液体火箭发动机推力室粘性流场数值模拟和实验验证  

Numerical simulation and experimental validation for viscous flow field in rocket engine chamber

作　　者：费继友[1] 俞炳丰[1] 张杰[1] 夏学礼[2] 高强[1] 

机构地区：[1]西安交通大学能源与动力工程学院,陕西西安710049 [2]第二炮兵工程学院,陕西西安710025

出　　处：《推进技术》2003年第4期292-295,共4页Journal of Propulsion Technology

摘　　要：运用耦合点隐式方法的MacCormak两步差分格式结合k ε湍流模型求解肼类燃料发动机推力室中的粘性化学反应流动。化学反应采用17种组分,12个主要反应的有限速率的化学反应模型,得到了流动参数在推力室中的分布情况。其结果同理论分析的相一致,最后用实验验证了用数值模拟方法的正确性,研究结果对发动机的设计、性能和理论研究具有重要的实际意义和参考价值。To solve the viscous chemical reacting flow governing equations in the species of hydrazine fuel rocket engine thrust chamber, MacCormak two-step difference scheme with coupled-implicit method combined with the k-Ε turbulence model was applied. In chemical reaction model, there were 17 species and 12 limit speed chemical reactions. The results agree well with the theoretical analysis. Finally, numerical simulation is validated by experiment. The results are useful and important to the design, performance improvement and theoretical exploration for rocket motor.

关 键 词：液体推进剂火箭发动机 流动分布 数值仿真 推力燃烧室 纳维尔.斯托克斯方程 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]