Coolant-carrying liner for combustion chambers runs cooler and tolerates high-temperature excursions without burning out. Hot gases flowing through core prevented by liner from damaging shell. Concept applicable to such high-temperature chambers as rocket pre-burners, turbojet cans, stationary-turbine combustors, oil burners, and high-pressure chemical reactors.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Ribbed Coolant Liners for Combustion Chambers


    Beteiligte:
    Wagner, W. R. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1984-11-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Ceramic Matrix Composite as Liners for Improved Ablative Chambers

    Wilson, Andrea / Bostwick, Christopher / Besnard, Eric et al. | AIAA | 2009


    FLOW INVESTIGATION IN A TWO-PASS COOLANT CHANNEL WITH/WITHOUT RIBBED WALLS

    Jarius, M. P. / Elfert, M. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2003


    Dependency of Surface Temperature on Coolant Mass Flow and Heat Flux in Rocket Combustion Chambers

    Kringe, Pascal H. / Burger, Chris / Riccius, Jorg R. et al. | IEEE | 2022


    Coupled CFD Analysis of the Hot Gas and the Coolant Flow in Effusion Cooled Combustion Chambers

    Riccius, Joerg / Greuel, Dirk / Haidn, Oskar et al. | AIAA | 2005