A small, two-stage, transonic axial compressor was selected for a 5 lb/s airflow, 0.46 lb/hp · h, sfc turboshaft engine at 2500 F turbine-inlet gas temperature. The axial compressor was configured to supercharge a single-stage centrifugal compressor to provide an overall axial/centrifugal pressure ratio of 16:1.The axial compressor was designed, fabricated, and developed through rig testing. On final test, a pressure ratio of 3.1:1 was demonstrated at 80% efficiency with 10% surge margin.
Design and Development of a Small Highly Loaded, Two-Stage, Transonic Axial Compressor
Sae Technical Papers
National Farm, Construction, Industrial Machinery, Powerplant Meeting ; 1972
01.02.1972
Aufsatz (Konferenz)
Englisch
THE COMBINED TRANSONIC AXIAL AND CENTRIFUGAL STAGE COMPRESSOR
SAE Technical Papers | 1961
|Analysis of a Highly Loaded, Transonic, Inlet Compressor Stage: Isolated and Multi-stage Performance
British Library Conference Proceedings | 2000
|