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Validation of High Aspect Ratio Cooling in a 89 kN (20,000 lb(sub f)) Thrust Combustion ChamberIn order to validate the benefits of high aspect ratio cooling channels in a large scale rocket combustion chamber, a high pressure, 89 kN (20,000 lbf) thrust, contoured combustion chamber was tested in the NASA Lewis Research Center Rocket Engine Test Facility. The combustion chamber was tested at chamber pressures from 5.5 to 11.0 MPa (800-1600 psia). The propellants were gaseous hydrogen and liquid oxygen at a nominal mixture ratio of six, and liquid hydrogen was used as the coolant. The combustion chamber was extensively instrumented with 30 backside skin thermocouples, 9 coolant channel rib thermocouples, and 10 coolant channel pressure taps. A total of 29 thermal cycles, each with one second of steady state combustion, were completed on the chamber. For 25 thermal cycles, the coolant mass flow rate was equal to the fuel mass flow rate. During the remaining four thermal cycles, the coolant mass flow rate was progressively reduced by 5, 6, 11, and 20 percent. Computer analysis agreed with coolant channel rib thermocouples within an average of 9 percent and with coolant channel pressure drops within an average of 20 percent. Hot-gas-side wall temperatures of the chamber showed up to 25 percent reduction, in the throat region, over that of a conventionally cooled combustion chamber. Reducing coolant mass flow yielded a reduction of up to 27 percent of the coolant pressure drop from that of a full flow case, while still maintaining up to a 13 percent reduction in a hot-gas-side wall temperature from that of a conventionally cooled combustion chamber.
Document ID
19960035853
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wadel, Mary F. (NASA Cleveland, OH United States)
Meyer, Michael L. (NASA Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1996
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA Paper 96-2584
NASA-TM-107270
E-10337
NAS 1.15:107270
Meeting Information
Meeting: Joint Propulsion Conference
Location: Lake Buena Vista, FL
Country: United States
Start Date: July 1, 1996
End Date: July 3, 1996
Sponsors: American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc., American Society for Engineering Education
Accession Number
96N30553
Funding Number(s)
PROJECT: RTOP 242-20-06
Distribution Limits
Public
Copyright
Public Use Permitted.

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