用数值方法模拟了液体火箭发动机燃烧室内有无隔板两种情况的热态解。气相控制方程用欧拉坐标系下的Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程组描述，液相控制方程在Ｌａｇｒａｎｇｉａｎ坐标系下进行描述。分析对比了两种情况下燃烧室内部各个流场参数值，验证了隔板体的数值处理方法对求解热态解的有效性 The numerical solution is used to simulate the thermal solution of two situations in the liquid rocket engine combustion chamber. The gas phase control equations are described by the Navier-Stokes equations in the Euler coordinate system and the liquid phase control equations are described in the Lagrangian coordinate system. The parameters of each flow field inside the combustion chamber are analyzed and compared in two cases, and the validity of numerical method for solving the thermal state solution is verified