Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Reactive Fields Analysis of End-Burning Hybrid Combustor Using Tangential Oxidizer Injectors with Various Momentum Ratio

접선형 산화제 주입기의 운동량비에 따른 End-Burning 하이브리드 연소기의 연소유동장 해석

  • 민문기 (한국항공대학교 항공우주 및 기계공학과) ;
  • 김수종 (한국항공대학교 항공우주 및 기계공학부) ;
  • 김진곤 (한국항공대학교 항공우주 및 기계공학부) ;
  • 문희장 (한국항공대학교 항공우주 및 기계공학부)
  • Published : 2007.04.30
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Abstract

In this study, combustion fields of the end-burning hybrid combustor with tangential oxidizer injectors are examined. Momentum ratio of oxidizer is used as a main parameter to analyse the combustion efficiency with temperature, pressure, swirl velocity and mixture fraction field. It was found that as momentum ratio decreases the overall combustion efficiency is enhanced with the pressure field being insensitive to momentum ratio keeping quasi-uniform distribution. Irrespective to the momentum ratio, annular hot region commonly occurred in the upper combustion chamber where this phenomenon was left for a future improvement to be followed.

본 연구에서는 접선형 산화제 주입기를 갖는 end-burning 하이브리드 연소기에서 산화제 운동량비에 따른 연소 유동장을 해석하였다. 산화제의 운동량비가 감소할수록 연소효율은 연소기 전 영역에 걸쳐 증대되는 경향이 포착되었으며 이론 혼합분율과 온도장을 통해 연소실 전 영역에서 최적의 연소가 저 운동량비에서 발생됨을 확인하였다. 강한 선회류가 연소실 내부 유동장을 지배하지만 압력장은 비교적 균일한 분포를 보였다. 접선형 산화제 주입기를 가진 연소기는 운동량비에 관계없이 공통적으로 연료와 산화제가 만나는 연소실 상부에서 환형의 고온부가 발생했으며 향후 주요 개선 사항으로 판단되었다.

Keywords

References

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