液体火箭推力室微通道下的发汗冷却研究

The wall of liquid rocket thrust chamber is washed by high enthalpy flow for a long time, which brings great challenge to the stable and safe operation of the engine. In this paper, micro-scale wire mesh transpiration channel and macro-scale transpiration model of liquid rocket thrust chamber were established respectively to explore the flow heat transfer characteristics under the condition of transpiration cooling. The results show that the increase of coolant flow rate in the pore scale transpiration channel can significantly increase the flow rate in the channel and reduce the outlet temperature, and the small porosity can improve the heat transport capacity of the coolant. Within a certain range, the greater the flow rate of transpiration coolant, the higher the overall transpiration cooling efficiency of thrust chamber; The larger the porosity, the higher the cooling efficiency of thrust chamber contraction section.