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提出了描写航空发动机加力燃烧室内气液两相湍流燃烧的控制方程，采用了双流体模型，高温辐射通量模型，双时间尺度湍流Ｋ－ε模型，应用ＳＩＭＰＬＥ方法解这组方程，对二维轴对称的涡喷加力燃烧室进行计算，证明应用本文的液雾燃烧模型可以得出合理的计算结果。
A control equation describing the two-phase turbulent combustion of gas-liquid two-phase in aero-engine afterburner is proposed. Two-fluid model, high-temperature radiation flux model and dual time-scale turbulent K- Axisymmetric turbo-charged afterburner to prove that the reasonable calculation results can be obtained by applying the liquid mist combustion model in this paper.