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.
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Reference
E. L. Dowtv and D. W. Murphy, in: Advances in Cryogenic Engineering, Vol. 13, Plenum Press, New York (1968), p. 590.
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© 1969 Springer Science+Business Media New York
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Barron, R.F., Timmerhaus, K.D. (1969). Note on Heat Exchanger Design for Cryogenic Propellant Tanks. In: Timmerhaus, K.D. (eds) Advances in Cryogenic Engineering. Advances in Cryogenic Engineering, vol 14. Springer, Boston, MA. https://doi.org/10.1007/978-1-4757-0549-2_23
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DOI: https://doi.org/10.1007/978-1-4757-0549-2_23
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