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为准确预测液体火箭发动机推力室身部再生冷却换热状况,采用数值模拟方法,对燃气、推力室壁和超临界气氢进行三维流动和换热耦合计算。采用6组分9步反应动力学模型计算燃气的非平衡化学反应,采用DO模型计算燃气辐射换热,考虑超临界气氢物性随温度和压力的变化。获得了室壁温度场、燃气及冷却剂流场。结果表明,Redlich-Kwong方程、Peng-Robinson方程、Lucas法、TRAPP法能分别准确计算超临界氢的密度、定压比热容、粘度、导热系数,采用燃气非平衡流计算所得流场值更符合实际情况。
In order to accurately predict the regenerative cooling heat transfer in the thrust chamber of a liquid propellant rocket engine, a numerical simulation method was used to calculate the three-dimensional flow and heat transfer coupling of gas, thrust chamber wall and supercritical gas hydrogen. The 6-component 9-step kinetic model was used to calculate the non-equilibrium chemical reaction of gas. The DO model was used to calculate the radiative heat transfer of gas. The physical and chemical properties of supercritical gas and hydrogen with temperature and pressure were also considered. Obtained wall temperature field, gas and coolant flow field. The results show that the Redlich-Kwong equation, the Peng-Robinson equation, the Lucas method and the TRAPP method can accurately calculate the supercritical hydrogen density, the specific heat capacity at constant pressure, the viscosity, the thermal conductivity, and the flow field values calculated by the gas non-equilibrium flow, respectively Happening.