A liquid rocket engine cools a thruster body by pumping propellant through cooling channels integrated in the thruster body between internal and external surfaces. One or more of the cooling channel surfaces has a variable depth along a thrust axis to mix propellant flow and destroy thermal stratification, such as a depth that varies with a repeated contiguous sinusoidal form along the thrust axis. Fuel passed through the cooling channels injects from the combustion chamber wall towards a central portion of the combustion chamber to cross impinge with oxygen injected at the combustion chamber head so that a toroidal vortex forms to enhance propellant mixing.


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    Title :

    Liquid rocket engine cross impinged propellant injection



    Publication date :

    2022-05-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS / F23L SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL , Zufuhr von Luft oder nichtbrennbarer Flüssigkeiten oder Gase zu Feuerungen allgemein




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    Liquid-Propellant Rocket Engine Injector Dynamics

    Vladimir G. Bazarov / Vigor Yang | AIAA | 1998


    Liquid-Propellant Rocket Engine Injector Dynamics

    Bazarov, V. G. / Yang, V. | British Library Conference Proceedings | 1998