Pratt and Whitney Rocketdyne (PWR), a NASA subcontractor, is executing the Design, Development, Test, and Evaluation (DDT&E) of a liquid oxygen, liquid hydrogen two hundred ninety-four thousand pound thrust rocket engine initially intended for the Upper Stage (US) and Earth Departure Stage (EDS) of the Constellation Program Ares-I Crew Launch Vehicle (CLV). A key element of the design approach was to base the new J-2X engine on the heritage J-2S engine which was a design upgrade of the flight proven J-2 engine used to put American astronauts on the moon. This paper will discuss the design trades and analyses performed to achieve the required uprated Oxidizer Turbopump performance; structural margins and rotordynamic margins; incorporate updated materials and fabrication capability; and reflect lessons learned from legacy and existing Liquid Rocket Propulsion Engine turbomachinery. These engineering design, analysis, fabrication and assembly activities support the Oxidizer Turbopump readiness for J-2X engine test in 2011.


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    Title :

    The J-2X Oxidizer Turbopump - Design, Development, and Test



    Conference:

    JANNAF 8th Modeling and Simulation Subcommittee Meeting ; 2011 ; Huntsville, AL, United States
    JANNAF 6th Liquid Propulsion Subcommittee Meeting ; 2011 ; Huntsville, AL, United States
    JANNAF 5th Spacecraft Propulsion Subcommittee Meeting ; 2011 ; Huntsville, AL, United States


    Publication date :

    2011-12-05


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English