Abstract: To better predict the regeneratively cooled liquid rocket engine thrust chamber heat transfer. Three dimensional numerical simulation was carried out for hot gas,solid wall and coolant coupled flow and heat transfer.The 9 steps with 6 specices chemical reaction model was used to simulate gas non-equilibrium chemical reactions. The radiative heat transfer was simulated with DO model.The coolant is supercritical hydrogen whose thermophysical properties are varied with both temperature and pressure.The results show that Redlich-Kwong equation of state,Peng-Robinson equation of state,Lucas method,TRAPP method can be used to predict hydrogen density,specific heat at constant pressure,viscosity,thermal conductivity,respectively.The simulated results using non-equilibrium flow are more accordant with real condition. 

Key words: Regenerative cooling;Nonequilibrium flow; Fluid flow;Heat transfer;Numerical simulations

摘要： 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。

关键词: 再生冷却;化学非平衡流;流动;传热;数值仿真