Results are presented from a test program that compares predictions and measurements for a model version of the Space Shuttle Main Engine (SSME) Alternate Turbopump Development (ATD) High-Pressure Fuel Turbopump (HPFTP), with and without a swirl brake. The tests were conducted in order to establish a degree of confidence in seal calculations for the ATD turbopumps. Test results demonstrate that the proposed swirl brake design is effective in reducing the seal destabilizing forces. Without the swirl brake, the cross-coupled stiffness k increases monotonically with increasing inlet tangential velocity. With the swirl break, k tends to either be constant or decrease with increasing inlet tangential velocity. Comparisons between Scharrer's (1988) theory and measurements for the seal without a swirl brake indicate that the predictions can be used to provide design guidelines only.


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    Title :

    Seal-rotordynamic-coefficient test results for a model SSME ATD-HPFTP turbine interstage seal with and without a swirl brake


    Contributors:
    Childs, D. W. (author) / Ramsey, C. (author)

    Publication date :

    1990-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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