This report covers an experimental test program to determine the scalability of the LMDE centrally located, coaxial injector to much higher thrust levels than previously tested. A 250,000 lbf thrust, 300 psia chamber pressure Thrust Chamber Assembly (TCA) was fabricated and tested at a reduced thrust level of approximately 50,000 lbf thrust. The TCA design consisted of a centrally located coaxial injector, based upon the LMDE design, and heat sink combustion chamber. Performance levels in excess of the contractual requirements were achieved. Dynamic combustion stability test firings, employing nondirectional explosive charges, verified the combustion stability characteristics of the coaxial injector. (Author)
Advancement of Injector and Thrust Chamber Technology
1967
63 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Combustion & Ignition , Fuel injectors , Combustion chambers , Orifices , Manifolds(Engines) , Welding , Heat sinks , Liquid propellant rocket engines , Cost effectiveness , Manufacturing , Captive tests , Stability , Flanges , Model tests , Nitrogen oxide(NO2) , Steel 4130 , Steel t-1
The effect of injector design on thrust- chamber erosion
NTRS | 1966
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AIAA | 1965
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