Circular manifold with tangential orifices at the inner circumference provides for the vapor constituent of a vaporized cryogenic propellant to enter a rocket combustion chamber before the liquid constituent. The vapor is separated from the liquid by centrifugal action and precedes it into the chamber through carefully positioned orifices.


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    Titel :

    Combustion chamber inlet manifold separates vapor from liquid


    Beteiligte:
    Baker, D. I. (Autor:in)

    Erscheinungsdatum :

    01.02.1966


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


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