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对液体火箭发动机推力室发汗冷却传热过程的二维局部非热平衡模型进行了数值计算。计算中采用了正交曲线坐标系（贴体坐标），并计及了冷却剂（氢）的热物性参数随温度和压力的剧烈变化及固体壁沿轴向的导热。结果表明：推力室多孔壁面中靠近燃烧室的部分温度梯度很大；固体骨架与冷却剂的温度差异在推力室内壁面上最大；推力室多孔壁面材料导热系数的提高有利于降低壁面温度及温度梯度；随着冷却剂流量的增大，推力室壁中的最高温度明显下降；若设计合理，发汗冷却所需要的冷却剂的量只占总流量的２％左右。
The two-dimensional local non-thermal equilibrium model of sweat cooling heat transfer in a liquid rocket engine thrust chamber is numerically calculated. The orthogonal curvilinear coordinates (body coordinates) are used in the calculation, and the dramatic changes in the thermal properties of the coolant (hydrogen) with temperature and pressure and the thermal conductivity along the axial direction of the solid wall are taken into account. The results show that the temperature gradient near the combustion chamber in the porous wall of the thrust chamber is very large. The temperature difference between the solid skeleton and the coolant is the largest on the thrust chamber wall. Increasing the thermal conductivity of the porous wall material in the thrust chamber is helpful to reduce the wall temperature and temperature gradient ; As the coolant flow rate increases, the maximum temperature in the thrust chamber wall significantly drops; if properly designed, the amount of coolant required for sweat cooling accounts for only about 2% of the total flow rate.