made to the design or material of the
probe assembly, and when the probe becomes bent. With such probes, a
visual inspection shall be made of the fully assembled probe before each
field test to determine if a bend is visible. The probe shall be rotated
to detect bends. The inspection results shall be documented in the field
test report. If a bend in the probe is visible, the horizontal
straightness check shall be performed before the probe is used.
8.3 Rotational Position Check. Before each field test, and each time
an extension is added to the probe during a field test, a rotational
position check shall be performed on all manually operated probes
(except as noted in section 8.3.5, below) to ensure that, throughout
testing, the angle-measuring device is either: aligned to within 1[deg] of the rotational position of the reference
scribe line; or is affixed to the probe such that the rotational offset
of the device from the reference scribe line is known to within 1[deg]. This check shall consist of direct measurements
of the
[[Page 55]]
rotational positions of the reference scribe line and angle-measuring
device sufficient to verify that these specifications are met. Annex A
in section 18 of this method gives recommended procedures for performing
the rotational position check, and Table 2F-2 gives an example data
form. Procedures other than those recommended in Annex A in section 18
may be used, provided they demonstrate whether the alignment
specification is met and are explained in detail in the field test
report.
8.3.1 Angle-measuring device rotational offset. The tester shall
maintain a record of the angle-measuring device rotational offset,
RADO, as defined in section 3.1. Note that RADO is
assigned a value of 0[deg] when the angle-measuring device is aligned to
within 1[deg] of the rotational position of the
reference scribe line. The RADO shall be used to determine
the yaw angle of flow in accordance with section 8.9.4.
8.3.2 Sign of angle-measuring device rotational offset. The sign of
RADO is positive when the angle-measuring device (as viewed
from the ``tail'' end of the probe) is positioned in a clockwise
direction from the reference scribe line and negative when the device is
positioned in a counterclockwise direction from the reference scribe
line.
8.3.3 Angle-measuring devices that can be independently adjusted
(e.g., by means of a set screw), after being locked into position on the
probe sheath, may be used. However, the RADO must also take
into account this adjustment.
8.3.4 Post-test check. If probe extensions remain attached to the
main probe throughout the field test, the rotational position check
shall be repeated, at a minimum, at the completion of the field test to
ensure that the angle-measuring device has remained within 2[deg] of its rotational position established prior to
testing. At the discretion of the tester, additional checks may be
conducted after completion of testing at any sample port or after any
test run. If the 2[deg] specification is not met,
all measurements made since the last successful rotational position
check must be repeated. Section 18.1.1.3 of Annex A provides an example
procedure for performing the post-test check.
8.3.5 Exceptions.
8.3.5.1 A rotational position check need not be performed if, for
measurements taken at all velocity traverse points, the yaw angle-
measuring device is mounted and aligned directly on the reference scribe
line specified in sections 6.1.6.1 and 6.1.6.3 and no independent
adjustments, as described in section 8.3.3, are made to the device's
rotational position.
8.3.5.2 If extensions are detached and re-attached to the probe
during a field test, a rotational position check need only be performed
the first time an extension is added to the probe, rather than each time
the extension is re-attached, if the probe extension is designed to be
locked into a mechanically fixed rotational position (e.g., through use
of interlocking grooves) that can re-establish the initial rotational
position to within 1[deg].
8.4 Leak Checks. A pre-test leak check shall be conducted before
each field test. A post-test check shall be performed at the end of the
field test, but additional leak checks may be conducted after any test
run or group of test runs. The post-test check may also serve as the
pre-test check for the next group of test runs. If any leak check is
failed, all runs since the last passed leak check are invalid. While
performing the leak check procedures, also check each pressure device's
responsiveness to the changes in pressure.
8.4.1 To perform the leak check, pressurize the probe's
P1 pressure port until at least 7.6 cm H2O (3 in.
H2O) pressure, or a pressure corresponding to approximately
75 percent of the pressure-measuring device's measurement scale,
whichever is less, registers on the device; then, close off the pressure
port. The pressure shall remain stable [2.5 mm
H2O (0.10 in. H2O)] for at
least 15 seconds. Check the P2, P3, P4,
and P5 pressure ports in the same fashion. Other leak-check
procedures may be used, if approved by the Administrator.
8.5 Zeroing the Differential Pressure-measuring Device. Zero each
differential pressure-measuring device, including the device used for
yaw nulling, before each field test. At a minimum, check the zero after
each field test. A zero check may also be performed after any test run
or group of test runs. For fluid manometers and mechanical pressure
gauges (e.g., Magnehelic[Delta] gauges), the zero reading
shall not deviate from zero by more than 0.8 mm
H2O (0.03 in. H2O) or one
minor scale division, whichever is greater, between checks. For
electronic manometers, the zero reading shall not deviate from zero
between checks by more than: 0.3 mm H2O
(0.01 in. H2O), for full scales less
than or equal to 5.1 cm H2O (2.0 in. H2O); or
0.8 mm H2O (0.03
in. H2O), for full scales greater than 5.1 cm H2O
(2.0 in. H2O). (Note: If negative zero drift is not directly
readable, estimate the reading based on the position of the gauge oil in
the manometer or of the needle on the pressure gauge.) In addition, for
all pressure-measuring devices except those used exclusively for yaw
nulling, the zero reading shall not deviate from zero by more than 5
percent of the average measured differential pressure at any distinct
process condition or load level. If any zero check is failed at a
specific process condition or load level, all runs conducted at that
process condition or load level since the last passed zero check are
invalid.
8.6 Traverse Point Verification. The number and location of the
traverse points shall be selected based on Method 1 guidelines.
[[Page 56]]
The stack or duct diameter and port nipple lengths, including any
extension of the port nipples into stack or duct, shall be verified the
first time the test is performed; retain and use this information for
subsequent field tests, updating it as required. Physically measure the
stack or duct dimensions or use a calibrated laser device; do not use
engineering drawings of the stack or duct. The probe length necessary to
reach each traverse point shall be recorded to within 6.4 mm (1/4 in.) and, for manual
probes, marked on the probe sheath. In determining these lengths, the
tester shall take into account both the distance that the port flange
projects outside of the stack and the depth that any port nipple extends
into the gas stream. The resulting point positions shall reflect the
true distances from the inside wall of the stack or duct, so that when
the tester aligns any of the markings with the outside face of the stack
port, the probe's impact port shall be located at the appropriate
distance from the inside wall for the respective Method 1 traverse
point. Before beginning testing at a particular location, an out-of-
stack or duct verification shall be performed on each probe that will be
used to ensure that these position markings are correct. The distances
measured during the verification must agree with the previously
calculated distances to within 1/4 in. For manual
probes, the traverse point positions shall be verified by measuring the
distance of each mark from the probe's P1 pressure port. A
comparable out-of-stack test shall be performed on automated probe
systems. The probe shall be extended to each of the prescribed traverse
point positions. Then, the accuracy of the positioning for each traverse
point shall be verified by measuring the distance between the port
flange and the probe's P1 pressure port.
8.7 Probe Installation. Insert the probe into the test port. A solid
material shall be used to seal the port.
8.8 System Response Time. Determine the response time of the probe
measurement system. Insert and position the ``cold'' probe (at ambient
temperature and pressure) at any Method 1 traverse point. Read and
record the probe's P1-P2 differential pressure,
temperature, and elapsed time at 15-second intervals until stable
readings for both pressure and temperature are achieved. The response
time is the longer of these two elapsed times. Record the response time.
8.9 Sampling.
8.9.1 Yaw angle measurement protocol. With manual probes, yaw angle
measurements may be obtained in two alternative ways during the field
test, either by using a yaw angle-measuring device (e.g., digital
inclinometer) affixed to the probe, or using a protractor wheel and
pointer assembly. For horizontal traversing, either approach may be
used. For vertical traversing, i.e., when measuring from on top or into
the bottom of a horizontal duct, only the protractor wheel and pointer
assembly may be used. With automated probes, curve-fitting protocols may
be used to obtain yaw-angle measurements.
8.9.1.1 If a yaw angle-measuring device affixed to the probe is to
be used, lock the device on the probe sheath, aligning it either on the
reference scribe line or in the rotational offset position established
under section 8.3.1.
8.9.1.2 If a protractor wheel and pointer assembly is to be used,
follow the procedures in Annex B of this method.
8.9.1.3 Other yaw angle-determination procedures. If approved by the
Administrator, other procedures for determining yaw angle may be used,
provided that they are verified in a wind tunnel to be able to perform
the yaw angle calibration procedure as described in section 10.5.
8.9.2 Sampling strategy. At each traverse point, first yaw-null the
probe, as described in section 8.9.3, below. Then, with the probe
oriented into the direction of flow, measure and record the yaw angle,
the differential pressures and the temperature at the traverse point,
after stable readings are achieved, in accordance with sections 8.9.4
and 8.9.5. At the start of testing in each port (i.e., after a probe has
been inserted into the flue gas stream), allow at least the response
time to elapse before beginning to take measurements at the first
traverse point accessed from that port. Provided that the probe is not
removed from the flue gas stream, measurements may be taken at
subsequent traverse points accessed from the same test port without
waiting again for the response time to elapse.
8.9.3 Yaw-nulling procedure. In preparation for yaw angle
determination, the probe must first be yaw nulled. After positioning the
probe at the appropriate traverse point, perform the following
procedures.
8.9.3.1 Rotate the probe until a null differential pressure reading
(the difference in pressures across the P2 and P3
pressure ports is zero, i.e., P2=P3) is indicated
by the yaw angle pressure gauge. Read and record the angle displayed by
the angle-measuring device.
8.9.3.2 Sign of the measured angle. The angle displayed on the
angle-measuring device is considered positive when the probe's impact
pressure port (as viewed from the ``tail'' end of the probe) is oriented
in a clockwise rotational position relative to the stack or duct axis
and is considered negative when the probe's impact pressure port is
oriented in a counterclockwise rotational position (see Figure 2F-10).
8.9.4 Yaw angle determination. After performing the yaw-nulling
procedure in section
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8.9.3, determine the yaw angle of flow according to one of the following
procedures. Special care must be observed to take into account the signs
of the recorded angle and all offsets.
8.9.4.1 Direct-reading. If all rotational offsets are zero or if the
angle-measuring device rotational offset (RADO) determined in
section 8.3 exactly compensates for the scribe line rotational offset
(RSLO) determined in section 10.5, then the magnitude of the
yaw angle is equal to the displayed angle-measuring device reading from
section 8.9.3.1. The algebraic sign of the yaw angle is determined in
accordance with section 8.9.3.2.
Note: Under certain circumstances (e.g., testing of horizontal
ducts), a 90[deg] adjustment to the angle-measuring device readings may
be necessary to obtain the correct yaw angles.
8.9.4.2 Compensation for rotational offsets during data reduction.
When the angle-measuring device rotational offset does not compensate
for reference scribe line rotational offset, the following procedure
shall be used to determine the yaw angle:
(a) Enter the reading indicated by the angle-measuring device from
section 8.9.3.1.
(b) Associate the proper algebraic sign from section 8.9.3.2 with
the reading in step (a).
(c) Subtract the reference scribe line rotational offset,
RSLO, from the reading in step (b).
(d) Subtract the angle-measuring device rotational offset,
RADO, if any, from the result obtained in step (c).
(e) The final result obtained in step (d) is the yaw angle of flow.
Note: It may be necessary to first apply a 90[deg] adjustment to the
reading in step (a), in order to obtain the correct yaw angle.
8.9.4.3 Record the yaw angle measurements on a form similar to Table
2F-3.
8.9.5 Velocity determination. Maintain the probe rotational position
established during the yaw angle determination. Then, begin recording
the pressure-measuring device readings for the impact pressure
(P1-P2) and pitch angle pressure (P4-
P5). These pressure measurements shall be taken over a
sampling period of sufficiently long duration to ensure representative
readings at each traverse point. If the pressure measurements are
determined from visual readings of the pressure device or display, allow
sufficient time to observe the pulsation in the readings to obtain a
sight-weighted average, which is then recorded manually. If an automated
data acquisition system (e.g., data logger, computer-based data
recorder, strip chart recorder) is used to record the pressure
measurements, obtain an integrated average of all pressure readings at
the traverse point. Stack or duct gas temperature measurements shall be
recorded, at a minimum, once at each traverse point. Record all
necessary data as shown in the example field data form (Table 2F-3).
8.9.6 Alignment check. For manually operated probes, after the
required yaw angle and differential pressure and temperature
measurements have been made at each traverse point, verify (e.g., by
visual inspection) that the yaw angle-measuring device has remained in
proper alignment with the reference scribe line or with the rotational
offset position established in section 8.3. If, for a particular
traverse point, the angle-measuring device is found to be in proper
alignment, proceed to the next traverse point; otherwise, re-align the
device and repeat the angle and differential pressure measurements at
the traverse point. In the course of a traverse, if a mark used to
properly align the angle-measuring device (e.g., as described in section
18.1.1.1) cannot be located, re-establish the alignment mark before
proceeding with the traverse.
8.10 Probe Plugging. Periodically check for plugging of the pressure
ports by observing the responses on pressure differential readouts.
Plugging causes erratic results or sluggish responses. Rotate the probe
to determine whether the readouts respond in the expected direction. If
plugging is detected, correct the problem and repeat the affected
measurements.
8.11 Static Pressure. Measure the static pressure in the stack or
duct using the equipment described in section 6.7.
8.11.1 If a Type DA or DAT probe is used for this measurement,
position the probe at or between any traverse point(s) and rotate the
probe until a null differential pressure reading is obtained at
P2-P3. Rotate the probe 90[deg]. Disconnect the
P2 pressure side of the probe and read the pressure
P1-Pbar and record as the static pressure. (Note:
The spherical probe, specified in section 6.1.2, is unable to provide
this measurement and shall not be used to take static pressure
measurements.)
8.11.2 If a Type S probe is used for this measurement, position the
probe at or between any traverse point(s) and rotate the probe until a
null differential pressure reading is obtained. Disconnect the tubing
from one of the pressure ports; read and record the [Delta]P. For
pressure devices with one-directional scales, if a deflection in the
positive direction is noted with the negative side disconnected, then
the static pressure is positive. Likewise, if a deflection in the
positive direction is noted with the positive side disconnected, then
the static pressure is negative.
8.12 Atmospheric Pressure. Determine the atmospheric pressure at the
sampling elevation during each test run following the procedure
described in section 2.5 of Method 2.
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8.13 Molecular Weight. Determine the stack gas dry molecular weight.
For combustion processes or processes that emit essentially
CO2, O2, CO, and N2, use Method 3 or
3A. For processes emitting essentially air, an analysis need not be
conducted; use a dry molecular weight of 29.0. Other methods may be
used, if approved by the Administrator.
8.14 Moisture. Determine the moisture content of the stack gas using
Method 4 or equivalent.
8.15 Data Recording and Calculations. Record all required data on a
form similar to Table 2F-3.
8.15.1 Selection of appropriate calibration curves. Choose the
appropriate pair of F1 and F2 versus pitch angle
calibration curves, created as described in section 10.6.
8.15.2 Pitch angle derivation. Use the appropriate calculation
procedures in section 12.2 to find the pitch angle ratios that are
applicable at each traverse point. Then, find the pitch angles
corresponding to these pitch angle ratios on the ``F1 versus
pitch angle'' curve for the probe.
8.15.3 Velocity calibration coefficient derivation. Use the pitch
angle obtained following the procedures described in section 8.15.2 to
find the corresponding velocity calibration coefficients from the
``F2 versus pitch angle'' calibration curve for the probe.
8.15.4 Calculations. Calculate the axial velocity at each traverse
point using the equations presented in section 12.2 to account for the
yaw and pitch angles of flow. Calculate the test run average stack gas
velocity by finding the arithmetic average of the point velocity results
in accordance with sections 12.3 and 12.4, and calculate the stack gas
volumetric flow rate in accordance with section 12.5 or 12.6, as
applicable.
9.0 Quality Control
9.1 Quality Control Activities. In conjunction with the yaw angle
determination and the pressure and temperature measurements specified in
section 8.9, the following quality control checks should be performed.
9.1.1 Range of the differential pressure gauge. In accordance with
the specifications in section 6.4, ensure that the proper differential
pressure gauge is being used for the range of [Delta]P values
encountered. If it is necessary to change to a more sensitive gauge,
replace the gauge with a gauge calibrated according to section 10.3.3,
perform the leak check described in section 8.4 and the zero check
described in section 8.5, and repeat the differential pressure and
temperature readings at each traverse point.
9.1.2 Horizontal stability check. For horizontal traverses of a
stack or duct, visually check that the probe shaft is maintained in a
horizontal position prior to taking a pressure reading. Periodically,
during a test run, the probe's horizontal stability should be verified
by placing a carpenter's level, a digital inclinometer, or other angle-
measuring device on the portion of the probe sheath that extends outside
of the test port. A comparable check should be performed by automated
systems.
10.0 Calibration
10.1 Wind Tunnel Qualification Checks. To qualify for use in
calibrating probes, a wind tunnel shall have the design features
specified in section 6.11 and satisfy the following qualification
criteria. The velocity pressure cross-check in section 10.1.1 and axial
flow verification in section 10.1.2 shall be performed before the
initial use of the wind tunnel and repeated immediately after any
alteration occurs in the wind tunnel's configuration, fans, interior
surfaces, straightening vanes, controls, or other properties that could
reasonably be expected to alter the flow pattern or velocity stability
in the tunnel. The owner or operator of a wind tunnel used to calibrate
probes according to this method shall maintain records documenting that
the wind tunnel meets the requirements of sections 10.1.1 and 10.1.2 and
shall provide these records to the Administrator upon request.
10.1.1 Velocity pressure cross-check. To verify that the wind tunnel
produces the same velocity at the tested probe head as at the
calibration pitot tube impact port, perform the following cross-check.
Take three differential pressure measurements at the fixed calibration
pitot tube location, using the calibration pitot tube specified in
section 6.10, and take three measurements with the calibration pitot
tube at the wind tunnel calibration location, as defined in section
3.20. Alternate the measurements between the two positions. Perform this
procedure at the lowest and highest velocity settings at which the
probes will be calibrated. Record the values on a form similar to Table
2F-4. At each velocity setting, the average velocity pressure obtained
at the wind tunnel calibration location shall be within 2 percent or 2.5 mm H2O (0.01 in.
H2O), whichever is less restrictive, of the average velocity
pressure obtained at the fixed calibration pitot tube location. This
comparative check shall be performed at 2.5-cm (1-in.), or smaller,
intervals across the full length, width, and depth (if applicable) of
the wind tunnel calibration location. If the criteria are not met at
every tested point, the wind tunnel calibration location must be
redefined, so that acceptable results are obtained at every point.
Include the results of the velocity pressure cross-check in the
calibration data section of the field test report. (See section 16.1.4.)
10.1.2 Axial flow verification. The following procedures shall be
performed to demonstrate that there is fully developed axial flow within
the calibration location
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and at the calibration pitot tube location. Two testing options are
available to conduct this check.
10.1.2.1 Using a calibrated 3-D probe. A 3-D probe that has been
previously calibrated in a wind tunnel with documented axial flow (as
defined in section 3.21) may be used to conduct this check. Insert the
calibrated 3-D probe into the wind tunnel test section using the tested
probe port. Following the procedures in sections 8.9 and 12.2 of this
method, determine the yaw and pitch angles at all the point(s) in the
test section where the velocity pressure cross-check, as specified in
section 10.1.1, is performed. This includes all the points in the
calibration location and the point where the calibration pitot tube will
be located. Determine the yaw and pitch angles at each point. Repeat
these measurements at the highest and lowest velocities at which the
probes will be calibrated. Record the values on a form similar to Table
2F-5. Each measured yaw and pitch angle shall be within 3[deg] of 0[deg]. Exceeding the limits indicates
unacceptable flow in the test section. Until the problem is corrected
and acceptable flow is verified by repetition of this procedure, the
wind tunnel shall not be used for calibration of probes. Include the
results of the axial flow verification in the calibration data section
of the field test report. (See section 16.1.4.)
10.1.2.2 Using alternative probes. Axial flow verification may be
performed using an uncalibrated prism-shaped 3-D probe (e.g., DA or DAT
probe) or an uncalibrated wedge probe. (Figure 2F-11 illustrates a
typical wedge probe.) This approach requires use of two ports: the
tested probe port and a second port located 90[deg] from the tested
probe port. Each port shall provide access to all the points within the
wind tunnel test section where the velocity pressure cross-check, as
specified in section 10.1.1, is conducted. The probe setup shall include
establishing a reference yaw-null position on the probe sheath to serve
as the location for installing the angle-measuring device. Physical
design features of the DA, DAT, and wedge probes are relied on to
determine the reference position. For the DA or DAT probe, this
reference position can be determined by setting a digital inclinometer
on the flat facet where the P1 pressure port is located and
then identifying the rotational position on the probe sheath where a
second angle-measuring device would give the same angle reading. The
reference position on a wedge probe shaft can be determined either
geometrically or by placing a digital inclinometer on each side of the
wedge and rotating the probe until equivalent readings are obtained.
With the latter approach, the reference position is the rotational
position on the probe sheath where an angle-measuring device would give
a reading of 0[deg]. After installing the angle-measuring device in the
reference yaw-null position on the probe sheath, determine the yaw angle
from the tested port. Repeat this measurement using the 90[deg] offset
port, which provides the pitch angle of flow. Determine the yaw and
pitch angles at all the point(s) in the test section where the velocity
pressure cross-check, as specified in section 10.1.1, is performed. This
includes all the points in the wind tunnel calibration location and the
point where the calibration pitot tube will be located. Perform this
check at the highest and lowest velocities at which the probes will be
calibrated. Record the values on a form similar to Table 2F-5. Each
measured yaw and pitch angle shall be within 3[deg] of 0[deg]. Exceeding the limits indicates
unacceptable flow in the test section. Until the problem is corrected
and acceptable flow is verified by repetition of this procedure, the
wind tunnel shall not be used for calibration of probes. Include the
results in the probe calibration report.
10.1.3 Wind tunnel audits.
10.1.3.1 Procedure. Upon the request of the Administrator, the owner
or operator of a wind tunnel shall calibrate a 3-D audit probe in
accordance with the procedures described in sections 10.3 through 10.6.
The calibration shall be performed at two velocities and over a pitch
angle range that encompasses the velocities and pitch angles typically
used for this method at the facility. The resulting calibration data and
curves shall be submitted to the Agency in an audit test report. These
results shall be compared by the Agency to reference calibrations of the
audit probe at the same velocity and pitch angle settings obtained at
two different wind tunnels.
10.1.3.2 Acceptance criteria. The audited tunnel's calibration is
acceptable if all of the following conditions are satisfied at each
velocity and pitch setting for the reference calibration obtained from
at least one of the wind tunnels. For pitch angle settings between -
15[deg] and +15[deg], no velocity calibration coefficient (i.e.,
F2) may differ from the corresponding reference value by more
than 3 percent. For pitch angle settings outside of this range (i.e.,
less than -15[deg] and greater than +15[deg]), no velocity calibration
coefficient may differ by more than 5 percent from the corresponding
reference value. If the acceptance criteria are not met, the audited
wind tunnel shall not be used to calibrate probes for use under this
method until the problems are resolved and acceptable results are
obtained upon completion of a subsequent audit.
10.2 Probe Inspection. Before each calibration of a 3-D probe,
carefully examine the physical condition of the probe head. Particular
attention shall be paid to the edges of the pressure ports and the
surfaces surrounding these ports. Any dents, scratches, or asymmetries
on the edges of the pressure ports and any scratches or indentations on
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the surfaces surrounding the pressure ports shall be noted because of
the potential effect on the probe's pressure readings. If the probe has
been previously calibrated, compare the current condition of the probe's
pressure ports and surfaces to the results of the inspection performed
during the probe's most recent wind tunnel calibration. Record the
results of this inspection on a form and in diagrams similar to Table
2F-1. The information in Table 2F-1 will be used as the basis for
comparison during the probe head inspections performed before each
subsequent field use.
10.3 Pre-Calibration Procedures. Prior to calibration, a scribe line
shall have been placed on the probe in accordance with section 10.4. The
yaw angle and velocity calibration procedures shall not begin until the
pre-test requirements in sections 10.3.1 through 10.3.4 have been met.
10.3.1 Perform the horizontal straightness check described in
section 8.2 on the probe assembly that will be calibrated in the wind
tunnel.
10.3.2 Perform a leak check in accordance with section 8.4.
10.3.3 Except as noted in section 10.3.3.3, calibrate all
differential pressure-measuring devices to be used in the probe
calibrations, using the following procedures. At a minimum, calibrate
these devices on each day that probe calibrations are performed.
10.3.3.1 Procedure. Before each wind tunnel use, all differential
pressure-measuring devices shall be calibrated against the reference
device specified in section 6.4.3 using a common pressure source.
Perform the calibration at three reference pressures representing 30,
60, and 90 percent of the full-scale range of the pressure-measuring
device being calibrated. For an inclined-vertical manometer, perform
separate calibrations on the inclined and vertical portions of the
measurement scale, considering each portion of the scale to be a
separate full-scale range. [For example, for a manometer with a 0- to
2.5-cm H2O (0- to 1-in. H2O) inclined scale and a
2.5- to 12.7-cm H2O (1- to 5-in. H2O) vertical
scale, calibrate the inclined portion at 7.6, 15.2, and 22.9 mm
H2O (0.3, 0.6, and 0.9 in. H2O), and calibrate the
vertical portion at 3.8, 7.6, and 11.4 cm H2O (1.5, 3.0, and
4.5 in. H2O).] Alternatively, for the vertical portion of the
scale, use three evenly spaced reference pressures, one of which is
equal to or higher than the highest differential pressure expected in
field applications.
10.3.3.2 Acceptance criteria. At each pressure setting, the two
pressure readings made using the reference device and the pressure-
measuring device being calibrated shall agree to within 2 percent of full scale of the device being calibrated
or 0.5 mm H2O (0.02 in. H2O), whichever is less
restrictive. For an inclined-vertical manometer, these requirements
shall be met separately using the respective full-scale upper limits of
the inclined and vertical portions of the scale. Differential pressure-
measuring devices not meeting the 2 percent of full scale or
0.5 mm H2O (0.02 in. H2O) calibration requirement
shall not be used.
10.3.3.3 Exceptions. Any precision manometer that meets the
specifications for a reference device in section 6.4.3 and that is not
used for field testing does not require calibration, but must be leveled
and zeroed before each wind tunnel use. Any pressure device used
exclusively for yaw nulling does not require calibration, but shall be
checked for responsiveness to rotation of the probe prior to each wind
tunnel use.
10.3.4 Calibrate digital inclinometers on each day of wind tunnel or
field testing (prior to beginning testing) using the following
procedures. Calibrate the inclinometer according to the manufacturer's
calibration procedures. In addition, use a triangular block (illustrated
in Figure 2F-12) with a known angle, [theta] independently determined
using a protractor or equivalent device, between two adjacent sides to
verify the inclinometer readings.
Note: If other angle-measuring devices meeting the provisions of
section 6.2.3 are used in place of a digital inclinometer, comparable
calibration procedures shall be performed on such devices.)
Secure the triangular block in a fixed position. Place the inclinometer
on one side of the block (side A) to measure the angle of inclination
(R1). Repeat this measurement on the adjacent side of the
block (side B) using the inclinometer to obtain a second angle reading
(R2). The difference of the sum of the two readings from
180[deg] (i.e., 180[deg] -R1 -R2) shall be within
2[deg] of the known angle, [Theta]
10.4 Placement of Reference Scribe Line. Prior to the first
calibration of a probe, a line shall be permanently inscribed on the
main probe sheath to serve as a reference mark for determining yaw
angles. Annex C in section 18 of this method gives a guideline for
placement of the reference scribe line.
10.4.1 This reference scribe line shall meet the specifications in
sections 6.1.6.1 and 6.1.6.3 of this method. To verify that the
alignment specification in section 6.1.6.3 is met, secure the probe in a
horizontal position and measure the rotational angle of each scribe line
and scribe line segment using an angle-measuring device that meets the
specifications in section 6.2.1 or 6.2.3. For any scribe line that is
longer than 30.5 cm (12 in.), check the line's rotational position at
30.5-cm (12-in.) intervals. For each line segment that is 30.5 cm (12
in.) or less in length, check the rotational position at the two
endpoints of the segment. To meet the alignment specification in section
6.1.6.3, the minimum and maximum of all of the rotational angles that
are measured along the full
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length of the main probe must not differ by more than 2[deg].
Note: A short reference scribe line segment [e.g., 15.2 cm (6 in.)
or less in length] meeting the alignment specifications in section
6.1.6.3 is fully acceptable under this method. See section 18.1.1.1 of
Annex A for an example of a probe marking procedure, suitable for use
with a short reference scribe line.
10.4.2 The scribe line should be placed on the probe first and then
its offset from the yaw-null position established (as specified in
section 10.5). The rotational position of the reference scribe line
relative to the yaw-null position of the probe, as determined by the yaw
angle calibration procedure in section 10.5, is defined as the reference
scribe line rotational offset, RSLO. The reference scribe
line rotational offset shall be recorded and retained as part of the
probe's calibration record.
10.4.3 Scribe line for automated probes. A scribe line may not be
necessary for an automated probe system if a reference rotational
position of the probe is built into the probe system design. For such
systems, a ``flat'' (or comparable, clearly identifiable physical
characteristic) should be provided on the probe casing or flange plate
to ensure that the reference position of the probe assembly remains in a
vertical or horizontal position. The rotational offset of the flat (or
comparable, clearly identifiable physical characteristic) needed to
orient the reference position of the probe assembly shall be recorded
and maintained as part of the automated probe system's specifications.
