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Test program to provide confidence in liquid oxygen cooling of hydrocarbon fueled rocket thrust chambersAn experimental program has been planned at the NASA Lewis Research Center to build confidence in the feasibility of liquid oxygen cooling for hydrocarbon fueled rocket engines. Although liquid oxygen cooling has previously been incorporated in test hardware, more runtime is necessary to gain confidence in this concept. In the previous tests, small oxygen leaks developed at the throat of the thrust chamber and film cooled the hot-gas side of the chamber wall without resulting in catastrophic failure. However, more testing is necessary to demonstrate that a catastrophic failure would not occur if cracks developed further upstream between the injector and the throat, where the boundary layer has not been established. Since under normal conditions cracks are expected to form in the throat region of the thrust chamber, cracks must be initiated artificially in order to control their location. Several methods of crack initiation are discussed in this report. Four thrust chambers, three with cracks and one without, should be tested. The axial location of the cracks should be varied parametrically. Each chamber should be instrumented to determine the effects of the cracks, as well as the overall performance and durability of the chambers.
Document ID
19860022174
Document Type
Technical Memorandum (TM)
Authors
Armstrong, E. S.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1986
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-88816
NAS 1.15:88816
E-3174
Meeting Information
Meeting: JANNAF Propulsion Meeting
Location: New Orleans, LA
Country: United States
Start Date: August 25, 1986
End Date: August 28, 1986
Accession Number
86N31646
Funding Number(s)
PROJECT: RTOP 505-42-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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