Saturn Booster Liquid-Oxygen Heat Exchanger Design and Development

  • G. K. Platt
  • C. C. Wood
Conference paper
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 7)


Liquid propellant rocket vehicles require tank pressurization during powered flight to prevent pump cavitation and provide tank structural rigidity. In the Saturn booster, liquid-oxygen tank pressurant is obtained by evaporating liquid oxygen, bled from the main liquid-oxygen pump discharge of each engine, in eight heat exchangers, one extracting heat from each turbine exhaust. The problem was to develop a heat exchanger which would satisfy the pressurization requirements for two different engine thrust levels while operating at a steady flow rate and pressure.


Heat Exchanger Liquid Oxygen Tank Pressure Heat Exchanger Surface Turbine Exhaust 
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Copyright information

© Springer Science+Business Media New York 1962

Authors and Affiliations

  • G. K. Platt
    • 1
  • C. C. Wood
    • 1
  1. 1.George C. Marshall Space Flight CenterNational Aeronautics and Space AdministrationHuntsvilleUSA

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