A heated tube facility for rocket coolant channel research | Zendy

James Green | Zendy; Gary Pease | Zendy; Michaël Meyer | Zendy

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A heated tube facility for rocket coolant channel research

Author(s) -

James Green,

Gary Pease,

Michaël Meyer

Publication year - 1995

Publication title -

31st joint propulsion conference and exhibit

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1995-2936

Subject(s) - coolant , tube (container) , rocket (weapon) , channel (broadcasting) , nuclear engineering , aerospace engineering , materials science , engineering , mechanical engineering , electrical engineering

The capabilities of a heated tube facility used for testing rocket engine coolant channels at the NASA Lewis Research Center are presented. The facility uses high current, low voltage power supplies to resistively heat a test section to outer wall temperatures as high as 730 C (1350 F). Liquid or gaseous nitrogen, gaseous helium, or combustible liquids can be used as the test section coolant. The test section is enclosed in a vacuum chamber to minimize heat loss to the surrounding system. Test section geometry, size, and material; coolant properties; and heating levels can be varied to generate heat transfer and coolant performance data bases.

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