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)

Abstract

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.

Keywords

Heat Exchanger Liquid Oxygen Tank Pressure Heat Exchanger Surface Turbine Exhaust 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

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    W.M. Kays and A.L. London, Compact Heat Exchangers, National Press (1955).Google Scholar
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    A. J. Gram, C.O. Mackey, and E.S. Monroe, “Convection Heat Transfer and Pressure Drop of Air Flowing Across In-Line Tube Banks.” ASME Paper 56-A-127.Google Scholar
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    G. P. Sutton, Rocket Propulsion Elements, John Wiley and Sons, Inc., New York (1958).Google Scholar
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    H. Itō, “Friction Factors for Turbulent Flow in Curved Pipes,” ASME Paper 58–8A-14.Google Scholar
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    N. Ledinegg, “Flow Distribution in Forced Circulation Boilers,” Maschinenbau und Waermewirtschaft. Vol. 3, No. 4 (1948).Google Scholar

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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