This program demonstrated the feasibility of virtually all the components in present-day, high-energy, liquid-rocket engines. Transpiration and film-cooled thrust chambers were successfully operated. The first liquid-hydrogen tests of the coaxial injector was conducted and the first pump to successfully produce high pressures in pumping liquid hydrogen was tested. A 1,000-lb-thrust gaseous propellant and a 3,000-lb-thrust liquid-propellant thrust chamber were operated satisfactorily. Also, the first tests were conducted to evaluate the effects of jet overexpansion and separation on performance of rocket thrust chambers with hydrogen-oxygen propellants.


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    Titel :

    Liquid-hydrogen rocket engine development at Aerojet, 1944 - 1950


    Beteiligte:
    Osborn, G. H. (Autor:in) / Gordon, R. (Autor:in) / Coplen, H. L. (Autor:in) / James, G. S. (Autor:in)


    Erscheinungsdatum :

    1977-09-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :