An evaluation of reusable thrust chambers for the space shuttle orbit maneuvering engine was conducted. Tests were conducted using subscale injector hot-fire procedures for the injector configurations designed for a regenerative cooled engine. The effect of operating conditions and fuel temperature on combustion chamber performance was determined. Specific objectives of the evaluation were to examine the optimum like-doublet element geometry for operation at conditions consistent with a fuel regeneratively cooled engine (hot fuel, 200 to 250 F) and the sensitivity of the triplet injector element to hot fuels. (Author)
Space Shuttle Orbit Maneuvering Engine, Reusable Thrust Chamber Program. Task 6: Data Dump Hot Fuel Element Investigation
1974
45 pages
Report
Keine Angabe
Englisch