There is considerable evidence based on both full scale firings and cold flow simulations that hydrodynamically unstable shear flows in solid propellant rocket motors can lead to acoustic pressure fluctuations of significant amplitude. Although a comprehensive theoretical understanding of this problem does not yet exist, procedures were explored for generating useful analytical models describing the vortex shedding phenomenon and the mechanisms of coupling to the acoustic field in a rocket combustion chamber. Since combustion stability prediction procedures cannot be successful without incorporation of all acoustic gains and losses, it is clear that a vortex driving model comparable in quality to the analytical models currently employed to represent linear combustion instability must be formulated.


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    Titel :

    Modeling of vortex generated sound in solid propellant rocket motors


    Beteiligte:
    Flandro, G. A. (Autor:in)


    Erscheinungsdatum :

    01.11.1980


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Solid propellant rocket motors

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    Testing solid-propellant rocket motors

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    Ignition-transient modeling for solid propellant rocket motors

    Alavilli, P. / Buckmaster, J. / Jackson, T. et al. | AIAA | 2000