Advantages to be gained from reduction in thrust towards end of burning period and methods of throttling rocket engine are examined; low frequency combustion instability which can arise when engine is operated below its normal thrust level is considered and effect of such instability on engine performance; means of ensuring stable operation in main thrust chamber and turbine gas generator are described and compared; mechanism of heat transfer to main injector and modifications to injection pattern necessary to maintain this at safe level; effect of pressure change on thrust chamber performance is considered with reference to studies made on Rolls-Royce RZ.2 engine.
Thrust throttling of large liquid propellant rocket engines
Roy Aeronautical Soc -- J
Royal Aeronautical Society -- Journal ; 68 , n 647
1964
8 pages
Article (Journal)
English
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