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[1]乔 野,聂万胜,丰松江,等.液氢/液氧火箭发动机尾焰流场特性仿真研究[J].火箭推进,2015,41(05):43-48.
　QIAO Ye,NIE Wansheng,FENG Songjiang,et al.Simulation research on fluid field characteristics of LH2/LOX rocket engine plume[J].Journal of Rocket Propulsion,2015,41(05):43-48.
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液氢/液氧火箭发动机尾焰流场特性仿真研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年05期 页码: 43-48 栏目: 研究与设计 出版日期: 2015-10-31
Title:
Simulation research on fluid field characteristics of LH2/LOX rocket engine plume
作者:
乔 野; 聂万胜; 丰松江; 蔡红华; 吴高杨
中国人民解放军装备学院，北京101416
Author(s):
QIAO Ye;  NIE Wansheng;  FENG Songjiang;  CAI Honghua;  WU Gaoyang
Equipment Academy of PLA, Beijing 101416, China
关键词:
尾焰; 液氢/液氧火箭发动机; 单步化学反应; 冲击波; 数值仿真
Keywords:
exhaust plumeLH2/LOX rocket engineone-step chemical reactionshock wavenumerical simulation
分类号:
V434-34
文献标志码:
A
摘要:
为研究液氢/液氧发动机燃烧尾焰射流流动特点，采用耦合了Realizable k-ε湍流模型、液氢/液氧单步化学反应的N-S方程，化学反应速率采用湍流脉动机制和Arrhenius机制控制，运用PISO算法对液氢/液氧火箭发动机在地面发射阶段的燃烧尾焰射流流场进行了一体化仿真计算，得到了液氢/液氧发动机燃烧尾焰射流近场激波系结构，并与理论分析结果进行对比，证明了算法的有效性和正确性。分析了燃烧尾焰压力场的动态形成过程，捕捉到尾焰半球形冲击波的发展过程，并认为冲击波为正激波且进行匀速传播。获得了尾焰流场各项参数的分布情况，为开展燃烧尾焰射流的辐射计算提供数据基础。
Abstract:
To research the burning plume exhaust flow field of LH2/LOX rocket engine, the N-S equation is adopted, in which Realizable model and the LH2/LOX one-step chemical reaction are coupled. The chemical reaction rate is controlled by Eddy-Dissipation and Arrhenius Mechanism. The integration simulation calculation of the LH2/LOX rocket engine plume during the period of launch was performed with PISO algorithm, by which the shock wave system structure of the plume jet flow in the near field is acquired and compared with the theoretical analysis results. The effectiveness and correctness of this algorithm is proved. The dynamical forming process of the burning plume pressure field is analyzed, the developing process of the hemispheric impact wave has been gain, and it is considered that the impact wave is a normal shock wave and moves in the uniform velocity. The distribution of different parameters in the plume field has been acquired, which can provide a data foundation for the study on radiation of the plume jet flow.

参考文献/References:

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相似文献/References:

[1]丰松江,聂万胜,解庆纷,等.燃烧室内燃烧模型对尾焰流场及其辐射的影响[J].火箭推进,2006,32(02):6.
　Feng Songjiang,Nie Wansheng,Xie Qingfen,et al.Influence of combustion model in chamber on exhaust plume flow field and radiance[J].Journal of Rocket Propulsion,2006,32(05):6.

备注/Memo

收稿日期：2015-01-08；修回日期：2015-06-29 基金项目：国家自然科学基金（51206185，91441123）

更新日期/Last Update: 1900-01-01