10.5 Yaw Angle Calibration Procedure. For each probe used to measure
yaw angles with this method, a calibration procedure shall be performed
in a wind tunnel meeting the specifications in section 10.1 to determine
the rotational position of the reference scribe line relative to the
probe's yaw-null position. This procedure shall be performed on the main
probe with all devices that will be attached to the main probe in the
field [such as thermocouples or resistance temperature detectors (RTDs)]
that may affect the flow around the probe head. Probe shaft extensions
that do not affect flow around the probe head need not be attached
during calibration. At a minimum, this procedure shall include the
following steps.
10.5.1 Align and lock the angle-measuring device on the reference
scribe line. If a marking procedure (such as that described in section
18.1.1.1) is used, align the angle-measuring device on a mark within
1[deg] of the rotational position of the reference
scribe line. Lock the angle-measuring device onto the probe sheath at
this position.
10.5.2 Zero the pressure-measuring device used for yaw nulling.
10.5.3 Insert the probe assembly into the wind tunnel through the
entry port, positioning the probe's impact port at the calibration
location. Check the responsiveness of the pressure-measurement device to
probe rotation, taking corrective action if the response is
unacceptable.
10.5.4 Ensure that the probe is in a horizontal position, using a
carpenter's level.
10.5.5 Rotate the probe either clockwise or counterclockwise until a
yaw null (P2=P3) is obtained.
10.5.6 Use the reading displayed by the angle-measuring device at
the yaw-null position to determine the magnitude of the reference scribe
line rotational offset, RSLO, as defined in section 3.15.
Annex D in section 18 of this method provides a recommended procedure
for determining the magnitude of RSLO with a digital
inclinometer and a second procedure for determining the magnitude of
RSLO with a protractor wheel and pointer device. Table 2F-6
presents an example data form and Table 2F-7 is a look-up table with the
recommended procedure. Procedures other than those recommended in Annex
D in section 18 may be used, if they can determine RSLO to
within 1[deg] and are explained in detail in the
field test report. The algebraic sign of RSLO will either be
positive, if the rotational position of the reference scribe line (as
viewed from the ``tail'' end of the probe) is clockwise, or negative, if
counterclockwise with respect to the probe's yaw-null position. (This is
illustrated in Figure 2F-13.)
10.5.7 The steps in sections 10.5.3 through 10.5.6 shall be
performed twice at each of the velocities at which the probe will be
calibrated (in accordance with section 10.6). Record the values of
RSLO.
10.5.8 The average of all of the RSLO values shall be
documented as the reference scribe line rotational offset for the probe.
10.5.9 Use of reference scribe line offset. The reference scribe
line rotational offset shall be used to determine the yaw angle of flow
in accordance with section 8.9.4.
10.6 Pitch Angle and Velocity Pressure Calibrations. Use the
procedures in sections 10.6.1 through 10.6.16 to generate an appropriate
set (or sets) of pitch angle and velocity pressure calibration curves
for each probe. The calibration procedure shall be performed on the main
probe and all devices that will be attached to the main probe in the
field (e.g., thermocouple or RTDs) that may affect the flow around the
probe head. Probe shaft extensions that do not affect flow around the
probe head need not be attached during calibration. (Note: If a sampling
nozzle is part of the assembly, a wind tunnel demonstration shall be
performed that shows the probe's ability to measure velocity and yaw
null is not impaired when the nozzle is drawing a sample.) The
calibration
[[Page 62]]
procedure involves generating two calibration curves, F1
versus pitch angle and F2 versus pitch angle. To generate
these two curves, F1 and F2 shall be derived using
Equations 2F-1 and 2F-2, below. Table 2F-8 provides an example wind
tunnel calibration data sheet, used to log the measurements needed to
derive these two calibration curves.
10.6.1 Calibration velocities. The tester may calibrate the probe at
two nominal wind tunnel velocity settings of 18.3 m/sec and 27.4 m/sec
(60 ft/sec and 90 ft/sec) and average the results of these calibrations,
as described in section 10.6.16.1, in order to generate a set of
calibration curves. If this option is selected, this single set of
calibration curves may be used for all field applications over the
entire velocity range allowed by the method. Alternatively, the tester
may customize the probe calibration for a particular field test
application (or for a series of applications), based on the expected
average velocity(ies) at the test site(s). If this option is selected,
generate each set of calibration curves by calibrating the probe at two
nominal wind tunnel velocity settings, at least one of which is greater
than or equal to the expected average velocity(ies) for the field
application(s), and average the results as described in section
10.6.16.1. Whichever calibration option is selected, the probe
calibration coefficients (F2 values) obtained at the two
nominal calibration velocities shall, for the same pitch angle setting,
meet the conditions specified in section 10.6.16.
10.6.2 Pitch angle calibration curve (F1 versus pitch
angle). The pitch angle calibration involves generating a calibration
curve of calculated F1 values versus tested pitch angles,
where F1 is the ratio of the pitch pressure to the velocity
pressure, i.e.,
[GRAPHIC] [TIFF OMITTED] TR14MY99.049
See Figure 2F-14 for an example F1 versus pitch angle
calibration curve.
10.6.3 Velocity calibration curve (F2 versus pitch
angle). The velocity calibration involves generating a calibration curve
of the 3-D probe's F2 coefficient against the tested pitch
angles, where
[GRAPHIC] [TIFF OMITTED] TR14MY99.050
and
Cp=calibration pitot tube coefficient, and
[Delta]Pstd=velocity pressure from the calibration pitot
tube.
See Figure 2F-15 for an example F2 versus pitch angle
calibration curve.
10.6.4 Connect the tested probe and calibration pitot probe to their
respective pressure-measuring devices. Zero the pressure-measuring
devices. Inspect and leak-check all pitot lines; repair or replace, if
necessary. Turn on the fan, and allow the wind tunnel air flow to
stabilize at the first of the two selected nominal velocity settings.
10.6.5 Position the calibration pitot tube at its measurement
location (determined as outlined in section 6.11.4.3), and align the
tube so that its tip is pointed directly into the flow. Ensure that the
entry port surrounding the tube is properly sealed. The calibration
pitot tube may either remain in the wind tunnel throughout the
calibration, or be removed from the wind tunnel while measurements are
taken with the probe being calibrated.
10.6.6 Set up the pitch protractor plate on the tested probe's entry
port to establish the pitch angle positions of the probe to within
2[deg].
10.6.7 Check the zero setting of each pressure-measuring device.
10.6.8 Insert the tested probe into the wind tunnel and align it so
that its P1 pressure port is pointed directly into the flow
and is positioned within the calibration location (as defined in section
3.20). Secure the probe at the 0[deg] pitch angle position. Ensure that
the entry port surrounding the probe is properly sealed.
10.6.9 Read the differential pressure from the calibration pitot
tube ([Delta]Pstd), and record its value. Read the barometric
pressure to within 2.5 mm Hg (0.1 in. Hg) and the temperature in the wind tunnel to
within 0.6 [deg]C (1 [deg]F). Record these values on a data form similar
to Table 2F-8.
10.6.10 After the tested probe's differential pressure gauges have
had sufficient time to stabilize, yaw null the probe, then obtain
differential pressure readings for (P1-P2) and
(P4-P5). Record the yaw angle and differential
pressure readings. After taking these readings, ensure that the tested
probe has remained at the yaw-null position.
10.6.11 Either take paired differential pressure measurements with
both the calibration pitot tube and tested probe (according to sections
10.6.9 and 10.6.10) or take readings only with the tested probe
(according to section 10.6.10) in 5[deg] increments over the pitch-angle
range for which the probe is to be calibrated. The calibration pitch-
angle range shall be symmetric around 0[deg] and shall exceed the
largest pitch angle expected in the field by 5[deg]. At a minimum,
probes shall be calibrated over the range of -15[deg] to +15[deg]. If
paired calibration pitot tube and tested probe measurements are not
taken at each pitch angle setting, the differential pressure from the
calibration pitot tube shall be read, at a minimum, before taking the
tested probe's differential pressure reading at the first pitch angle
setting and after taking the tested probe's differential pressure
readings
[[Page 63]]
at the last pitch angle setting in each replicate.
10.6.12 Perform a second replicate of the procedures in sections
10.6.5 through 10.6.11 at the same nominal velocity setting.
10.6.13 For each replicate, calculate the F1 and
F2 values at each pitch angle. At each pitch angle, calculate
the percent difference between the two F2 values using
Equation 2F-3.
[GRAPHIC] [TIFF OMITTED] TR14MY99.051
If the percent difference is less than or equal to 2 percent,
calculate an average F1 value and an average F2
value at that pitch angle. If the percent difference is greater than 2
percent and less than or equal to 5 percent, perform a third repetition
at that angle and calculate an average F1 value and an
average F2 value using all three repetitions. If the percent
difference is greater than 5 percent, perform four additional
repetitions at that angle and calculate an average F1 value
and an average F2 value using all six repetitions. When
additional repetitions are required at any pitch angle, move the probe
by at least 5[deg] and then return to the specified pitch angle before
taking the next measurement. Record the average values on a form similar
to Table 2F-9.
10.6.14 Repeat the calibration procedures in sections 10.6.5 through
10.6.13 at the second selected nominal wind tunnel velocity setting.
10.6.15 Velocity drift check. The following check shall be
performed, except when paired calibration pitot tube and tested probe
pressure measurements are taken at each pitch angle setting. At each
velocity setting, calculate the percent difference between consecutive
differential pressure measurements made with the calibration pitot tube.
If a measurement differs from the previous measurement by more than 2
percent or 0.25 mm H2O (0.01 in. H2O), whichever
is less restrictive, the calibration data collected between these
calibration pitot tube measurements may not be used, and the
measurements shall be repeated.
10.6.16 Compare the averaged F2 coefficients obtained
from the calibrations at the two selected nominal velocities, as
follows. At each pitch angle setting, use Equation 2F-3 to calculate the
difference between the corresponding average F2 values at the
two calibration velocities. At each pitch angle in the -15[deg] to
+15[deg] range, the percent difference between the average F2
values shall not exceed 3.0 percent. For pitch angles outside this range
(i.e., less than -15[deg]0 and greater than +15[deg]), the percent
difference shall not exceed 5.0 percent.
10.6.16.1 If the applicable specification in section 10.6.16 is met
at each pitch angle setting, average the results obtained at the two
nominal calibration velocities to produce a calibration record of
F1 and F2 at each pitch angle tested. Record these
values on a form similar to Table 2F-9. From these values, generate one
calibration curve representing F1 versus pitch angle and a
second curve representing F2 versus pitch angle. Computer
spreadsheet programs may be used to graph the calibration data and to
develop polynomial equations that can be used to calculate pitch angles
and axial velocities.
10.6.16.2 If the applicable specification in section 10.6.16 is
exceeded at any pitch angle setting, the probe shall not be used unless:
(1) the calibration is repeated at that pitch angle and acceptable
results are obtained or (2) values of F1 and F2
are obtained at two nominal velocities for which the specifications in
section 10.6.16 are met across the entire pitch angle range.
10.7 Recalibration. Recalibrate the probe using the procedures in
section 10 either within 12 months of its first field use after its most
recent calibration or after 10 field tests (as defined in section 3.4),
whichever occurs later. In addition, whenever there is visible damage to
the 3-D head, the probe shall be recalibrated before it is used again.
10.8 Calibration of pressure-measuring devices used in field tests.
Before its initial use in a field test, calibrate each pressure-
measuring device (except those used exclusively for yaw nulling) using
the three-point calibration procedure described in section 10.3.3. The
device shall be recalibrated according to the procedure in section
10.3.3 no later than 90 days after its first field use following its
most recent calibration. At the discretion of the tester, more frequent
calibrations (e.g., after a field test) may be performed. No
adjustments, other than adjustments to the zero setting, shall be made
to the device between calibrations.
10.8.1 Post-test calibration check. A single-point calibration check
shall be performed on each pressure-measuring device after completion of
each field test. At the discretion of the tester, more frequent single-
point calibration checks (e.g., after one or more field test runs) may
be performed. It is recommended that the post-test check be performed
before leaving the field test site. The check shall be performed at a
pressure between 50 and 90 percent of full scale by taking a common
pressure reading with the tested device and a reference pressure-
measuring device (as described in section 6.4.4) or by challenging the
tested device with a reference pressure source (as described in section
6.4.4) or by performing an equivalent check using a reference device
approved by the Administrator.
10.8.2 Acceptance criterion. At the selected pressure setting, the
pressure readings made using the reference device and the tested device
shall agree to within 3 percent of
[[Page 64]]
full scale of the tested device or 0.8 mm H2O (0.03 in.
H2O), whichever is less restrictive. If this specification is
met, the test data collected during the field test are valid. If the
specification is not met, all test data collected since the last
successful calibration or calibration check are invalid and shall be
repeated using a pressure-measuring device with a current, valid
calibration. Any device that fails the calibration check shall not be
used in a field test until a successful recalibration is performed
according to the procedures in section 10.3.3.
10.9 Temperature Gauges. Same as Method 2, section 4.3. The
alternative thermocouple calibration procedures outlined in Emission
Measurement Center (EMC) Approved Alternative Method (ALT-011)
``Alternative Method 2 Thermocouple Calibration Procedure'' may be
performed. Temperature gauges shall be calibrated no more than 30 days
prior to the start of a field test or series of field tests and
recalibrated no more than 30 days after completion of a field test or
series of field tests.
10.10 Barometer. Same as Method 2, section 4.4. The barometer shall
be calibrated no more than 30 days prior to the start of a field test or
series of field tests.
11.0 Analytical Procedure
Sample collection and analysis are concurrent for this method (see
section 8.0).
12.0 Data Analysis and Calculations
These calculations use the measured yaw angle, derived pitch angle,
and the differential pressure and temperature measurements at individual
traverse points to derive the axial flue gas velocity (va(i))
at each of those points. The axial velocity values at all traverse
points that comprise a full stack or duct traverse are then averaged to
obtain the average axial flue gas velocity (va (avg)). Round
off figures only in the final calculation of reported values.
12.1 Nomenclature
A=Cross-sectional area of stack or duct, m\2\ (ft \2\).
Bws=Water vapor in the gas stream (from Method 4 or
alternative), proportion by volume.
Kp Conversion factor (a constant),
[GRAPHIC] [TIFF OMITTED] TR14MY99.052
for the metric system, and
[GRAPHIC] [TIFF OMITTED] TR14MY99.053
for the English system.
Md=Molecular weight of stack or duct gas, dry basis (see
section 8.13), g/g-mole (lb/lb-mole).
Ms=Molecular weight of stack or duct gas, wet basis, g/g-mole
(lb/lb-mole).
[GRAPHIC] [TIFF OMITTED] TR14MY99.054
Pbar=Barometric pressure at measurement site, mm Hg (in. Hg).
Pg=Stack or duct static pressure, mm H2O (in.
H2O).
Ps=Absolute stack or duct pressure, mm Hg (in. Hg),
[GRAPHIC] [TIFF OMITTED] TR14MY99.055
Pstd=Standard absolute pressure, 760 mm Hg (29.92 in. Hg).
13.6=Conversion from mm H2O (in. H2O) to mm Hg
(in. Hg).
Qsd=Average dry-basis volumetric stack or duct gas flow rate
corrected to standard conditions, dscm/hr (dscf/hr).
Qsw=Average wet-basis volumetric stack or duct gas flow rate
corrected to standard conditions, wscm/hr (wscf/hr).
Ts(avg)=Average absolute stack or duct gas temperature across
all traverse points.
ts(i)=Stack or duct gas temperature, C (F), at traverse point
i.
Ts(i)=Absolute stack or duct gas temperature, K (R), at
traverse point i,
[GRAPHIC] [TIFF OMITTED] TR14MY99.056
for the metric system, and
[GRAPHIC] [TIFF OMITTED] TR14MY99.057
for the English system.
Tstd=Standard absolute temperature, 293 [deg]K (528 [deg]R).
F1(i)=Pitch angle ratio, applicable at traverse point i,
dimensionless.
F2(i)=3-D probe velocity calibration coefficient, applicable
at traverse point i, dimensionless.
(P4-P5)i=Pitch differential pressure of
stack or duct gas flow, mm H2O (in. H2O), at
traverse point i.
(P1-P2)i=Velocity head (differential
pressure) of stack or duct gas flow, mm H2O (in.
H2O), at traverse point i.
va(i)=Reported stack or duct gas axial velocity, m/sec (ft/
sec), at traverse point i.
va(avg)=Average stack or duct gas axial velocity, m/sec (ft/
sec), across all traverse points.
3,600=Conversion factor, sec/hr.
18.0=Molecular weight of water, g/g-mole (lb/lb-mole).
[theta]y(i)=Yaw angle, degrees, at traverse point i.
[theta]p(i)=Pitch angle, degrees, at traverse point i.
n=Number of traverse points.
12.2 Traverse Point Velocity Calculations. Perform the following
calculations from the
[[Page 65]]
measurements obtained at each traverse point.
12.2.1 Selection of calibration curves. Select calibration curves as
described in section 10.6.1.
12.2.2 Traverse point pitch angle ratio. Use Equation 2F-1, as
described in section 10.6.2, to calculate the pitch angle ratio,
F1(i), at each traverse point.
12.2.3 Pitch angle. Use the pitch angle ratio, F1(i), to
derive the pitch angle, [theta]p(i), at traverse point i from
the F1 versus pitch angle calibration curve generated under
section 10.6.16.1.
12.2.4 Velocity calibration coefficient. Use the pitch angle,
[theta]p(i), to obtain the probe velocity calibration
coefficient, F2(i), at traverse point i from the ``velocity
pressure calibration curve,'' i.e., the F2 versus pitch angle
calibration curve generated under section 10.6.16.1.
12.2.5 Axial velocity. Use the following equation to calculate the
axial velocity, va(i), from the differential pressure
(P1-P2)i and yaw angle,
[theta]y(i), measured at traverse point i and the previously
calculated values for the velocity calibration coefficient,
F2(i), absolute stack or duct standard temperature,
Ts(i), absolute stack or duct pressure, Ps,
molecular weight, Ms, and pitch angle,
``[theta]p(i).
[GRAPHIC] [TIFF OMITTED] TR14MY99.058
12.2.6 Handling multiple measurements at a traverse point. For
pressure or temperature devices that take multiple measurements at a
traverse point, the multiple measurements (or where applicable, their
square roots) may first be averaged and the resulting average values
used in the equations above. Alternatively, the individual measurements
may be used in the equations above and the resulting multiple calculated
values may then be averaged to obtain a single traverse point value.
With either approach, all of the individual measurements recorded at a
traverse point must be used in calculating the applicable traverse point
value.
12.3 Average Axial Velocity in Stack or Duct. Use the reported
traverse point axial velocity in the following equation.
[GRAPHIC] [TIFF OMITTED] TR14MY99.059
12.4 Acceptability of Results. The test results are acceptable and
the calculated value of va(avg) may be reported as the
average axial velocity for the test run if the conditions in either
section 12.4.1 or 12.4.2 are met.
12.4.1 The calibration curves were generated at nominal velocities
of 18.3 m/sec and 27.4 m/sec (60 ft/sec and 90 ft/sec).
12.4.2 The calibration curves were generated at nominal velocities
other than 18.3 m/sec and 27.4 m/sec (60 ft/sec and 90 ft/sec), and the
value of va(avg) obtained using Equation 2F-9 is less than or
equal to at least one of the nominal velocities used to derive the
F1 and F2 calibration curves.
12.4.3 If the conditions in neither section 12.4.1 nor section
12.4.2 are met, the test results obtained in Equation 2F-9 are not
acceptable, and the steps in sections 12.2 and 12.3 must be repeated
using a set of F1 and F2 calibration curves that
satisfies the conditions specified in section 12.4.1 or 12.4.2.
12.5 Average Gas Wet Volumetric Flow Rate in Stack or Duct. Use the
following equation to compute the average volumetric flow rate on a wet
basis.
[GRAPHIC] [TIFF OMITTED] TR14MY99.060
12.6 Average Gas Dry Volumetric Flow Rate in Stack or Duct. Use the
following equation to compute the average volumetric flow rate on a dry
basis.
[[Page 66]]
[GRAPHIC] [TIFF OMITTED] TR14MY99.061
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 Reporting
16.1 Field Test Reports. Field test reports shall be submitted to
the Agency according to applicable regulatory requirements. Field test
reports should, at a minimum, include the following elements.
16.1.1 Description of the source. This should include the name and
location of the test site, descriptions of the process tested, a
description of the combustion source, an accurate diagram of stack or
duct cross-sectional area at the test site showing the dimensions of the
stack or duct, the location of the test ports, and traverse point
locations and identification numbers or codes. It should also include a
description and diagram of the stack or duct layout, showing the
distance of the test location from the nearest upstream and downstream
disturbances and all structural elements (including breachings, baffles,
fans, straighteners, etc.) affecting the flow pattern. If the source and
test location descriptions have been previously submitted to the Agency
in a document (e.g., a monitoring plan or test plan), referencing the
document in lieu of including this information in the field test report
is acceptable.
16.1.2 Field test procedures. These should include a description of
test equipment and test procedures. Testing conventions, such as
traverse point numbering and measurement sequence (e.g., sampling from
center to wall, or wall to center), should be clearly stated. Test port
identification and directional reference for each test port should be
included on the appropriate field test data sheets.
16.1.3 Field test data.
16.1.3.1 Summary of results. This summary should include the dates
and times of testing and the average axial gas velocity and the average
flue gas volumetric flow results for each run and tested condition.
16.1.3.2 Test data. The following values for each traverse point
should be recorded and reported:
(a) P1-P2 and P4-P5
differential pressures
(b) Stack or duct gas temperature at traverse point i
(ts(i))
(c) Absolute stack or duct gas temperature at traverse point i
(Ts(i))
(d) Yaw angle at each traverse point i ([theta]y(i))
(e) Pitch angle at each traverse point i ([theta]p(i))
(f) Stack or duct gas axial velocity at traverse point i
(va(i))
16.1.3.3 The following values should be reported once per run:
(a) Water vapor in the gas stream (from Method 4 or alternative),
proportion by volume (Bws), measured at the frequency
specified in the applicable regulation
(b) Molecular weight of stack or duct gas, dry basis (Md)
(c) Molecular weight of stack or duct gas, wet basis (Ms)
(d) Stack or duct static pressure (Pg)
(e) Absolute stack or duct pressure (Ps)
(f) Carbon dioxide concentration in the flue gas, dry basis (\0/
0\d CO2)
(g) Oxygen concentration in the flue gas, dry basis (\0/
0\d O2)
(h) Average axial stack or duct gas velocity (va(avg))
across all traverse points
(i) Gas volumetric flow rate corrected to standard conditions, dry
or wet basis as required by the applicable regulation (Qsd or
Qsw)
16.1.3.4 The following should be reported once per complete set of test
runs:
(a) Cross-sectional area of stack or duct at the test location (A)
(b) Measurement system response time (sec)
(c) Barometric pressure at measurement site (Pbar)
16.1.4 Calibration data. The field test report should include
calibration data for all probes and test equipment used in the field
test. At a minimum, the probe calibration data reported to the Agency
should include the following:
(a) Date of calibration
(b) Probe type
(c) Probe identification number(s) or code(s)
(d) Probe inspection sheets
(e) Pressure measurements and intermediate calculations of
F1 and F2 at each pitch angle used to obtain
calibration curves in accordance with section 10.6 of this method
(f) Calibration curves (in graphic or equation format) obtained in
accordance with sections 10.6.11 of this method
(g) Description and diagram of wind tunnel used for the calibration,
including dimensions of cross-sectional area and position and size of
the test section
(h) Documentation of wind tunnel qualification tests performed in
accordance with section 10.1 of this method
[[Page 67]]
16.1.5 Quality Assurance. Specific quality assurance and quality
control procedures used during the test should be described.
17.0 Bibliography
(1) 40 CFR Part 60, Appendix A, Method 1--Sample and velocity
traverses for stationary sources.
(2) 40 CFR Part 60, Appendix A, Method 2H--Determination of stack
gas velocity taking into account velocity decay near the stack wall.
(3) 40 CFR Part 60, Appendix A, Method 2--Determination of stack gas
velocity and volumetric flow rate (Type S pitot tube).
(4) 40 CFR Part 60, Appendix A, Method 3--Gas analysis for carbon
dioxide, oxygen, excess air, and dry molecular weight.
(5) 40 CFR Part 60, Appendix A, Method 3A--Determination of oxygen
and carbon dioxide concentrations in emissions from stationary sources
(instrumental analyzer procedure).
(6) 40 CFR Part 60, Appendix A, Method 4--Determination of moisture
content in stack gases.
(7) Emission Measurement Center (EMC) Approved Alternative Method
(ALT-011) ``Alternative Method 2 Thermocouple Calibration Procedure.''
(8) Electric Power Research Institute, Interim Report EPRI TR-
106698, ``Flue Gas Flow Rate Measurement Errors,'' June 1996.
(9) Electric Power Research Institute, Final Report EPRI TR-108110,
``Evaluation of Heat Rate Discrepancy from Continuous Emission
Monitoring Systems,'' August 1997.
(10) Fossil Energy Research Corporation, Final Report, ``Velocity
Probe Tests in Non-axial Flow Fields,'' November 1998, Prepared for the
U.S. Environmental Protection Agency.
(11) Fossil Energy Research Corporation, ``Additional Swirl Tunnel
Tests: E-DAT and T-DAT Probes,'' February 24, 1999, Technical Memorandum
Prepared for U.S. Environmental Protection Agency, P.O. No. 7W-1193-
NALX.
(12) Massachusetts Institute of Technology, Report WBWT-TR-1317,
``Calibration of Eight Wind Speed Probes Over a Reynolds Number Range of
46,000 to 725,000 Per Foot, Text and Summary Plots,'' Plus appendices,
October 15, 1998, Prepared for The Cadmus Group, Inc.
(13) National Institute of Standards and Technology, Special
Publication 250, ``NIST Calibration Services Users Guide 1991,'' Revised
October 1991, U.S. Department of Commerce, p. 2.
(14) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Four Prandtl Probes, Four
S-Type Probes, Four French Probes, Four Modified Kiel Probes,'' Prepared
for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(15) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Five Autoprobes,''
Prepared for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(16) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Eight Spherical Probes,''
Prepared for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(17) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Four DAT Probes,''
Prepared for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(18) Norfleet, S.K., ``An Evaluation of Wall Effects on Stack Flow
Velocities and Related Overestimation Bias in EPA's Stack Flow Reference
Methods,'' EPRI CEMS User's Group Meeting, New Orleans, Louisiana, May
13-15, 1998.
(19) Page, J.J., E.A. Potts, and R.T. Shigehara, ``3-D Pitot Tube
Calibration Study,'' EPA Contract No. 68-D1-0009, Work Assignment No. I-
121, March 11, 1993.
(20) Shigehara, R.T., W.F. Todd, and W.S. Smith, ``Significance of
Errors in Stack Sampling Measurements,'' Presented at the Annual Meeting
of the Air Pollution Control Association, St. Louis, Missouri, June 14-
19, 1970.
(21) The Cadmus Group, Inc., May 1999, ``EPA Flow Reference Method
Testing and Analysis: Findings Report,'' EPA/430-R-99-009.
(22) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Texas Utilities, DeCordova Steam
Electric Station, Volume I: Test Description and Appendix A (Data
Distribution Package),'' EPA/430-R-98-015a.
(23) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Texas Utilities, Lake Hubbard Steam
Electric Station, Volume I: Test Description and Appendix A (Data
Distribution Package),'' EPA/430-R-98-017a.
(24) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Pennsylvania Electric Co., G.P.U.
Genco Homer City Station: Unit 1, Volume I: Test Description and
Appendix A (Data Distribution Package),'' EPA/430-R-98-018a.
(25) The Cadmus Group, Inc., 1997, ``EPA Flow Reference Method
Testing and Analysis: Wind Tunnel Experimental Results,'' EPA/430-R-97-
013.
18.0 Annexes
Annex A, C, and D describe recommended procedures for meeting
certain provisions in sections 8.3, 10.4, and 10.5 of this method. Annex
B describes procedures to be followed
[[Page 68]]
when using the protractor wheel and pointer assembly to measure yaw
angles, as provided under section 8.9.1.
18.1 Annex A--Rotational Position Check. The following are
recommended procedures that may be used to satisfy the rotational
position check requirements of section 8.3 of this method and to
determine the angle-measuring device rotational offset RADO.
18.1.1 Rotational position check with probe outside stack. Where
physical constraints at the sampling location allow full assembly of the
probe outside the stack and insertion into the test port, the following
procedures should be performed before the start of testing. Two angle-
measuring devices that meet the specifications in section 6.2.1 or 6.2.3
are required for the rotational position check. An angle measuring
device whose position can be independently adjusted (e.g., by means of a
set screw) after being locked into position on the probe sheath shall
not be used for this check unless the independent adjustment is set so
that the device performs exactly like a device without the capability
for independent adjustment. That is, when aligned on the probe such a
device must give the same reading as a device that does not have the
capability of being independently adjusted. With the fully assembled
probe (including probe shaft extensions, if any) secured in a horizontal
position, affix one yaw angle-measuring device to the probe sheath and
lock it into position on the reference scribe line specified in section
6.1.6.1. Position the second angle-measuring device using the procedure
in section 18.1.1.1 or 18.1.1.2.
