In order to mitigate the risk of rocket propulsion development, efficient, accurate, detailed fluid dynamics analysis and testing of the turbomachinery is necessary. To support this requirement, a task was developed at NASA Marshall Space Flight Center (MSFC) to improve turbine aerodynamic performance through the application of advanced design and analysis tools. These tools were applied to optimize a supersonic turbine design suitable for a reusable launch vehicle (RLV). The hot gas path and blading were redesigned-to obtain an increased efficiency. The goal of the demonstration was to increase the total-to- static efficiency of the turbine by eight points over the baseline design. A sub-scale, cold flow test article modeling the final optimized turbine was designed, manufactured, and tested in air at MSFC s Turbine Airflow Facility. Extensive on- and off- design point performance data, steady-state data, and unsteady blade loading data were collected during testing.


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    Titel :

    Experimental Performance Evaluation of a Supersonic Turbine for Rocket Engine Applications


    Beteiligte:

    Kongress:

    39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ; 2003 ; Huntsville, AL, United States


    Erscheinungsdatum :

    2003-07-08


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch