Cryogenic-liquid transfer system, containing a ring structure with tensioned small diameter, high strength wires, provides adequate physical support for the piping, minimizes the conductive heat paths between the piping and jacket, and allows for thermal expansion and contraction of the piping

Hows, G. E.

Wright, B. J.

English

NASA Technical Reports Server

NASA TECH BRIEF S
Support Wire 
July 1970	 Brief 70-10306 
NASA Tech Briefs announce new technology derived from the U .S. space program. They are issued to encourage commercial 
application. Tech Briefs are available on a subscription basis from the Clearinghouse for Federal Scientific and Technical 
Information, Springfield, Virginia 22151. Requests for individual copies or questions relating to the Tech Brief program may 
be directed to the Technology Utilization Division, NASA, Code UT, Washington, D.C. 20546. 
Low Heat-Gain Cryogenic-Liquid Transfer System 
Clamp
nd View of Support 
Outer Ring 
Wherever cryogenic liquids are transferred by pip-
ing, it is essential to keep heat gains to thesystem at 
an absolute minimum to prevent boil-off. A conven-
tional means of reducing heat flow into the transfer 
piping is to enclose the piping in a vacuum jacket to 
insulate the cryogenic liquid from conductive heating. 
However, the means of supporting the piping within 
the evacuated jacket must be designed not only to 
provide adequate physical support, but also to mini-
mize conductive heat paths between the piping and 
jacket, and to allow for thermal expansion and con-
traction of the.piping. 
A conceptual design to accomplish these ends takes 
advantage of the fact that a ring structure with ten-
sioned small-diameter, high-strength wires will provide 
the necessary rigid support, with a sufficiently small 
thermal cross section to reduce conductive heating to 
an acceptable minimum. As shown in the figure, the 
(continued overleaf) 
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wires are tensioned between inner and outer rings 
which form concentric supports A and B for the pip-
ing. The inner ring of support A is clamped to the 
piping, and the outer ring locks into the end flange 
of the jacket by a snap ring. The arrangement of the 
tensioned wires within this support and the means of 
attaching the inner and outer ring are designed to limit 
the movement (from thermal contraction or expan-
sion) of the piping to the length between support A 
and the expansion joint. Support B is also clamped 
to the piping but is free to slide within the jacket to 
enable unrestricted expansion or contraction of the 
piping. 
Notes: 
1. Calculations show that the piping supports made 
of stainless steel will conduct less than 10% of the 
heat conducted by a laminated polyester block 
designed for the same application.
This development is in the conceptual stage only, 
and as of the date of publication of this Tech Brief 
neither a model nor prototype has been constructed. 
Requests for further information may be directed 
to:
Technology Utilization Officer 
Manned Spacecraft Center, Code BM7 
Houston, Texas 77058 
Reference: B70-10306 
Patent status: 
No patent action is contemplated by NASA. 
Source: George E. Hows and Ben J. Wright of 
North American Rockwell Corporation 
under contract to 
Manned Spacecraft Center 
(MSC-15165) 
Brief 70-10306 Category 07


Low heat-gain cryogenic-liquid transfer system

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