Predicting instabilities in liquid rocket engines requires the ability to simulate unsteady reacting flows al high pressures. Intake manifolds, injector design and placement, addition of baffles and acoustic cavities add to the complexity and size of the computational problem at hand. The current effort is focused on the improvement of the basic building blocks which make up the simulation tool. The ability of the toll to track acoustic waves in a low Mach number, unsteady flow with chemical reactions was demonstrated.


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    Liquid rocket spray combustion stability analysis

    LITCHFORD, RON / JENG, SAN-MOU | AIAA | 1992


    Liquid Rocket Motor Combustion Stability Using Coaxial Injections

    Micci, M. M. / Air Force Office of Scientific Research | British Library Conference Proceedings | 1994


    Acoustic Stability Analysis of Liquid Propellant Rocket Combustion Chambers

    Kim, Seong-Ku / Kim, Hong / Seol, Woo et al. | AIAA | 2004


    Aspects of combustion stability in liquid propellant rocket motors

    Crocco, L. | Engineering Index Backfile | 1952


    Acoustic Stability Analysis of Liquid Propellant Rocket Combustion Chambers

    Kim, S.-K. / Kim, H. J. / Seol, W. S. et al. | British Library Conference Proceedings | 2004