氢氧发动机推力室化学反应流场计算

Numerical Simulation of Chemical Reacting Flow in H 2/O 2 Rocket Engine Thrust Chamber

采用弱耦合点隐式方法的ＭａｃＣｏｒｍａｃｋ格式对氢氧火箭发动机推力室化学反应粘性流场进行数值模拟．数值模拟时采用６种组分、８个反应有限速率的化学反应模型，湍流模型采用ＢａｌｄｗｉｎＬｏｍａｘ代数湍流模型．数值模拟得到了流场参数在燃烧室和喷管中的分布．结果分析表明，得到的数值模拟结果与理论分析一致，说明结果是可靠的．本文的工作为氢氧火箭发动机喷管设计提供了依据，并为进一步开展火箭发动机推力室有化学反应的两相流动的数值模拟打下了基础．

The viscous chemical reacting flow in the hydrogen oxygen rocket engine chamber and nozzle is simulated by using loosely coupled point implicit MacCormack scheme. In the numerical simulation the combustion process is modeled by using a 6 specis, 8 step finite rate chemical reaction model, and the Baldwin Lomax algebraic turbulent model is adopted. The distributions of flow parameters in the chamber and nozzle are presented. Analysis of the results show that the numerical simulation results are the same as the distributions of flow parameters in the hydrogen oxygen rocket engine chamber and nozzle, so the result is proved to be reliable. The work of this paper lays a foundation for the numerical simulation of two phase chemical reacting flow.