STP1111

    Test Experience with a High-Pressure Oxygen Turbopump and Heat Exchanger

    Published: Jan 1991


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    Abstract

    Test results of a 97 KW (130 hp) Monel turbopump assembly driven by 300 K (540 R), 27.6 MPa (4000 psi) oxygen at a speed of 62,000 rpm while supported on oxygen-pressurized hydrostatic bearings is presented, along with test results for a 27.6 MPa (4000 psi), 644 K (1159 R) oxygen/hydrogen heat exchanger. These new rocket components incorporate design and material selection criteria which have evolved from NASA and ASTM G-4 standards and test methods. Both components employ alloys that have low heats of combustion and high thermal diffusivity as a means of meeting a self-extinguishing safety criteria.

    Keywords:

    metal ignition, oxygen turbopump, oxygen heat exchanger, oxygen compatibility, nickel and copper alloys


    Author Information:

    Schoenman, L
    Senior Research Engineer, Space Systems, Sacramento, CA

    Sabiers, RL
    Senior Engineering Specialist, Space Systems, Sacramento, CA

    McIlwain, MC
    Director, Space Systems, Sacramento, CA


    Paper ID: STP17787S

    Committee/Subcommittee: G04.01

    DOI: 10.1520/STP17787S


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