Project Title:

EFFICIENT COOLING OF TURBINE DISKS

Creare Incorporated
P.O. Box 71
Hanover, NH 03755

93-101.01 3800    AMOUNT REQUESTED $69,958

EFFICIENT COOLING OF TURBINE DISKS

Abstract:

In this program Creare will develop test data and design methods
for confident design of efficient cooling systems for turbine disks
in aircraft gas turbine engines. Cooling systems must prevent
ingress of hot combustion gases into the cavity between the turbine
disk and its stator when there is an intense, swirling flow past
the turbine disk from the turbine nozzles. In previous tests at
Creare, this swirling flow has been found to increase the cooling
flow requirements. We propose to develop a body of test data
applying to basic disk/stator configurations, simple theory to
assess the effects of design changes, and qualified computational
models for detailed assessment of designs. Innovations are: (1) a
small, low-speed test facility in which water is used to simulate,
observe, and measure the flow in the disk/stator gap of a gas
turbine, and (2) original mechanistic design models based on
analysis of the forces which govern the flow in the gap. In Phase
I we will prove the feasibility of our approach by developing a
basic theory for the effects of external flow on the required
cooling flow and showing that theoretical predictions agree with
Creare's existing database of test results. In Phase II we will
perform detailed tests using flow models which simulate aircraft
engines and develop qualified theory and computational models for
cooling system design.

Results of this program are important for manufacturers of aircraft
gas turbines, who require design methods for efficient disk cooling
systems. Results are also important for manufacturers of energy
recovery turbines used in the chemical process and petrochemical
industries. These turbines may operate with highly corrosive
process gases and sealing the turbine disk from the process gas is
vital.

gas turbines, disk cooling