发动机推力室燃烧及传热耦合仿真  

Simulation of Combustion and Heat Transfer in Full Scale Engine Thrust Chamber

作　　者：韩长霖 田原[1] Han Chang-lin;Tian Yuan(Beijing Aerospace Propulsion Institute,Beijing 100076)

机构地区：[1]北京航天动力研究所

出　　处：《导弹与航天运载技术》2020年第1期48-53,共6页Missiles and Space Vehicles

摘　　要：为了研究推力室工作时内部物理场特点,以某推力室试验件为研究对象,采用独立计算,边界耦合的仿真思想,对推力室的燃烧和传热过程进行仿真,当相邻两次温度误差在1%之内时认为仿真收敛。分析发现推力室壁面在喉部达到最高温度;由于流动通道中冷却剂的流量不同,推力室壁面周向温度分布不均匀;受流动通道横截面积的影响,冷却剂的流速变化剧烈。To study the state of the physical field in the thrust chamber,the combustion and heat transfer process of a thrust chamber are simulated by numerical method.The simulation is considered to be convergent when the current and latter temperature errors are within 1%.The results indicate that the maximum temperature of the thrust chamber appears near the throat.Because of the different coolant mass flow in every channel,the circumferential temperature distribution of the thrust chamber wall is not uniform.The velocity of coolant changes dramatically,which is mainly caused by the change of cross-sectional area.

关 键 词：火箭发动机 推力室 燃烧仿真 传热仿真 

分 类 号：V434.13-14[航空宇航科学与技术—航空宇航推进理论与工程]