Abstract
The nonlinear stability characteristics of a liquid-propellant rocket motor with uniformly injected propellants, a distributed combustion process, and a multi-orifice nozle are investigated. It is shown that, for moderate amplitudes and low-Mach-number mean flow, the unsteady combustor flow can be described by a single nonlinear wave equation. This equation is solved with the aid of a modified version of the Galerkin method. Computed results predict the existence of both stable and unstable finite-amplitude limit cycles. It is shown that the amplitude of the pressure oscillation increases as one moves away from the linear stability limit. Decreasing the ratio ū e /z e and/or excitation of the radial modes improves the stability of the engine. Predicted nonlinear behavior as well as computed nonlinear waveforms are in agreement with experimental data as well as other theoretical predictions.
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