Nonlinear Interactions between Vortices and Acoustic Waves in a Rocket Combustion Chamber,
UTAH UNIV SALT LAKE CITY
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In order to carry out useful predictive analyses of solid propellant rocket or ramjet combustion oscillation problems, it is necessary that all loss and gain mechanisms be accounted for. Recent motor experience has demonstrated that flow of oscillatory energy from vortex shedding to the acoustic field of the chamber is one of these mechanisms in the ramjet problem it is probably the major source of oscillatory behavior. The coupling between the vortex instability which arises in regions of highly sheared flow and the chamber acoustic field represents a problem of great complexity. In this paper, a detailed analysis is described which addresses several basic features of this coupling. Some of the goals of the analysis are 1 Determine growth rate corrections for use in standard stability assessment codes, 2 Determine the limit cycle processes of the vortical region of flow, and 3 Assess the global limiting behavior of the coupled nonlinear acousticalvortical flow.