This report describes the results of the testing performed at the Air Force Rocket Propulsion Laboratory. The purpose of this program was to demonstrate the performance, stability, injector/chamber compatibility and long-duration operation of low-cost scalable pressure-fed engines which use storable propellants. Tests were conducted at the 250,000-pound-thrust level with thrust chamber assemblies using two different design approaches: a pintle injector designed by TRW Systems and a modular injector designed by Rocketdyne. Short-duration tests were performed to measure performance, stability and effects of design variation. Long-duration tests were conducted to demonstrate performance, injector/chamber compatibility, and to measure the performance potential of low-cost ablative chambers. The program goals of achieving 90 percent of theoretical specific impulse, 140-second-duration firing and low-cost thrust chamber assemblies were all achieved.
Injector/Chamber Scaling Evaluation
1972
299 pages
Report
Keine Angabe
Englisch
Combustion & Ignition , Rocket Propellants , Fuel injectors , Storable rocket propellants , Combustion chambers , Liquid propellant rocket engines , Methyl hydrazines , Heat sinks , Heat transfer , Thrust , Specific impulse , Pressure , Combustion , Stability , Combustion chamber liners , Manifolds(Engines) , Ablation , Manufacturing , Fuel injection , Design , Performance(Engineering)
Injector/Chamber Scaling Evaluation, Facility Checkout
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