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Volume 24 Issue 6
Jun.  1998
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Journal of Beijing University of Aeronautics and Astronautics  > 1998  >  24(6): 671-675.
Cai Guobiao, Zhang Huazhao, Zhuang Fengganet al. Numerical Simulation of Chemical Reacting Flow in H2/O2 Rocket Engine Thrust Chamber[J]. Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(6): 671-675. (in Chinese)
Citation: Cai Guobiao, Zhang Huazhao, Zhuang Fengganet al. Numerical Simulation of Chemical Reacting Flow in H2/O2 Rocket Engine Thrust Chamber[J]. Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(6): 671-675. (in Chinese)
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Numerical Simulation of Chemical Reacting Flow in H2/O2 Rocket Engine Thrust Chamber

  • 1.

    Beijing University of Aeronautics and Astronautics,School of Astronautics

  • 2. Beijing Institute of Space System Engineering

  • 3. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics

  • Received Date: 09 Apr 1998
  • Publish Date: 30 Jun 1998
    Abstract
  • The viscous chemical reacting flow in the hydrogen-oxygen rocket engine chamber and nozzle is simulated by using loosely coupled point-implicit MacCormack scheme. In the numerical simulation the combustion process is modeled by using a 6-specis, 8-step finite-rate chemical reaction model, and the Baldwin-Lomax algebraic turbulent model is adopted. The distributions of flow parameters in the chamber and nozzle are presented. Analysis of the results show that the numerical simulation results are the same as the distributions of flow parameters in the hydrogen-oxygen rocket engine chamber and nozzle, so the result is proved to be reliable. The work of this paper lays a foundation for the numerical simulation of two-phase chemical reacting flow.

     

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    • References(1)
  • 1. Evans J S,Schexnayder C J. Critical influence of finite rate chemistry and unmixdness on ignition and combustion of supersonic H2-air streams. AIAA Paper 79-0355,1979 2. Drummond J P,Rongers R C,Hussaini M Y.A detail numerical model of a supersonic reacting mixing layer.AIAA Paper 86-1427,1986 3. Imlay S,Eberhardt S.A diagonal implicit scheme for computing flow with finite-rate chemistry.AIAA Paper 90-1577,1990 4. 刘国球,任汉芬,朱宁昌,等编.液体火箭发动机原理.北京:宇航出版社,1993
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