18.1.1.1 Marking procedure. The procedures in this section should be
performed at each location on the fully assembled probe where the yaw
angle-measuring device will be mounted during the velocity traverse.
Place the second yaw angle-measuring device on the main probe sheath (or
extension) at the position where a yaw angle will be measured during the
velocity traverse. Adjust the position of the second angle-measuring
device until it indicates the same angle (1[deg])
as the reference device, and affix the second device to the probe sheath
(or extension). Record the angles indicated by the two angle-measuring
devices on a form similar to Table 2F-2. In this position, the second
angle-measuring device is considered to be properly positioned for yaw
angle measurement. Make a mark, no wider than 1.6 mm (1/16 in.), on the
probe sheath (or extension), such that the yaw angle-measuring device
can be re-affixed at this same properly aligned position during the
velocity traverse.
18.1.1.2 Procedure for probe extensions with scribe lines. If,
during a velocity traverse the angle-measuring device will be affixed to
a probe extension having a scribe line as specified in section 6.1.6.2,
the following procedure may be used to align the extension's scribe line
with the reference scribe line instead of marking the extension as
described in section 18.1.1.1. Attach the probe extension to the main
probe. Align and lock the second angle-measuring device on the probe
extension's scribe line. Then, rotate the extension until both measuring
devices indicate the same angle (1[deg]). Lock the
extension at this rotational position. Record the angles indicated by
the two angle-measuring devices on a form similar to Table 2F-2. An
angle-measuring device may be aligned at any position on this scribe
line during the velocity traverse, if the scribe line meets the
alignment specification in section 6.1.6.3.
18.1.1.3 Post-test rotational position check. If the fully assembled
probe includes one or more extensions, the following check should be
performed immediately after the completion of a velocity traverse. At
the discretion of the tester, additional checks may be conducted after
completion of testing at any sample port. Without altering the alignment
of any of the components of the probe assembly used in the velocity
traverse, secure the fully assembled probe in a horizontal position.
Affix an angle-measuring device at the reference scribe line specified
in section 6.1.6.1. Use the other angle-measuring device to check the
angle at each location where the device was checked prior to testing.
Record the readings from the two angle-measuring devices.
18.1.2 Rotational position check with probe in stack. This section
applies only to probes that, due to physical constraints, cannot be
inserted into the test port as fully assembled with all necessary
extensions needed to reach the inner-most traverse point(s).
18.1.2.1 Perform the out-of-stack procedure in section 18.1.1 on the
main probe and any attached extensions that will be initially inserted
into the test port.
18.1.2.2 Use the following procedures to perform additional
rotational position check(s) with the probe in the stack, each time a
probe extension is added. Two angle-measuring devices are required. The
first of these is the device that was used to measure yaw angles at the
preceding traverse point, left in its properly aligned measurement
position. The second angle-measuring device is positioned on the added
probe extension. Use the applicable procedures in section 18.1.1.1 or
18.1.1.2 to align, adjust, lock, and mark (if necessary) the position of
the second angle-measuring device to within 1[deg]
of the first device. Record the readings of the two devices on a form
similar to Table 2F-2.
18.1.2.3 The procedure in section 18.1.2.2 should be performed at
the first port where measurements are taken. The procedure should be
repeated each time a probe extension is re-attached at a subsequent
port, unless the probe extensions are designed to be locked into a
mechanically fixed rotational
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position (e.g., through use of interlocking grooves), which can be
reproduced from port to port as specified in section 8.3.5.2.
18.2 Annex B--Angle Measurement Protocol for Protractor Wheel and
Pointer Device. The following procedure shall be used when a protractor
wheel and pointer assembly, such as the one described in section 6.2.2
and illustrated in Figure 2F-7 is used to measure the yaw angle of flow.
With each move to a new traverse point, unlock, re-align, and re-lock
the probe, angle-pointer collar, and protractor wheel to each other. At
each such move, particular attention is required to ensure that the
scribe line on the angle pointer collar is either aligned with the
reference scribe line on the main probe sheath or is at the rotational
offset position established under section 8.3.1. The procedure consists
of the following steps:
18.2.1 Affix a protractor wheel to the entry port for the test probe
in the stack or duct.
18.2.2 Orient the protractor wheel so that the 0[deg] mark
corresponds to the longitudinal axis of the stack or duct. For stacks,
vertical ducts, or ports on the side of horizontal ducts, use a digital
inclinometer meeting the specifications in section 6.2.1 to locate the
0[deg] orientation. For ports on the top or bottom of horizontal ducts,
identify the longitudinal axis at each test port and permanently mark
the duct to indicate the 0[deg] orientation. Once the protractor wheel
is properly aligned, lock it into position on the test port.
18.2.3 Move the pointer assembly along the probe sheath to the
position needed to take measurements at the first traverse point. Align
the scribe line on the pointer collar with the reference scribe line or
at the rotational offset position established under section 8.3.1.
Maintaining this rotational alignment, lock the pointer device onto the
probe sheath. Insert the probe into the entry port to the depth needed
to take measurements at the first traverse point.
18.2.4 Perform the yaw angle determination as specified in sections
8.9.3 and 8.9.4 and record the angle as shown by the pointer on the
protractor wheel. Then, take velocity pressure and temperature
measurements in accordance with the procedure in section 8.9.5. Perform
the alignment check described in section 8.9.6.
18.2.5 After taking velocity pressure measurements at that traverse
point, unlock the probe from the collar and slide the probe through the
collar to the depth needed to reach the next traverse point.
18.2.6 Align the scribe line on the pointer collar with the
reference scribe line on the main probe or at the rotational offset
position established under section 8.3.1. Lock the collar onto the
probe.
18.2.7 Repeat the steps in sections 18.2.4 through 18.2.6 at the
remaining traverse points accessed from the current stack or duct entry
port.
18.2.8 After completing the measurement at the last traverse point
accessed from a port, verify that the orientation of the protractor
wheel on the test port has not changed over the course of the traverse
at that port. For stacks, vertical ducts, or ports on the side of
horizontal ducts, use a digital inclinometer meeting the specifications
in section 6.2.1 to check the rotational position of the 0[deg] mark on
the protractor wheel. For ports on the top or bottom of horizontal
ducts, observe the alignment of the angle wheel 0[deg] mark relative to
the permanent 0[deg] mark on the duct at that test port. If these
observed comparisons exceed 2[deg] of 0[deg], all
angle and pressure measurements taken at that port since the protractor
wheel was last locked into position on the port shall be repeated.
18.2.9 Move to the next stack or duct entry port and repeat the
steps in sections 18.2.1 through 18.2.8.
18.3 Annex C--Guideline for Reference Scribe Line Placement. Use of
the following guideline is recommended to satisfy the requirements of
section 10.4 of this method. The rotational position of the reference
scribe line should be either 90[deg] or 180[deg] from the probe's impact
pressure port.
18.4 Annex D--Determination of Reference Scribe Line Rotational
Offset. The following procedures are recommended for determining the
magnitude and sign of a probe's reference scribe line rotational offset,
RSLO. Separate procedures are provided for two types of
angle-measuring devices: digital inclinometers and protractor wheel and
pointer assemblies.
18.4.1 Perform the following procedures on the main probe with all
devices that will be attached to the main probe in the field [such as
thermocouples or resistance temperature detectors (RTDs)] that may
affect the flow around the probe head. Probe shaft extensions that do
not affect flow around the probe head need not be attached during
calibration.
18.4.2 The procedures below assume that the wind tunnel duct used
for probe calibration is horizontal and that the flow in the calibration
wind tunnel is axial as determined by the axial flow verification check
described in section 10.1.2. Angle-measuring devices are assumed to
display angles in alternating 0[deg] to 90[deg] and 90[deg] to 0[deg]
intervals. If angle-measuring devices with other readout conventions are
used or if other calibration wind tunnel duct configurations are used,
make the appropriate calculational corrections.
18.4.2.1 Position the angle-measuring device in accordance with one
of the following procedures.
18.4.2.1.1 If using a digital inclinometer, affix the calibrated
digital inclinometer to
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the probe. If the digital inclinometer can be independently adjusted
after being locked into position on the probe sheath (e.g., by means of
a set screw), the independent adjustment must be set so that the device
performs exactly like a device without the capability for independent
adjustment. That is, when aligned on the probe the device must give the
same readings as a device that does not have the capability of being
independently adjusted. Either align it directly on the reference scribe
line or on a mark aligned with the scribe line determined according to
the procedures in section 18.1.1.1. Maintaining this rotational
alignment, lock the digital inclinometer onto the probe sheath.
18.4.2.1.2 If using a protractor wheel and pointer device, orient
the protractor wheel on the test port so that the 0[deg] mark is aligned
with the longitudinal axis of the wind tunnel duct. Maintaining this
alignment, lock the wheel into place on the wind tunnel test port. Align
the scribe line on the pointer collar with the reference scribe line or
with a mark aligned with the reference scribe line, as determined under
section 18.1.1.1. Maintaining this rotational alignment, lock the
pointer device onto the probe sheath.
18.4.2.2 Zero the pressure-measuring device used for yaw nulling.
18.4.2.3 Insert the probe assembly into the wind tunnel through the
entry port, positioning the probe's impact port at the calibration
location. Check the responsiveness of the pressure-measuring device to
probe rotation, taking corrective action if the response is
unacceptable.
18.4.2.4 Ensure that the probe is in a horizontal position using a
carpenter's level.
18.4.2.5 Rotate the probe either clockwise or counterclockwise until
a yaw null (P2=P3) is obtained.
18.4.2.6 Read and record the value of [theta]null, the
angle indicated by the angle-measuring device at the yaw-null position.
Record the angle reading on a form similar to Table 2F-6. Do not
associate an algebraic sign with this reading.
18.4.2.7 Determine the magnitude and algebraic sign of the reference
scribe line rotational offset, RSLO. The magnitude of
RSLO will be equal to either [theta]null or
(90[deg]-[theta]null), depending on the angle-measuring
device used. (See Table 2F-7 for a summary.) The algebraic sign of
RSLO will either be positive, if the rotational position of
the reference scribe line is clockwise, or negative, if counterclockwise
with respect to the probe's yaw-null position. Figure 2F-13 illustrates
how the magnitude and sign of RSLO are determined.
18.4.2.8 Perform the steps in sections 18.4.2.3 through 18.4.2.7
twice at each of the two calibration velocities selected for the probe
under section 10.6. Record the values of RSLO in a form
similar to Table 2F-6.
18.4.2.9 The average of all RSLO values is the reference
scribe line rotational offset for the probe.
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[36 FR 24877, Dec. 23, 1971]
Editorial Note: For Federal Register citations affecting appendix A-
1 to part 60, see the List of CFR Sections Affected, which appears in
the Finding Aids section of the printed volume and at www.fdsys.gov.
[[Page 90]]
Sec. Appendix A-2 to Part 60--Test Methods 2G through 3C
Method 2G--Determination of Stack Gas Velocity and Volumetric Flow Rate
With Two-Dimensional Probes
Method 2H--Determination of Stack Gas Velocity Taking Into Account
Velocity Decay Near the Stack Wall
Method 3--Gas analysis for the determination of dry molecular weight
Method 3A--Determination of Oxygen and Carbon Dioxide Concentrations in
Emissions From Stationary Sources (Instrumental Analyzer Procedure)
Method 3B--Gas analysis for the determination of emission rate
correction factor or excess air
Method 3C--Determination of carbon dioxide, methane, nitrogen, and
oxygen from stationary sources
The test methods in this appendix are referred to in Sec. 60.8
(Performance Tests) and Sec. 60.11 (Compliance With Standards and
Maintenance Requirements) of 40 CFR part 60, subpart A (General
Provisions). Specific uses of these test methods are described in the
standards of performance contained in the subparts, beginning with
Subpart D.
Within each standard of performance, a section title ``Test Methods
and Procedures'' is provided to: (1) Identify the test methods to be
used as reference methods to the facility subject to the respective
standard and (2) identify any special instructions or conditions to be
followed when applying a method to the respective facility. Such
instructions (for example, establish sampling rates, volumes, or
temperatures) are to be used either in addition to, or as a substitute
for procedures in a test method. Similarly, for sources subject to
emission monitoring requirements, specific instructions pertaining to
any use of a test method as a reference method are provided in the
subpart or in Appendix B.
Inclusion of methods in this appendix is not intended as an
endorsement or denial of their applicability to sources that are not
subject to standards of performance. The methods are potentially
applicable to other sources; however, applicability should be confirmed
by careful and appropriate evaluation of the conditions prevalent at
such sources.
The approach followed in the formulation of the test methods
involves specifications for equipment, procedures, and performance. In
concept, a performance specification approach would be preferable in all
methods because this allows the greatest flexibility to the user. In
practice, however, this approach is impractical in most cases because
performance specifications cannot be established. Most of the methods
described herein, therefore, involve specific equipment specifications
and procedures, and only a few methods in this appendix rely on
performance criteria.
Minor changes in the test methods should not necessarily affect the
validity of the results and it is recognized that alternative and
equivalent methods exist. Section 60.8 provides authority for the
Administrator to specify or approve (1) equivalent methods, (2)
alternative methods, and (3) minor changes in the methodology of the
test methods. It should be clearly understood that unless otherwise
identified all such methods and changes must have prior approval of the
Administrator. An owner employing such methods or deviations from the
test methods without obtaining prior approval does so at the risk of
subsequent disapproval and retesting with approved methods.
Within the test methods, certain specific equipment or procedures
are recognized as being acceptable or potentially acceptable and are
specifically identified in the methods. The items identified as
acceptable options may be used without approval but must be identified
in the test report. The potentially approvable options are cited as
``subject to the approval of the Administrator'' or as ``or
equivalent.'' Such potentially approvable techniques or alternatives may
be used at the discretion of the owner without prior approval. However,
detailed descriptions for applying these potentially approvable
techniques or alternatives are not provided in the test methods. Also,
the potentially approvable options are not necessarily acceptable in all
applications. Therefore, an owner electing to use such potentially
approvable techniques or alternatives is responsible for: (1) assuring
that the techniques or alternatives are in fact applicable and are
properly executed; (2) including a written description of the
alternative method in the test report (the written method must be clear
and must be capable of being performed without additional instruction,
and the degree of detail should be similar to the detail contained in
the test methods); and (3) providing any rationale or supporting data
necessary to show the validity of the alternative in the particular
application. Failure to meet these requirements can result in the
Administrator's disapproval of the alternative.
Method 2G--Determination of Stack Gas Velocity and Volumetric Flow Rate
With Two-Dimensional Probes
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material has been incorporated from other methods in
this part. Therefore, to obtain reliable results, those using this
method should have a thorough knowledge of at least the following
[[Page 91]]
additional test methods: Methods 1, 2, 3 or 3A, and 4.
1.0 Scope and Application
1.1 This method is applicable for the determination of yaw angle,
near-axial velocity, and the volumetric flow rate of a gas stream in a
stack or duct using a two-dimensional (2-D) probe.
2.0 Summary of Method
2.1 A 2-D probe is used to measure the velocity pressure and the yaw
angle of the flow velocity vector in a stack or duct. Alternatively,
these measurements may be made by operating one of the three-dimensional
(3-D) probes described in Method 2F, in yaw determination mode only.
From these measurements and a determination of the stack gas density,
the average near-axial velocity of the stack gas is calculated. The
near-axial velocity accounts for the yaw, but not the pitch, component
of flow. The average gas volumetric flow rate in the stack or duct is
then determined from the average near-axial velocity.
3.0 Definitions
3.1. Angle-measuring Device Rotational Offset (RADO). The rotational
position of an angle-measuring device relative to the reference scribe
line, as determined during the pre-test rotational position check
described in section 8.3.
3.2 Calibration Pitot Tube. The standard (Prandtl type) pitot tube
used as a reference when calibrating a probe under this method.
3.3 Field Test. A set of measurements conducted at a specific unit
or exhaust stack/duct to satisfy the applicable regulation (e.g., a
three-run boiler performance test, a single-or multiple-load nine-run
relative accuracy test).
3.4 Full Scale of Pressure-measuring Device. Full scale refers to
the upper limit of the measurement range displayed by the device. For
bi-directional pressure gauges, full scale includes the entire pressure
range from the lowest negative value to the highest positive value on
the pressure scale.
3.5 Main probe. Refers to the probe head and that section of probe
sheath directly attached to the probe head. The main probe sheath is
distinguished from probe extensions, which are sections of sheath added
onto the main probe to extend its reach.
3.6 ``May,'' ``Must,'' ``Shall,'' ``Should,'' and the imperative
form of verbs.
3.6.1 ``May'' is used to indicate that a provision of this method is
optional.
3.6.2 ``Must,'' ``Shall,'' and the imperative form of verbs (such as
``record'' or ``enter'') are used to indicate that a provision of this
method is mandatory.
3.6.3 ``Should'' is used to indicate that a provision of this method
is not mandatory, but is highly recommended as good practice.
3.7 Method 1. Refers to 40 CFR part 60, appendix A, ``Method 1--
Sample and velocity traverses for stationary sources.''
3.8 Method 2. Refers to 40 CFR part 60, appendix A, ``Method 2--
Determination of stack gas velocity and volumetric flow rate (Type S
pitot tube).''
3.9 Method 2F. Refers to 40 CFR part 60, appendix A, ``Method 2F--
Determination of stack gas velocity and volumetric flow rate with three-
dimensional probes.''
3.10 Near-axial Velocity. The velocity vector parallel to the axis
of the stack or duct that accounts for the yaw angle component of gas
flow. The term ``near-axial'' is used herein to indicate that the
velocity and volumetric flow rate results account for the measured yaw
angle component of flow at each measurement point.
3.11 Nominal Velocity. Refers to a wind tunnel velocity setting that
approximates the actual wind tunnel velocity to within 1.5 m/sec (5 ft/sec).
3.12 Pitch Angle. The angle between the axis of the stack or duct
and the pitch component of flow, i.e., the component of the total
velocity vector in a plane defined by the traverse line and the axis of
the stack or duct. (Figure 2G-1 illustrates the ``pitch plane.'') From
the standpoint of a tester facing a test port in a vertical stack, the
pitch component of flow is the vector of flow moving from the center of
the stack toward or away from that test port. The pitch angle is the
angle described by this pitch component of flow and the vertical axis of
the stack.
3.13 Readability. For the purposes of this method, readability for
an analog measurement device is one half of the smallest scale division.
For a digital measurement device, it is the number of decimals displayed
by the device.
3.14 Reference Scribe Line. A line permanently inscribed on the main
probe sheath (in accordance with section 6.1.5.1) to serve as a
reference mark for determining yaw angles.
3.15 Reference Scribe Line Rotational Offset (RSLO). The rotational
position of a probe's reference scribe line relative to the probe's yaw-
null position, as determined during the yaw angle calibration described
in section 10.5.
3.16 Response Time. The time required for the measurement system to
fully respond to a change from zero differential pressure and ambient
temperature to the stable stack or duct pressure and temperature
readings at a traverse point.
3.17 Tested Probe. A probe that is being calibrated.
3.18 Three-dimensional (3-D) Probe. A directional probe used to
determine the velocity
[[Page 92]]
pressure and the yaw and pitch angles in a flowing gas stream.
3.19 Two-dimensional (2-D) Probe. A directional probe used to
measure velocity pressure and yaw angle in a flowing gas stream.
3.20 Traverse Line. A diameter or axis extending across a stack or
duct on which measurements of velocity pressure and flow angles are
made.
3.21 Wind Tunnel Calibration Location. A point, line, area, or
volume within the wind tunnel test section at, along, or within which
probes are calibrated. At a particular wind tunnel velocity setting, the
average velocity pressures at specified points at, along, or within the
calibration location shall vary by no more than 2 percent or 0.3 mm
H20 (0.01 in. H2O), whichever is less restrictive,
from the average velocity pressure at the calibration pitot tube
location. Air flow at this location shall be axial, i.e., yaw and pitch
angles within 3[deg] of 0[deg]. Compliance with
these flow criteria shall be demonstrated by performing the procedures
prescribed in sections 10.1.1 and 10.1.2. For circular tunnels, no part
of the calibration location may be closer to the tunnel wall than 10.2
cm (4 in.) or 25 percent of the tunnel diameter, whichever is farther
from the wall. For elliptical or rectangular tunnels, no part of the
calibration location may be closer to the tunnel wall than 10.2 cm (4
in.) or 25 percent of the applicable cross-sectional axis, whichever is
farther from the wall.
3.22 Wind Tunnel with Documented Axial Flow. A wind tunnel facility
documented as meeting the provisions of sections 10.1.1 (velocity
pressure cross-check) and 10.1.2 (axial flow verification) using the
procedures described in these sections or alternative procedures
determined to be technically equivalent.
3.23 Yaw Angle. The angle between the axis of the stack or duct and
the yaw component of flow, i.e., the component of the total velocity
vector in a plane perpendicular to the traverse line at a particular
traverse point. (Figure 2G-1 illustrates the ``yaw plane.'') From the
standpoint of a tester facing a test port in a vertical stack, the yaw
component of flow is the vector of flow moving to the left or right from
the center of the stack as viewed by the tester. (This is sometimes
referred to as ``vortex flow,'' i.e., flow around the centerline of a
stack or duct.) The yaw angle is the angle described by this yaw
component of flow and the vertical axis of the stack. The algebraic sign
convention is illustrated in Figure 2G-2.
3.24 Yaw Nulling. A procedure in which a Type-S pitot tube or a 3-D
probe is rotated about its axis in a stack or duct until a zero
differential pressure reading (``yaw null'') is obtained. When a Type S
probe is yaw-nulled, the rotational position of its impact port is
90[deg] from the direction of flow in the stack or duct and the [Delta]P
reading is zero. When a 3-D probe is yaw-nulled, its impact pressure
port (P1) faces directly into the direction of flow in the
stack or duct and the differential pressure between pressure ports
P2 and P3 is zero.
4.0 Interferences [Reserved]
5.0 Safety
5.1 This test method may involve hazardous operations and the use of
hazardous materials or equipment. This method does not purport to
address all of the safety problems associated with its use. It is the
responsibility of the user to establish and implement appropriate safety
and health practices and to determine the applicability of regulatory
limitations before using this test method.
6.0 Equipment and Supplies
6.1 Two-dimensional Probes. Probes that provide both the velocity
pressure and the yaw angle of the flow vector in a stack or duct, as
listed in sections 6.1.1 and 6.1.2, qualify for use based on
comprehensive wind tunnel and field studies involving both inter-and
intra-probe comparisons by multiple test teams. Each 2-D probe shall
have a unique identification number or code permanently marked on the
main probe sheath. Each probe shall be calibrated prior to use according
to the procedures in section 10. Manufacturer-supplied calibration data
shall be used as example information only, except when the manufacturer
calibrates the probe as specified in section 10 and provides complete
documentation.
6.1.1 Type S (Stausscheibe or reverse type) pitot tube. This is the
same as specified in Method 2, section 2.1, except for the following
additional specifications that enable the pitot tube to accurately
determine the yaw component of flow. For the purposes of this method,
the external diameter of the tubing used to construct the Type S pitot
tube (dimension Dt in Figure 2-2 of Method 2) shall be no
less than 9.5 mm (3/8 in.). The pitot tube shall also meet the following
alignment specifications. The angles [alpha]1,
[alpha]2, [beta]1, and [beta]2, as
shown in Method 2, Figure 2-3, shall not exceed 2[deg]. The dimensions w and z, shown in Method 2,
Figure 2-3 shall not exceed 0.5 mm (0.02 in.).
6.1.1.1 Manual Type S probe. This refers to a Type S probe that is
positioned at individual traverse points and yaw nulled manually by an
operator.
6.1.1.2 Automated Type S probe. This refers to a system that uses a
computer-controlled motorized mechanism to position the Type S pitot
head at individual traverse points and perform yaw angle determinations.
6.1.2 Three-dimensional probes used in 2-D mode. A 3-D probe, as
specified in sections 6.1.1 through 6.1.3 of Method 2F, may, for the
[[Page 93]]
purposes of this method, be used in a two-dimensional mode (i.e.,
measuring yaw angle, but not pitch angle). When the 3-D probe is used as
a 2-D probe, only the velocity pressure and yaw-null pressure are
obtained using the pressure taps referred to as P1,
P2, and P3. The differential pressure
P1-P2 is a function of total velocity and
corresponds to the [Delta]P obtained using the Type S probe. The
differential pressure P2-P3 is used to yaw null
the probe and determine the yaw angle. The differential pressure
P4-P5, which is a function of pitch angle, is not
measured when the 3-D probe is used in 2-D mode.
6.1.3 Other probes. [Reserved]
6.1.4 Probe sheath. The probe shaft shall include an outer sheath
to: (1) provide a surface for inscribing a permanent reference scribe
line, (2) accommodate attachment of an angle-measuring device to the
probe shaft, and (3) facilitate precise rotational movement of the probe
for determining yaw angles. The sheath shall be rigidly attached to the
probe assembly and shall enclose all pressure lines from the probe head
to the farthest position away from the probe head where an angle-
measuring device may be attached during use in the field. The sheath of
the fully assembled probe shall be sufficiently rigid and straight at
all rotational positions such that, when one end of the probe shaft is
held in a horizontal position, the fully extended probe meets the
horizontal straightness specifications indicated in section 8.2 below.
6.1.5 Scribe lines.
6.1.5.1 Reference scribe line. A permanent line, no greater than 1.6
mm (1/16 in.) in width, shall be inscribed on each manual probe that
will be used to determine yaw angles of flow. This line shall be placed
on the main probe sheath in accordance with the procedures described in
section 10.4 and is used as a reference position for installation of the
yaw angle-measuring device on the probe. At the discretion of the
tester, the scribe line may be a single line segment placed at a
particular position on the probe sheath (e.g., near the probe head),
multiple line segments placed at various locations along the length of
the probe sheath (e.g., at every position where a yaw angle-measuring
device may be mounted), or a single continuous line extending along the
full length of the probe sheath.
6.1.5.2 Scribe line on probe extensions. A permanent line may also
be inscribed on any probe extension that will be attached to the main
probe in performing field testing. This allows a yaw angle-measuring
device mounted on the extension to be readily aligned with the reference
scribe line on the main probe sheath.
6.1.5.3 Alignment specifications. This specification shall be met
separately, using the procedures in section 10.4.1, on the main probe
and on each probe extension. The rotational position of the scribe line
or scribe line segments on the main probe or any probe extension must
not vary by more than 2[deg]. That is, the difference between the
minimum and maximum of all of the rotational angles that are measured
along the full length of the main probe or the probe extension must not
exceed 2[deg].
6.1.6 Probe and system characteristics to ensure horizontal
stability.
6.1.6.1 For manual probes, it is recommended that the effective
length of the probe (coupled with a probe extension, if necessary) be at
least 0.9 m (3 ft.) longer than the farthest traverse point mark on the
probe shaft away from the probe head. The operator should maintain the
probe's horizontal stability when it is fully inserted into the stack or
duct. If a shorter probe is used, the probe should be inserted through a
bushing sleeve, similar to the one shown in Figure 2G-3, that is
installed on the test port; such a bushing shall fit snugly around the
probe and be secured to the stack or duct entry port in such a manner as
to maintain the probe's horizontal stability when fully inserted into
the stack or duct.
6.1.6.2 An automated system that includes an external probe casing
with a transport system shall have a mechanism for maintaining
horizontal stability comparable to that obtained by manual probes
following the provisions of this method. The automated probe assembly
shall also be constructed to maintain the alignment and position of the
pressure ports during sampling at each traverse point. The design of the
probe casing and transport system shall allow the probe to be removed
from the stack or duct and checked through direct physical measurement
for angular position and insertion depth.
6.1.7 The tubing that is used to connect the probe and the pressure-
measuring device should have an inside diameter of at least 3.2 mm (\1/
8\ in.), to reduce the time required for pressure equilibration, and
should be as short as practicable.
6.1.8 If a detachable probe head without a sheath [e.g., a pitot
tube, typically 15.2 to 30.5 cm (6 to 12 in.) in length] is coupled with
a probe sheath and calibrated in a wind tunnel in accordance with the
yaw angle calibration procedure in section 10.5, the probe head shall
remain attached to the probe sheath during field testing in the same
configuration and orientation as calibrated. Once the detachable probe
head is uncoupled or re-oriented, the yaw angle calibration of the probe
is no longer valid and must be repeated before using the probe in
subsequent field tests.
6.2 Yaw Angle-measuring Device. One of the following devices shall
be used for measurement of the yaw angle of flow.
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6.2.1 Digital inclinometer. This refers to a digital device capable
of measuring and displaying the rotational position of the probe to
within 1[deg]. The device shall be able to be
locked into position on the probe sheath or probe extension, so that it
indicates the probe's rotational position throughout the test. A
rotational position collar block that can be attached to the probe
sheath (similar to the collar shown in Figure 2G-4) may be required to
lock the digital inclinometer into position on the probe sheath.
6.2.2 Protractor wheel and pointer assembly. This apparatus, similar
to that shown in Figure 2G-5, consists of the following components.
6.2.2.1 A protractor wheel that can be attached to a port opening
and set in a fixed rotational position to indicate the yaw angle
position of the probe's scribe line relative to the longitudinal axis of
the stack or duct. The protractor wheel must have a measurement ring on
its face that is no less than 17.8 cm (7 in.) in diameter, shall be able
to be rotated to any angle and then locked into position on the stack or
duct test port, and shall indicate angles to a resolution of 1[deg].
