液体火箭发动机推力室复合冷却流动与传热研究

To predict the compound cooling performance of the liquid rocket engine thrust chamber, the three-dimensional simulation model of regenerative cooling channel and supercritical hydrogen and the axisymmetric two-dimensional simulation model of gas and supercritical hydrogen film in thrust chamber were established. A numerical simulation method of compound cooling flow and heat transfer in liquid rocket engine thrust chamber was developed by means of boundary coupling. The flow and heat transfer of gas, supercritical film, chamber wall and regenerated coolant of space shuttle main engine thrust chamber were coupling calculated by numerical simulation. Results show that the simulation method adopted can predict the flow and heat transfer of gas and coolant well, and the maximum heat flux on the gas side wall is 129MW/m², the maximum wall temperature is 885K, the coolant temperature rise is 192K, and the pressure drop is 8.8MPa. The results are in good agreement with the existing data. The model and simulation method can be used to calculate the flow and heat transfer and optimize the cooling structure of the liquid rocket engine thrust chamber cooling system.