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. (Author)


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    Title :

    Performance of Inlet Stage of Transonic Compressor


    Contributors:
    D. C. Urasek (author) / R. J. Steinke (author) / G. W. Lewis (author)

    Publication date :

    1976


    Size :

    72 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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