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Hydrogen film/conductive cooling

Authors :
Ewen, R. L
Publication Year :
1972
Publisher :
United States: NASA Center for Aerospace Information (CASI), 1972.

Abstract

Small 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.

Subjects

Subjects :
Thermodynamics And Combustion

Details

Language :
English
Database :
NASA Technical Reports
Notes :
NAS3-14343
Publication Type :
Report
Accession number :
edsnas.19730003243
Document Type :
Report