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Hot fire test results of subscale tubular combustion chambersAdvanced, subscale, tubular combustion chambers were built and test fired with hydrogen-oxygen propellants to assess the increase in fatigue life that can be obtained with this type of construction. Two chambers were tested: one ran for 637 cycles without failing, compared to a predicted life of 200 cycles for a comparable smooth-wall milled-channel liner configuration. The other chamber failed at 256 cycles, compared to a predicted life of 118 cycles for a comparable smooth-wall milled-channel liner configuration. Posttest metallographic analysis determined that the strain-relieving design (structural compliance) of the tubular configuration was the cause of this increase in life.
Document ID
19930002426
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Kazaroff, John M.
(NASA Lewis Research Center Cleveland, OH, United States)
Jankovsky, Robert S.
(NASA Lewis Research Center Cleveland, OH, United States)
Pavli, Albert J.
(Sverdrup Technology, Inc. Brook Park, OH., United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.60:3222
NASA-TP-3222
E-6849
Report Number: NAS 1.60:3222
Report Number: NASA-TP-3222
Report Number: E-6849
Accession Number
93N11614
Funding Number(s)
PROJECT: RTOP 593-12-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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