A liquid propellant rocket engine includes a combustion chamber that has a throat and a nozzle aft of the throat. The nozzle has a first nozzle section adjacent the throat and a second nozzle section aft of the first nozzle section. The first nozzle section includes active cooling features and the second nozzle section excludes any active cooling features. The first nozzle section is operative via at least the active cooling features to form a condensate that passively cools the second nozzle section.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Liquid propellant rocket engine nozzle with passive condensate cooling


    Beteiligte:
    PATEL JITEN R (Autor:in) / CLARK JIM A (Autor:in) / WHIPPLE IV CHARLES (Autor:in)

    Erscheinungsdatum :

    2021-03-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS




    COOLING VALVE FOR ROCKET ENGINE WITH CRYOGENIC PROPELLANT AND ROCKET ENGINE COMPRISING THE COOLING VALVE

    PHILIPPE NOMERANGE / OLIVIER FAYE | Europäisches Patentamt | 2021

    Freier Zugriff

    Liquid-Propellant Rocket Engine Injector Dynamics

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



    Liquid-Propellant Rocket Engine Injector Dynamics

    Vladimir G. Bazarov / Vigor Yang | AIAA | 1998