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Combustion chamber heat transfer characterization of LOX/hydrocarbon-type propellantsThe gas-side heat transfer rates for LOX/propane and LOX/ethanol are experimentally characterized using a 1000 lb thrust water-cooled calorimeter chamber. The effects of injector element type and fuel film cooling are defined as a function of mixture ratio. The interaction of fuel injected through the resonator cavities on heat transfer and wall soot buildup are displayed as a function of time, axial distance, fuel coolant flow rate, and mixture ratio. Comparisons between clean-burning ethanol and sooting propane show a large difference between the two fuels and significantly higher than expected heat flux levels for ethanol in the throat region.
Document ID
19870057980
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schoenman, Leonard
(Aerojet TechSystems Co. Sacramento, CA, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1987
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 87-1857
Accession Number
87A45254
Funding Number(s)
CONTRACT_GRANT: NAS9-15958
Distribution Limits
Public
Copyright
Other

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