A prototype rotor was designed to investigate the supersonic axial component at the inlet face of a compressor. A flexible inflatable nozzle is installed in the inlet duct in order to simulate a continuously variable inlet Mach number up to 1.5. A relative inlet Mach number of 2.4 is achieved at 90 percent of the design speed. The transition from the subsonic to the supersonic axial component is explored. A blade failure prevented completion of the research on the dynamic response of the compressor to throttle valve, speed, and inlet nozzle variations.
Axial Supersonic Inlet Compound
1988
25 pages
Report
No indication
English
Supersonic Elliptical Ramp Inlet
NTRS | 2016
|Supersonic inlet contour interpolation
AIAA | 1975
|