Abstract: A physical mathematical model on the transpiration cooling of a liquid rocket thruster chamber was derived.A local non thermal equilibrium assumption between the coolant and the structural material of the thruster chamber was used in the model.In addition,the sharp variation of the thermophysical properties of the coolant(hydrogen)with temperature and pressure,and the longitudinal conduction in the solid wall were considered in the model.

Key words: Liguid propellant rocket engine;Thrust chamber;Sweat cooling;Heat transfer;Mathematical model

摘要： 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。

关键词: 液体推进剂火箭发动机;推力燃烧室;发汗冷却;传热;数学模型