The overall and blade-element performance of a transonic compressor stage is presented over the stable operating range at rotative speeds from 50 to 100 percent of design speed. Stage peak efficiency of 0.784 was obtained at a weight flow of 28.6 kilograms per second and a pressure ratio of 1.706. Stall margin at design speed was 11.4 percent. The peak efficiency being significantly less than design efficiency was attributed to: (1) the stator loss and the radial gradient of losses being much higher than design, (2) the losses and blockages associated with the rotor part-span dampers not being incorporated into the design, and (3) mismatch of the rotor and stator badle elements. (Author)


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    Title :

    Performance of a Single-Stage Axial-Flow Transonic Compressor Stage with a Blade Tip Solidity of 1.7


    Contributors:
    R. D. Moore (author) / L. Reid (author)

    Publication date :

    1972


    Size :

    113 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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