6.2.2.2 A pointer assembly that includes an indicator needle mounted
on a collar that can slide over the probe sheath and be locked into a
fixed rotational position on the probe sheath. The pointer needle shall
be of sufficient length, rigidity, and sharpness to allow the tester to
determine the probe's angular position to within 1[deg] from the
markings on the protractor wheel. Corresponding to the position of the
pointer, the collar must have a scribe line to be used in aligning the
pointer with the scribe line on the probe sheath.
6.2.3 Other yaw angle-measuring devices. Other angle-measuring
devices with a manufacturer's specified precision of 1[deg] or better
may be used, if approved by the Administrator.
6.3 Probe Supports and Stabilization Devices. When probes are used
for determining flow angles, the probe head should be kept in a stable
horizontal position. For probes longer than 3.0 m (10 ft.), the section
of the probe that extends outside the test port shall be secured. Three
alternative devices are suggested for maintaining the horizontal
position and stability of the probe shaft during flow angle
determinations and velocity pressure measurements: (1) monorails
installed above each port, (2) probe stands on which the probe shaft may
be rested, or (3) bushing sleeves of sufficient length secured to the
test ports to maintain probes in a horizontal position. Comparable
provisions shall be made to ensure that automated systems maintain the
horizontal position of the probe in the stack or duct. The physical
characteristics of each test platform may dictate the most suitable type
of stabilization device. Thus, the choice of a specific stabilization
device is left to the judgement of the testers.
6.4 Differential Pressure Gauges. The velocity pressure ([Delta]P)
measuring devices used during wind tunnel calibrations and field testing
shall be either electronic manometers (e.g., pressure transducers),
fluid manometers, or mechanical pressure gauges (e.g.,
Magnehelic[Delta] gauges). Use of electronic manometers is
recommended. Under low velocity conditions, use of electronic manometers
may be necessary to obtain acceptable measurements.
6.4.1 Differential pressure-measuring device. This refers to a
device capable of measuring pressure differentials and having a
readability of 1 percent of full scale. The device
shall be capable of accurately measuring the maximum expected pressure
differential. Such devices are used to determine the following pressure
measurements: velocity pressure, static pressure, and yaw-null pressure.
For an inclined-vertical manometer, the readability specification of
1 percent shall be met separately using the
respective full-scale upper limits of the inclined anvertical portions
of the scales. To the extent practicable, the device shall be selected
such that most of the pressure readings are between 10 and 90 percent of
the device's full-scale measurement range (as defined in section 3.4).
In addition, pressure-measuring devices should be selected such that the
zero does not drift by more than 5 percent of the average expected
pressure readings to be encountered during the field test. This is
particularly important under low pressure conditions.
6.4.2 Gauge used for yaw nulling. The differential pressure-
measuring device chosen for yaw nulling the probe during the wind tunnel
calibrations and field testing shall be bi-directional, i.e., capable of
reading both positive and negative differential pressures. If a
mechanical, bi-directional pressure gauge is chosen, it shall have a
full-scale range no greater than 2.6 cm (i.e., -1.3 to +1.3 cm) [1 in.
H2O (i.e., -0.5 in. to +0.5 in.)].
6.4.3 Devices for calibrating differential pressure-measuring
devices. A precision manometer (e.g., a U-tube, inclined, or inclined-
vertical manometer, or micromanometer) or NIST (National Institute of
Standards and Technology) traceable pressure source shall be used for
calibrating differential pressure-measuring devices. The device shall be
maintained under laboratory conditions or in a similar protected
environment (e.g., a climate-controlled trailer). It shall not be used
in field tests. The precision manometer shall have a scale gradation of
0.3 mm H2O (0.01 in. H2O), or less, in the range
of 0 to 5.1 cm H2O (0 to 2 in. H2O) and 2.5 mm
H2O (0.1 in. H2O), or less, in the range of 5.1 to
25.4 cm H2O (2 to 10 in. H2O). The manometer shall
have manufacturer's documentation that it meets an accuracy
specification of at least 0.5 percent of full scale. The NIST-traceable
pressure source shall be recertified annually.
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6.4.4 Devices used for post-test calibration check. A precision
manometer meeting the specifications in section 6.4.3, a pressure-
measuring device or pressure source with a documented calibration
traceable to NIST, or an equivalent device approved by the Administrator
shall be used for the post-test calibration check. The pressure-
measuring device shall have a readability equivalent to or greater than
the tested device. The pressure source shall be capable of generating
pressures between 50 and 90 percent of the range of the tested device
and known to within 1 percent of the full scale of
the tested device. The pressure source shall be recertified annually.
6.5 Data Display and Capture Devices. Electronic manometers (if
used) shall be coupled with a data display device (such as a digital
panel meter, personal computer display, or strip chart) that allows the
tester to observe and validate the pressure measurements taken during
testing. They shall also be connected to a data recorder (such as a data
logger or a personal computer with data capture software) that has the
ability to compute and retain the appropriate average value at each
traverse point, identified by collection time and traverse point.
6.6 Temperature Gauges. For field tests, a thermocouple or
resistance temperature detector (RTD) capable of measuring temperature
to within 3 [deg]C (5
[deg]F) of the stack or duct temperature shall be used. The thermocouple
shall be attached to the probe such that the sensor tip does not touch
any metal. The position of the thermocouple relative to the pressure
port face openings shall be in the same configuration as used for the
probe calibrations in the wind tunnel. Temperature gauges used for wind
tunnel calibrations shall be capable of measuring temperature to within
0.6 [deg]C (1 [deg]F) of the
temperature of the flowing gas stream in the wind tunnel.
6.7 Stack or Duct Static Pressure Measurement. The pressure-
measuring device used with the probe shall be as specified in section
6.4 of this method. The static tap of a standard (Prandtl type) pitot
tube or one leg of a Type S pitot tube with the face opening planes
positioned parallel to the gas flow may be used for this measurement.
Also acceptable is the pressure differential reading of P1-
Pbar from a five-hole prism-shaped 3-D probe, as specified in
section 6.1.1 of Method 2F (such as the Type DA or DAT probe), with the
P1 pressure port face opening positioned parallel to the gas
flow in the same manner as the Type S probe. However, the 3-D spherical
probe, as specified in section 6.1.2 of Method 2F, is unable to provide
this measurement and shall not be used to take static pressure
measurements. Static pressure measurement is further described in
section 8.11.
6.8 Barometer. Same as Method 2, section 2.5.
6.9 Gas Density Determination Equipment. Method 3 or 3A shall be
used to determine the dry molecular weight of the stack or duct gas.
Method 4 shall be used for moisture content determination and
computation of stack or duct gas wet molecular weight. Other methods may
be used, if approved by the Administrator.
6.10 Calibration Pitot Tube. Same as Method 2, section 2.7.
6.11 Wind Tunnel for Probe Calibration. Wind tunnels used to
calibrate velocity probes must meet the following design specifications.
6.11.1 Test section cross-sectional area. The flowing gas stream
shall be confined within a circular, rectangular, or elliptical duct.
The cross-sectional area of the tunnel must be large enough to ensure
fully developed flow in the presence of both the calibration pitot tube
and the tested probe. The calibration site, or ``test section,'' of the
wind tunnel shall have a minimum diameter of 30.5 cm (12 in.) for
circular or elliptical duct cross-sections or a minimum width of 30.5 cm
(12 in.) on the shorter side for rectangular cross-sections. Wind
tunnels shall meet the probe blockage provisions of this section and the
qualification requirements prescribed in section 10.1. The projected
area of the portion of the probe head, shaft, and attached devices
inside the wind tunnel during calibration shall represent no more than 4
percent of the cross-sectional area of the tunnel. The projected area
shall include the combined area of the calibration pitot tube and the
tested probe if both probes are placed simultaneously in the same cross-
sectional plane in the wind tunnel, or the larger projected area of the
two probes if they are placed alternately in the wind tunnel.
6.11.2 Velocity range and stability. The wind tunnel should be
capable of maintaining velocities between 6.1 m/sec and 30.5 m/sec (20
ft/sec and 100 ft/sec). The wind tunnel shall produce fully developed
flow patterns that are stable and parallel to the axis of the duct in
the test section.
6.11.3 Flow profile at the calibration location. The wind tunnel
shall provide axial flow within the test section calibration location
(as defined in section 3.21). Yaw and pitch angles in the calibration
location shall be within 3[deg] of 0[deg]. The
procedure for determining that this requirement has been met is
described in section 10.1.2.
6.11.4 Entry ports in the wind tunnel test section.
6.11.4.1 Port for tested probe. A port shall be constructed for the
tested probe. This port shall be located to allow the head of the tested
probe to be positioned within the wind tunnel calibration location (as
defined in section 3.21). The tested probe shall be able to be locked
into the 0[deg] pitch angle position. To facilitate alignment of the
probe during calibration, the test section should include a
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window constructed of a transparent material to allow the tested probe
to be viewed.
6.11.4.2 Port for verification of axial flow. Depending on the
equipment selected to conduct the axial flow verification prescribed in
section 10.1.2, a second port, located 90[deg] from the entry port for
the tested probe, may be needed to allow verification that the gas flow
is parallel to the central axis of the test section. This port should be
located and constructed so as to allow one of the probes described in
section 10.1.2.2 to access the same test point(s) that are accessible
from the port described in section 6.11.4.1.
6.11.4.3 Port for calibration pitot tube. The calibration pitot tube
shall be used in the port for the tested probe or in a separate entry
port. In either case, all measurements with the calibration pitot tube
shall be made at the same point within the wind tunnel over the course
of a probe calibration. The measurement point for the calibration pitot
tube shall meet the same specifications for distance from the wall and
for axial flow as described in section 3.21 for the wind tunnel
calibration location.
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection and Analysis
8.1 Equipment Inspection and Set Up
8.1.1 All 2-D and 3-D probes, differential pressure-measuring
devices, yaw angle-measuring devices, thermocouples, and barometers
shall have a current, valid calibration before being used in a field
test. (See sections 10.3.3, 10.3.4, and 10.5 through 10.10 for the
applicable calibration requirements.)
8.1.2 Before each field use of a Type S probe, perform a visual
inspection to verify the physical condition of the pitot tube. Record
the results of the inspection. If the face openings are noticeably
misaligned or there is visible damage to the face openings, the probe
shall not be used until repaired, the dimensional specifications
verified (according to the procedures in section 10.2.1), and the probe
recalibrated.
8.1.3 Before each field use of a 3-D probe, perform a visual
inspection to verify the physical condition of the probe head according
to the procedures in section 10.2 of Method 2F. Record the inspection
results on a form similar to Table 2F-1 presented in Method 2F. If there
is visible damage to the 3-D probe, the probe shall not be used until it
is recalibrated.
8.1.4 After verifying that the physical condition of the probe head
is acceptable, set up the apparatus using lengths of flexible tubing
that are as short as practicable. Surge tanks installed between the
probe and pressure-measuring device may be used to dampen pressure
fluctuations provided that an adequate measurement system response time
(see section 8.8) is maintained.
8.2 Horizontal Straightness Check. A horizontal straightness check
shall be performed before the start of each field test, except as
otherwise specified in this section. Secure the fully assembled probe
(including the probe head and all probe shaft extensions) in a
horizontal position using a stationary support at a point along the
probe shaft approximating the location of the stack or duct entry port
when the probe is sampling at the farthest traverse point from the stack
or duct wall. The probe shall be rotated to detect bends. Use an angle-
measuring device or trigonometry to determine the bend or sag between
the probe head and the secured end. (See Figure 2G-6.) Probes that are
bent or sag by more than 5[deg] shall not be used. Although this check
does not apply when the probe is used for a vertical traverse, care
should be taken to avoid the use of bent probes when conducting vertical
traverses. If the probe is constructed of a rigid steel material and
consists of a main probe without probe extensions, this check need only
be performed before the initial field use of the probe, when the probe
is recalibrated, when a change is made to the design or material of the
probe assembly, and when the probe becomes bent. With such probes, a
visual inspection shall be made of the fully assembled probe before each
field test to determine if a bend is visible. The probe shall be rotated
to detect bends. The inspection results shall be documented in the field
test report. If a bend in the probe is visible, the horizontal
straightness check shall be performed before the probe is used.
8.3 Rotational Position Check. Before each field test, and each time
an extension is added to the probe during a field test, a rotational
position check shall be performed on all manually operated probes
(except as noted in section 8.3.5 below) to ensure that, throughout
testing, the angle-measuring device is either: aligned to within 1[deg] of the rotational position of the reference
scribe line; or is affixed to the probe such that the rotational offset
of the device from the reference scribe line is known to within 1[deg]. This check shall consist of direct measurements
of the rotational positions of the reference scribe line and angle-
measuring device sufficient to verify that these specifications are met.
Annex A in section 18 of this method gives recommended procedures for
performing the rotational position check, and Table 2G-2 gives an
example data form. Procedures other than those recommended in Annex A in
section 18 may be used, provided they demonstrate whether the alignment
specification is met and are explained in detail in the field test
report.
8.3.1 Angle-measuring device rotational offset. The tester shall
maintain a record of the angle-measuring device rotational offset,
RADO, as defined in section 3.1. Note that RADO is
assigned a value of 0[deg] when the angle-
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measuring device is aligned to within 1[deg] of
the rotational position of the reference scribe line. The
RADO shall be used to determine the yaw angle of flow in
accordance with section 8.9.4.
8.3.2 Sign of angle-measuring device rotational offset. The sign of
RADO is positive when the angle-measuring device (as viewed
from the ``tail'' end of the probe) is positioned in a clockwise
direction from the reference scribe line and negative when the device is
positioned in a counterclockwise direction from the reference scribe
line.
8.3.3 Angle-measuring devices that can be independently adjusted
(e.g., by means of a set screw), after being locked into position on the
probe sheath, may be used. However, the RADO must also take
into account this adjustment.
8.3.4 Post-test check. If probe extensions remain attached to the
main probe throughout the field test, the rotational position check
shall be repeated, at a minimum, at the completion of the field test to
ensure that the angle-measuring device has remained within 2[deg] of its rotational position established prior to
testing. At the discretion of the tester, additional checks may be
conducted after completion of testing at any sample port or after any
test run. If the 2[deg] specification is not met,
all measurements made since the last successful rotational position
check must be repeated. Section 18.1.1.3 of Annex A provides an example
procedure for performing the post-test check.
8.3.5 Exceptions.
8.3.5.1 A rotational position check need not be performed if, for
measurements taken at all velocity traverse points, the yaw angle-
measuring device is mounted and aligned directly on the reference scribe
line specified in sections 6.1.5.1 and 6.1.5.3 and no independent
adjustments, as described in section 8.3.3, are made to device's
rotational position.
8.3.5.2 If extensions are detached and re-attached to the probe
during a field test, a rotational position check need only be performed
the first time an extension is added to the probe, rather than each time
the extension is re-attached, if the probe extension is designed to be
locked into a mechanically fixed rotational position (e.g., through the
use of interlocking grooves), that can re-establish the initial
rotational position to within 1[deg].
8.4 Leak Checks. A pre-test leak check shall be conducted before
each field test. A post-test check shall be performed at the end of the
field test, but additional leak checks may be conducted after any test
run or group of test runs. The post-test check may also serve as the
pre-test check for the next group of test runs. If any leak check is
failed, all runs since the last passed leak check are invalid. While
performing the leak check procedures, also check each pressure device's
responsiveness to changes in pressure.
8.4.1 To perform the leak check on a Type S pitot tube, pressurize
the pitot impact opening until at least 7.6 cm H2O (3 in.
H2O) velocity pressure, or a pressure corresponding to
approximately 75 percent of the pressure device's measurement scale,
whichever is less, registers on the pressure device; then, close off the
impact opening. The pressure shall remain stable (2.5 mm H2O, 0.10 in.
H2O) for at least 15 seconds. Repeat this procedure for the
static pressure side, except use suction to obtain the required
pressure. Other leak-check procedures may be used, if approved by the
Administrator.
8.4.2 To perform the leak check on a 3-D probe, pressurize the
probe's impact (P1) opening until at least 7.6 cm
H2O (3 in. H2O) velocity pressure, or a pressure
corresponding to approximately 75 percent of the pressure device's
measurement scale, whichever is less, registers on the pressure device;
then, close off the impact opening. The pressure shall remain stable
(2.5 mm H2O, 0.10
in. H2O) for at least 15 seconds. Check the P2 and
P3 pressure ports in the same fashion. Other leak-check
procedures may be used, if approved by the Administrator.
8.5 Zeroing the Differential Pressure-measuring Device. Zero each
differential pressure-measuring device, including the device used for
yaw nulling, before each field test. At a minimum, check the zero after
each field test. A zero check may also be performed after any test run
or group of test runs. For fluid manometers and mechanical pressure
gauges (e.g., Magnehelic[Delta] gauges), the zero reading
shall not deviate from zero by more than 0.8 mm
H2O (0.03 in. H2O) or one
minor scale division, whichever is greater, between checks. For
electronic manometers, the zero reading shall not deviate from zero
between checks by more than: 0.3 mm H2O
(0.01 in. H2O), for full scales less
than or equal to 5.1 cm H2O (2.0 in. H2O); or
0.8 mm H2O (0.03
in. H2O), for full scales greater than 5.1 cm H2O
(2.0 in. H2O). (Note: If negative zero drift is not directly
readable, estimate the reading based on the position of the gauge oil in
the manometer or of the needle on the pressure gauge.) In addition, for
all pressure-measuring devices except those used exclusively for yaw
nulling, the zero reading shall not deviate from zero by more than 5
percent of the average measured differential pressure at any distinct
process condition or load level. If any zero check is failed at a
specific process condition or load level, all runs conducted at that
process condition or load level since the last passed zero check are
invalid.
8.6 Traverse Point Verification. The number and location of the
traverse points shall be selected based on Method 1 guidelines.
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The stack or duct diameter and port nipple lengths, including any
extension of the port nipples into the stack or duct, shall be verified
the first time the test is performed; retain and use this information
for subsequent field tests, updating it as required. Physically measure
the stack or duct dimensions or use a calibrated laser device; do not
use engineering drawings of the stack or duct. The probe length
necessary to reach each traverse point shall be recorded to within
6.4 mm (\1/4\ in.) and, for
manual probes, marked on the probe sheath. In determining these lengths,
the tester shall take into account both the distance that the port
flange projects outside of the stack and the depth that any port nipple
extends into the gas stream. The resulting point positions shall reflect
the true distances from the inside wall of the stack or duct, so that
when the tester aligns any of the markings with the outside face of the
stack port, the probe's impact port shall be located at the appropriate
distance from the inside wall for the respective Method 1 traverse
point. Before beginning testing at a particular location, an out-of-
stack or duct verification shall be performed on each probe that will be
used to ensure that these position markings are correct. The distances
measured during the verification must agree with the previously
calculated distances to within \1/4\ in. For
manual probes, the traverse point positions shall be verified by
measuring the distance of each mark from the probe's impact pressure
port (the P1 port for a 3-D probe). A comparable out-of-stack
test shall be performed on automated probe systems. The probe shall be
extended to each of the prescribed traverse point positions. Then, the
accuracy of the positioning for each traverse point shall be verified by
measuring the distance between the port flange and the probe's impact
pressure port.
8.7 Probe Installation. Insert the probe into the test port. A solid
material shall be used to seal the port.
8.8 System Response Time. Determine the response time of the probe
measurement system. Insert and position the ``cold'' probe (at ambient
temperature and pressure) at any Method 1 traverse point. Read and
record the probe differential pressure, temperature, and elapsed time at
15-second intervals until stable readings for both pressure and
temperature are achieved. The response time is the longer of these two
elapsed times. Record the response time.
8.9 Sampling.
8.9.1 Yaw angle measurement protocol. With manual probes, yaw angle
measurements may be obtained in two alternative ways during the field
test, either by using a yaw angle-measuring device (e.g., digital
inclinometer) affixed to the probe, or using a protractor wheel and
pointer assembly. For horizontal traversing, either approach may be
used. For vertical traversing, i.e., when measuring from on top or into
the bottom of a horizontal duct, only the protractor wheel and pointer
assembly may be used. With automated probes, curve-fitting protocols may
be used to obtain yaw-angle measurements.
8.9.1.1 If a yaw angle-measuring device affixed to the probe is to
be used, lock the device on the probe sheath, aligning it either on the
reference scribe line or in the rotational offset position established
under section 8.3.1.
8.9.1.2 If a protractor wheel and pointer assembly is to be used,
follow the procedures in Annex B of this method.
8.9.1.3 Curve-fitting procedures. Curve-fitting routines sweep
through a range of yaw angles to create curves correlating pressure to
yaw position. To find the zero yaw position and the yaw angle of flow,
the curve found in the stack is computationally compared to a similar
curve that was previously generated under controlled conditions in a
wind tunnel. A probe system that uses a curve-fitting routine for
determining the yaw-null position of the probe head may be used,
provided that it is verified in a wind tunnel to be able to determine
the yaw angle of flow to within 1[deg].
8.9.1.4 Other yaw angle determination procedures. If approved by the
Administrator, other procedures for determining yaw angle may be used,
provided that they are verified in a wind tunnel to be able to perform
the yaw angle calibration procedure as described in section 10.5.
8.9.2 Sampling strategy. At each traverse point, first yaw-null the
probe, as described in section 8.9.3, below. Then, with the probe
oriented into the direction of flow, measure and record the yaw angle,
the differential pressure and the temperature at the traverse point,
after stable readings are achieved, in accordance with sections 8.9.4
and 8.9.5. At the start of testing in each port (i.e., after a probe has
been inserted into the flue gas stream), allow at least the response
time to elapse before beginning to take measurements at the first
traverse point accessed from that port. Provided that the probe is not
removed from the flue gas stream, measurements may be taken at
subsequent traverse points accessed from the same test port without
waiting again for the response time to elapse.
8.9.3 Yaw-nulling procedure. In preparation for yaw angle
determination, the probe must first be yaw nulled. After positioning the
probe at the appropriate traverse point, perform the following
procedures.
8.9.3.1 For Type S probes, rotate the probe until a null
differential pressure reading is obtained. The direction of the probe
rotation shall be such that the thermocouple is located downstream of
the probe pressure ports at the yaw-null position. Rotate the
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probe 90[deg] back from the yaw-null position to orient the impact
pressure port into the direction of flow. Read and record the angle
displayed by the angle-measuring device.
8.9.3.2 For 3-D probes, rotate the probe until a null differential
pressure reading (the difference in pressures across the P2
and P3 pressure ports is zero, i.e.,
P2=P3) is indicated by the yaw angle pressure
gauge. Read and record the angle displayed by the angle-measuring
device.
8.9.3.3 Sign of the measured angle. The angle displayed on the
angle-measuring device is considered positive when the probe's impact
pressure port (as viewed from the ``tail'' end of the probe) is oriented
in a clockwise rotational position relative to the stack or duct axis
and is considered negative when the probe's impact pressure port is
oriented in a counterclockwise rotational position (see Figure 2G-7).
8.9.4 Yaw angle determination. After performing the applicable yaw-
nulling procedure in section 8.9.3, determine the yaw angle of flow
according to one of the following procedures. Special care must be
observed to take into account the signs of the recorded angle reading
and all offsets.
8.9.4.1 Direct-reading. If all rotational offsets are zero or if the
angle-measuring device rotational offset (RADO) determined in
section 8.3 exactly compensates for the scribe line rotational offset
(RSLO) determined in section 10.5, then the magnitude of the
yaw angle is equal to the displayed angle-measuring device reading from
section 8.9.3.1 or 8.9.3.2. The algebraic sign of the yaw angle is
determined in accordance with section 8.9.3.3. [Note: Under certain
circumstances (e.g., testing of horizontal ducts) a 90[deg] adjustment
to the angle-measuring device readings may be necessary to obtain the
correct yaw angles.]
8.9.4.2 Compensation for rotational offsets during data reduction.
When the angle-measuring device rotational offset does not compensate
for reference scribe line rotational offset, the following procedure
shall be used to determine the yaw angle:
(a) Enter the reading indicated by the angle-measuring device from
section 8.9.3.1 or 8.9.3.2.
(b) Associate the proper algebraic sign from section 8.9.3.3 with
the reading in step (a).
(c) Subtract the reference scribe line rotational offset,
RSLO, from the reading in step (b).
(d) Subtract the angle-measuring device rotational offset,
RADO, if any, from the result obtained in step (c).
(e) The final result obtained in step (d) is the yaw angle of flow.
[Note: It may be necessary to first apply a 90[deg] adjustment to
the reading in step (a), in order to obtain the correct yaw angle.]
8.9.4.3 Record the yaw angle measurements on a form similar to Table
2G-3.
8.9.5 Impact velocity determination. Maintain the probe rotational
position established during the yaw angle determination. Then, begin
recording the pressure-measuring device readings. These pressure
measurements shall be taken over a sampling period of sufficiently long
duration to ensure representative readings at each traverse point. If
the pressure measurements are determined from visual readings of the
pressure device or display, allow sufficient time to observe the
pulsation in the readings to obtain a sight-weighted average, which is
then recorded manually. If an automated data acquisition system (e.g.,
data logger, computer-based data recorder, strip chart recorder) is used
to record the pressure measurements, obtain an integrated average of all
pressure readings at the traverse point. Stack or duct gas temperature
measurements shall be recorded, at a minimum, once at each traverse
point. Record all necessary data as shown in the example field data form
(Table 2G-3).
8.9.6 Alignment check. For manually operated probes, after the
required yaw angle and differential pressure and temperature
measurements have been made at each traverse point, verify (e.g., by
visual inspection) that the yaw angle-measuring device has remained in
proper alignment with the reference scribe line or with the rotational
offset position established in section 8.3. If, for a particular
traverse point, the angle-measuring device is found to be in proper
alignment, proceed to the next traverse point; otherwise, re-align the
device and repeat the angle and differential pressure measurements at
the traverse point. In the course of a traverse, if a mark used to
properly align the angle-measuring device (e.g., as described in section
18.1.1.1) cannot be located, re-establish the alignment mark before
proceeding with the traverse.
8.10 Probe Plugging. Periodically check for plugging of the pressure
ports by observing the responses on the pressure differential readouts.
Plugging causes erratic results or sluggish responses. Rotate the probe
to determine whether the readouts respond in the expected direction. If
plugging is detected, correct the problem and repeat the affected
measurements.
8.11 Static Pressure. Measure the static pressure in the stack or
duct using the equipment described in section 6.7.
8.11.1 If a Type S probe is used for this measurement, position the
probe at or between any traverse point(s) and rotate the probe until a
null differential pressure reading is obtained. Disconnect the tubing
from one of the pressure ports; read and record the [Delta]P. For
pressure devices with one-directional
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scales, if a deflection in the positive direction is noted with the
negative side disconnected, then the static pressure is positive.
Likewise, if a deflection in the positive direction is noted with the
positive side disconnected, then the static pressure is negative.
8.11.2 If a 3-D probe is used for this measurement, position the
probe at or between any traverse point(s) and rotate the probe until a
null differential pressure reading is obtained at P2-
P3. Rotate the probe 90[deg]. Disconnect the P2
pressure side of the probe and read the pressure P1-
Pbar and record as the static pressure. (Note: The spherical
probe, specified in section 6.1.2 of Method 2F, is unable to provide
this measurement and shall not be used to take static pressure
measurements.)
8.12 Atmospheric Pressure. Determine the atmospheric pressure at the
sampling elevation during each test run following the procedure
described in section 2.5 of Method 2.
8.13 Molecular Weight. Determine the stack or duct gas dry molecular
weight. For combustion processes or processes that emit essentially
CO2, O2, CO, and N2, use Method 3 or
3A. For processes emitting essentially air, an analysis need not be
conducted; use a dry molecular weight of 29.0. Other methods may be
used, if approved by the Administrator.
8.14 Moisture. Determine the moisture content of the stack gas using
Method 4 or equivalent.
8.15 Data Recording and Calculations. Record all required data on a
form similar to Table 2G-3.
8.15.1 2-D probe calibration coefficient. When a Type S pitot tube
is used in the field, the appropriate calibration coefficient as
determined in section 10.6 shall be used to perform velocity
calculations. For calibrated Type S pitot tubes, the A-side coefficient
shall be used when the A-side of the tube faces the flow, and the B-side
coefficient shall be used when the B-side faces the flow.
8.15.2 3-D calibration coefficient. When a 3-D probe is used to
collect data with this method, follow the provisions for the calibration
of 3-D probes in section 10.6 of Method 2F to obtain the appropriate
velocity calibration coefficient (F2 as derived using
Equation 2F-2 in Method 2F) corresponding to a pitch angle position of
0[deg].
8.15.3 Calculations. Calculate the yaw-adjusted velocity at each
traverse point using the equations presented in section 12.2. Calculate
the test run average stack gas velocity by finding the arithmetic
average of the point velocity results in accordance with sections 12.3
and 12.4, and calculate the stack gas volumetric flow rate in accordance
with section 12.5 or 12.6, as applicable.
9.0 Quality Control
9.1 Quality Control Activities. In conjunction with the yaw angle
determination and the pressure and temperature measurements specified in
section 8.9, the following quality control checks should be performed.
9.1.1 Range of the differential pressure gauge. In accordance with
the specifications in section 6.4, ensure that the proper differential
pressure gauge is being used for the range of [Delta]P values
encountered. If it is necessary to change to a more sensitive gauge,
replace the gauge with a gauge calibrated according to section 10.3.3,
perform the leak check described in section 8.4 and the zero check
described in section 8.5, and repeat the differential pressure and
temperature readings at each traverse point.
