Determination of the relative resistance to ignition of selected turbopump materials in high-pressure, high-temperature, oxygen environments, volume 1.

Author:: Benz, Frank J.
Published:: Jul 21, 1986.
Physical Description:: 1 electronic document
Additional Creators:: Stoltzfus, Joel M.

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Summary:

Advances in the design of the liquid oxygen, liquid hydrogen engines for the Space Transportation System call for the use of warm, high-pressure oxygen as the driving gas in the liquid oxygen turbopump. The NASA Lewis Research Center requested the NASA White Sands Test Facility (WSTF) to design a test program to determine the relative resistance to ignition of nine selected turbopump materials: Hastelloy X, Inconel 600, Invar 36, Monel K-500, nickel 200, silicon carbide, stainless steel 316, and zirconium copper. The materials were subjected to particle impact and to frictional heating in high-pressure oxygen.

Other Subject(s):

INORGANIC AND PHYSICAL CHEMISTRY

Collection:

NASA Technical Reports Server (NTRS) Collection.

Note:

Document ID: 19890006632.
Accession ID: 89N16003.
NAS 1.26:179505-VOL-1.
TR-324-001-VOL-1.
NASA-CR-179505-VOL-1.

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