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Volume 42 Issue 6
Jun.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(6): 1195-1202.
FENG Wei, NIE Wansheng, LI Bin, et al. Numerical analysis of unstable combustion developing process in model combustor[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(6): 1195-1202. doi: 10.13700/j.bh.1001-5965.2015.0457(in Chinese)
Citation: FENG Wei, NIE Wansheng, LI Bin, et al. Numerical analysis of unstable combustion developing process in model combustor[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(6): 1195-1202. doi: 10.13700/j.bh.1001-5965.2015.0457(in Chinese)
shu

Numerical analysis of unstable combustion developing process in model combustor

doi: 10.13700/j.bh.1001-5965.2015.0457
  • 1.

    Department of Space Equipment, Equipment Academy, Beijing 101416, China

  • 2. Xi'an Aerospace Propulsion Institute, Xi'an 710100, China

  • Received Date: 08 Jul 2015
  • Publish Date: 20 Jun 2016
    Abstract
  • Gas-liquid two-phase unsteady combustion process was simulated with the Euler-Lagrange method to analyze the combustion instability, which was observed in hypergolic propellant combustor. The pressure oscillations amplitude and spectral characteristics agreed with the experimental results. And the variation rule of pressure and heat release in different combustion stages was analyzed. The results indicate that, while the pressure oscillation amplitudes exceed 10% of the average pressure, the pressure oscillation frequency is 9 200 Hz, and the transverse pressure distribution is in accordance with the first-order tangential vibration mode. The generation and developing process of the first-order tangential self-excited high frequency unstable combustion have been reproduced in simulation. At the early stage of the change from stable to unstable combustion, the pressure oscillation obtains energy from part of the combustion heat release fluctuations and the pressure oscillation amplitude increases slowly. With the combustion, the phase and spectral characteristics between the combustion heat release and pressure oscillation tend to be the same, and the pressure oscillation increases sharply. When they are fully coupled, the pressure oscillation amplitude in combustion chamber exceeds 200% of average chamber pressure and reaches the limits of saturation.

     

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