Research on Flow and Heat Transfer of Regenerative Cooling in Thrust Chamber of Space Orbit Control Engine

To study the liquid film regeneration composite cooling effect of space track control engines, a model including combustion flow, gas radiation, liquid film cooling, wall heat conduction, regenerative cooling, and wall radiation cooling is proposed, based on a coupled heat transfer calculation method using thermal boundary data transfer. This coupled heat transfer method was used for numerical simulation of a 5 kN regenerative cooling liquid rocket engine. The results show that as the edge flow rate increases, the complete evaporation distance of the liquid film becomes longer, and the gas-side heat flux and coolant temperature rise decrease significantly. As the combustion chamber length decreases, the segment of the coolant temperature rise shortens, resulting in a decrease in the overall coolant temperature rise. Increasing the height of the regenerative cooling channel improves the cooling effect. This can better predict the performance of regenerative cooling liquid rocket engines and provide reference support for cooling channel design.