Two methods are commonly used to control the secondary/separated flows (and associated losses) in supersonic turbines: endwall contouring and airfoil stacking. In the current investigation the flow path between the first-stage vanes and rotors, and the stacking of the first-stage vanes were varied in an effort to improve turbine performance. The geometric variations have been studied by performing a series of unsteady three-dimensional numerical simulations for the two-stage turbine.


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    Titel :

    Effects of Endwall Geometry and Stacking on Two-Stage Supersonic Turbine Performance


    Beteiligte:
    Dorney, Daniel J. (Autor:in) / Griffin, Lisa W. (Autor:in) / Huber, Frank W. (Autor:in) / Sondak, Douglas L. (Autor:in) / Turner, Jim (Autor:in)

    Kongress:

    2002 AIAA Aerospace Sciences Meeting


    Erscheinungsdatum :

    2002-01-01


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch




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    Dorney, D. / Griffin, L. / Huber, F. et al. | AIAA | 2002


    Effects of End Wall Geometry and Stacking on Supersonic Turbine Performance

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