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Effects of cooling flow on the flow structure and acoustic oscillation in a swirl-stabilized combustor. Part II: Acoustic analysis

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Abstract

The proper orthogonal decomposition (POD) analysis was implemented to extract the acoustic modes from the flow field inside a swirl-stabilized combustor obtained from non-reacting large eddy simulation. The major frequencies and the spatial distribution of fluctuating pressure of dominant POD modes were presented. The first four dominant modes occupied more than 70 % of the total energy of the oscillatory flow fields. Cooling flow injection suppressed the amplitude of pressure fluctuation and tended to dissipate the high-order longitudinal acoustic modes. The dominant acoustic modes observed in the fluctuating pressure field in the case with no cooling flow injection were dissipated or shifted by the injection of cooling flow.

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Acknowledgments

This research was supported by Korea Research Foundation Grant (KRF-2010-0024204) and National Space Laboratory (NSL) Program (No. 2008-2006287) through the National Research Foundation of Korea (NRF) funded by the Ministry of Education, Science and Technology.

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Authors and Affiliations

  1. High-Speed Propulsion and Combustion Control Lab., Department of Aerospace and Mechanical Engineering, Korea Aerospace University, Gyeonggi-do, 412-791, Korea

    Hong-Gye Sung, Kwang-Hee Yoo & Jong-Chan Kim

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  1. Hong-Gye Sung
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  2. Kwang-Hee Yoo
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  3. Jong-Chan Kim
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Correspondence to Hong-Gye Sung.

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Sung, HG., Yoo, KH. & Kim, JC. Effects of cooling flow on the flow structure and acoustic oscillation in a swirl-stabilized combustor. Part II: Acoustic analysis. J Vis 17, 69–76 (2014). https://doi.org/10.1007/s12650-013-0193-y

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  • DOI: https://doi.org/10.1007/s12650-013-0193-y

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