9.1.2 Horizontal stability check. For horizontal traverses of a
stack or duct, visually check that the probe shaft is maintained in a
horizontal position prior to taking a pressure reading. Periodically,
during a test run, the probe's horizontal stability should be verified
by placing a carpenter's level, a digital inclinometer, or other angle-
measuring device on the portion of the probe sheath that extends outside
of the test port. A comparable check should be performed by automated
systems.
10.0 Calibration
10.1 Wind Tunnel Qualification Checks. To qualify for use in
calibrating probes, a wind tunnel shall have the design features
specified in section 6.11 and satisfy the following qualification
criteria. The velocity pressure cross-check in section 10.1.1 and axial
flow verification in section 10.1.2 shall be performed before the
initial use of the wind tunnel and repeated immediately after any
alteration occurs in the wind tunnel's configuration, fans, interior
surfaces, straightening vanes, controls, or other properties that could
reasonably be expected to alter the flow pattern or velocity stability
in the tunnel. The owner or operator of a wind tunnel used to calibrate
probes according to this method shall maintain records documenting that
the wind tunnel meets the requirements of sections 10.1.1 and 10.1.2 and
shall provide these records to the Administrator upon request.
10.1.1 Velocity pressure cross-check. To verify that the wind tunnel
produces the same velocity at the tested probe head as at the
calibration pitot tube impact port, perform the following cross-check.
Take three differential pressure measurements at the fixed calibration
pitot tube location, using the calibration pitot tube specified in
section 6.10, and take three measurements with the calibration pitot
tube at the wind tunnel calibration location, as defined in section
3.21. Alternate the measurements between the two positions. Perform this
procedure at
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the lowest and highest velocity settings at which the probes will be
calibrated. Record the values on a form similar to Table 2G-4. At each
velocity setting, the average velocity pressure obtained at the wind
tunnel calibration location shall be within 2
percent or 2.5 mm H2O (0.01 in. H2O), whichever is
less restrictive, of the average velocity pressure obtained at the fixed
calibration pitot tube location. This comparative check shall be
performed at 2.5-cm (1-in.), or smaller, intervals across the full
length, width, and depth (if applicable) of the wind tunnel calibration
location. If the criteria are not met at every tested point, the wind
tunnel calibration location must be redefined, so that acceptable
results are obtained at every point. Include the results of the velocity
pressure cross-check in the calibration data section of the field test
report. (See section 16.1.4.)
10.1.2 Axial flow verification. The following procedures shall be
performed to demonstrate that there is fully developed axial flow within
the wind tunnel calibration location and at the calibration pitot tube
location. Two options are available to conduct this check.
10.1.2.1 Using a calibrated 3-D probe. A probe that has been
previously calibrated in a wind tunnel with documented axial flow (as
defined in section 3.22) may be used to conduct this check. Insert the
calibrated 3-D probe into the wind tunnel test section using the tested
probe port. Following the procedures in sections 8.9 and 12.2 of Method
2F, determine the yaw and pitch angles at all the point(s) in the test
section where the velocity pressure cross-check, as specified in section
10.1.1, is performed. This includes all the points in the calibration
location and the point where the calibration pitot tube will be located.
Determine the yaw and pitch angles at each point. Repeat these
measurements at the highest and lowest velocities at which the probes
will be calibrated. Record the values on a form similar to Table 2G-5.
Each measured yaw and pitch angle shall be within 3[deg] of 0[deg]. Exceeding the limits indicates
unacceptable flow in the test section. Until the problem is corrected
and acceptable flow is verified by repetition of this procedure, the
wind tunnel shall not be used for calibration of probes. Include the
results of the axial flow verification in the calibration data section
of the field test report. (See section 16.1.4.)
10.1.2.2 Using alternative probes. Axial flow verification may be
performed using an uncalibrated prism-shaped 3-D probe (e.g., DA or DAT
probe) or an uncalibrated wedge probe. (Figure 2G-8 illustrates a
typical wedge probe.) This approach requires use of two ports: the
tested probe port and a second port located 90[deg] from the tested
probe port. Each port shall provide access to all the points within the
wind tunnel test section where the velocity pressure cross-check, as
specified in section 10.1.1, is conducted. The probe setup shall include
establishing a reference yaw-null position on the probe sheath to serve
as the location for installing the angle-measuring device. Physical
design features of the DA, DAT, and wedge probes are relied on to
determine the reference position. For the DA or DAT probe, this
reference position can be determined by setting a digital inclinometer
on the flat facet where the P1 pressure port is located and
then identifying the rotational position on the probe sheath where a
second angle-measuring device would give the same angle reading. The
reference position on a wedge probe shaft can be determined either
geometrically or by placing a digital inclinometer on each side of the
wedge and rotating the probe until equivalent readings are obtained.
With the latter approach, the reference position is the rotational
position on the probe sheath where an angle-measuring device would give
a reading of 0[deg]. After installation of the angle-measuring device in
the reference yaw-null position on the probe sheath, determine the yaw
angle from the tested port. Repeat this measurement using the 90[deg]
offset port, which provides the pitch angle of flow. Determine the yaw
and pitch angles at all the point(s) in the test section where the
velocity pressure cross-check, as specified in section 10.1.1, is
performed. This includes all the points in the wind tunnel calibration
location and the point where the calibration pitot tube will be located.
Perform this check at the highest and lowest velocities at which the
probes will be calibrated. Record the values on a form similar to Table
2G-5. Each measured yaw and pitch angle shall be within 3[deg] of 0[deg]. Exceeding the limits indicates
unacceptable flow in the test section. Until the problem is corrected
and acceptable flow is verified by repetition of this procedure, the
wind tunnel shall not be used for calibration of probes. Include the
results in the probe calibration report.
10.1.3 Wind tunnel audits.
10.1.3.1 Procedure. Upon the request of the Administrator, the owner
or operator of a wind tunnel shall calibrate a 2-D audit probe in
accordance with the procedures described in sections 10.3 through 10.6.
The calibration shall be performed at two velocities that encompass the
velocities typically used for this method at the facility. The resulting
calibration data shall be submitted to the Agency in an audit test
report. These results shall be compared by the Agency to reference
calibrations of the audit probe at the same velocity settings obtained
at two different wind tunnels.
10.1.3.2 Acceptance criterion. The audited tunnel's calibration
coefficient is acceptable if it is within 3
percent of the reference calibrations obtained at each velocity setting
by
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one (or both) of the wind tunnels. If the acceptance criterion is not
met at each calibration velocity setting, the audited wind tunnel shall
not be used to calibrate probes for use under this method until the
problems are resolved and acceptable results are obtained upon
completion of a subsequent audit.
10.2 Probe Inspection.
10.2.1 Type S probe. Before each calibration of a Type S probe,
verify that one leg of the tube is permanently marked A, and the other,
B. Carefully examine the pitot tube from the top, side, and ends.
Measure the angles ([alpha]1, [alpha]2,
[beta]1, and [beta]2) and the dimensions (w and z)
illustrated in Figures 2-2 and 2-3 in Method 2. Also measure the
dimension A, as shown in the diagram in Table 2G-1, and the external
tubing diameter (dimension Dt, Figure 2-2b in Method 2). For
the purposes of this method, Dt shall be no less than 9.5 mm
(\3/8\ in.). The base-to-opening plane distances PA and
PB in Figure 2-3 of Method 2 shall be equal, and the
dimension A in Table 2G-1 should be between 2.10Dt and
3.00Dt. Record the inspection findings and probe measurements
on a form similar to Table CD2-1 of the ``Quality Assurance Handbook for
Air Pollution Measurement Systems: Volume III, Stationary Source-
Specific Methods'' (EPA/600/R-94/038c, September 1994). For reference,
this form is reproduced herein as Table 2G-1. The pitot tube shall not
be used under this method if it fails to meet the specifications in this
section and the alignment specifications in section 6.1.1. All Type S
probes used to collect data with this method shall be calibrated
according to the procedures outlined in sections 10.3 through 10.6
below. During calibration, each Type S pitot tube shall be configured in
the same manner as used, or planned to be used, during the field test,
including all components in the probe assembly (e.g., thermocouple,
probe sheath, sampling nozzle). Probe shaft extensions that do not
affect flow around the probe head need not be attached during
calibration.
10.2.2 3-D probe. If a 3-D probe is used to collect data with this
method, perform the pre-calibration inspection according to procedures
in Method 2F, section 10.2.
10.3 Pre-Calibration Procedures. Prior to calibration, a scribe line
shall have been placed on the probe in accordance with section 10.4. The
yaw angle and velocity calibration procedures shall not begin until the
pre-test requirements in sections 10.3.1 through 10.3.4 have been met.
10.3.1 Perform the horizontal straightness check described in
section 8.2 on the probe assembly that will be calibrated in the wind
tunnel.
10.3.2 Perform a leak check in accordance with section 8.4.
10.3.3 Except as noted in section 10.3.3.3, calibrate all
differential pressure-measuring devices to be used in the probe
calibrations, using the following procedures. At a minimum, calibrate
these devices on each day that probe calibrations are performed.
10.3.3.1 Procedure. Before each wind tunnel use, all differential
pressure-measuring devices shall be calibrated against the reference
device specified in section 6.4.3 using a common pressure source.
Perform the calibration at three reference pressures representing 30,
60, and 90 percent of the full-scale range of the pressure-measuring
device being calibrated. For an inclined-vertical manometer, perform
separate calibrations on the inclined and vertical portions of the
measurement scale, considering each portion of the scale to be a
separate full-scale range. [For example, for a manometer with a 0-to
2.5-cm H2O (0-to 1-in. H2O) inclined scale and a
2.5-to 12.7-cm H2O (1-to 5-in. H2O) vertical
scale, calibrate the inclined portion at 7.6, 15.2, and 22.9 mm
H2O (0.3, 0.6, and 0.9 in. H2O), and calibrate the
vertical portion at 3.8, 7.6, and 11.4 cm H2O (1.5, 3.0, and
4.5 in. H2O).] Alternatively, for the vertical portion of the
scale, use three evenly spaced reference pressures, one of which is
equal to or higher than the highest differential pressure expected in
field applications.
10.3.3.2 Acceptance criteria. At each pressure setting, the two
pressure readings made using the reference device and the pressure-
measuring device being calibrated shall agree to within 2 percent of full scale of the device being calibrated
or 0.5 mm H2O (0.02 in. H2O), whichever is less
restrictive. For an inclined-vertical manometer, these requirements
shall be met separately using the respective full-scale upper limits of
the inclined and vertical portions of the scale. Differential pressure-
measuring devices not meeting the 2 percent of
full scale or 0.5 mm H2O (0.02 in. H2O)
calibration requirement shall not be used.
10.3.3.3 Exceptions. Any precision manometer that meets the
specifications for a reference device in section 6.4.3 and that is not
used for field testing does not require calibration, but must be leveled
and zeroed before each wind tunnel use. Any pressure device used
exclusively for yaw nulling does not require calibration, but shall be
checked for responsiveness to rotation of the probe prior to each wind
tunnel use.
10.3.4 Calibrate digital inclinometers on each day of wind tunnel or
field testing (prior to beginning testing) using the following
procedures. Calibrate the inclinometer according to the manufacturer's
calibration procedures. In addition, use a triangular block (illustrated
in Figure 2G-9) with a known angle [theta], independently determined
using a protractor or equivalent device, between two adjacent sides to
verify the inclinometer readings. (Note: If other angle-measuring
devices meeting the provisions of
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section 6.2.3 are used in place of a digital inclinometer, comparable
calibration procedures shall be performed on such devices.) Secure the
triangular block in a fixed position. Place the inclinometer on one side
of the block (side A) to measure the angle of inclination
(R1). Repeat this measurement on the adjacent side of the
block (side B) using the inclinometer to obtain a second angle reading
(R2). The difference of the sum of the two readings from
180[deg] (i.e., 180[deg]-R1-R2) shall be within
2[deg] of the known angle, [theta].
10.4 Placement of Reference Scribe Line. Prior to the first
calibration of a probe, a line shall be permanently inscribed on the
main probe sheath to serve as a reference mark for determining yaw
angles. Annex C in section 18 of this method gives a guideline for
placement of the reference scribe line.
10.4.1 This reference scribe line shall meet the specifications in
sections 6.1.5.1 and 6.1.5.3 of this method. To verify that the
alignment specification in section 6.1.5.3 is met, secure the probe in a
horizontal position and measure the rotational angle of each scribe line
and scribe line segment using an angle-measuring device that meets the
specifications in section 6.2.1 or 6.2.3. For any scribe line that is
longer than 30.5 cm (12 in.), check the line's rotational position at
30.5-cm (12-in.) intervals. For each line segment that is 12 in. or less
in length, check the rotational position at the two endpoints of the
segment. To meet the alignment specification in section 6.1.5.3, the
minimum and maximum of all of the rotational angles that are measured
along the full length of main probe must not differ by more than 2[deg].
(Note: A short reference scribe line segment [e.g., 15.2 cm (6 in.) or
less in length] meeting the alignment specifications in section 6.1.5.3
is fully acceptable under this method. See section 18.1.1.1 of Annex A
for an example of a probe marking procedure, suitable for use with a
short reference scribe line.)
10.4.2 The scribe line should be placed on the probe first and then
its offset from the yaw-null position established (as specified in
section 10.5). The rotational position of the reference scribe line
relative to the yaw-null position of the probe, as determined by the yaw
angle calibration procedure in section 10.5, is the reference scribe
line rotational offset, RSLO. The reference scribe line
rotational offset shall be recorded and retained as part of the probe's
calibration record.
10.4.3 Scribe line for automated probes. A scribe line may not be
necessary for an automated probe system if a reference rotational
position of the probe is built into the probe system design. For such
systems, a ``flat'' (or comparable, clearly identifiable physical
characteristic) should be provided on the probe casing or flange plate
to ensure that the reference position of the probe assembly remains in a
vertical or horizontal position. The rotational offset of the flat (or
comparable, clearly identifiable physical characteristic) needed to
orient the reference position of the probe assembly shall be recorded
and maintained as part of the automated probe system's specifications.
10.5 Yaw Angle Calibration Procedure. For each probe used to measure
yaw angles with this method, a calibration procedure shall be performed
in a wind tunnel meeting the specifications in section 10.1 to determine
the rotational position of the reference scribe line relative to the
probe's yaw-null position. This procedure shall be performed on the main
probe with all devices that will be attached to the main probe in the
field [such as thermocouples, resistance temperature detectors (RTDs),
or sampling nozzles] that may affect the flow around the probe head.
Probe shaft extensions that do not affect flow around the probe head
need not be attached during calibration. At a minimum, this procedure
shall include the following steps.
10.5.1 Align and lock the angle-measuring device on the reference
scribe line. If a marking procedure (such as described in section
18.1.1.1) is used, align the angle-measuring device on a mark within
1[deg] of the rotational position of the reference
scribe line. Lock the angle-measuring device onto the probe sheath at
this position.
10.5.2 Zero the pressure-measuring device used for yaw nulling.
10.5.3 Insert the probe assembly into the wind tunnel through the
entry port, positioning the probe's impact port at the calibration
location. Check the responsiveness of the pressure-measurement device to
probe rotation, taking corrective action if the response is
unacceptable.
10.5.4 Ensure that the probe is in a horizontal position, using a
carpenter's level.
10.5.5 Rotate the probe either clockwise or counterclockwise until a
yaw null [zero [Delta]P for a Type S probe or zero (P2-
P3) for a 3-D probe] is obtained. If using a Type S probe
with an attached thermocouple, the direction of the probe rotation shall
be such that the thermocouple is located downstream of the probe
pressure ports at the yaw-null position.
10.5.6 Use the reading displayed by the angle-measuring device at
the yaw-null position to determine the magnitude of the reference scribe
line rotational offset, RSLO, as defined in section 3.15.
Annex D in section 18 of this method gives a recommended procedure for
determining the magnitude of RSLO with a digital inclinometer
and a second procedure for determining the magnitude of RSLO
with a protractor wheel and pointer device. Table 2G-6 gives an example
data form and Table 2G-7 is a look-up table with the recommended
procedure. Procedures other than those recommended in Annex D in section
18 may be used, if they can determine RSLO to within 1[deg]
and are explained in detail
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in the field test report. The algebraic sign of RSLO will
either be positive if the rotational position of the reference scribe
line (as viewed from the ``tail'' end of the probe) is clockwise, or
negative, if counterclockwise with respect to the probe's yaw-null
position. (This is illustrated in Figure 2G-10.)
10.5.7 The steps in sections 10.5.3 through 10.5.6 shall be
performed twice at each of the velocities at which the probe will be
calibrated (in accordance with section 10.6). Record the values of
RSLO.
10.5.8 The average of all of the RSLO values shall be
documented as the reference scribe line rotational offset for the probe.
10.5.9 Use of reference scribe line offset. The reference scribe
line rotational offset shall be used to determine the yaw angle of flow
in accordance with section 8.9.4.
10.6 Velocity Calibration Procedure. When a 3-D probe is used under
this method, follow the provisions for the calibration of 3-D probes in
section 10.6 of Method 2F to obtain the necessary velocity calibration
coefficients (F2 as derived using Equation 2F-2 in Method 2F)
corresponding to a pitch angle position of 0[deg]. The following
procedure applies to Type S probes. This procedure shall be performed on
the main probe and all devices that will be attached to the main probe
in the field (e.g., thermocouples, RTDs, sampling nozzles) that may
affect the flow around the probe head. Probe shaft extensions that do
not affect flow around the probe head need not be attached during
calibration. (Note: If a sampling nozzle is part of the assembly, two
additional requirements must be satisfied before proceeding. The
distance between the nozzle and the pitot tube shall meet the minimum
spacing requirement prescribed in Method 2, and a wind tunnel
demonstration shall be performed that shows the probe's ability to yaw
null is not impaired when the nozzle is drawing sample.) To obtain
velocity calibration coefficient(s) for the tested probe, proceed as
follows.
10.6.1 Calibration velocities. The tester may calibrate the probe at
two nominal wind tunnel velocity settings of 18.3 m/sec and 27.4 m/sec
(60 ft/sec and 90 ft/sec) and average the results of these calibrations,
as described in sections 10.6.12 through 10.6.14, in order to generate
the calibration coefficient, Cp. If this option is selected,
this calibration coefficient may be used for all field applications
where the velocities are 9.1 m/sec (30 ft/sec) or greater.
Alternatively, the tester may customize the probe calibration for a
particular field test application (or for a series of applications),
based on the expected average velocity(ies) at the test site(s). If this
option is selected, generate the calibration coefficients by calibrating
the probe at two nominal wind tunnel velocity settings, one of which is
less than or equal to and the other greater than or equal to the
expected average velocity(ies) for the field application(s), and average
the results as described in sections 10.6.12 through 10.6.14. Whichever
calibration option is selected, the probe calibration coefficient(s)
obtained at the two nominal calibration velocities shall meet the
conditions specified in sections 10.6.12 through 10.6.14.
10.6.2 Connect the tested probe and calibration pitot tube to their
respective pressure-measuring devices. Zero the pressure-measuring
devices. Inspect and leak-check all pitot lines; repair or replace them,
if necessary. Turn on the fan, and allow the wind tunnel air flow to
stabilize at the first of the selected nominal velocity settings.
10.6.3 Position the calibration pitot tube at its measurement
location (determined as outlined in section 6.11.4.3), and align the
tube so that its tip is pointed directly into the flow. Ensure that the
entry port surrounding the tube is properly sealed. The calibration
pitot tube may either remain in the wind tunnel throughout the
calibration, or be removed from the wind tunnel while measurements are
taken with the probe being calibrated.
10.6.4 Check the zero setting of each pressure-measuring device.
10.6.5 Insert the tested probe into the wind tunnel and align it so
that the designated pressure port (e.g., either the A-side or B-side of
a Type S probe) is pointed directly into the flow and is positioned
within the wind tunnel calibration location (as defined in section
3.21). Secure the probe at the 0[deg] pitch angle position. Ensure that
the entry port surrounding the probe is properly sealed.
10.6.6 Read the differential pressure from the calibration pitot
tube ([Delta]Pstd), and record its value. Read the barometric
pressure to within 2.5 mm Hg (0.1 in. Hg) and the temperature in the wind tunnel to
within 0.6 [deg]C (1 [deg]F). Record these values on a data form similar
to Table 2G-8.
10.6.7 After the tested probe's differential pressure gauges have
had sufficient time to stabilize, yaw null the probe (and then rotate it
back 90[deg] for Type S probes), then obtain the differential pressure
reading ([Delta]P). Record the yaw angle and differential pressure
readings.
10.6.8 Take paired differential pressure measurements with the
calibration pitot tube and tested probe (according to sections 10.6.6
and 10.6.7). The paired measurements in each replicate can be made
either simultaneously (i.e., with both probes in the wind tunnel) or by
alternating the measurements of the two probes (i.e., with only one
probe at a time in the wind tunnel).
10.6.9 Repeat the steps in sections 10.6.6 through 10.6.8 at the
same nominal velocity setting until three pairs of [Delta]P readings
have been obtained from the calibration pitot tube and the tested probe.
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10.6.10 Repeat the steps in sections 10.6.6 through 10.6.9 above for
the A-side and B-side of the Type S pitot tube. For a probe assembly
constructed such that its pitot tube is always used in the same
orientation, only one side of the pitot tube need be calibrated (the
side that will face the flow). However, the pitot tube must still meet
the alignment and dimension specifications in section 6.1.1 and must
have an average deviation ([sigma]) value of 0.01 or less as provided in
section 10.6.12.4.
10.6.11 Repeat the calibration procedures in sections 10.6.6 through
10.6.10 at the second selected nominal wind tunnel velocity setting.
10.6.12 Perform the following calculations separately on the A-side
and B-side values.
10.6.12.1 Calculate a Cp value for each of the three
replicates performed at the lower velocity setting where the
calibrations were performed using Equation 2-2 in section 4.1.4 of
Method 2.
10.6.12.2 Calculate the arithmetic average, Cp(avg-low),
of the three Cp values.
10.6.12.3 Calculate the deviation of each of the three individual
values of Cp from the A-side average Cp(avg-low)
value using Equation 2-3 in Method 2.
10.6.12.4 Calculate the average deviation ([sigma]) of the three
individual Cp values from Cp(avg-low) using
Equation 2-4 in Method 2. Use the Type S pitot tube only if the values
of [sigma] (side A) and [sigma] (side B) are less than or equal to 0.01.
If both A-side and B-side calibration coefficients are calculated, the
absolute value of the difference between Cp(avg-low) (side A)
and Cp(avg-low) (side B) must not exceed 0.01.
10.6.13 Repeat the calculations in section 10.6.12 using the data
obtained at the higher velocity setting to derive the arithmetic
Cp values at the higher velocity setting,
Cp(avg-high), and to determine whether the conditions in
10.6.12.4 are met by both the A-side and B-side calibrations at this
velocity setting.
10.6.14 Use equation 2G-1 to calculate the percent difference of the
averaged Cp values at the two calibration velocities.
[GRAPHIC] [TIFF OMITTED] TR14MY99.062
The percent difference between the averaged Cp values shall
not exceed 3 percent. If the specification is met,
average the A-side values of Cp(avg-low) and
Cp(avg-high) to produce a single A-side calibration
coefficient, Cp. Repeat for the B-side values if calibrations
were performed on that side of the pitot. If the specification is not
met, make necessary adjustments in the selected velocity settings and
repeat the calibration procedure until acceptable results are obtained.
10.6.15 If the two nominal velocities used in the calibration were
18.3 and 27.4 m/sec (60 and 90 ft/sec), the average Cp from
section 10.6.14 is applicable to all velocities 9.1 m/sec (30 ft/sec) or
greater. If two other nominal velocities were used in the calibration,
the resulting average Cp value shall be applicable only in
situations where the velocity calculated using the calibration
coefficient is neither less than the lower nominal velocity nor greater
than the higher nominal velocity.
10.7 Recalibration. Recalibrate the probe using the procedures in
section 10 either within 12 months of its first field use after its most
recent calibration or after 10 field tests (as defined in section 3.3),
whichever occurs later. In addition, whenever there is visible damage to
the probe head, the probe shall be recalibrated before it is used again.
10.8 Calibration of pressure-measuring devices used in the field.
Before its initial use in a field test, calibrate each pressure-
measuring device (except those used exclusively for yaw nulling) using
the three-point calibration procedure described in section 10.3.3. The
device shall be recalibrated according to the procedure in section
10.3.3 no later than 90 days after its first field use following its
most recent calibration. At the discretion of the tester, more frequent
calibrations (e.g., after a field test) may be performed. No
adjustments, other than adjustments to the zero setting, shall be made
to the device between calibrations.
10.8.1 Post-test calibration check. A single-point calibration check
shall be performed on each pressure-measuring device after completion of
each field test. At the discretion of the tester, more frequent single-
point calibration checks (e.g., after one or more field test runs) may
be performed. It is recommended that the post-test check be performed
before leaving the field test site. The check shall be performed at a
pressure between 50 and 90 percent of full scale by taking a common
pressure reading with the tested probe and a reference pressure-
measuring device (as described in section 6.4.4) or by challenging the
tested device with a reference pressure source (as described in section
6.4.4) or by performing an equivalent check using a reference device
approved by the Administrator.
[[Page 106]]
10.8.2 Acceptance criterion. At the selected pressure setting, the
pressure readings made using the reference device and the tested device
shall agree to within 3 percent of full scale of
the tested device or 0.8 mm H2O (0.03 in. H2O),
whichever is less restrictive. If this specification is met, the test
data collected during the field test are valid. If the specification is
not met, all test data collected since the last successful calibration
or calibration check are invalid and shall be repeated using a pressure-
measuring device with a current, valid calibration. Any device that
fails the calibration check shall not be used in a field test until a
successful recalibration is performed according to the procedures in
section 10.3.3.
10.9 Temperature Gauges. Same as Method 2, section 4.3. The
alternative thermocouple calibration procedures outlined in Emission
Measurement Center (EMC) Approved Alternative Method (ALT-011)
``Alternative Method 2 Thermocouple Calibration Procedure'' may be
performed. Temperature gauges shall be calibrated no more than 30 days
prior to the start of a field test or series of field tests and
recalibrated no more than 30 days after completion of a field test or
series of field tests.
10.10 Barometer. Same as Method 2, section 4.4. The barometer shall
be calibrated no more than 30 days prior to the start of a field test or
series of field tests.
11.0 Analytical Procedure
Sample collection and analysis are concurrent for this method (see
section 8.0).
12.0 Data Analysis and Calculations
These calculations use the measured yaw angle and the differential
pressure and temperature measurements at individual traverse points to
derive the near-axial flue gas velocity (va(i)) at each of
those points. The near-axial velocity values at all traverse points that
comprise a full stack or duct traverse are then averaged to obtain the
average near-axial stack or duct gas velocity (va(avg)).
12.1 Nomenclature
A=Cross-sectional area of stack or duct at the test port location, m\2\
(ft \2\).
Bws=Water vapor in the gas stream (from Method 4 or
alternative), proportion by volume.
Cp=Pitot tube calibration coefficient, dimensionless.
F2(i)=3-D probe velocity coefficient at 0 pitch, applicable
at traverse point i.
Kp=Pitot tube constant,
[GRAPHIC] [TIFF OMITTED] TR14MY99.063
for the metric system, and
[GRAPHIC] [TIFF OMITTED] TR14MY99.064
for the English system.
Md=Molecular weight of stack or duct gas, dry basis (see
section 8.13), g/g-mole (lb/lb-mole).
Ms=Molecular weight of stack or duct gas, wet basis, g/g-mole
(lb/lb-mole).
[GRAPHIC] [TIFF OMITTED] TR14MY99.065
Pbar=Barometric pressure at velocity measurement site, mm Hg
(in. Hg).
Pg=Stack or duct static pressure, mm H2O (in.
H2O).
Ps=Absolute stack or duct pressure, mm Hg (in. Hg),
[GRAPHIC] [TIFF OMITTED] TR14MY99.066
Pstd=Standard absolute pressure, 760 mm Hg (29.92 in. Hg).
13.6=Conversion from mm H2O (in. H2O) to mm Hg
(in. Hg).
Qsd=Average dry-basis volumetric stack or duct gas flow rate
corrected to standard conditions, dscm/hr (dscf/hr).
Qsw=Average wet-basis volumetric stack or duct gas flow rate
corrected to standard conditions, wscm/hr (wscf/hr).
ts(i)=Stack or duct temperature, [deg]C ([deg]F), at traverse
point i.
Ts(i)=Absolute stack or duct temperature, [deg]K ([deg]R), at
traverse point i.
[GRAPHIC] [TIFF OMITTED] TR14MY99.067
for the metric system, and
[GRAPHIC] [TIFF OMITTED] TR14MY99.068
for the English system.
Ts(avg)=Average absolute stack or duct gas temperature across
all traverse points.
Tstd=Standard absolute temperature, 293 [deg]K (528 [deg]R).
va(i)=Measured stack or duct gas impact velocity, m/sec (ft/
sec), at traverse point i.
va(avg)=Average near-axial stack or duct gas velocity, m/sec
(ft/sec) across all traverse points.
[Delta]Pi=Velocity head (differential pressure) of stack or
duct gas, mm H2O (in. H2O), applicable at traverse
point i.
(P1-P2)=Velocity head (differential pressure) of
stack or duct gas measured by a 3-D probe, mm H2O (in.
H2O), applicable at traverse point i.
3,600=Conversion factor, sec/hr.
18.0=Molecular weight of water, g/g-mole (lb/lb-mole).
[[Page 107]]
[theta]y(i)=Yaw angle of the flow velocity vector, at
traverse point i.
n=Number of traverse points.
