Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines. Volume I. Design
Final technical rept. 1 Jan-30 Sep 1966 on Phase 1
CURTISS-WRIGHT CORP WOOD-RIDGE NJ WRIGHT AERONAUTICAL DIV
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The design of a single stage axial supersonic compressor with a predicted performance of 2.81 stage pressure ratio at 82 adiabatic efficiency and 4 lbsec airflow is discussed. The results of a gas generator performance study to evaluate non-regenerated designs with 161 pressure ratio compressors and turbine inlet temperatures between 2500 F and 3000 F are presented and discussed. The design point specific fuel consumption of the engines studied ranged from 0.415 to 0.438 lbhphr. At 50 power this range increased to 0.465 and 0.534 respectively. The engine configuration which indicated the lowest specific fuel consumption has a two spool gas generator and variable stator free power turbine. The preliminary designs of a two stage axialcentrifugal compressor and an advanced gas generator which incorporates this compressor are discussed. The predicted performance of the compressor is 161 pressure ratio at an adiabatic efficiency of 77.5 and an airflow of 4 lbsec. The predicted design point specific fuel consumption and power at a 2500 F turbine inlet temperature are 0.431 lbhphr and 785 hp respectively. The results of a preliminary design study for a variable geometry axial compressor rotor concept are also discussed. This concept offers the potential for improved part speed compressor performance and stage matching.
- Hydraulic and Pneumatic Equipment
- Jet and Gas Turbine Engines