偏二甲肼/四氧化二氮火箭发动机尾焰流场特性三维仿真研究  

Three-dimensional Simulation Study of UDMH/NTO Rocket Engine Plume Flow Field Characteristics

作　　者：吴睿[1] 聂万胜[1] 蔡红华[1] 乔野[1] 冯伟[1] 

机构地区：[1]中国人民解放军装备学院航天装备系,北京101416

出　　处：《导弹与航天运载技术》2016年第5期74-79,共6页Missiles and Space Vehicles

基　　金：国家自然科学基金项目(51206185;91441123)

摘　　要：以偏二甲肼/四氧化二氮(UDMH/NTO)火箭发动机为研究对象,采用κ-ε湍流模型,运用PISO算法分别对发动机内流-场和尾焰流场进行三维仿真。采用相同方法计算液氢/液氧(LH2/LOX)火箭发动机尾焰,仿真结果和试验结果吻合得较好,证明了计算模型的正确性与有效性;同时对比分析了UDMH/NTO发动机与LH2/LOX发动机尾焰流场特性。结果表明,两者具有相似的温度和马赫数变化趋势,但是UDMH/NTO发动机尾焰核心区温度相对较低,而LH2/LOX发动机尾焰将更快衰减至亚声速射流。This passage is modeled with UDMH/NTO rocket engine, and use the κ-ε turbulence model, PISO algorithm to simulate the rocket flow filed and exhaust plume flow field. With the compare between the simulation andexperiment of LH2/LOX rocket exhaust plume, the model is proved to be effective and correct. What＇s more, the characteristic analysis of plume flow field between UDMH/NTO engine and LH2/LOX engine shows that tendency of temperature and mach number are the same, but the UDMH/NTO engine exhaust plume has a core of lower temperature and LH2/LOX engine exhaust plume attenuation to the subsonic flow faster.

关 键 词：液体火箭发动机 三维数值仿真 尾焰流场特征 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]