12.2 Traverse Point Velocity Calculations. Perform the following
calculations from the measurements obtained at each traverse point.
12.2.1 Selection of calibration coefficient. Select the calibration
coefficient as described in section 10.6.1.
12.2.2 Near-axial traverse point velocity. When using a Type S
probe, use the following equation to calculate the traverse point near-
axial velocity (va(i)) from the differential pressure
([Delta]Pi), yaw angle ([theta]y(i)), absolute
stack or duct standard temperature (Ts(i)) measured at
traverse point i, the absolute stack or duct pressure (Ps),
and molecular weight (Ms).
[GRAPHIC] [TIFF OMITTED] TR14MY99.069
Use the following equation when using a 3-D probe.
[GRAPHIC] [TIFF OMITTED] TR14MY99.070
12.2.3 Handling multiple measurements at a traverse point. For
pressure or temperature devices that take multiple measurements at a
traverse point, the multiple measurements (or where applicable, their
square roots) may first be averaged and the resulting average values
used in the equations above. Alternatively, the individual measurements
may be used in the equations above and the resulting calculated values
may then be averaged to obtain a single traverse point value. With
either approach, all of the individual measurements recorded at a
traverse point must be used in calculating the applicable traverse point
value.
12.3 Average Near-Axial Velocity in Stack or Duct. Use the reported
traverse point near-axial velocity in the following equation.
[GRAPHIC] [TIFF OMITTED] TR14MY99.071
12.4 Acceptability of Results. The acceptability provisions in
section 12.4 of Method 2F apply to 3-D probes used under Method 2G. The
following provisions apply to Type S probes. For Type S probes, the test
results are acceptable and the calculated value of va(avg)
may be reported as the average near-axial velocity for the test run if
the conditions in either section 12.4.1 or 12.4.2 are met.
12.4.1 The average calibration coefficient Cp used in
Equation 2G-6 was generated at nominal velocities of 18.3 and 27.4 m/sec
(60 and 90 ft/sec) and the value of va(avg) calculated using
Equation 2G-8 is greater than or equal to 9.1 m/sec (30 ft/sec).
12.4.2 The average calibration coefficient Cp used in
Equation 2G-6 was generated at nominal velocities other than 18.3 or
27.4 m/sec (60 or 90 ft/sec) and the value of va(avg)
calculated using Equation 2G-8 is greater than or equal to the lower
nominal velocity and less than or equal to the higher nominal velocity
used to derive the average Cp.
12.4.3 If the conditions in neither section 12.4.1 nor section
12.4.2 are met, the test results obtained from Equation 2G-8 are not
acceptable, and the steps in sections 12.2 and 12.3 must be repeated
using an average calibration coefficient Cp that satisfies
the conditions in section 12.4.1 or 12.4.2.
12.5 Average Gas Volumetric Flow Rate in Stack or Duct (Wet Basis).
Use the following equation to compute the average volumetric flow rate
on a wet basis.
[[Page 108]]
[GRAPHIC] [TIFF OMITTED] TR14MY99.072
12.6 Average Gas Volumetric Flow Rate in Stack or Duct (Dry Basis).
Use the following equation to compute the average volumetric flow rate
on a dry basis.
[GRAPHIC] [TIFF OMITTED] TR14MY99.073
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 Reporting.
16.1 Field Test Reports. Field test reports shall be submitted to
the Agency according to applicable regulatory requirements. Field test
reports should, at a minimum, include the following elements.
16.1.1 Description of the source. This should include the name and
location of the test site, descriptions of the process tested, a
description of the combustion source, an accurate diagram of stack or
duct cross-sectional area at the test site showing the dimensions of the
stack or duct, the location of the test ports, and traverse point
locations and identification numbers or codes. It should also include a
description and diagram of the stack or duct layout, showing the
distance of the test location from the nearest upstream and downstream
disturbances and all structural elements (including breachings, baffles,
fans, straighteners, etc.) affecting the flow pattern. If the source and
test location descriptions have been previously submitted to the Agency
in a document (e.g., a monitoring plan or test plan), referencing the
document in lieu of including this information in the field test report
is acceptable.
16.1.2 Field test procedures. These should include a description of
test equipment and test procedures. Testing conventions, such as
traverse point numbering and measurement sequence (e.g., sampling from
center to wall, or wall to center), should be clearly stated. Test port
identification and directional reference for each test port should be
included on the appropriate field test data sheets.
16.1.3 Field test data.
16.1.3.1 Summary of results. This summary should include the dates
and times of testing, and the average near-axial gas velocity and the
average flue gas volumetric flow results for each run and tested
condition.
16.1.3.2 Test data. The following values for each traverse point
should be recorded and reported:
(a) Differential pressure at traverse point i ([Delta]Pi)
(b) Stack or duct temperature at traverse point i (ts(i))
(c) Absolute stack or duct temperature at traverse point i
(Ts(i))
(d) Yaw angle at traverse point i ([theta]y(i))
(e) Stack gas near-axial velocity at traverse point i
(va(i))
16.1.3.3 The following values should be reported once per run:
(a) Water vapor in the gas stream (from Method 4 or alternative),
proportion by volume (Bws), measured at the frequency
specified in the applicable regulation
(b) Molecular weight of stack or duct gas, dry basis (Md)
(c) Molecular weight of stack or duct gas, wet basis (Ms)
(d) Stack or duct static pressure (Pg)
(e) Absolute stack or duct pressure (Ps)
(f) Carbon dioxide concentration in the flue gas, dry basis
(%d CO2)
(g) Oxygen concentration in the flue gas, dry basis (%d
O2)
(h) Average near-axial stack or duct gas velocity
(va(avg)) across all traverse points
(i) Gas volumetric flow rate corrected to standard conditions, dry
or wet basis as required by the applicable regulation (Qsd or
Qsw)
16.1.3.4 The following should be reported once per complete set of
test runs:
(a) Cross-sectional area of stack or duct at the test location (A)
(b) Pitot tube calibration coefficient (Cp)
(c) Measurement system response time (sec)
(d) Barometric pressure at measurement site (Pbar)
16.1.4 Calibration data. The field test report should include
calibration data for all
[[Page 109]]
probes and test equipment used in the field test. At a minimum, the
probe calibration data reported to the Agency should include the
following:
(a) Date of calibration
(b) Probe type
(c) Probe identification number(s) or code(s)
(d) Probe inspection sheets
(e) Pressure measurements and calculations used to obtain
calibration coefficients in accordance with section 10.6 of this method
(f) Description and diagram of wind tunnel used for the calibration,
including dimensions of cross-sectional area and position and size of
the test section
(g) Documentation of wind tunnel qualification tests performed in
accordance with section 10.1 of this method
16.1.5 Quality assurance. Specific quality assurance and quality
control procedures used during the test should be described.
17.0 Bibliography.
(1) 40 CFR Part 60, Appendix A, Method 1--Sample and velocity
traverses for stationary sources.
(2) 40 CFR Part 60, Appendix A, Method 2--Determination of stack gas
velocity and volumetric flow rate (Type S pitot tube) .
(3) 40 CFR Part 60, Appendix A, Method 2F--Determination of stack
gas velocity and volumetric flow rate with three-dimensional probes.
(4) 40 CFR Part 60, Appendix A, Method 2H--Determination of stack
gas velocity taking into account velocity decay near the stack wall.
(5) 40 CFR Part 60, Appendix A, Method 3--Gas analysis for carbon
dioxide, oxygen, excess air, and dry molecular weight.
(6) 40 CFR Part 60, Appendix A, Method 3A--Determination of oxygen
and carbon dioxide concentrations in emissions from stationary sources
(instrumental analyzer procedure).
(7) 40 CFR Part 60, Appendix A, Method 4--Determination of moisture
content in stack gases.
(8) Emission Measurement Center (EMC) Approved Alternative Method
(ALT-011) ``Alternative Method 2 Thermocouple Calibration Procedure.''
(9) Electric Power Research Institute, Interim Report EPRI TR-
106698, ``Flue Gas Flow Rate Measurement Errors,'' June 1996.
(10) Electric Power Research Institute, Final Report EPRI TR-108110,
``Evaluation of Heat Rate Discrepancy from Continuous Emission
Monitoring Systems,'' August 1997.
(11) Fossil Energy Research Corporation, Final Report, ``Velocity
Probe Tests in Non-axial Flow Fields,'' November 1998, Prepared for the
U.S. Environmental Protection Agency.
(12) Fossil Energy Research Corporation, ``Additional Swirl Tunnel
Tests: E-DAT and T-DAT Probes,'' February 24, 1999, Technical Memorandum
Prepared for U.S. Environmental Protection Agency, P.O. No. 7W-1193-
NALX.
(13) Massachusetts Institute of Technology, Report WBWT-TR-1317,
``Calibration of Eight Wind Speed Probes Over a Reynolds Number Range of
46,000 to 725,000 Per Foot, Text and Summary Plots,'' Plus appendices,
October 15, 1998, Prepared for The Cadmus Group, Inc.
(14) National Institute of Standards and Technology, Special
Publication 250, ``NIST Calibration Services Users Guide 1991,'' Revised
October 1991, U.S. Department of Commerce, p. 2.
(15) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Four Prandtl Probes, Four
S-Type Probes, Four French Probes, Four Modified Kiel Probes,'' Prepared
for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(16) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed In-strumentation, Five Autoprobes,''
Prepared for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(17) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Eight Spherical Probes,''
Prepared for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(18) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Four DAT Probes, ``
Prepared for the U.S. Environmental Protection Agency under IAG
DW13938432-01-0.
(19) Norfleet, S.K., ``An Evaluation of Wall Effects on Stack Flow
Velocities and Related Overestimation Bias in EPA's Stack Flow Reference
Methods,'' EPRI CEMS User's Group Meeting, New Orleans, Louisiana, May
13-15, 1998.
(20) Page, J.J., E.A. Potts, and R.T. Shigehara, ``3-D Pitot Tube
Calibration Study,'' EPA Contract No. 68D10009, Work Assignment No. I-
121, March 11, 1993.
(21) Shigehara, R.T., W.F. Todd, and W.S. Smith, ``Significance of
Errors in Stack Sampling Measurements,'' Presented at the Annual Meeting
of the Air Pollution Control Association, St. Louis, Missouri, June
1419, 1970.
(22) The Cadmus Group, Inc., May 1999, ``EPA Flow Reference Method
Testing and Analysis: Findings Report,'' EPA/430-R-99-009.
(23) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Texas Utilities, DeCordova Steam
Electric Station, Volume
[[Page 110]]
I: Test Description and Appendix A (Data Distribution Package),'' EPA/
430-R-98-015a.
(24) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Texas Utilities, Lake Hubbard Steam
Electric Station, Volume I: Test Description and Appendix A (Data
Distribution Package),'' EPA/430-R-98-017a.
(25) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Pennsylvania Electric Co., G.P.U.
Genco Homer City Station: Unit 1, Volume I: Test Description and
Appendix A (Data Distribution Package),'' EPA/430-R-98-018a.
(26) The Cadmus Group, Inc., 1997, ``EPA Flow Reference Method
Testing and Analysis: Wind Tunnel Experimental Results,'' EPA/430-R-97-
013.
18.0 Annexes
Annex A, C, and D describe recommended procedures for meeting
certain provisions in sections 8.3, 10.4, and 10.5 of this method. Annex
B describes procedures to be followed when using the protractor wheel
and pointer assembly to measure yaw angles, as provided under section
8.9.1.
18.1 Annex A--Rotational Position Check. The following are
recommended procedures that may be used to satisfy the rotational
position check requirements of section 8.3 of this method and to
determine the angle-measuring device rotational offset
(RADO).
18.1.1 Rotational position check with probe outside stack. Where
physical constraints at the sampling location allow full assembly of the
probe outside the stack and insertion into the test port, the following
procedures should be performed before the start of testing. Two angle-
measuring devices that meet the specifications in section 6.2.1 or 6.2.3
are required for the rotational position check. An angle measuring
device whose position can be independently adjusted (e.g., by means of a
set screw) after being locked into position on the probe sheath shall
not be used for this check unless the independent adjustment is set so
that the device performs exactly like a device without the capability
for independent adjustment. That is, when aligned on the probe such a
device must give the same reading as a device that does not have the
capability of being independently adjusted. With the fully assembled
probe (including probe shaft extensions, if any) secured in a horizontal
position, affix one yaw angle-measuring device to the probe sheath and
lock it into position on the reference scribe line specified in section
6.1.5.1. Position the second angle-measuring device using the procedure
in section 18.1.1.1 or 18.1.1.2.
18.1.1.1 Marking procedure. The procedures in this section should be
performed at each location on the fully assembled probe where the yaw
angle-measuring device will be mounted during the velocity traverse.
Place the second yaw angle-measuring device on the main probe sheath (or
extension) at the position where a yaw angle will be measured during the
velocity traverse. Adjust the position of the second angle-measuring
device until it indicates the same angle (1[deg])
as the reference device, and affix the second device to the probe sheath
(or extension). Record the angles indicated by the two angle-measuring
devices on a form similar to table 2G-2. In this position, the second
angle-measuring device is considered to be properly positioned for yaw
angle measurement. Make a mark, no wider than 1.6 mm (\1/16\ in.), on
the probe sheath (or extension), such that the yaw angle-measuring
device can be re-affixed at this same properly aligned position during
the velocity traverse.
18.1.1.2 Procedure for probe extensions with scribe lines. If,
during a velocity traverse the angle-measuring device will be affixed to
a probe extension having a scribe line as specified in section 6.1.5.2,
the following procedure may be used to align the extension's scribe line
with the reference scribe line instead of marking the extension as
described in section 18.1.1.1. Attach the probe extension to the main
probe. Align and lock the second angle-measuring device on the probe
extension's scribe line. Then, rotate the extension until both measuring
devices indicate the same angle (1[deg]). Lock the
extension at this rotational position. Record the angles indicated by
the two angle-measuring devices on a form similar to table 2G-2. An
angle-measuring device may be aligned at any position on this scribe
line during the velocity traverse, if the scribe line meets the
alignment specification in section 6.1.5.3.
18.1.1.3 Post-test rotational position check. If the fully assembled
probe includes one or more extensions, the following check should be
performed immediately after the completion of a velocity traverse. At
the discretion of the tester, additional checks may be conducted after
completion of testing at any sample port. Without altering the alignment
of any of the components of the probe assembly used in the velocity
traverse, secure the fully assembled probe in a horizontal position.
Affix an angle-measuring device at the reference scribe line specified
in section 6.1.5.1. Use the other angle-measuring device to check the
angle at each location where the device was checked prior to testing.
Record the readings from the two angle-measuring devices.
18.1.2 Rotational position check with probe in stack. This section
applies only to probes that, due to physical constraints, cannot be
inserted into the test port as fully assembled with all necessary
extensions needed to reach the inner-most traverse point(s).
18.1.2.1 Perform the out-of-stack procedure in section 18.1.1 on the
main probe and
[[Page 111]]
any attached extensions that will be initially inserted into the test
port.
18.1.2.2 Use the following procedures to perform additional
rotational position check(s) with the probe in the stack, each time a
probe extension is added. Two angle-measuring devices are required. The
first of these is the device that was used to measure yaw angles at the
preceding traverse point, left in its properly aligned measurement
position. The second angle-measuring device is positioned on the added
probe extension. Use the applicable procedures in section 18.1.1.1 or
18.1.1.2 to align, adjust, lock, and mark (if necessary) the position of
the second angle-measuring device to within 1[deg]
of the first device. Record the readings of the two devices on a form
similar to Table 2G-2.
18.1.2.3 The procedure in section 18.1.2.2 should be performed at
the first port where measurements are taken. The procedure should be
repeated each time a probe extension is re-attached at a subsequent
port, unless the probe extensions are designed to be locked into a
mechanically fixed rotational position (e.g., through use of
interlocking grooves), which can be reproduced from port to port as
specified in section 8.3.5.2.
18.2 Annex B--Angle Measurement Protocol for Protractor Wheel and
Pointer Device. The following procedure shall be used when a protractor
wheel and pointer assembly, such as the one described in section 6.2.2
and illustrated in Figure 2G-5 is used to measure the yaw angle of flow.
With each move to a new traverse point, unlock, re-align, and re-lock
the probe, angle-pointer collar, and protractor wheel to each other. At
each such move, particular attention is required to ensure that the
scribe line on the angle pointer collar is either aligned with the
reference scribe line on the main probe sheath or is at the rotational
offset position established under section 8.3.1. The procedure consists
of the following steps:
18.2.1 Affix a protractor wheel to the entry port for the test probe
in the stack or duct.
18.2.2 Orient the protractor wheel so that the 0[deg] mark
corresponds to the longitudinal axis of the stack or duct. For stacks,
vertical ducts, or ports on the side of horizontal ducts, use a digital
inclinometer meeting the specifications in section 6.2.1 to locate the
0[deg] orientation. For ports on the top or bottom of horizontal ducts,
identify the longitudinal axis at each test port and permanently mark
the duct to indicate the 0[deg] orientation. Once the protractor wheel
is properly aligned, lock it into position on the test port.
18.2.3 Move the pointer assembly along the probe sheath to the
position needed to take measurements at the first traverse point. Align
the scribe line on the pointer collar with the reference scribe line or
at the rotational offset position established under section 8.3.1.
Maintaining this rotational alignment, lock the pointer device onto the
probe sheath. Insert the probe into the entry port to the depth needed
to take measurements at the first traverse point.
18.2.4 Perform the yaw angle determination as specified in sections
8.9.3 and 8.9.4 and record the angle as shown by the pointer on the
protractor wheel. Then, take velocity pressure and temperature
measurements in accordance with the procedure in section 8.9.5. Perform
the alignment check described in section 8.9.6.
18.2.5 After taking velocity pressure measurements at that traverse
point, unlock the probe from the collar and slide the probe through the
collar to the depth needed to reach the next traverse point.
18.2.6 Align the scribe line on the pointer collar with the
reference scribe line on the main probe or at the rotational offset
position established under section 8.3.1. Lock the collar onto the
probe.
18.2.7 Repeat the steps in sections 18.2.4 through 18.2.6 at the
remaining traverse points accessed from the current stack or duct entry
port.
18.2.8 After completing the measurement at the last traverse point
accessed from a port, verify that the orientation of the protractor
wheel on the test port has not changed over the course of the traverse
at that port. For stacks, vertical ducts, or ports on the side of
horizontal ducts, use a digital inclinometer meeting the specifications
in section 6.2.1 to check the rotational position of the 0[deg] mark on
the protractor wheel. For ports on the top or bottom of horizontal
ducts, observe the alignment of the angle wheel 0[deg] mark relative to
the permanent 0[deg] mark on the duct at that test port. If these
observed comparisons exceed 2[deg] of 0[deg], all
angle and pressure measurements taken at that port since the protractor
wheel was last locked into position on the port shall be repeated.
18.2.9 Move to the next stack or duct entry port and repeat the
steps in sections 18.2.1 through 18.2.8.
18.3 Annex C--Guideline for Reference Scribe Line Placement. Use of
the following guideline is recommended to satisfy the requirements of
section 10.4 of this method. The rotational position of the reference
scribe line should be either 90[deg] or 180[deg] from the probe's impact
pressure port. For Type-S probes, place separate scribe lines, on
opposite sides of the probe sheath, if both the A and B sides of the
pitot tube are to be used for yaw angle measurements.
18.4 Annex D--Determination of Reference Scribe Line Rotational
Offset. The following procedures are recommended for determining the
magnitude and sign of a probe's reference scribe line rotational offset,
RSLO. Separate procedures are provided for two types of
angle-measuring devices:
[[Page 112]]
digital inclinometers and protractor wheel and pointer assemblies.
18.4.1 Perform the following procedures on the main probe with all
devices that will be attached to the main probe in the field [such as
thermocouples, resistance temperature detectors (RTDs), or sampling
nozzles] that may affect the flow around the probe head. Probe shaft
extensions that do not affect flow around the probe head need not be
attached during calibration.
18.4.2 The procedures below assume that the wind tunnel duct used
for probe calibration is horizontal and that the flow in the calibration
wind tunnel is axial as determined by the axial flow verification check
described in section 10.1.2. Angle-measuring devices are assumed to
display angles in alternating 0[deg] to 90[deg] and 90[deg] to 0[deg]
intervals. If angle-measuring devices with other readout conventions are
used or if other calibration wind tunnel duct configurations are used,
make the appropriate calculational corrections. For Type-S probes,
calibrate the A-side and B-sides separately, using the appropriate
scribe line (see section 18.3, above), if both the A and B sides of the
pitot tube are to be used for yaw angle determinations.
18.4.2.1 Position the angle-measuring device in accordance with one
of the following procedures.
18.4.2.1.1 If using a digital inclinometer, affix the calibrated
digital inclinometer to the probe. If the digital inclinometer can be
independently adjusted after being locked into position on the probe
sheath (e.g., by means of a set screw), the independent adjustment must
be set so that the device performs exactly like a device without the
capability for independent adjustment. That is, when aligned on the
probe the device must give the same readings as a device that does not
have the capability of being independently adjusted. Either align it
directly on the reference scribe line or on a mark aligned with the
scribe line determined according to the procedures in section 18.1.1.1.
Maintaining this rotational alignment, lock the digital inclinometer
onto the probe sheath.
18.4.2.1.2 If using a protractor wheel and pointer device, orient
the protractor wheel on the test port so that the 0[deg] mark is aligned
with the longitudinal axis of the wind tunnel duct. Maintaining this
alignment, lock the wheel into place on the wind tunnel test port. Align
the scribe line on the pointer collar with the reference scribe line or
with a mark aligned with the reference scribe line, as determined under
section 18.1.1.1. Maintaining this rotational alignment, lock the
pointer device onto the probe sheath.
18.4.2.2 Zero the pressure-measuring device used for yaw nulling.
18.4.2.3 Insert the probe assembly into the wind tunnel through the
entry port, positioning the probe's impact port at the calibration
location. Check the responsiveness of the pressure-measuring device to
probe rotation, taking corrective action if the response is
unacceptable.
18.4.2.4 Ensure that the probe is in a horizontal position using a
carpenter's level.
18.4.2.5 Rotate the probe either clockwise or counterclockwise until
a yaw null [zero [Delta]P for a Type S probe or zero (P2-
P3) for a 3-D probe] is obtained. If using a Type S probe
with an attached thermocouple, the direction of the probe rotation shall
be such that the thermocouple is located downstream of the probe
pressure ports at the yaw-null position.
18.4.2.6 Read and record the value of [theta]null, the
angle indicated by the angle-measuring device at the yaw-null position.
Record the angle reading on a form similar to Table 2G-6. Do not
associate an algebraic sign with this reading.
18.4.2.7 Determine the magnitude and algebraic sign of the reference
scribe line rotational offset, RSLO. The magnitude of
RSLO will be equal to either [theta]null or
(90[deg]-[theta]null), depending on the type of probe being
calibrated and the type of angle-measuring device used. (See Table 2G-7
for a summary.) The algebraic sign of RSLO will either be
positive if the rotational position of the reference scribe line is
clockwise or negative if counterclockwise with respect to the probe's
yaw-null position. Figure 2G-10 illustrates how the magnitude and sign
of RSLO are determined.
18.4.2.8 Perform the steps in sections 18.3.2.3 through 18.3.2.7
twice at each of the two calibration velocities selected for the probe
under section 10.6. Record the values of RSLO in a form
similar to Table 2G-6.
18.4.2.9 The average of all RSLO values is the reference
scribe line rotational offset for the probe.
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Method 2H--Determination of Stack Gas Velocity Taking Into Account
Velocity Decay Near the Stack Wall
1.0 Scope and Application
1.1 This method is applicable in conjunction with Methods 2, 2F, and
2G (40 CFR Part 60, Appendix A) to account for velocity decay near the
wall in circular stacks and ducts.
1.2 This method is not applicable for testing stacks and ducts less
than 3.3 ft (1.0 m) in diameter.
1.3 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method
2.1 A wall effects adjustment factor is determined. It is used to
adjust the average stack gas velocity obtained under Method 2, 2F, or 2G
of this appendix to take into account velocity decay near the stack or
duct wall.
2.2 The method contains two possible procedures: a calculational
approach which derives an adjustment factor from velocity measurements
and a default procedure which assigns a generic adjustment factor based
on the construction of the stack or duct.
2.2.1 The calculational procedure derives a wall effects adjustment
factor from velocity measurements taken using Method 2, 2F, or 2G at 16
(or more) traverse points specified under Method 1 of this appendix and
a total of eight (or more) wall effects traverse points specified under
this method. The calculational procedure based on velocity measurements
is not applicable for horizontal circular ducts where build-up of
particulate matter or other material in the bottom of the duct is
present.
2.2.2 A default wall effects adjustment factor of 0.9900 for brick
and mortar stacks and 0.9950 for all other types of stacks and ducts may
be used without taking wall effects measurements in a stack or duct.
2.3 When the calculational procedure is conducted as part of a
relative accuracy test audit (RATA) or other multiple-run test
procedure, the wall effects adjustment factor derived from a single
traverse (i.e., single RATA run) may be applied to all runs of the same
RATA without repeating the wall effects measurements. Alternatively,
wall effects adjustment factors may be derived for several traverses and
an average wall effects adjustment factor applied to all runs of the
same RATA.
3.0 Definitions.
3.1 Complete wall effects traverse means a traverse in which
measurements are taken at drem (see section 3.3) and at 1-in.
intervals in each of the four Method 1 equal-area sectors closest to the
wall, beginning not farther than 4 in. (10.2 cm) from the wall and
extending either (1) across the entire width of the Method 1 equal-area
sector or (2) for stacks or ducts where this width exceeds 12 in. (30.5
cm) (i.e., stacks or ducts greater than or equal to 15.6 ft [4.8 m] in
diameter), to a distance of not less than 12 in. (30.5 cm) from the
wall. Note: Because this method specifies that measurements must be
taken at whole number multiples of 1 in. from a stack or duct wall, for
clarity numerical quantities in this method are expressed in English
units followed by metric units in parentheses. To enhance readability,
hyphenated terms such as ``1-in. intervals'' or ``1-in. incremented,''
are expressed in English units only.
3.2 dlast Depending on context, dlast means either (1) the distance
from the wall of the last 1-in. incremented wall effects traverse point
or (2) the traverse point located at that distance (see Figure 2H-2).
3.3 drem Depending on context, drem means either (1) the distance
from the wall of the centroid of the area between dlast and the interior
edge of the Method 1 equal-area sector closest to the wall or (2) the
traverse point located at that distance (see Figure 2H-2).
3.4 ``May,'' ``Must,'' ``Shall,'' ``Should,'' and the imperative
form of verbs.
3.4.1 ``May'' is used to indicate that a provision of this method is
optional.
3.4.2 ``Must,'' ``Shall,'' and the imperative form of verbs (such as
``record'' or ``enter'') are used to indicate that a provision of this
method is mandatory.
3.4.3 ``Should'' is used to indicate that a provision of this method
is not mandatory but is highly recommended as good practice.
3.5 Method 1 refers to 40 CFR part 60, appendix A, ``Method 1--
Sample and velocity traverses for stationary sources.''
3.6 Method 1 exterior equal-area sector and Method 1 equal-area
sector closest to the wall mean any one of the four equal-area sectors
that are closest to the wall for a circular stack or duct laid out in
accordance with section 2.3.1 of Method 1 (see Figure 2H-1).
3.7 Method 1 interior equal-area sector means any of the equal-area
sectors other than the Method 1 exterior equal-area sectors (as defined
in section 3.6) for a circular stack or duct laid out in accordance with
section 2.3.1 of Method 1 (see Figure 2H-1).
3.8 Method 1 traverse point and Method 1 equal-area traverse point
mean a traverse point located at the centroid of an equal-area sector of
a circular stack laid out in accordance with section 2.3.1 of Method 1.
3.9 Method 2 refers to 40 CFR part 60, appendix A, ``Method 2--
Determination of stack gas velocity and volumetric flow rate (Type S
pitot tube).''
3.10 Method 2F refers to 40 CFR part 60, appendix A, ``Method 2F--
Determination of stack gas velocity and volumetric flow rate with three-
dimensional probes.''
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3.11 Method 2G refers to 40 CFR part 60, appendix A, ``Method 2G--
Determination of stack gas velocity and volumetric flow rate with two-
dimensional probes.''
3.12 1-in. incremented wall effects traverse point means any of the
wall effects traverse points that are located at 1-in. intervals, i.e.,
traverse points d1 through dlast (see Figure 2H-2).
3.13 Partial wall effects traverse means a traverse in which
measurements are taken at fewer than the number of traverse points
required for a ``complete wall effects traverse'' (as defined in section
3.1), but are taken at a minimum of two traverse points in each Method 1
equal-area sector closest to the wall, as specified in section 8.2.2.
3.14 Relative accuracy test audit (RATA) is a field test procedure
performed in a stack or duct in which a series of concurrent
measurements of the same stack gas stream is taken by a reference method
and an installed monitoring system. A RATA usually consists of series of
9 to 12 sets of such concurrent measurements, each of which is referred
to as a RATA run. In a volumetric flow RATA, each reference method run
consists of a complete traverse of the stack or duct.
3.15 Wall effects-unadjusted average velocity means the average
stack gas velocity, not accounting for velocity decay near the wall, as
determined in accordance with Method 2, 2F, or 2G for a Method 1
traverse consisting of 16 or more points.
3.16 Wall effects-adjusted average velocity means the average stack
gas velocity, taking into account velocity decay near the wall, as
calculated from measurements at 16 or more Method 1 traverse points and
at the additional wall effects traverse points specified in this method.
