C-H-O-N体系液体火箭发动机喷管流场数值模拟  

Numerical simulation of C-H-O-N system liquid rocket engine nozzle flow

作　　者：蔡国飙[1] 马朝恺[1] 张化照 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]北京宇航系统工程研究所,北京100076

出　　处：《推进技术》2002年第5期391-393,共3页Journal of Propulsion Technology

基　　金：国家"八六三"基金资助项目。

摘　　要：采用弱耦合点隐式方法的MacCormack格式对C H O N体系的液体火箭发动机喷管内粘性流场进行了数值模拟,采用了考虑化学反应和不考虑化学反应的两种模型,其中化学动力学模型为C H O N体系的12组分、14反应有限速率的化学反应模型。数值模拟得到了流场参数在喷管中的分布。结果表明,数值模拟结果与理论分析一致,为发动机的设计及试验提供了参考。The viscous flow in the C-H-O-N system liquid rocket engine nozzle was simulated by using the loosely coupled point-implicit MacCormack scheme. The reacting model and non-reacting model were used in the simulation, and a 12-species, 14-steps finite-rate chemical reaction model was adopted in the C-H-O-N reacting model. The distribution of low parameters in the nozzle were presented. The analysis of the results shows that the numerical simulation results are in accordance with the theoretical distribution of flow parameters in the nozzle. The numerical results provide a reference for the design and experiment of the rocket engine.

关 键 词：液体推进剂火箭发动机 发动机喷管 喷管气流 流动分析 反应动力学 数值仿真 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程] V434