Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle

As one of the most common methods to be used as the flame holding mechanism in the propulsion system of the integrated hypersonic vehicle, the research of cavity flame holder has drawn an ever increasing attention of many researchers. The two-dimensional coupled implicit NS equations, the standard k-ɛ turbulent models and the finite-rate/eddy-dissipation reaction model were employed to simulate the experimental items arranged by the orthogonal design, and the variance analysis method was used to investigate the effects of the geometric parameters of the cavity flame holder on the aero-propulsive performance of the integrated hypersonic vehicle, namely the depth, the ratio of length-to-depth and the sweepback angle. The obtained results show that the geometric parameters make only a little difference to the aero-propulsive performance of the vehicle in the range considered in this paper, and the cavity flame holder with its sweepback angle 45° can satisfy the performance requirement of the integrated hypersonic vehicle further. The hydrogen injected from the upper stream of the cavity makes the boundary layer separate on the lower wall of the engine, and a separate region appears in the upper stream and down stream of the injection slot, respectively.

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