An investigation is in progress at the Langley Laboratory of the NACA to explore the possibilities of axial-flow compressors operating with supersonic velocities relative to the blade rows. The first phase of this investigation, a study of supersonic diffusers, has been reported. The second phase, an analysis of supersonic compressors, has also been reported. Preliminary calculations have shown that very high pressure ratios across a stage, together with somewhat increased mass flows, are possible with compressors which decelerate air through the speed of sound in their rotor blading. These performance characteristics are desirable in compressors for aircraft jet propulsion units, gas turbines, or superchargers. The third phase, presented here, is a preliminary experimental investigation of a supersonic compressor designed to produce a high pressure ratio in a single stage.
Investigation of an Experimental Supersonic Axial-Flow Compressor
1947
59 pages
Report
No indication
English
Aerodynamics , Aircraft , Jet & Gas Turbine Engines , Turbocompressors , Aircraft engines , Propulsion system performance , Pressure ratio , Pressure distribution , Jet propulsion , Gas turbines , Axial flow , Jet aircraft , Supersonic speed , Rotor blades , Ratio , Supsonic velocities , Axial-flow compressors
Supersonic axial-flow compressor
Engineering Index Backfile | 1950
|Supersonic Axial-Flow Compressor
NTIS | 1946
|The Supersonic Axial-Flow Compressor
NTRS | 1950
|