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Hydrogen film/conductive coolingSmall scale nozzle tests using heated nitrogen were run to obtain effectiveness and wall heat transfer data with hydrogen film cooling. Effectiveness data are compared with an entrainment model developed from planar, unaccelerated flow data. Results indicate significant effects due to flow turning and acceleration. With injection velocity effects accounted for explicitly, heat transfer correlation coefficients were found to be the same with and without film cooling when properties are evaluated at an appropriate reference temperature for the local gas composition defined by the coolant effectiveness. A design study for an O2/H2 application with 300 psia (207 N/sq cm) chamber pressure and 1500 lbs (6670 N) thrust indicates an adiabatic wall design requires 4 to 5 percent of the total flow as hydrogen film cooling. Internal regenerative cooling designs were found to offer no reduction in coolant requirements.
Document ID
19730003243
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Ewen, R. L.
(Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 2, 2013
Publication Date
November 1, 1972
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-CR-120926
Report Number: NASA-CR-120926
Accession Number
73N11970
Funding Number(s)
CONTRACT_GRANT: NAS3-14343
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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