应用计算流体动力学方法对液体火箭发动机燃烧室内高频不稳定燃烧现象进行了数值仿真。气相方程用欧拉坐标系下的Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程组描述，液相控制方程用Ｌａｇｒａｎｇｉａｎ坐标系下进行描述，湍流模型采用高雷诺数的ｋ－ε双方程模型。在燃烧室内加入正弦形脉冲扰动评定燃烧稳定性。引用Ｒａｙｌｅｉｇｈ热释放声放大机理对计算结果进行了分析，并对不同的扰动系数和液滴初始直径描出了燃烧稳定性极限图 The computational fluid dynamics (CFD) method is used to simulate the high frequency instability combustion in liquid rocket engine combustion chamber. The gas-phase equation is described by the Navier-Stokes equations in the Eulerian coordinate system. The liquid-phase governing equations are described in the Lagrangian coordinate system. The turbulence model uses the k-ε two-equation model with high Reynolds number. Sine pulse perturbation was added to the combustion chamber to evaluate the combustion stability. The Rayleigh heat release amplification mechanism is used to analyze the calculation results and the combustion stability limit maps are described for different disturbance coefficients and initial droplet diameters