Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines. Volume I. Design
Abstract
The design of a single stage axial supersonic compressor with a predicted performance of 2.8:1 stage pressure ratio at 82% adiabatic efficiency and 4 lb/sec airflow is discussed. The results of a gas generator performance study to evaluate non-regenerated designs with 16:1 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 lb/hp/hr. 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 axial/centrifugal compressor and an advanced gas generator which incorporates this compressor are discussed. The predicted performance of the compressor is 16:1 pressure ratio at an adiabatic efficiency of 77.5% and an airflow of 4 lb/sec. The predicted design point specific fuel consumption and power at a 2500 F turbine inlet temperature are 0.431 lb/hp/hr 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1969
- Accession Number
- AD0502325
Entities
People
- Andrew Sabatiuk
- Charles H. Muller
- Howard W. Weiser
- William Litke