Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Numerical Study of High Resolution Schemes for GH2/GO2 Rocket Combustor using Single Shear Coaxial Injector

단일 전단 동축 분사기를 가지는 GH2/GO2 로켓 연소기의 고해상도 수치해석

  • Jeong, Seung-Min (Department of Aerospace Engineering, Pusan National University) ;
  • Um, Jae-Ryeong (Satellite System Team, Korea Aerospace Industries LTD) ;
  • Choi, Jeong-Yeol (Department of Aerospace Engineering, Pusan National University)
  • Received : 2018.04.25
  • Accepted : 2018.08.02
  • Published : 2018.12.01
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Abstract

In this study, a series of CFD analyses were carried out for a hydrogen rocket combustor with a single shear coaxial injector. A hybrid RANS/LES approach was used for the turbulent combustion analysis with a two-dimensional axisymmetric configuration. Three reaction mechanisms, three spatial discretization methods, and three levels of grid resolution were compared to determine an appropriate CFD approach. The performance of the CFD prediction were investigated by comparing the wall heat flux with experimental data. Investigation of the flow field results provides an insight into the characteristics of the turbulent reacting flow of a rocket combustor with a shear coaxial injector.

본 연구에서는 단일 전단 동축 분사기를 이용한 수소 로켓 연소기의 전산유체 해석을 수행하였다. 2차원 축대칭 형상에서 난류연소 해석을 위해 hybrid RANS/LES 난류모델을 적용하였다. 적합한 해석기법을 찾기 위해 3가지 화학 반응기구, 3가지 고해상도 기법 및 3단계 격자해상도 조합을 비교하였다. 벽면 열유속을 실험결과와 비교하여 해석 성능을 살펴보았으며, 유동장 결과 분석으로 동축 분사기를 가지는 로켓 연소기의 난류연소특성을 살펴볼 수 있었다.

Keywords

References

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