A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine which includes a lox post terminating in a cylindrical barrel. A lox plug received within the barrel which is threaded in the lox post and includes an interchangeable lox metering sieve which meters the lox into an annular lox passage. A second annular gas passage is coaxial with the annular lox passage. A cylindrical sieve surrounds the annular gas passage and includes an interchangeable gas metering sieve with metering orifices through which a hot gas passes into the annular passage. The jets which emerge from the annular lox passage and annular gas passage intersect at a point which is recessed away from the combustion area. The procedure enhances mixing and combustion stability.


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    Title :

    Low Loss Injector for Liquid Propellant Rocket Engines


    Contributors:

    Publication date :

    1985


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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