3.17 Wall effects traverse point means a traverse point located in
accordance with sections 8.2.2 or 8.2.3 of this method.
4.0 Interferences [Reserved]
5.0 Safety
5.1 This method may involve hazardous materials, operations, and
equipment. This method does not purport to address all of the health and
safety considerations associated with its use. It is the responsibility
of the user of this method to establish appropriate health and safety
practices and to determine the applicability of occupational health and
safety regulatory requirements prior to performing this method.
6.0 Equipment and Supplies
6.1 The provisions pertaining to equipment and supplies in the
method that is used to take the traverse point measurements (i.e.,
Method 2, 2F, or 2G) are applicable under this method.
7.0 Reagents and Standards [Reserved]
8.0 Sample Collection and Analysis
8.1 Default Wall Effects Adjustment Factors. A default wall effects
adjustment factor of 0.9900 for brick and mortar stacks and 0.9950 for
all other types of stacks and ducts may be used without conducting the
following procedures.
8.2 Traverse Point Locations. Determine the location of the Method 1
traverse points in accordance with section 8.2.1 and the location of the
traverse points for either a partial wall effects traverse in accordance
with section 8.2.2 or a complete wall effects traverse in accordance
with section 8.2.3.
8.2.1 Method 1 equal-area traverse point locations. Determine the
location of the Method 1 equal-area traverse points for a traverse
consisting of 16 or more points using Table 1-2 (Location of Traverse
Points in Circular Stacks) of Method 1.
8.2.2 Partial wall effects traverse. For a partial wall effects
traverse, measurements must be taken at a minimum of the following two
wall effects traverse point locations in all four Method 1 equal-area
sectors closest to the wall: (1) 1 in. (2.5 cm) from the wall (except as
provided in section 8.2.2.1) and (2) drem, as determined
using Equation 2H-1 or 2H-2 (see section 8.2.2.2).
8.2.2.1 If the probe cannot be positioned at 1 in. (2.5 cm) from the
wall (e.g., because of insufficient room to withdraw the probe shaft) or
if velocity pressure cannot be detected at 1 in. (2.5 cm) from the wall
(for any reason other than build-up of particulate matter in the bottom
of a duct), take measurements at the 1-in. incremented wall effects
traverse point closest to the wall where the probe can be positioned and
velocity pressure can be detected.
8.2.2.2 Calculate the distance of drem from the wall to
within \1/4\ in. (6.4 mm) using Equation 2H-1 or
Equation 2H-2 (for a 16-point traverse).
[GRAPHIC] [TIFF OMITTED] TR14MY99.074
Where:
r=the stack or duct radius determined from direct measurement of the
stack or duct diameter in accordance with section 8.6 of Method 2F or
Method 2G, in. (cm);
p=the number of Method 1 equal-area traverse points on a diameter, p
= 8 (e.g., for a 16-point traverse, p=8); dlast and drem are
defined in sections 3.2 and 3.3 respectively, in. (cm).
For a 16-point Method 1 traverse, Equation 2H-1 becomes:
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8.2.2.3 Measurements may be taken at any number of additional wall
effects traverse points, with the following provisions.
(a) dlast must not be closer to the center of the stack or duct than
the distance of the interior edge (boundary), db, of the Method 1 equal-
area sector closest to the wall (see Figure 2H-2 or 2H-3). That is,
Where:
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Table 2H-1 shows db as a function of the stack or duct radius, r, for
traverses ranging from 16 to 48 points (i.e., for values of p ranging
from 8 to 24).
(b) Each point must be located at a distance that is a whole number
(e.g., 1, 2, 3) multiple of 1 in. (2.5 cm).
(c) Points do not have to be located at consecutive 1-in. intervals.
That is, one or more 1-in. incremented points may be skipped. For
example, it would be acceptable for points to be located at 1 in. (2.5
cm), 3 in. (7.6 cm), 5 in. (12.7 cm), dlast, and drem; or at 1 in. (2.5
cm), 2 in. (5.1 cm), 4 in. (10.2 cm), 7 in. (17.8 cm), dlast, and drem.
Follow the instructions in section 8.7.1.2 of this method for recording
results for wall effects traverse points that are skipped. It should be
noted that the full extent of velocity decay may not be accounted for if
measurements are not taken at all 1-in. incremented points close to the
wall.
8.2.3 Complete wall effects traverse. For a complete wall effects
traverse, measurements must be taken at the following points in all four
Method 1 equal-area sectors closest to the wall.
(a) The 1-in. incremented wall effects traverse point closest to the
wall where the probe can be positioned and velocity can be detected, but
no farther than 4 in. (10.2 cm) from the wall.
(b) Every subsequent 1-in. incremented wall effects traverse point
out to the interior edge of the Method 1 equal-area sector or to 12 in.
(30.5 cm) from the wall, whichever comes first. Note: In stacks or ducts
with diameters greater than 15.6 ft (4.8 m) the interior edge of the
Method 1 equal-area sector is farther from the wall than 12 in. (30.5
cm).
(c) drem, as determined using Equation 2H-1 or 2H-2 (as
applicable). Note: For a complete traverse of a stack or duct with a
diameter less than 16.5 ft (5.0 m), the distance between drem
and dlast is less than or equal to \1/2\ in. (12.7 mm). As
discussed in section 8.2.4.2, when the distance between drem
and dlast is less than or equal to \1/2\ in. (12.7 mm), the
velocity measured at dlast may be used for drem.
Thus, it is not necessary to calculate the distance of drem
or to take measurements at drem when conducting a complete
traverse of a stack or duct with a diameter less than 16.5 ft (5.0 m).
8.2.4 Special considerations. The following special considerations
apply when the distance between traverse points is less than or equal to
\1/2\ in. (12.7 mm).
8.2.4.1 A wall effects traverse point and the Method 1 traverse
point. If the distance between a wall effects traverse point and the
Method 1 traverse point is less than or equal to \1/2\ in. (12.7 mm),
taking measurements at both points is allowed but not required or
recommended; if measurements are taken at only one point, take the
measurements at the point that is farther from the wall and use the
velocity obtained at that point as the value for both points (see
sections 8.2.3 and 9.2 for related requirements).
8.2.4.2 drem and dlast. If the distance
between drem and dlast is less than or equal to
\1/2\ in. (12.7 mm), taking measurements at drem is allowed
but not required or recommended; if measurements are not taken at
drem, the measured velocity value at dlast must be
used as the value for both dlast and drem.
8.3 Traverse Point Sampling Order and Probe Selection. Determine the
sampling order of the Method 1 and wall effects traverse points and
select the appropriate probe for the measurements, taking into account
the following considerations.
8.3.1 Traverse points on any radius may be sampled in either
direction (i.e., from the wall toward the center of the stack or duct,
or vice versa).
8.3.2 To reduce the likelihood of velocity variations during the
time of the traverse and the attendant potential impact on the wall
effects-adjusted and unadjusted average velocities, the following
provisions of this method shall be met.
8.3.2.1 Each complete set of Method 1 and wall effects traverse
points accessed from the same port shall be sampled without
interruption. Unless traverses are performed simultaneously in all ports
using separate probes at each port, this provision disallows first
sampling all Method 1 points at all ports and then sampling all the wall
effects points.
8.3.2.2 The entire integrated Method 1 and wall effects traverse
across all test ports shall be as short as practicable, consistent with
the measurement system response time
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(see section 8.4.1.1) and sampling (see section 8.4.1.2) provisions of
this method.
8.3.3 It is recommended but not required that in each Method 1
equal-area sector closest to the wall, the Method 1 equal-area traverse
point should be sampled in sequence between the adjacent wall effects
traverse points. For example, for the traverse point configuration shown
in Figure 2H-2, it is recommended that the Method 1 equal-area traverse
point be sampled between dlast and drem. In this
example, if the traverse is conducted from the wall toward the center of
the stack or duct, it is recommended that measurements be taken at
points in the following order: d1, d2,
dlast, the Method 1 traverse point, drem, and then
at the traverse points in the three Method 1 interior equal-area
sectors.
8.3.4 The same type of probe must be used to take measurements at
all Method 1 and wall effects traverse points. However, different copies
of the same type of probe may be used at different ports (e.g., Type S
probe 1 at port A, Type S probe 2 at port B) or at different traverse
points accessed from a particular port (e.g., Type S probe 1 for Method
1 interior traverse points accessed from port A, Type S probe 2 for wall
effects traverse points and the Method 1 exterior traverse point
accessed from port A). The identification number of the probe used to
obtain measurements at each traverse point must be recorded.
8.4 Measurements at Method 1 and Wall Effects Traverse Points.
Conduct measurements at Method 1 and wall effects traverse points in
accordance with Method 2, 2F, or 2G and in accordance with the
provisions of the following subsections (some of which are included in
Methods 2F and 2G but not in Method 2), which are particularly important
for wall effects testing.
8.4.1 Probe residence time at wall effects traverse points. Due to
the steep temperature and pressure gradients that can occur close to the
wall, it is very important for the probe residence time (i.e., the total
time spent at a traverse point) to be long enough to ensure collection
of representative temperature and pressure measurements. The provisions
of Methods 2F and 2G in the following subsections shall be observed.
8.4.1.1 System response time. Determine the response time of each
probe measurement system by inserting and positioning the ``cold'' probe
(at ambient temperature and pressure) at any Method 1 traverse point.
Read and record the probe differential pressure, temperature, and
elapsed time at 15-second intervals until stable readings for both
pressure and temperature are achieved. The response time is the longer
of these two elapsed times. Record the response time.
8.4.1.2 Sampling. At the start of testing in each port (i.e., after
a probe has been inserted into the stack gas stream), allow at least the
response time to elapse before beginning to take measurements at the
first traverse point accessed from that port. Provided that the probe is
not removed from the stack gas stream, measurements may be taken at
subsequent traverse points accessed from the same test port without
waiting again for the response time to elapse.
8.4.2 Temperature measurement for wall effects traverse points.
Either (1) take temperature measurements at each wall effects traverse
point in accordance with the applicable provisions of Method 2, 2F, or
2G; or (2) use the temperature measurement at the Method 1 traverse
point closest to the wall as the temperature measurement for all the
wall effects traverse points in the corresponding equal-area sector.
8.4.3 Non-detectable velocity pressure at wall effects traverse
points. If the probe cannot be positioned at a wall effects traverse
point or if no velocity pressure can be detected at a wall effects
point, measurements shall be taken at the first subsequent wall effects
traverse point farther from the wall where velocity can be detected.
Follow the instructions in section 8.7.1.2 of this method for recording
results for wall effects traverse points where velocity pressure cannot
be detected. It should be noted that the full extent of velocity decay
may not be accounted for if measurements are not taken at the 1-in.
incremented wall effects traverse points closest to the wall.
8.5 Data Recording. For each wall effects and Method 1 traverse
point where measurements are taken, record all pressure, temperature,
and attendant measurements prescribed in section 3 of Method 2 or
section 8.0 of Method 2F or 2G, as applicable.
8.6 Point Velocity Calculation. For each wall effects and Method 1
traverse point, calculate the point velocity value (vi) in accordance
with sections 12.1 and 12.2 of Method 2F for tests using Method 2F and
in accordance with sections 12.1 and 12.2 of Method 2G for tests using
Method 2 and Method 2G. (Note that the term (vi) in this method
corresponds to the term (va(i)) in Methods 2F and 2G.) When the
equations in the indicated sections of Method 2G are used in deriving
point velocity values for Method 2 tests, set the value of the yaw
angles appearing in the equations to 0[deg].
8.7 Tabulating Calculated Point Velocity Values for Wall Effects
Traverse Points. Enter the following values in a hardcopy or electronic
form similar to Form 2H-1 (for 16-point Method 1 traverses) or Form 2H-2
(for Method 1 traverses consisting of more than 16 points). A separate
form must be completed for each of the four Method 1 equal-area sectors
that are closest to the wall.
(a) Port ID (e.g., A, B, C, or D)
(b) Probe type
(c) Probe ID
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(d) Stack or duct diameter in ft (m) (determined in accordance with
section 8.6 of Method 2F or Method 2G)
(e) Stack or duct radius in in. (cm)
(f) Distance from the wall of wall effects traverse points at 1-in.
intervals, in ascending order starting with 1 in. (2.5 cm) (column A of
Form 2H-1 or 2H-2)
(g) Point velocity values (vd) for 1-in. incremented traverse points
(see section 8.7.1), including dlast (see section 8.7.2)
(h) Point velocity value (vdrem) at drem (see section 8.7.3).
8.7.1 Point velocity values at wall effects traverse points other
than dlast. For every 1-in. incremented wall effects traverse point
other than dlast, enter in column B of Form 2H-1 or 2H-2 either the
velocity measured at the point (see section 8.7.1.1) or the velocity
measured at the first subsequent traverse point farther from the wall
(see section 8.7.1.2). A velocity value must be entered in column B of
Form 2H-1 or 2H-2 for every 1-in. incremented traverse point from d1
(representing the wall effects traverse point 1 in. [2.5 cm] from the
wall) to dlast.
8.7.1.1 For wall effects traverse points where the probe can be
positioned and velocity pressure can be detected, enter the value
obtained in accordance with section 8.6.
8.7.1.2 For wall effects traverse points that were skipped [see
section 8.2.2.3(c)] and for points where the probe cannot be positioned
or where no velocity pressure can be detected, enter the value obtained
at the first subsequent traverse point farther from the wall where
velocity pressure was detected and measured and follow the entered value
with a ``flag,'' such as the notation ``NM,'' to indicate that ``no
measurements'' were actually taken at this point.
8.7.2 Point velocity value at dlast. For dlast, enter in column B of
Form 2H-1 or 2H-2 the measured value obtained in accordance with section
8.6.
8.7.3 Point velocity value (vdrem) at drem. Enter the point velocity
value obtained at drem in column G of row 4a in Form 2H-1 or 2H-2. If
the distance between drem and dlast is less than or equal to \1/2\ in.
(12.7 mm), the measured velocity value at dlast may be used as the value
at drem (see section 8.2.4.2).
9.0 Quality Control.
9.1 Particulate Matter Build-up in Horizontal Ducts. Wall effects
testing of horizontal circular ducts should be conducted only if build-
up of particulate matter or other material in the bottom of the duct is
not present.
9.2 Verifying Traverse Point Distances. In taking measurements at
wall effects traverse points, it is very important for the probe impact
pressure port to be positioned as close as practicable to the traverse
point locations in the gas stream. For this reason, before beginning
wall effects testing, it is important to calculate and record the
traverse point positions that will be marked on each probe for each
port, taking into account the distance that each port nipple (or probe
mounting flange for automated probes) extends out of the stack and any
extension of the port nipple (or mounting flange) into the gas stream.
To ensure that traverse point positions are properly identified, the
following procedures should be performed on each probe used.
9.2.1 Manual probes. Mark the probe insertion distance of the wall
effects and Method 1 traverse points on the probe sheath so that when a
mark is aligned with the outside face of the stack port, the probe
impact port is located at the calculated distance of the traverse point
from the stack inside wall. The use of different colored marks is
recommended for designating the wall effects and Method 1 traverse
points. Before the first use of each probe, check to ensure that the
distance of each mark from the center of the probe impact pressure port
agrees with the previously calculated traverse point positions to within
\1/4\ in. (6.4 mm).
9.2.2 Automated probe systems. For automated probe systems that
mechanically position the probe head at prescribed traverse point
positions, activate the system with the probe assemblies removed from
the test ports and sequentially extend the probes to the programmed
location of each wall effects traverse point and the Method 1 traverse
points. Measure the distance between the center of the probe impact
pressure port and the inside of the probe assembly mounting flange for
each traverse point. The measured distances must agree with the
previously calculated traverse point positions to within \1/4\ in. (6.4 mm).
9.3 Probe Installation. Properly sealing the port area is
particularly important in taking measurements at wall effects traverse
points. For testing involving manual probes, the area between the probe
sheath and the port should be sealed with a tightly fitting flexible
seal made of an appropriate material such as heavy cloth so that leakage
is minimized. For automated probe systems, the probe assembly mounting
flange area should be checked to verify that there is no leakage.
9.4 Velocity Stability. This method should be performed only when
the average gas velocity in the stack or duct is relatively constant
over the duration of the test. If the average gas velocity changes
significantly during the course of a wall effects test, the test results
should be discarded.
10.0 Calibration
10.1 The calibration coefficient(s) or curves obtained under Method
2, 2F, or 2G and used to perform the Method 1 traverse are applicable
under this method.
[[Page 133]]
11.0 Analytical Procedure
11.1 Sample collection and analysis are concurrent for this method
(see section 8).
12.0 Data Analysis and Calculations
12.1 The following calculations shall be performed to obtain a wall
effects adjustment factor (WAF) from (1) the wall effects-unadjusted
average velocity (T4avg), (2) the replacement velocity (vej) for each of
the four Method 1 sectors closest to the wall, and (3) the average stack
gas velocity that accounts for velocity decay near the wall (vavg).
12.2 Nomenclature. The following terms are listed in the order in
which they appear in Equations 2H-5 through 2H-21.
vavg=the average stack gas velocity, unadjusted for wall effects, actual
ft/sec (m/sec);
vii=stack gas point velocity value at Method 1 interior equal-area
sectors, actual ft/sec (m/sec);
vej=stack gas point velocity value, unadjusted for wall effects, at
Method 1 exterior equal-area sectors, actual ft/sec (m/sec);
i=index of Method 1 interior equal-area traverse points;
j=index of Method 1 exterior equal-area traverse points;
n=total number of traverse points in the Method 1 traverse;
vdecd=the wall effects decay velocity for a sub-sector located between
the traverse points at distances d-1 (in metric units, d-2.5) and d from
the wall, actual ft/sec (m/sec);
vd=the measured stack gas velocity at distance d from the wall, actual
ft/sec (m/sec); Note: v0=0;
d=the distance of a 1-in. incremented wall effects traverse point from
the wall, for traverse points d1 through dlast, in. (cm);
Ad=the cross-sectional area of a sub-sector located between the traverse
points at distances d-1 (in metric units, d-2.5) and d from the wall,
in.\2\ (cm\2\) ( e.g., sub-sector A2 shown in Figures 2H-3
and 2H-4);
r=the stack or duct radius, in. (cm);
Qd=the stack gas volumetric flow rate for a sub-sector located between
the traverse points at distances d-1 (in metric units, d-2.5) and d from
the wall, actual ft-in.\2\/sec (m-cm\2\/sec);
Qd1[rarr]dlast=the total stack gas volumetric flow rate for all sub-
sectors located between the wall and dlast, actual ft-in.\2\/sec (m-
cm\2\/sec);
dlast=the distance from the wall of the last 1-in. incremented wall
effects traverse point, in. (cm);
Adrem=the cross-sectional area of the sub-sector located between dlast
and the interior edge of the Method 1 equal-area sector closest to the
wall, in.\2\ (cm\2\) (see Figure 2H-4);
p=the number of Method 1 traverse points per diameter, p=8
(e.g., for a 16-point traverse, p=8);
drem=the distance from the wall of the centroid of the area between
dlast and the interior edge of the Method 1 equal-area sector closest to
the wall, in. (cm);
Qdrem=the total stack gas volumetric flow rate for the sub-sector
located between dlast and the interior edge of the Method 1 equal-area
sector closest to the wall, actual ft-in.\2\/sec (m-cm\2\/sec);
vdrem=the measured stack gas velocity at distance drem from the wall,
actual ft/sec (m/sec);
QT=the total stack gas volumetric flow rate for the Method 1 equal-area
sector closest to the wall, actual ft-in.\2\/sec (m-cm\2\/sec);
vej=the replacement stack gas velocity for the Method 1 equal-area
sector closest to the wall, i.e., the stack gas point velocity value,
adjusted for wall effects, for the j\th\ Method 1 equal-area sector
closest to the wall, actual ft/sec (m/sec);
vavg=the average stack gas velocity that accounts for velocity decay
near the wall, actual ft/sec (m/sec);
WAF=the wall effects adjustment factor derived from vavg and vavg for a
single traverse, dimensionless;
vfinal=the final wall effects-adjusted average stack gas velocity that
replaces the unadjusted average stack gas velocity obtained using Method
2, 2F, or 2G for a field test consisting of a single traverse, actual
ft/sec (m/sec);
WAF=the wall effects adjustment factor that is applied to the average
velocity, unadjusted for wall effects, in order to obtain the final wall
effects-adjusted stack gas velocity, vfinal or, vfinal(k),
dimensionless;
vfinal(k)=the final wall effects-adjusted average stack gas velocity
that replaces the unadjusted average stack gas velocity obtained using
Method 2, 2F, or 2G on run k of a RATA or other multiple-run field test
procedure, actual ft/sec (m/sec);
vavg(k)=the average stack gas velocity, obtained on run k of a RATA or
other multiple-run procedure, unadjusted for velocity decay near the
wall, actual ft/sec (m/sec);
k=index of runs in a RATA or other multiple-run procedure.
12.3 Calculate the average stack gas velocity that does not account
for velocity decay near the wall (vavg) using Equation 2H-5.
[GRAPHIC] [TIFF OMITTED] TR14MY99.077
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(Note that vavg in Equation 2H-5 is the same as v(a)avg in Equations 2F-
9 and 2G-8 in Methods 2F and 2G, respectively.)
For a 16-point traverse, Equation 2H-5 may be written as follows:
[GRAPHIC] [TIFF OMITTED] TR14MY99.078
12.4 Calculate the replacement velocity, vej, for each of the four
Method 1 equal-area sectors closest to the wall using the procedures
described in sections 12.4.1 through 12.4.8. Forms 2H-1 and 2H-2 provide
sample tables that may be used in either hardcopy or spreadsheet format
to perform the calculations described in sections 12.4.1 through 12.4.8.
Forms 2H-3 and 2H-4 provide examples of Form 2H-1 filled in for partial
and complete wall effects traverses.
12.4.1 Calculate the average velocity (designated the ``decay
velocity,'' vdecd) for each sub-sector located between the
wall and dlast (see Figure 2H-3) using Equation 2H-7.
[GRAPHIC] [TIFF OMITTED] TR14MY99.079
For each line in column A of Form 2H-1 or 2H-2 that contains a value of
d, enter the corresponding calculated value of vdecd in
column C.
12.4.2 Calculate the cross-sectional area between the wall and the
first 1-in. incremented wall effects traverse point and between
successive 1-in. incremented wall effects traverse points, from the wall
to dlast (see Figure 2H-3), using Equation 2H-8.
[GRAPHIC] [TIFF OMITTED] TR14MY99.080
For each line in column A of Form 2H-1 or 2H-2 that contains a value of
d, enter the value of the expression \1/4\ [pi](r-d+1)\2\ in column D,
the value of the expression \1/4\ [pi](r-d)\2\ in column E, and the
value of Ad in column F. Note that Equation 2H-8 is designed
for use only with English units (in.). If metric units (cm) are used,
the first term, \1/4\ [pi](r-d+1)\2\, must be changed to \1/4\ [pi](r-
d+2.5)\2\. This change must also be made in column D of Form 2H-1 or 2H-
2.
12.4.3 Calculate the volumetric flow through each cross-sectional
area derived in section 12.4.2 by multiplying the values of vdecd,
derived according to section 12.4.1, by the cross-sectional areas
derived in section 12.4.2 using Equation 2H-9.
[GRAPHIC] [TIFF OMITTED] TR14MY99.081
For each line in column A of Form 2H-1 or 2H-2 that contains a value of
d, enter the corresponding calculated value of Qd in column G.
12.4.4 Calculate the total volumetric flow through all sub-sectors
located between the wall and dlast, using Equation 2H-10.
[GRAPHIC] [TIFF OMITTED] TN09JY99.003
Enter the calculated value of Qd1[rarr]cdlast in line 3 of column G of
Form 2H-1 or 2H-2.
12.4.5 Calculate the cross-sectional area of the sub-sector located
between dlast and the interior edge of the Method 1 equal-area sector
(e.g., sub-sector Adrem shown in Figures 2H-3 and 2H-4) using Equation
2H-11.
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For a 16-point traverse (eight points per diameter), Equation 2H-11 may
be written as follows:
[GRAPHIC] [TIFF OMITTED] TR14MY99.084
Enter the calculated value of Adrem in line 4b of column G of
Form 2H-1 or 2H-2.
12.4.6 Calculate the volumetric flow for the sub-sector located
between dlast and the interior edge of the Method 1 equal-
area sector, using Equation 2H-13.
[GRAPHIC] [TIFF OMITTED] TR14MY99.085
In Equation 2H-13, vdrem is either (1) the measured velocity
value at drem or (2) the measured velocity at
dlast, if the distance between drem and
dlast is less than or equal to \1/2\ in. (12.7 mm) and no
velocity measurement is taken at drem (see section 8.2.4.2).
Enter the calculated value of Qdrem in line 4c of column G of
Form 2H-1 or 2H-2.
12.4.7 Calculate the total volumetric flow for the Method 1 equal-
area sector closest to the wall, using Equation 2H-14.
[GRAPHIC] [TIFF OMITTED] TR14MY99.086
Enter the calculated value of QT in line 5a of column G of
Form 2H-1 or 2H-2.
12.4.8 Calculate the wall effects-adjusted replacement velocity
value for the Method 1 equal-area sector closest to the wall, using
Equation 2H-15.
[GRAPHIC] [TIFF OMITTED] TR14MY99.087
For a 16-point traverse (eight points per diameter), Equation 2H-15 may
be written as follows:
[GRAPHIC] [TIFF OMITTED] TR14MY99.088
Enter the calculated value of vej in line 5B of column G of Form 2H-1 or
2H-2.
12.5 Calculate the wall effects-adjusted average velocity, vavg, by
replacing the four values of vej shown in Equation 2H-5 with
the four wall effects-adjusted replacement velocity
values,vej, calculated according to section 12.4.8, using
Equation 2H-17.
[GRAPHIC] [TIFF OMITTED] TR14MY99.089
For a 16-point traverse, Equation 2H-17 may be written as follows:
[GRAPHIC] [TIFF OMITTED] TR14MY99.090
12.6 Calculate the wall effects adjustment factor, WAF, using
Equation 2H-19.
[GRAPHIC] [TIFF OMITTED] TR14MY99.091
12.6.1 Partial wall effects traverse. If a partial wall effects
traverse (see section 8.2.2) is conducted, the value obtained from
Equation 2H-19 is acceptable and may be reported as the wall effects
adjustment factor provided that the value is greater than or equal to
0.9800. If the value is less than 0.9800, it shall not be used and a
wall effects adjustment factor of 0.9800 may be used instead.
12.6.2 Complete wall effects traverse. If a complete wall effects
traverse (see section 8.2.3) is conducted, the value obtained from
Equation 2H-19 is acceptable and may be reported as the wall effects
adjustment factor provided that the value is greater than or equal to
0.9700. If the value is less than 0.9700, it shall not be used and a
wall effects adjustment factor of 0.9700 may be used instead. If the
wall effects adjustment factor for a particular stack or duct is less
than 0.9700, the tester may (1) repeat the wall effects test, taking
measurements at more Method 1 traverse points and (2) recalculate the
wall effects adjustment factor from these measurements, in an attempt to
obtain a wall effects adjustment factor that meets the 0.9700
specification and completely characterizes the wall effects.
12.7 Applying a Wall Effects Adjustment Factor. A default wall
effects adjustment factor, as specified in section 8.1, or a calculated
wall effects adjustment factor meeting the requirements of section
12.6.1 or 12.6.2
[[Page 136]]
may be used to adjust the average stack gas velocity obtained using
Methods 2, 2F, or 2G to take into account velocity decay near the wall
of circular stacks or ducts. Default wall effects adjustment factors
specified in section 8.1 and calculated wall effects adjustment factors
that meet the requirements of section 12.6.1 and 12.6.2 are summarized
in Table 2H-2.
12.7.1 Single-run tests. Calculate the final wall effects-adjusted
average stack gas velocity for field tests consisting of a single
traverse using Equation 2H-20.
[GRAPHIC] [TIFF OMITTED] TR14MY99.092
The wall effects adjustment factor, WAF, shown in Equation 2H-20, may be
(1) a default wall effects adjustment factor, as specified in section
8.1, or (2) a calculated adjustment factor that meets the specifications
in sections 12.6.1 or 12.6.2. If a calculated adjustment factor is used
in Equation 2H-20, the factor must have been obtained during the same
traverse in which vavg was obtained.
12.7.2 RATA or other multiple run test procedure. Calculate the
final wall effects-adjusted average stack gas velocity for any run k of
a RATA or other multiple-run procedure using Equation 2H-21.
[GRAPHIC] [TIFF OMITTED] TR14MY99.093
The wall effects adjustment factor, WAF, shown in Equation 2H-21 may be
(1) a default wall effects adjustment factor, as specified in section
8.1; (2) a calculated adjustment factor (meeting the specifications in
sections 12.6.1 or 12.6.2) obtained from any single run of the RATA that
includes run k; or (3) the arithmetic average of more than one WAF (each
meeting the specifications in sections 12.6.1 or 12.6.2) obtained
through wall effects testing conducted during several runs of the RATA
that includes run k. If wall effects adjustment factors (meeting the
specifications in sections 12.6.1 or 12.6.2) are determined for more
than one RATA run, the arithmetic average of all of the resulting
calculated wall effects adjustment factors must be used as the value of
WAF and applied to all runs of that RATA. If a calculated, not a
default, wall effects adjustment factor is used in Equation 2H-21, the
average velocity unadjusted for wall effects, vavg(k) must be
obtained from runs in which the number of Method 1 traverse points
sampled does not exceed the number of Method 1 traverse points in the
runs used to derive the wall effects adjustment factor, WAF, shown in
Equation 2H-21.
