The development of analytical techniques and numerical methods for the prediction of the stability behavior of liquid propellant rocket combustors is discussed. The studies involved nonlinear wave propagation effects and nonlinear combustion zone, liner, and nozzle responses. A second primary extension of the basic theory was directed at the inclusion of the effects of injector face baffles. Attention was restricted to the linear (small amplitude) problem, finite Mach numbers, three dimensional oscillations, and distributed combustion effects.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Combustion instability with partial length acoustic liners


    Beteiligte:
    Mitchell, C. E. (Autor:in) / Espander, W. R. (Autor:in) / Baer, M. R. (Autor:in)

    Erscheinungsdatum :

    01.12.1974


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch