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Heavy hydrocarbon main injector technology programThe Heavy Hydrocarbon Main Injector Program was an analytical, design, and test program to demonstrate an injection concept applicable to an Isolated Combustion Compartment of a full-scale, high pressure, LOX/RP-1 engine. Several injector patterns were tested in a 3.4-in. combustor. Based on these results, features of the most promising injector design were incorporated into a 5.7-in. injector which was then hot-fire tested. In turn, a preliminary design of a 5-compartment 2D combustor was based on this pattern. Also the additional subscale injector testing and analysis was performed with an emphasis on improving analytical techniques and acoustic cavity design methodology. Several of the existing 3.5-in. diameter injectors were hot-fire tested with and without acoustic cavities for spontaneous and dynamic stability characteristics.
Document ID
19910011922
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Arbit, H. A.
(Rockwell International Corp. Canoga Park, CA, United States)
Tuegel, L. M.
(Rockwell International Corp. Canoga Park, CA, United States)
Dodd, F. E.
(Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1991
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
RI/RD-91-118
NASA-CR-184161
NAS 1.26:184161
Report Number: RI/RD-91-118
Report Number: NASA-CR-184161
Report Number: NAS 1.26:184161
Accession Number
91N21235
Funding Number(s)
CONTRACT_GRANT: NAS8-36369
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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