12.8 Calculating Volumetric Flow Using Final Wall Effects-Adjusted
Average Velocity Value. To obtain a stack gas flow rate that accounts
for velocity decay near the wall of circular stacks or ducts, replace
vs in Equation 2-10 in Method 2, or va(avg) in
Equations 2F-10 and 2F-11 in Method 2F, or va(avg) in
Equations 2G-9 and 2G-10 in Method 2G with one of the following.
12.8.1 For single-run test procedures, use the final wall effects-
adjusted average stack gas velocity, vfinal, calculated according to
Equation 2H-20.
12.8.2 For RATA and other multiple run test procedures, use the
final wall effects-adjusted average stack gas velocity, vfinal(k),
calculated according to Equation 2H-21.
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 Reporting
16.1 Field Test Reports. Field test reports shall be submitted to
the Agency according to the applicable regulatory requirements. When
Method 2H is performed in conjunction with Method 2, 2F, or 2G to derive
a wall effects adjustment factor, a single consolidated Method 2H/2F (or
2H/2G) field test report should be prepared. At a minimum, the
consolidated field test report should contain (1) all of the general
information, and data for Method 1 points, specified in section 16.0 of
Method 2F (when Method 2H is used in conjunction with Method 2F) or
section 16.0 of Method 2G (when Method 2H is used in conjunction with
Method 2 or 2G) and (2) the additional general information, and data for
Method 1 points and wall effects points, specified in this section (some
of which are included in section 16.0 of Methods 2F and 2G and are
repeated in this section to ensure complete reporting for wall effects
testing).
16.1.1 Description of the source and site. The field test report
should include the descriptive information specified in section 16.1.1
of Method 2F (when using Method 2F) or 2G (when using either Method 2 or
2G). It should also include a description of the stack or duct's
construction material along with the diagram showing the dimensions of
the stack or duct at the test port elevation prescribed in Methods 2F
and 2G. The diagram should indicate the location of all wall effects
traverse points where measurements were taken as well as the Method 1
traverse points. The diagram should provide a unique identification
number for each wall effects and Method 1 traverse point, its distance
from the wall, and its location relative to the probe entry ports.
16.1.2 Field test forms. The field test report should include a copy
of Form 2H-1, 2H-2, or an equivalent for each Method 1 exterior equal-
area sector.
16.1.3 Field test data. The field test report should include the
following data for the Method 1 and wall effects traverse.
16.1.3.1 Data for each traverse point. The field test report should
include the values
[[Page 137]]
specified in section 16.1.3.2 of Method 2F (when using Method 2F) or 2G
(when using either Method 2 or 2G) for each Method 1 and wall effects
traverse point. The provisions of section 8.4.2 of Method 2H apply to
the temperature measurements reported for wall effects traverse points.
For each wall effects and Method 1 traverse point, the following values
should also be included in the field test report.
(a) Traverse point identification number for each Method 1 and wall
effects traverse point.
(b) Probe type.
(c) Probe identification number.
(d) Probe velocity calibration coefficient (i.e., Cp when Method 2
or 2G is used; F2 when Method 2F is used).
For each Method 1 traverse point in an exterior equal-area sector,
the following additional value should be included.
(e) Calculated replacement velocity, vej, accounting for wall
effects.
16.1.3.2 Data for each run. The values specified in section 16.1.3.3
of Method 2F (when using Method 2F) or 2G (when using either Method 2 or
2G) should be included in the field test report once for each run. The
provisions of section 12.8 of Method 2H apply for calculating the
reported gas volumetric flow rate. In addition, the following Method 2H
run values should also be included in the field test report.
(a) Average velocity for run, accounting for wall effects, vavg.
(b) Wall effects adjustment factor derived from a test run, WAF.
16.1.3.3 Data for a complete set of runs. The values specified in
section 16.1.3.4 of Method 2F (when using Method 2F) or 2G (when using
either Method 2 or 2G) should be included in the field test report once
for each complete set of runs. In addition, the field test report should
include the wall effects adjustment factor, WAF, that is applied in
accordance with section 12.7.1 or 12.7.2 to obtain the final wall
effects-adjusted average stack gas velocity vfinal or vfinal(k).
16.1.4 Quality assurance and control. Quality assurance and control
procedures, specifically tailored to wall effects testing, should be
described.
16.2 Reporting a Default Wall Effects Adjustment Factor. When a
default wall effects adjustment factor is used in accordance with
section 8.1 of this method, its value and a description of the stack or
duct's construction material should be reported in lieu of submitting a
test report.
17.0 References.
(1) 40 CFR Part 60, Appendix A, Method 1--Sample and velocity
traverses for stationary sources.
(2) 40 CFR Part 60, Appendix A, Method 2--Determination of stack gas
velocity and volumetric flow rate (Type S pitot tube).
(3) 40 CFR Part 60, Appendix A, Method 2F--Determination of stack
gas velocity and volumetric flow rate with three-dimensional probes.
(4) 40 CFR Part 60, Appendix A, Method 2G--Determination of stack
gas velocity and volumetric flow rate with two-dimensional probes.
(5) 40 CFR Part 60, Appendix A, Method 3--Gas analysis for carbon
dioxide, oxygen, excess air, and dry molecular weight.
(6) 40 CFR Part 60, Appendix A, Method 3A--Determination of oxygen
and carbon dioxide concentrations in emissions from stationary sources
(instrumental analyzer procedure).
(7) 40 CFR Part 60, Appendix A, Method 4--Determination of moisture
content in stack gases.
(8) Emission Measurement Center (EMC) Approved Alternative Method
(ALT-011) ``Alternative Method 2 Thermocouple Calibration Procedure.''
(9) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Texas Utilities, DeCordova Steam
Electric Station, Volume I: Test Description and Appendix A (Data
Distribution Package),'' EPA/430-R-98-015a.
(10) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Texas Utilities, Lake Hubbard Steam
Electric Station, Volume I: Test Description and Appendix A (Data
Distribution Package),'' EPA/430-R-98-017a.
(11) The Cadmus Group, Inc., 1998, ``EPA Flow Reference Method
Testing and Analysis: Data Report, Pennsylvania Electric Co., G.P.U.
Genco Homer City Station: Unit 1, Volume I: Test Description and
Appendix A (Data Distribution Package),'' EPA/430-R-98-018a.
(12) The Cadmus Group, Inc., May 1999, ``EPA Flow Reference Method
Testing and Analysis: Findings Report,'' EPA/430-R-99-009.
(13) The Cadmus Group, Inc., 1997, ``EPA Flow Reference Method
Testing and Analysis: Wind Tunnel Experimental Results,'' EPA/430-R-97-
013.
(14) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Four Prandtl Probes, Four
S-Type Probes, Four French Probes, Four Modified Kiel Probes,'' Prepared
for the U.S. Environmental Protection Agency under IAG No. DW13938432-
01-0.
(15) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Five Autoprobes,''
Prepared for the U.S. Environmental Protection Agency under IAG No.
DW13938432-01-0.
[[Page 138]]
(16) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Eight Spherical Probes,''
Prepared for the U.S. Environmental Protection Agency under IAG No.
DW13938432-01-0.
(17) National Institute of Standards and Technology, 1998, ``Report
of Special Test of Air Speed Instrumentation, Four DAT Probes,''
Prepared for the U.S. Environmental Protection Agency under IAG No.
DW13938432-01-0.
(18) Massachusetts Institute of Technology (MIT), 1998,
``Calibration of Eight Wind Speed Probes Over a Reynolds Number Range of
46,000 to 725,000 per Foot, Text and Summary Plots,'' Plus Appendices,
WBWT-TR-1317, Prepared for The Cadmus Group, Inc., under EPA Contract
68-W6-0050, Work Assignment 0007AA-3.
(19) Fossil Energy Research Corporation, Final Report, ``Velocity
Probe Tests in Non-axial Flow Fields,'' November 1998, Prepared for the
U.S. Environmental Protection Agency.
(20) Fossil Energy Research Corporation, ``Additional Swirl Tunnel
Tests: E-DAT and T-DAT Probes,'' February 24, 1999, Technical Memorandum
Prepared for U.S. Environmental Protection Agency, P.O. No. 7W-1193-
NALX.
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Method 3--Gas Analysis for the Determination of Dry Molecular Weight
Note: This method does not include all of the specifications (e.g.,
equipment and supplies) and procedures (e.g., sampling) essential to its
performance. Some material is incorporated by reference from other
methods in this part. Therefore, to obtain reliable results, persons
using this method should also have a thorough knowledge of Method 1.
1.0 Scope and Application
1.1 Analytes.
[[Page 147]]
------------------------------------------------------------------------
Analytes CAS No. Sensitivity
------------------------------------------------------------------------
Oxygen (O2)....................... 7782-44-7 2,000 ppmv.
Nitrogen (N2)..................... 7727-37-9 N/A.
Carbon dioxide (CO2).............. 124-38-9 2,000 ppmv.
Carbon monoxide (CO).............. 630-08-0 N/A.
------------------------------------------------------------------------
1.2 Applicability. This method is applicable for the determination
of CO2 and O2 concentrations and dry molecular
weight of a sample from an effluent gas stream of a fossil-fuel
combustion process or other process.
1.3 Other methods, as well as modifications to the procedure
described herein, are also applicable for all of the above
determinations. Examples of specific methods and modifications include:
(1) A multi-point grab sampling method using an Orsat analyzer to
analyze the individual grab sample obtained at each point; (2) a method
for measuring either CO2 or O2 and using
stoichiometric calculations to determine dry molecular weight; and (3)
assigning a value of 30.0 for dry molecular weight, in lieu of actual
measurements, for processes burning natural gas, coal, or oil. These
methods and modifications may be used, but are subject to the approval
of the Administrator. The method may also be applicable to other
processes where it has been determined that compounds other than
CO2, O2, carbon monoxide (CO), and nitrogen
(N2) are not present in concentrations sufficient to affect
the results.
1.4 Data Quality Objectives. Adherence to the requirements of this
method will enhance the quality of the data obtained from air pollutant
sampling methods.
2.0 Summary of Method
2.1 A gas sample is extracted from a stack by one of the following
methods: (1) single-point, grab sampling; (2) single-point, integrated
sampling; or (3) multi-point, integrated sampling. The gas sample is
analyzed for percent CO2 and percent O2. For dry
molecular weight determination, either an Orsat or a Fyrite analyzer may
be used for the analysis.
3.0 Definitions [Reserved]
4.0 Interferences
4.1 Several compounds can interfere, to varying degrees, with the
results of Orsat or Fyrite analyses. Compounds that interfere with
CO2 concentration measurement include acid gases (e.g.,
sulfur dioxide, hydrogen chloride); compounds that interfere with
O2 concentration measurement include unsaturated hydrocarbons
(e.g., acetone, acetylene), nitrous oxide, and ammonia. Ammonia reacts
chemically with the O2 absorbing solution, and when present
in the effluent gas stream must be removed before analysis.
5.0 Safety
5.1 Disclaimer. This method may involve hazardous materials,
operations, and equipment. This test method may not address all of the
safety problems associated with its use. It is the responsibility of the
user of this test method to establish appropriate safety and health
practices and determine the applicability of regulatory limitations
prior to performing this test method.
5.2 Corrosive Reagents.
5.2.1 A typical Orsat analyzer requires four reagents: a gas-
confining solution, CO2 absorbent, O2 absorbent,
and CO absorbent. These reagents may contain potassium hydroxide, sodium
hydroxide, cuprous chloride, cuprous sulfate, alkaline pyrogallic acid,
and/or chromous chloride. Follow manufacturer's operating instructions
and observe all warning labels for reagent use.
5.2.2 A typical Fyrite analyzer contains zinc chloride, hydrochloric
acid, and either potassium hydroxide or chromous chloride. Follow
manufacturer's operating instructions and observe all warning labels for
reagent use.
6.0 Equipment and Supplies
Note: As an alternative to the sampling apparatus and systems
described herein, other sampling systems (e.g., liquid displacement) may
be used, provided such systems are capable of obtaining a representative
sample and maintaining a constant sampling rate, and are, otherwise,
capable of yielding acceptable results. Use of such systems is subject
to the approval of the Administrator.
6.1 Grab Sampling (See Figure 3-1).
6.1.1 Probe. Stainless steel or borosilicate glass tubing equipped
with an in-stack or out-of-stack filter to remove particulate matter (a
plug of glass wool is satisfactory for this purpose). Any other
materials, resistant to temperature at sampling conditions and inert to
all components of the gas stream, may be used for the probe. Examples of
such materials may include aluminum, copper, quartz glass, and Teflon.
6.1.2 Pump. A one-way squeeze bulb, or equivalent, to transport the
gas sample to the analyzer.
6.2 Integrated Sampling (Figure 3-2).
6.2.1 Probe. Same as in Section 6.1.1.
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6.2.2 Condenser. An air-cooled or water-cooled condenser, or other
condenser no greater than 250 ml that will not remove O2,
CO2, CO, and N2, to remove excess moisture which
would interfere with the operation of the pump and flowmeter.
6.2.3 Valve. A needle valve, to adjust sample gas flow rate.
6.2.4 Pump. A leak-free, diaphragm-type pump, or equivalent, to
transport sample gas to the flexible bag. Install a small surge tank
between the pump and rate meter to eliminate the pulsation effect of the
diaphragm pump on the rate meter.
6.2.5 Rate Meter. A rotameter, or equivalent, capable of measuring
flow rate to 2 percent of the selected flow rate.
A flow rate range of 500 to 1000 ml/min is suggested.
6.2.6 Flexible Bag. Any leak-free plastic (e.g., Tedlar, Mylar,
Teflon) or plastic-coated aluminum (e.g., aluminized Mylar) bag, or
equivalent, having a capacity consistent with the selected flow rate and
duration of the test run. A capacity in the range of 55 to 90 liters
(1.9 to 3.2 ft\3\) is suggested. To leak-check the bag, connect it to a
water manometer, and pressurize the bag to 5 to 10 cm H2O (2
to 4 in. H2O). Allow to stand for 10 minutes. Any
displacement in the water manometer indicates a leak. An alternative
leak-check method is to pressurize the bag to 5 to 10 cm (2 to 4 in.)
H2O and allow to stand overnight. A deflated bag indicates a
leak.
6.2.7 Pressure Gauge. A water-filled U-tube manometer, or
equivalent, of about 30 cm (12 in.), for the flexible bag leak-check.
6.2.8 Vacuum Gauge. A mercury manometer, or equivalent, of at least
760 mm (30 in.) Hg, for the sampling train leak-check.
6.3 Analysis. An Orsat or Fyrite type combustion gas analyzer.
7.0 Reagents and Standards
7.1 Reagents. As specified by the Orsat or Fyrite-type combustion
analyzer manufacturer.
7.2 Standards. Two standard gas mixtures, traceable to National
Institute of Standards and Technology (NIST) standards, to be used in
auditing the accuracy of the analyzer and the analyzer operator
technique:
7.2.1. Gas cylinder containing 2 to 4 percent O2 and 14
to 18 percent CO2.
7.2.2. Gas cylinder containing 2 to 4 percent CO2 and
about 15 percent O2.
8.0 Sample Collection, Preservation, Storage, and Transport
8.1 Single Point, Grab Sampling Procedure.
8.1.1 The sampling point in the duct shall either be at the centroid
of the cross section or at a point no closer to the walls than 1.0 m
(3.3 ft), unless otherwise specified by the Administrator.
8.1.2 Set up the equipment as shown in Figure 3-1, making sure all
connections ahead of the analyzer are tight. If an Orsat analyzer is
used, it is recommended that the analyzer be leak-checked by following
the procedure in Section 11.5; however, the leak-check is optional.
8.1.3 Place the probe in the stack, with the tip of the probe
positioned at the sampling point. Purge the sampling line long enough to
allow at least five exchanges. Draw a sample into the analyzer, and
immediately analyze it for percent CO2 and percent
O2 according to Section 11.2.
8.2 Single-Point, Integrated Sampling Procedure.
8.2.1 The sampling point in the duct shall be located as specified
in Section 8.1.1.
8.2.2 Leak-check (optional) the flexible bag as in Section 6.2.6.
Set up the equipment as shown in Figure 3-2. Just before sampling, leak-
check (optional) the train by placing a vacuum gauge at the condenser
inlet, pulling a vacuum of at least 250 mm Hg (10 in. Hg), plugging the
outlet at the quick disconnect, and then turning off the pump. The
vacuum should remain stable for at least 0.5 minute. Evacuate the
flexible bag. Connect the probe, and place it in the stack, with the tip
of the probe positioned at the sampling point. Purge the sampling line.
Next, connect the bag, and make sure that all connections are tight.
8.2.3 Sample Collection. Sample at a constant rate (10 percent). The sampling run should be simultaneous
with, and for the same total length of time as, the pollutant emission
rate determination. Collection of at least 28 liters (1.0 ft\3\) of
sample gas is recommended; however, smaller volumes may be collected, if
desired.
8.2.4 Obtain one integrated flue gas sample during each pollutant
emission rate determination. Within 8 hours after the sample is taken,
analyze it for percent CO2 and percent O2 using
either an Orsat analyzer or a Fyrite type combustion gas analyzer
according to Section 11.3.
Note: When using an Orsat analyzer, periodic Fyrite readings may be
taken to verify/confirm the results obtained from the Orsat.
8.3 Multi-Point, Integrated Sampling Procedure.
8.3.1 Unless otherwise specified in an applicable regulation, or by
the Administrator, a minimum of eight traverse points shall be used for
circular stacks having diameters less than 0.61 m (24 in.), a minimum of
nine shall be used for rectangular stacks having equivalent diameters
less than 0.61 m (24 in.), and a minimum of 12 traverse points shall be
used for all other cases. The traverse points shall be located according
to Method 1.
8.3.2 Follow the procedures outlined in Sections 8.2.2 through
8.2.4, except for the following: Traverse all sampling points, and
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sample at each point for an equal length of time. Record sampling data
as shown in Figure 3-3.
9.0 Quality Control
------------------------------------------------------------------------
Quality control
Section measure Effect
------------------------------------------------------------------------
8.2........................... Use of Fyrite to Ensures the accurate
confirm Orsat measurement of CO2
results. and O2.
10.1.......................... Periodic audit of Ensures that the
analyzer and analyzer is
operator operating properly
technique. and that the
operator performs
the sampling
procedure correctly
and accurately.
11.3.......................... Replicable Minimizes
analyses of experimental error.
integrated
samples.
------------------------------------------------------------------------
10.0 Calibration and Standardization
10.1 Analyzer. The analyzer and analyzer operator's technique should
be audited periodically as follows: take a sample from a manifold
containing a known mixture of CO2 and O2, and
analyze according to the procedure in Section 11.3. Repeat this
procedure until the measured concentration of three consecutive samples
agrees with the stated value 0.5 percent. If
necessary, take corrective action, as specified in the analyzer users
manual.
10.2 Rotameter. The rotameter need not be calibrated, but should be
cleaned and maintained according to the manufacturer's instruction.
11.0 Analytical Procedure
11.1 Maintenance. The Orsat or Fyrite-type analyzer should be
maintained and operated according to the manufacturers specifications.
11.2 Grab Sample Analysis. Use either an Orsat analyzer or a Fyrite-
type combustion gas analyzer to measure O2 and CO2
concentration for dry molecular weight determination, using procedures
as specified in the analyzer user's manual. If an Orsat analyzer is
used, it is recommended that the Orsat leak-check, described in Section
11.5, be performed before this determination; however, the check is
optional. Calculate the dry molecular weight as indicated in Section
12.0. Repeat the sampling, analysis, and calculation procedures until
the dry molecular weights of any three grab samples differ from their
mean by no more than 0.3 g/g-mole (0.3 lb/lb-mole). Average these three
molecular weights, and report the results to the nearest 0.1 g/g-mole
(0.1 lb/lb-mole).
11.3 Integrated Sample Analysis. Use either an Orsat analyzer or a
Fyrite-type combustion gas analyzer to measure O2 and
CO2 concentration for dry molecular weight determination,
using procedures as specified in the analyzer user's manual. If an Orsat
analyzer is used, it is recommended that the Orsat leak-check, described
in Section 11.5, be performed before this determination; however, the
check is optional. Calculate the dry molecular weight as indicated in
Section 12.0. Repeat the analysis and calculation procedures until the
individual dry molecular weights for any three analyses differ from
their mean by no more than 0.3 g/g-mole (0.3 lb/lb-mole). Average these
three molecular weights, and report the results to the nearest 0.1 g/g-
mole (0.1 lb/lb-mole).
11.4 Standardization. A periodic check of the reagents and of
operator technique should be conducted at least once every three series
of test runs as outlined in Section 10.1.
11.5 Leak-Check Procedure for Orsat Analyzer. Moving an Orsat
analyzer frequently causes it to leak. Therefore, an Orsat analyzer
should be thoroughly leak-checked on site before the flue gas sample is
introduced into it. The procedure for leak-checking an Orsat analyzer is
as follows:
11.5.1 Bring the liquid level in each pipette up to the reference
mark on the capillary tubing, and then close the pipette stopcock.
11.5.2 Raise the leveling bulb sufficiently to bring the confining
liquid meniscus onto the graduated portion of the burette, and then
close the manifold stopcock.
11.5.3 Record the meniscus position.
11.5.4 Observe the meniscus in the burette and the liquid level in
the pipette for movement over the next 4 minutes.
11.5.5 For the Orsat analyzer to pass the leak-check, two conditions
must be met:
11.5.5.1 The liquid level in each pipette must not fall below the
bottom of the capillary tubing during this 4-minute interval.
11.5.5.2 The meniscus in the burette must not change by more than
0.2 ml during this 4-minute interval.
11.5.6 If the analyzer fails the leak-check procedure, check all
rubber connections and stopcocks to determine whether they might be the
cause of the leak. Disassemble, clean, and regrease any leaking
stopcocks. Replace leaking rubber connections. After the analyzer is
reassembled, repeat the leak-check procedure.
12.0 Calculations and Data Analysis
12.1 Nomenclature.
[[Page 150]]
Md=Dry molecular weight, g/g-mole (lb/lb-mole).
%CO2=Percent CO2 by volume, dry basis.
%O2=Percent O2 by volume, dry basis.
%CO=Percent CO by volume, dry basis.
%N2=Percent N2 by volume, dry basis.
0.280 =Molecular weight of N2 or CO, divided by 100.
0.320 =Molecular weight of O2 divided by 100.
0.440 =Molecular weight of CO2 divided by 100.
12.2 Nitrogen, Carbon Monoxide Concentration. Determine the
percentage of the gas that is N2 and CO by subtracting the
sum of the percent CO2 and percent O2 from 100
percent.
12.3 Dry Molecular Weight. Use Equation 3-1 to calculate the dry
molecular weight of the stack gas.
[GRAPHIC] [TIFF OMITTED] TR17OC00.090
Note: The above Equation 3-1 does not consider the effect on
calculated dry molecular weight of argon in the effluent gas. The
concentration of argon, with a molecular weight of 39.9, in ambient air
is about 0.9 percent. A negative error of approximately 0.4 percent is
introduced. The tester may choose to include argon in the analysis using
procedures subject to approval of the Administrator.
13.0 Method Performance [Reserved]
14.0 Pollution Prevention [Reserved]
15.0 Waste Management [Reserved]
16.0 References
1. Altshuller, A.P. Storage of Gases and Vapors in Plastic Bags.
International Journal of Air and Water Pollution. 6:75-81. 1963.
2. Conner, William D. and J.S. Nader. Air Sampling with Plastic
Bags. Journal of the American Industrial Hygiene Association. 25:291-
297. 1964.
3. Burrell Manual for Gas Analysts, Seventh edition. Burrell
Corporation, 2223 Fifth Avenue, Pittsburgh, PA. 15219. 1951.
4. Mitchell, W.J. and M.R. Midgett. Field Reliability of the Orsat
Analyzer. Journal of Air Pollution Control Association. 26:491-495. May
1976.
5. Shigehara, R.T., R.M. Neulicht, and W.S. Smith. Validating Orsat
Analysis Data from Fossil Fuel-Fired Units. Stack Sampling News.
4(2):21-26. August 1976.
17.0 Tables, Diagrams, Flowcharts, and Validation Data
[GRAPHIC] [TIFF OMITTED] TR17OC00.091
[[Page 151]]
[GRAPHIC] [TIFF OMITTED] TR17OC00.092
----------------------------------------------------------------------------------------------------------------
Time Traverse point Q (liter/min) % Deviation \a\
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Average
----------------------------------------------------------------------------------------------------------------
\a\ % Dev.=[(Q-Qavg)/Qavg]x100 (Must be <=10%)
Figure 3-3. Sampling Rate Data
Method 3A--Determination of Oxygen and Carbon Dioxide Concentrations in
Emissions From Stationary Sources (Instrumental Analyzer Procedure)
1.0 Scope and Application
What is Method 3A?
Method 3A is a procedure for measuring oxygen (O2) and
carbon dioxide (CO2) in stationary source emissions using a
continuous instrumental analyzer. Quality assurance and quality control
requirements are included to assure that you, the tester, collect data
of known quality. You must document your adherence to these specific
requirements for equipment, supplies, sample collection and analysis,
calculations, and data analysis.
This method does not completely describe all equipment, supplies,
and sampling and
[[Page 152]]
analytical procedures you will need but refers to other methods for some
of the details. Therefore, to obtain reliable results, you should also
have a thorough knowledge of these additional test methods which are
found in appendix A to this part:
(a) Method 1--Sample and Velocity Traverses for Stationary Sources.
(b) Method 3--Gas Analysis for the Determination of Molecular
Weight.
(c) Method 4--Determination of Moisture Content in Stack Gases.
(d) Method 7E--Determination of Nitrogen Oxides Emissions from
Stationary Sources (Instrumental Analyzer Procedure).
1.1 Analytes. What does this method determine? This method measures
the concentration of oxygen and carbon dioxide.
------------------------------------------------------------------------
Analyte CAS No. Sensitivity
------------------------------------------------------------------------
Oxygen (O2).................... 7782-44-7 Typically <2% of
Calibration Span.
Carbon dioxide (CO2)........... 124-38-9 Typically <2% of
Calibration Span.
------------------------------------------------------------------------
1.2 Applicability. When is this method required? The use of Method
3A may be required by specific New Source Performance Standards, Clean
Air Marketing rules, State Implementation Plans and permits, where
measurements of O2 and CO2 concentrations in
stationary source emissions must be made, either to determine compliance
with an applicable emission standard or to conduct performance testing
of a continuous emission monitoring system (CEMS). Other regulations may
also require the use of Method 3A.
1.3 Data Quality Objectives. How good must my collected data be?
Refer to Section 1.3 of Method 7E.
2.0 Summary of Method
In this method, you continuously or intermittently sample the
effluent gas and convey the sample to an analyzer that measures the
concentration of O2 or CO2. You must meet the
performance requirements of this method to validate your data.
3.0 Definitions
Refer to Section 3.0 of Method 7E for the applicable definitions.
4.0 Interferences [Reserved]
5.0 Safety
Refer to Section 5.0 of Method 7E.
6.0 Equipment and Supplies
Figure 7E-1 in Method 7E is a schematic diagram of an acceptable
measurement system.
6.1 What do I need for the measurement system? The components of the
measurement system are described (as applicable) in Sections 6.1 and 6.2
of Method 7E, except that the analyzer described in Section 6.2 of this
method must be used instead of the analyzer described in Method 7E. You
must follow the noted specifications in Section 6.1 of Method 7E except
that the requirements to use stainless steel, Teflon, or non-reactive
glass filters do not apply. Also, a heated sample line is not required
to transport dry gases or for systems that measure the O2 or
CO2 concentration on a dry basis, provided that the system is
not also being used to concurrently measure SO2 and/or
NOX.
6.2 What analyzer must I use? You must use an analyzer that
continuously measures O2 or CO2 in the gas stream
and meets the specifications in Section 13.0.
7.0 Reagents and Standards
7.1 Calibration Gas. What calibration gasses do I need? Refer to
Section 7.1 of Method 7E for the calibration gas requirements. Example
calibration gas mixtures are listed below. Precleaned or scrubbed air
may be used for the O2 high-calibration gas provided it does
not contain other gases that interfere with the O2
measurement.
(a) CO2 in nitrogen (N2).
(b) CO2 in air.
(c) CO2/SO2 gas mixture in N2.
(d) O2/SO2 gas mixture in N2.
(e) O2/CO2/SO2 gas mixture in
N2.
(f) CO2/NOX gas mixture in N2.
(g) CO2/SO2/NOX gas mixture in
N2.
The tests for analyzer calibration error and system bias require
high-, mid-, and low-level gases.
7.2 Interference Check. What reagents do I need for the interference
check? Potential interferences may vary among available analyzers. Table
7E-3 of Method 7E lists a number of gases that should be considered in
conducting the interference test.
8.0 Sample Collection, Preservation, Storage, and Transport
8.1 Sampling Site and Sampling Points. You must follow the
procedures of Section 8.1 of Method 7E to determine the appropriate
sampling points, unless you are using Method 3A only to determine the
stack gas molecular weight and for no other purpose. In that case, you
may use single-point integrated sampling as described in Section 8.2.1
of Method 3. If the stratification test provisions in Section 8.1.2 of
Method 7E are used to reduce the number of required sampling points,
[[Page 153]]
the alternative acceptance criterion for 3-point sampling will be