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.


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    Title :

    Thrust throttling of large liquid propellant rocket engines


    Additional title:

    Roy Aeronautical Soc -- J


    Contributors:
    Smith, I.E. (author)

    Published in:

    Publication date :

    1964


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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