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Experimental fatigue life investigation of cylindrical thrust chambersTwenty-two cylindrical test sections of a cylindrical rocket thrust chamber were fabricated and 21 of them were cycled to failure to explore the failure mechanisms, determine the effects of wall temperature on cyclic life, and to rank the material life characteristics for comparison with results from isothermal tests of 12 alloys at 538 C. Cylinder liners were fabricated from OFHC copper, Amzirc, and NAR1loy-Z. Tests were conducted at a chamber pressure of 4.14 MW/sq m using hydrogen-oxygen propellants at an oxidant-fuel ratio of 6.0, which resulted in an average throat heat flux of 54 MW/sq m. The cylinders were cooled with liquid hydrogen at an average rate of 0.91 Kg/sec. All failures were characterized by a thinning of the cooling channel wall at the centerline and eventual failure by tensile rupture. Cyclic life rankings of the materials based on temperature do not agree with published rankings based on uniaxial, isothermal strain tests.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Quentmeyer, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1977
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
Meeting Information
Meeting: Propulsion Conf.
Location: Orlando, FL
Country: United States
Start Date: July 11, 1977
End Date: July 13, 1977
Sponsors: Soc. of Automotive Engineers, AIAA
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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