The paper describes three experimental facilities which are being developed at NASA's Marshall Space Flight Center (MSFC) for rocket injector cold-flow characterization. The first of these is an already operational cold-flow ambient-backpressure facility, which uses water and air to simulate LOX and gaseous hydrogen, respectively; the facility can be used to obtain discharge coefficients, to measure flow uniformity, and to develop diagnostic techniques for use in the high-backpressure cold-flow chamber that is being currently developed at MSFC. The second is a cold-flow acrylic model facility to be used for evaluating the effect of changes in the internal flow geometry on the performance and combustion stability characteristics of a swirl coaxial LOX post. The third is a high-pressure cold-flow facility to be used for the characterization of the injector elements' performance; a specific application is to determine the effect of swirl elements on the temperature striations in the SSME preburners.


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    Title :

    Rocket injector single element characterization at the Marshall Space Flight Center


    Contributors:
    Hutt, J. (author) / Robertson, T. (author) / Mcdaniels, D. (author) / Eskridge, R. (author) / Fisher, M. (author)

    Conference:

    AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States


    Publication date :

    1993-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Rocket injector single element characterization at the Marshall Space Flight Center

    HUTT, J. / ROBERTSON, T. / MCDANIELS, D. et al. | AIAA | 1993


    Advanced Rocket Injector Development at Marshall Space Flight Center

    Hutt, J. J. / Cramer, J. M. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1996