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本文采用非正交曲线坐标系下非交错网格的SIMPLE方法对航空发动机加力燃烧室无化学反应的湍流流场进行了数值计算，湍流模型采用k-ε双方程模型．差分网格采用分区方法生成，计算时对整个流场进行分区迭代直至得到收敛结果．加力燃烧室湍流流场数值计算结果合理．
In this paper, the SIMPLE method of non-staggered grid in non-orthogonal curvilinear coordinate system is used to calculate the turbulent flow field without chemical reactions in the afterburner of aeroengine. The turbulence model is k-ε two-equation model. The differential grid is generated by the partition method, and the entire flow field is partitioned and iterated until the convergence result is obtained. The numerical results of turbulent flow field in afterburner are reasonable.