An experimental investigation, whose objective was to demonstrate the influence of rotor blade tip clearance effects on the dynamic pressure induced on a downstream vane, was conducted in a large, low speed, single-stage research compressor. The blade tip clearance was 0.48% span. The rig was heavily instrumented with dynamic pressure gages on the vane hub, mean, and tip section suction and pressure surfaces. (Author)


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    Title :

    Influence of Blade Tip Clearance on Aerodynamically Induced Vibration


    Contributors:

    Publication date :

    1982


    Size :

    67 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English