Modeling and dynamics of nonlinear acoustic waves in a combustion chamber
Future combustors designed for better efficiency and lower pollutant emission are expected to operate closer to their stability boundary, thereby increasing the risk of encountering combustion instability. Onset of combustion instability leads to limit cycle oscillations in the acoustical fluctuations that can often reach amplitudes large enough to cause severe damage. Active control strategies are, therefore, being considered to prevent combustion instabilities, but their development requires nonlinear models that can faithfully capture the combustor system dynamics. A framework for the approximate analysis of the nonlinear acoustics in a combustion chamber exists, which includes all relevant linear contributions and also second order gasdynamic nonlinearities. Nonlinear combustion effects in the form of pressure and velocity coupling models have also been incorporated into the analysis with the aim of capturing the phenomenon of triggered instability, where the acoustical fluctuations are linearly stable to small perturbations, but show a limit cycle behavior for larger perturbations. However, several questions such as those relating to 1) modal truncation of the equations for the acoustic dynamics, 2) absence of triggered limit cycles in the formulation with only second order gasdynamic nonlinearities, and 3) the form of the velocity coupling function, including the need for a threshold character, have not been satisfactorily resolved. In this paper, we address some of these questions on modeling and dynamics of acoustic waves in combustion chambers, using the approximate analysis, that have remained unanswered over the years.
© 2002 AIAA. This work was supported in part by the California Institute of Technology; partly by the Caltech Multidisciplinary University Research Initiative under Grant No. N00014-95-1-1338 (Dr. Judah Goldwasser, Program Manager); partly by the Department of Energy Advanced Gas Turbine Systems Research (AGTSR) Program under Subcontract No. 98-02-SR072 (Dr. Larry Golan, Program Manager); and partly by the Air Force Office of Scientific Research (AFOSR) under Grant No. F49620-99-1-0118 (Dr. Mitat Birkan, Program Manager).
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