The overall and blade-element performances are presented over the stable flow operating range of the stage at the design tip speed of 426 m/sec. Stage peak efficiency of 0.83 was obtained at a weight flow of 28.8 kg/sec and a pressure ratio of 1.52. The stall margin for the stage was 8 percent based on weight flow and pressure ratio at peak efficiency and stall. The rotor appears to be stalling prematurely as evidenced by high rotor tip losses.
Performance of inlet stage of transonic compressor
1976-02-01
Report
No indication
English
Performance of Inlet Stage of Transonic Compressor
NTIS | 1976
|Performance of inlet stage of transonic compressor
TIBKAT | 1976
|Transonic radial compressor inlet design
Online Contents | 2003
|Analysis of a Highly Loaded, Transonic, Inlet Compressor Stage: Isolated and Multi-stage Performance
British Library Conference Proceedings | 2000
|