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The feasibility of transpiration cooling with hydrogen and helium, and the use of photo-etched copper platelets for heat transfer and coolant metering was successfully demonstrated.
Various transpiration coolant flow rates were tested with resultant local hot gas wall temperatures in the 800 F to 1400 F range. The engine burns LOX-hydrogen propellants at a chamber pressure of 600 psia. The analysis, design, fabrication, and testing of a liquid rocket engine thrust chamber which is gas transpiration cooled in the high heat flux convergent portion of the chamber and water jacket cooled (simulated regenerative) in the barrel and divergent sections of the chamber are described. Performance of a transpiration-regenerative cooled rocket thrust chamber A proof-of-concept test article has been fabricated and will he tested at Marshall Space Flight Center in the late Summer or Fall of 2000. The most significant innovations in this design was the development of a low-cost process for fabrication from copper tubing (nickel alloy was the usual practice) and use of graphite composite overwrap as the pressure containment, which yields an easily fabricated, lightweight pressure jacket around the copper tubes A regeneratively- cooled reusable thrust chamber can benefit the Fastrac engine program by allowing more efficient (cost and scheduler testing). Fabrication of regeneratively cooled thrust chambers by tubewall construction dates back to the early US ballistic missile programs. Inc.'s 12,000 lb regeneratively- cooled LOX/kerosene rocket engine. The thrust chamber design and fabrication approach was based upon Space America. The chamber was fabricated using hydraformed copper tubing to form the coolant jacket and wrapped with a fiber reinforced polymer composite Material to form a structural jacket. Sparks, Dave Woodcock, GordonĪbstract This paper presents the development of a low-cost, regeneratively- cooled thrust chamber for the Fastrac engine. A Regeneratively Cooled Thrust Chamber For The Fastrac Engineīrown, Kendall K.