Investigation of Thermal Fatigue in Non-Tubular Regeneratively Cooled Thrust Chambers. Volume 2
ROCKWELL INTERNATIONAL CANOGA PARK CA ROCKETDYNE DIV
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Long life non-tubular teneratively cooled thrust chambers were fabricated and hot-fire cyclic tested to verify the life prediction techniques established in Volume I of this report. Chambers incorporating copper alloy NARLoy-Z and zirconium copper and nickel for the hot gas wall material and electroformed nickel closures were fabricated by Rocketdyne and hot fire cyclic tested by Rocketdyne and hot fire cyclic tested by the AFRPL. Propellants were LO2H2 at a nominal mixture ratio of 61. Chamber pressure was 750 psia and thrust corrected to vacuum and with a full area ratio nozzle was 3300 pounds. A calorimeter thrust chamber assembly calorimeter thrust chamber and coaxial injector were also fabricated and hot-fire tested to establish the heat flux profile. Post-test analysis and metallurgical evaluation of the chamber were performed to locate and define fatigue cracks.
- Air Conditioning, Heating, Lighting and Ventilating
- Liquid Propellant Rocket Engines