Design and Development of a Small Highly Loaded, Two-Stage, Transonic Axial Compressor
720712
02/01/1972
- Event
- Content
- 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.
- Pages
- 16
- Citation
- Davis, J., "Design and Development of a Small Highly Loaded, Two-Stage, Transonic Axial Compressor," SAE Technical Paper 720712, 1972, https://doi.org/10.4271/720712.