Volume 39 Issue 11
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YANG Kun, TIAN Zemin, LIU Chongyang, et al. Numerical simulation and mechanism of flame flashback process based on model combustor[J]. Journal of Aerospace Power, 2024, 39（11）：20220948 doi: 10.13224/j.cnki.jasp.20220948
Citation: YANG Kun, TIAN Zemin, LIU Chongyang, et al. Numerical simulation and mechanism of flame flashback process based on model combustor[J]. Journal of Aerospace Power, 2024, 39（11）：20220948 doi: 10.13224/j.cnki.jasp.20220948
shu

Numerical simulation and mechanism of flame flashback process based on model combustor

doi: 10.13224/j.cnki.jasp.20220948
  • 1.

    College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

  • 2.

    Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Mianyang Sichuan 621000，China

  • Received Date: 2022-12-10
    Available Online: 2024-05-11
    Abstract

  • The boundary conditions and propagation process of flame flashback were experimentally obtained for aviation kerosene at different pressures in a premixed swirl model combustor. The reliable k-ε model of Reynolds average Navier-Stokes method, coupled with flamelet generated method (FGM), was applied to numerically capture the flame flashback. It was shown that the simulated critical pressure conditions were within 10% errors compared with the experimental results. Then the large eddy simulation method was used to reproduce the flame flashback process in detail. The analysis showed that the combination of fluctuations of pressure and density in the region near the exit of premix tube caused by increase of downstream pressure yielded reverse eddy with minus speed. As the reversed eddy was enlarged with the increase in downstream pressure, the hot flame outside the exit of premix tube was brought into the tube, which induced flame flashback. Then the flame in the premix tube propagated upstream due to the influence of baroclinic pressure.

     

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