An inlet stage of a transonic compressor was tested with three rotor tip casing treatment configurations: blade angle slots, circumferential grooves, and axial skewed slots. Significant increases in both rotor and stage total pressure ratio, total temperature ratio, efficiency, flow range, and very large improvements in stall margin were obtained with all three casing treatment configurations. The greatest improvement in performance was achieved with axial skewed slots. (Author)
Effect of Casing Treatment on Performance of an Inlet Stage for a Transonic Multistage Compressor
1976
125 pages
Report
No indication
English
Performance of inlet stage of transonic compressor
TIBKAT | 1976
|Performance of Inlet Stage of Transonic Compressor
NTIS | 1976
|Performance of inlet stage of transonic compressor
NTRS | 1976
|