An advanced transpiration-cooled thrust chamber concept has been tested extensively with both N204 and CLF3 as coolants. This concept utilizes stacked ultra-thin (0.001 to 0.020 in.) platelets to form a porous combustion chamber wall. Each platelet contains precise flow control channels which meter the coolant flow to the cooled surface and prevent the formation and growth of local hot spots. To demonstrate feasibility of the concept, two completely transpiration cooled chambers were fabricated and tested. A total of 121 tests were made with the N204-cooled chamber (stainless steel) for a cumulative firing duration of 3076.7 seconds. Ninety-six tests were made at the 100 lb thrust level and 25 tests at the 1000 lb thrust level. The cumulative firing duration for the CLF3-cooled chamber (nickel) was 197.3 seconds. Thirteen tests were made at the 100 lb thrust level and four tests were made at the 1000 lb thrust level. Thermal data obtained during these tests indicate that, aside from injector streaking effects, the TRANSPIRE system operated as designed. (Author)
Demonstration of an Advanced Transpiration-Cooled Thrust Chamber
1967
201 pages
Report
No indication
English
Rocket Engines & Motors , Rocket Propellants , Combustion & Ignition , Liquid propellant rocket engines , Liquid rocket propellants , Captive tests , Regenerative cooling , Fuel injection , Stainless steel , Heat transfer , Mathematical models , Specific impulse , Combustion chambers , Test facilities , Liquid rocket oxidizers , Liquid cooled , Oxygen , Hydrogen , Performance(Engineering) , Evapotranspiration , Film cooling , Nickel alloys , Thrust , Hydrazine , Dimethyl hydrazine (1-1) , Metal plates , Nitrogen compounds , Tetroxides , Aerozine 50 , Steel 1050 , Cooling , Transpiration
Technological Aspects of Transpiration Cooled Composite Structures for Thrust Chamber Applications
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