This paper discusses development and test of an advanced expander combustion chamber for a 50,000 pound (222.4 kN) thrust Upper Stage Expander Cycle Engine. The chamber is 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 Propulsion Technology (IHPRPT) program. The Advanced Expander Combustor is designed to provide increased heat pick-up to the coolant and improved system thrust to weight, increased specific impulse, and increased reliability. These benefits will be accomplished and demonstrated through design, development, and test of this high heat flux, compact thrust chamber capable of supporting a chamber pressure of 1375 psia 97 kg/sq cm in an expander cycle configuration.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Development and Test of an Advanced Expander Combustor


    Contributors:
    T. Jennings (author) / S. Fentress (author) / S. Peery (author) / A. Minick (author)

    Publication date :

    1999


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Development and test of an advanced expander combustor

    Jennings, T. / Fentress, S. / Peery, S. et al. | AIAA | 1999


    Fabrication and test of an advanced expander combustor

    Jennings, T. / Fentress, S. / Lyda, R. | AIAA | 2000


    FABRICATION AND TEST OF AN ADVANCED EXPANDER COMBUSTOR

    Jennings, T. / Fentress, S. / Lyda, R. et al. | British Library Conference Proceedings | 2000



    Advanced expander test bed program

    Masters, A. I. / Mitchell, J. C. | NTRS | 1991