What is it about?
Thermoacoustic instabilities of combustion pose a severe challenge to the development of aero and rocket engines. This type of self-excited instability results from feedback between fluctuations of heat release and acoustics in the combustion chamber. To order to increase damping of fluctuations and thus combustion stability, one frequently adds resonators to a combustor. Our paper uses a low-order model based on acoustic eigenmodes in a cylindrical combustion chamber to create a stability map, with emphasis on the effect of resonators on stability margins.
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Why is it important?
It is well understood that damping is maximized if the eigenfrequency of the resonator is properly tuned to the frequency of the instability. Our study shows that in order to tune a resonator in an optimal manner, it is necessary to consider the coupled system "resonator & combustion chamber" in the analysis.
Perspectives
If find it particularly satisfying to see that the low-order modelling approach affords results at low computational cost. As an added benefit, the low order method can providing more insight into problem physics and relevant design parameters than high resolution simulation strategies.
Professor Wolfgang Polifke
Technische Universitat Munchen
Read the Original
This page is a summary of: Mapping the Influence of Acoustic Resonators on Rocket Engine Combustion Stability, Journal of Propulsion and Power, July 2015, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.b35660.
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