Study of thermodynamic phenomena occurring during transfer of cryogenic liquids from dewar to receiver tank reveals that the basic cause of tank implosion is evaporation rate of droplets entering the tank in the early transfer phase. Analyses of the thermodynamics involved and implosion prevention techniques are included

Brogan, J. J.

Vernon, R. M.

English

NASA Technical Reports Server

May 1968	 Brief 68-10108 
NASA TECH BRIEF 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151. 
Study of Cryogenic Container Thermodynamics During Propellant Transfer 
During initial phases of transfer of cryogenic liquids 
from dewar to receiver tank, certain transient and 
complex thermodynamic phenomena are evident. 
These include pressure surging and flow oscillations in 
the transfer line and pressure fluctuations in the 
receiver tank. Catastrophic failures involving transfer 
line rupture and receiver tank implosion have been 
experienced. 
In order to pinpoint the causes of these problems, 
an exhaustive study has been made using laboratory 
model analyses derived from empirical data fed to a 
digital computer. Based on the computer printout, 
model systems have been operated for both transfer 
line and receiver tank reactions to programmed param-
eters of flow, pressure, fluid phase, and hardware con-
figuration. Of particular interest in receiver tank per-
formance is the reaction of tank pressure in early 
transfer phase to the average size of liquid droplets in 
the liquid/vapor jet entering the tank. 
The basic cause of tank implosion is found to be the 
evaporation rate of droplets entering the tank in the 
early transfer phase. If the droplets are small, evapora-
tion is rapid and energy is removed from the vapor in 
the tank thus causing a rapid drop in tank pressure. In
order to reduce the rate of pressure drop, a baffle is 
placed within the tank, facing the inlet. This forces the 
incoming liquid along the tank wall, and reduces 
ullage-liquid heat transfer. 
Notes: 
I. The study concludes with a summary of analyses 
of the results concerning transfer line thermo-
dynamics, tank fill thermodynamics, complete fill 
system thermodynamics, and implosion prevention 
techniques. 
. lnuiries concerning this study may be directed to:

Technology Utilization Officer 
Marshall Space Flight Center 
Huntsville, Alabama 35812 
Reference: B68-10108 
Patent status: 
No patent action is contemplated by NASA. 
Source: R. M. Vernon and J. J. Brogan 
of Lockheed Missiles and Space Company 
•	 under contract to 
Marshall Space Flight Center 
(M FS- 14310) 
Category 02 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United States
Government assumes any liability resulting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned rights.
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Study of cryogenic container thermodynamics during propellant transfer

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