This paper discusses design and development of an Advanced Liquid Hydrogen Turbopump for a 50,000 pound thrust Upper Stage Expander Cycle Engine being developed by Pratt & Whitney Liquid Space Propulsion under contract for the United States Air Force Research Laboratory (AFRL) to support the Integrated High Payoff Rocket Technology (IHPRPT) program. The Advanced Liquid Hydrogen Turbopump is designed to provide improved system thrust to weight, decreased hardware/support costs, and increased reliability. These benefits will be accomplished and demonstrated through design, development, and test of this high speed, high efficiency, two stage hydrogen turbopump capable of supplying 16 lbm/sec (7.3 kg/sec.) of liquid hydrogen at 4600 psia (323.4 kg/ sq cm).


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Design and Development of an Advanced Liquid Hydrogen Turbopump


    Contributors:
    A. Minick (author) / S. Peery (author)

    Publication date :

    1998


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Advanced liquid oxygen turbopump design and development

    Dimitrenko, A. / Ivanov, A. / Kravchenko, A. et al. | AIAA | 2000


    Testing of an advanced liquid hydrogen turbopump

    Grabowski, R. / Chapman, L. / Crease, G. et al. | AIAA | 2000


    Testing of an Advanced Liquid Hydrogen Turbopump

    L. Chapman / G. Crease / J. Friant et al. | NTIS | 2000


    Design and test results of an advanced liquid hydrogen turbopump

    Crease, G. / Lyda, R. / Park, J. et al. | AIAA | 1999