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2019 Vol.24, Issue 4 Preview Page

Research Article

Analysis of Combustion Instability in a GH2/GO2 Rocket combustor by Adopting Short Time Fourier Transform and Dynamic Mode Decomposition

STFT와 DMD를 이용한 GH2/GO2 로켓 연소기의 연소불안정성 분석

Minseok Kwak1
,
Truyen Luong Hung1
,
Hee Sun Han1
,
Chae Hoon Sohn1*
,
Seung-Min Jeong2
,
Jeong-Yeol Choi2
곽 민석1
,
Hung Truyen Luong1
,
한 희선1
,
손 채훈1*
,
정 승민2
,
최 정열2
1Department of Mechanical Engineering, Sejong University
2Department of Aerospace Engineering, Pusan National University
1세종대학교 기계공학과
2부산대학교 항공우주공학과
* Corresponding Author
30 December 2019. pp. 31-36
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Abstract

The post-processing analysis tools, Short Time Fourier Transform (STFT) and Dynamic Mode Decomposition (DMD) were applied to analyze dynamic characteristics of the GH2/GO2 rocket model combustor. The STFT analysis was performed with pressure data in the chamber to exhibit the appearance of frequency components at instant time. The STFT results indicate resonant frequencies of signal through their amplitudes. DMD analysis was conducted with the planar pressure data to extract the resonant frequencies and damping coefficients of acoustic modes. The damping coefficient is a parameter to evaluate the stability of a certain pressure oscillation in a dynamic system. By combining the results of STFT and DMD, the appearance of the resonant frequencies causing unstable combustion can be determined.

Keywords
Rocket combustion
Combustion instability
Dynamic mode decomposition
Short time fourier transform

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Information
  • Publisher :The Korean Society Combustion
  • Publisher(Ko) :한국연소학회
  • Journal Title :Journal of The Korean Society Combustion
  • Journal Title(Ko) :한국연소학회지
  • Volume : 24
  • No :4
  • Pages :31-36
  • Received Date : 2019-10-07
  • Revised Date : 2019-11-22
  • Accepted Date : 2019-12-02
  • DOI :https://doi.org/10.15231/jksc.2019.24.4.031
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