小型气氧/煤油火箭发动机试验及内流场数值模拟

Experiment and Internal Flow Field Numerical Simulation of an Experiment-scale Kero/GOX Liquid Rocket Engines

火箭发动机热试车过程中测量手段有限,为了详细展示试验发动机内流场各参数分布特征,指导发动机气膜冷却设计,针对热试车工况分别采用单步总包反应和9组分14步的化学反应模型进行三维数值计算。两种化学反应模型的计算结果对比显示,内流场压强分布基本相同且与试验测量值一致;内流场的温度和组分分布存在较大区别;单步化学反应内流场温度值比多步化学反应内流场温度值高;燃烧室高温区主要集中在燃烧室收敛段与喉部之间,验证了设置N2膜冷却系统的必要性,数值计算结果可以为气膜冷却系统的设计提供指导。

The measurement method is limited during the hot-test of rocket engine,in order to details each parameter distribution of internal flow field and guide the design of thin film cooling system,both single-step global reaction model and9components14chemical reaction model are used for three-dimensional numerical simulation which is on the basis of the hot-test.The numerical simulation results of two chemical reaction models are compared and show that the pressure results of the internal flow field are almost the same and accord with the experiment pressure value.However,there is a big difference between the two numerical simulation results in temperature and components distribution.The temperature of single-step global reaction model is higher.The necessity of N2thin film cooling system is verified by high temperature area between convergent section and throat,and the design of N2thin film cooling system could be directed by the numerical simulation results.