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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:
    Osborn, G. H. (author) / Gordon, R. (author) / Coplen, H. L. (author) / James, G. S. (author)


    Publication date :

    1977-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English