The Simulation Of Supercritical Hydrogen-oxygen Engine Combustion And Heat Transfer

The liquid rocket engine is the main power equipment on launch vehicle,because of the characteristics of high reliable,stable performance,adjustable thrust and reusability.Traditional engine design method mainly relies on the hot firing test,but this method costs too much time and money,besides that,there are potential security risks in this method.The practice has proved that the method of combining the numerical simulation and hot firing test is the best way to design a rocket engine.This paper simulated the combustion and heat transfer process respectively,and realized the coupling simulation of the two processes artificially.Used SST k-w model to simulate the turbulent flow in combustion domain,and used standard k-e model to simulate the heat transfer domain.Simulated the heat conduction and heat convection in heat transfer process.Used non-premixed combustion model to simulate the combustion process.Used SRK real gas equation to definite the density of propellant and the gas.Combined the UDF and empirical formulas to definite the physical property parameters of propellant and the gas.The physical parameters of the coolant in subscale thrust chamber were set as a function of temperature,and the physical parameters of the coolant in full scale thrust chamber were set as a function of temperature and pressure.In this paper,the combustion process and heat transfer process of a subscale thrust chamber were simulated by numerical simulation method.The simulation results were compared with the experimental data to verify the accuracy of the simulation model.The simulation results were presented in the form of data diagrams and physical field contours.This paper explained the reasons for high temperature area in the combustion region,explained the wall temperature difference along the circumferential direction,and explained the difference of coolant properties in different channels.Four simulation conditions were designed for the subscale thrust chamber model,the influence of coolant flow direction and propellant mass flow on the combustion and heat transfer process of the thrust chamber was studied respectively.The results showed that the coolant flow direction had no influence on the combustion process,but it would affect the temperature distribution of the thrust chamber wall.The increase of mass flow rate of propellant can lead to the increase of chamber pressure and the coolant temperature variation in the wall of thrust chamber,but it has little effect on combustion efficiency.The same numerical simulation method was used to simulate the combustion and heat transfer process in full scale engine thrust chamber.Compared with the result of hot firing test,the simulation results of combustion efficiency was 2.95% lower than the test data,the coolant temperature rise lower than the test data,and validated the accuracy of simulation method to simulate the combustion process and heat transfer process in full scale engine thrust chamber..The simulation results were presented in the form of data diagrams and physical field contours.This paper explained the reasons for high temperature area in the combustion region,explained the wall temperature difference along the circumferential direction,and explained the variation of coolant properties in channels.