航天推进技术研究院主办
[1]杜飞平,谭永华,陈建华.超燃燃烧室内流场数值模拟研究[J].火箭推进,2011,37(04):28-34.
DU Fei-ping,TAN Yong-hua,CHEN Jian-hua.Numerical simulation of flow field in hypersonic combustion chamber[J].Journal of Rocket Propulsion,2011,37(04):28-34.
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DU Fei-ping,TAN Yong-hua,CHEN Jian-hua.Numerical simulation of flow field in hypersonic combustion chamber[J].Journal of Rocket Propulsion,2011,37(04):28-34.
超燃燃烧室内流场数值模拟研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
37
期数:
2011年04期
页码:
28-34
栏目:
研究与设计
出版日期:
2011-08-15
- Title:
- Numerical simulation of flow field in hypersonic combustion chamber
- 文章编号:
- 1672-9374(2011)04-0028-08
- Keywords:
- hypersonic combustion chamber; one-dimensional flow field simulation; three-dimensional flow field simulation
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 对超燃燃烧室的高速流动与燃烧的耦合流场进行了一维和三维数值模拟，揭示了其流场的本质和各个参数的关系。首先阐述了超燃燃烧室一维流动特性，然后分析了一维流动模型，获得了芯流面积的计算公式。将一维流动模型应用到实际超燃燃烧室中，与试验数据对比，误差小于5%，并且选出了最优模型。由于一维模型仅能模拟轴向的一维参数变化规律，不能充分反映超燃燃烧流场的详细参数分布，而且二维计算中燃料的喷注不能得到完全真实的模拟, 因此为了能更为详细地获得流场各个参数，进行了三维NS方程数值模拟，在计算中考虑了中间一步反应模型，非绝热再附着段的计算结果误差小于2%，满足精度要求，获得了超燃燃烧室的流场全貌，弥补了一维分析模型的不足。
- Abstract:
- The 1D and 3D numerical simulations of the coupled flow field with high-speed flow and combustion in a hypersonic combustion chamber are carried out, by which the flow nature and the relationship between parameters are enunciated. The characteristic of 1D flow field in the hypersonic combustion chamber is elaborated. The one-dimensional flow model is analyzed to obtain the formula of the core flow area. The one-dimensional flow model applied to the actual supersonic chamber was compared with the experimental data. It is found that the error is less than 5%. The optimal model was selected by the comparison and analysis. Since one-dimensional numerical simulation can only simulate the variation law of the axial 1D parameters but can not adequately reflect the parameter distribution of the hypersonic combustion flow field, and the fuel injection can not be completely simulated in 2D calculation, 3D NS equation numerical simulation is conducted to obtain the detailed flow field parameters. The one step reaction model was considered in the calculation. The calculated error of the non-adiabatic reattachment stage is less than 2%. It meets the accuracy requirements. The eventual results show that 3D numerical simulation can reflecte the flowpath of the hypersonic combustion chamber, and make up the short of 1D model.
备注/Memo
收稿日期：2010-12-06；修回日期：2011-05-06
基金项目：总装备部预研项目
作者简介： 杜飞平（1986—），男，硕士，研究领域为液体火箭发动机动态特
更新日期/Last Update:
1900-01-01