An injector for use with the rocket thruster has a plurality of fuel ports separated from a plurality of oxidizer ports. The oxidizer and fuel ports are paired together directing their respective fluids along a path with radial and tangential components so that the two fluids impinge at a predetermined spaced apart distance from the chamber wall of the combustion chamber at an impingement track. By providing the fuel at a steeper angle relative to the chamber walls than the oxidizer, the fuel can be utilized to provide a fuel rich zone near the chamber walls to assist in cooling the chamber walls during operation.


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    Titel :

    Liquid Propellant Tracing Impingement Injector


    Beteiligte:
    George D Xenofos (Autor:in) / W Neill Myers (Autor:in) / Huu Trinh (Autor:in) / R Scott Michaels (Autor:in)

    Erscheinungsdatum :

    01.03.2005


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



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