Project Title:

A Swirl Annular Combustor for Aircraft Gas Turbine Engines.

Advanced Projects Research Incorporated
147 Ward Street
Hightstown, NJ, 08520

93-1 01.02    4986  AMOUNT REQUESTED $70,000

A Swirl Annular Combustor for Aircraft Gas Turbine Engines.

Abstract:

This proposal describes an innovative Ultra-Low NOx annular swirl
combustor concept for aircraft gas turbine engines. The concept is
based on previously demonstrated means for creating high mixing
rate regions in free shear flows by manipulating existing vorticity
to create multiple discrete vortices in the flow. This mixing
technique coupled with a Lean-Burn Direct-Ignition (LBDI)
combustion strategy will be used in a high-performance low-loss
combustor design. This design addresses the aeropropulsion system
component need for innovative combustors with greater efficiency,
lower emissions, and reduced aerodynamic drag. The objectives of
the proposed Phase I project are to explore the combustor design
parameter space numerically and to demonstrate the feasibility of
the proposed concept experimentally. The results of the effort will
provide parametric data on the combustor geometry that will be used
in scaling the device to large annular systems for gas turbine
applications as well as a proof of principle demonstration. The
NASA applications and benefits include advanced ultra-low emission
combustors to address the needs for improvement in technology for
conventional subsonic aircraft and the high speed research program.

The commercial applications for the proposed technology lie in two
areas. First, the need and market for high performance combustors
for aircraft and industrial gas turbine engines is large. Second,
proposed technology will also be applied by Advanced Projects
Research Incorporated in a combustor for a gaseous waste
incinerator and ultimately in other commercial and industrial
burner applications.

Combustor, Low Emissions, Lean Burn Direct Ignition