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.


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    Titel :

    Axial Supersonic Inlet Compound


    Beteiligte:

    Erscheinungsdatum :

    1988


    Format / Umfang :

    25 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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