双机并联氢氧火箭发动机尾焰流场特性三维数值仿真研究  

Three-dimensional Numerical Simulation of Couple LOX/LH_2 Engine Plume Characteristics in Parallel-running

作　　者：乔野[1] 聂万胜[1] 吴高杨 冯伟[1] 丰松江[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》2015年第5期30-34,共5页Missiles and Space Vehicles

基　　金：国家自然科学基金(51206185;91441123)

摘　　要：以氢氧火箭发动机为模型,采用耦合可实现k-ε湍流模型的N-S方程,对发动机在地面发射阶段双机并联工作状态下的尾焰流场进行数值仿真研究,得到尾焰流场的各项参数分布及其变化规律,与理论分析结果对比,证明了算法的有效性和正确性,为开展多台发动机并联工作下尾焰的撞击和辐射特性等研究奠定了基础。This passage is modeled with LOX/LH2 rocket engine, and uses the N-S equation coupled with realizable k-ε model to conduct numerical simulation research on the rocket plume flow field in the two-generator parallel-running station during the launch. The distribution and change rules of different parameters in the plume field have been gained. With the compare between the simulation data and the theoretical result, the algorithm is proved to be effective and correct. With that, a great foundation will be laid for the study of the plume impact and radiation in multi-generator parallel-running.

关 键 词：液体火箭发动机 双机并联 尾焰 数值仿真 激波 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]