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针对液体火箭发动机推力室的发汗冷却传热过程建立了数理模型。模型中考虑了冷却剂与结构材料之间存在温差、并进行对流换热，即采用了局部非热平衡模型。同时，模型中还计及了冷却剂（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过程。
A mathematical model was established for the sweat cooling heat transfer process of the liquid rocket engine thrust chamber. The model takes into account the temperature difference between the coolant and the structural material and performs convective heat transfer using a local non-thermal equilibrium model. At the same time, the model also takes into account the dramatic changes in the thermal properties of the coolant (hydrogen) with temperature and pressure and the thermal conduction along the axial direction of the solid wall.