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Note on Heat Exchanger Design for Cryogenic Propellant Tanks

  • R. F. Barron
  • K. D. Timmerhaus
Conference paper
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 14)

Abstract

In a recent study, Dowty and Murphy [1] presented a theoretical analysis with limited experimental data to verify a design of a vapor separator for zero gravity propellant tank venting. The vapor separator in this application utilizes a fluid expander coupled to a heat exchanger. The scheme basically permits the venting fluid to expand initially to a pressure and temperature below that of the bulk propellant, and then to absorb a sufficient amount of energy from the bulk propellant by means of the heat exchanger to assure that only vapor leaves the propellant tank.

Keywords

Heat Flux Heat Transfer Coefficient Heat Exchanger Energy Flow Dimensionless Form 
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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Reference

  1. 1.
    E. L. Dowtv and D. W. Murphy, in: Advances in Cryogenic Engineering, Vol. 13, Plenum Press, New York (1968), p. 590.Google Scholar

Copyright information

© Springer Science+Business Media New York 1969

Authors and Affiliations

  • R. F. Barron
    • 1
  • K. D. Timmerhaus
    • 2
  1. 1.Louisiana Polytechnic InstituteRustonUSA
  2. 2.University of ColoradoBoulderUSA

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