| 发汗冷却喷管多孔壁面的分段设计分析 |
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| 引用本文： | 金韶山,姜培学,孙纪国.发汗冷却喷管多孔壁面的分段设计分析[J].航空动力学报,2008,23(12):2346-2352. |
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| 作者姓名： | 金韶山 姜培学 孙纪国 |
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| 作者单位： | 清华大学热能工程系热科学与动力工程教育部重点实验室;北京航天动力研究所; |
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| 摘 要： | 对于采用烧结多孔结构作为发汗冷却壁面的喷管,为最大限度的减少冷却剂流量,提出了对多孔介质壁面沿轴向进行分段的发汗冷却结构.通过采用Fluent软件对分4段结构的多孔壁面推力室发汗冷却进行数值模拟并且与不分段的发汗冷却喷管比较发现,分4段的结构在满足室壁温冷却要求的前提下可将冷却剂与主气流量百分比从28.3%降至12.6%,这表明烧结多孔结构分段设计是减少喷管发汗冷却剂流量的有效手段.
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| 关 键 词： | 发汗冷却 喷管 多孔壁面 分段设计 |
| 收稿时间： | 2007/11/30 0:00:00 |
| 修稿时间： | 4/7/2008 10:56:00 PM |
Analysis of the subsection design of the porous wall of a transpiration cooling nozzle |
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| JIN Shao-shan,JIANG Pei-xue and SUN Ji-Guo.Analysis of the subsection design of the porous wall of a transpiration cooling nozzle[J].Journal of Aerospace Power,2008,23(12):2346-2352. |
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| Authors: | JIN Shao-shan JIANG Pei-xue and SUN Ji-Guo |
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| Institution: | Department of Thermal Engineering, Tsinghua University,Department of Thermal Engineering, Tsinghua University |
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| Abstract: | In order to minimize the coolant flow for transpiration cooling rocket nozzle with sintered porous media wall,an optimized transpiration cooling structure was presented in this paper,whose porous wall was divided into several sections along the axis direction.The transpiration cooling for a thruster with four-section structure porous wall was numerically studied by Fluent code and the results were compared with those of the one-section structure transpiration thruster.The results show that four-section stru... |
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| Keywords: | transpiration cooling nozzle porous media wall subsection design |
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