Abstract: This paper describes the aeromechanical design and development of a 3.3 kg/s (7.3 lb/sec), 14:1 pressure ratio two-stage centrifugal compressor, which is used in the T800-LHT-800 helicopter engine. ...

Abstract: Excessive stator end-wall and associated secondary flow losses were identified from test results of a small, low-aspect-ratio gas generator turbine. A research turbine was designed and tested for ...