The results of a measurement program using the Rocketdyne two-stage Space Shuttle Main Engine (SSME) fuel turbine are described. The experiments utilize a large shock tunnel to produce a short-duration source of heated and pressurized air which is subsequently passed through a turbine that is operating at the design values of flow function, stage pressure ratio, stage temperature ratio and corrected speed. The results reported here concentrate on the blade platform, blade tip, and stationary shroud. The blades of this turbine are unshrouded and move in close proximity to the stationary outer shroud. The pressure difference between the pressure and suction sides of the blade drives a leakage flow through the gap between the moving blade and the stationary shroud. The tip/shroud clearance in these experiments is consistent with the design value. Off-design speed heat-flux data are also presented for the blade tip, stationary shroud, and blade platform regions as well as for the vane and blade pressure and suction surfaces.


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    Title :

    Turbine blade platform, blade tip and shroud heat transfer


    Additional title:

    Wärmeübertragung an Turbinenschaufelfuß, -schaufelkopf und Turbinenmantel


    Contributors:
    Dunn, M.G. (author) / Kim, J. (author)


    Publication date :

    1995


    Size :

    16 Seiten, 18 Bilder, 2 Tabellen, 17 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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    Dunn, M. G. / Kim, J. / International Society for Air Breathing Engines; Australian Committee | British Library Conference Proceedings | 1995


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