| 抑涡孔结构对气膜冷却效率的影响 |
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| 引用本文： | 吴宏,孟恒辉,陶智,徐国强,丁水汀.抑涡孔结构对气膜冷却效率的影响[J].航空动力学报,2010,25(10):2238-2243. |
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| 作者姓名： | 吴宏 孟恒辉 陶智 徐国强 丁水汀 |
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| 作者单位： | 1. 北京航空航天大学,能源与动力工程学院,北京,100191
2. 中国航天科技集团公司,中国空间技术研究院,飞行器设计总体部,北京,100063 |
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| 基金项目： | 国家自然科学基金，航空基金 |
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| 摘 要： | 对不同孔间距模型的气膜冷却现象的流动和换热进行了数值计算,得到了不同吹风比下,展向和流向孔间距对气膜冷却效率的影响规律.研究结果表明,在主流雷诺数为4 797,吹风比为0.2～2.0的条件下:①展向方向上,S1/D=1为最佳布局;②流向方向上,相对于主孔靠后的辅助孔冷却效果较好;③流向方向上,辅助孔在主孔下游的模型受吹风比影响小,并且流向距离的改变,对涡量的量级不发生改变,对涡量的大小和方向影响较大.
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| 关 键 词： | 气膜冷却 冷却效率 数值计算 抑涡结构 气膜孔 换热 |
| 收稿时间： | 2009/9/15 0:00:00 |
| 修稿时间： | 2010/1/29 0:00:00 |
Numerical investigation on the effect of different anti-vortex hole configurations on film cooling effectiveness |
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| WU Hong,MENG Heng-hui,TAO Zhi,XU Guo-qiang and DING Shui-ting.Numerical investigation on the effect of different anti-vortex hole configurations on film cooling effectiveness[J].Journal of Aerospace Power,2010,25(10):2238-2243. |
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| Authors: | WU Hong MENG Heng-hui TAO Zhi XU Guo-qiang and DING Shui-ting |
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| Institution: | School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Beijing Institute of Spacecraft System Engineering, China Academy of Space Technology, China Aerospace Science and Technology Corporation, Beijing 100063, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | The flow and heat transfer of the film cooling from the film holes embedded in different space distributions were investigated numerically in several blowing ratios,so as to reveal the effects of span spaces and flow spaces.In the present study,the Reynolds number(Re) based on mainstream velocity and film hole diameter is 4 797,and the blowing ratio(M) alters from 0.2 to 2.0.Results show that:(1)in different span space models,the optimal span space is 1D;(2) better film cooling effectiveness is obtained in the assistant-behind hole model;(3) less influence of the blowing ration occurs in the assistant-behind hole model;and the level of vortex intensity keeps constant under the flow spaces,while the value and direction change sharply. |
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| Keywords: | film cooling cooling effectiveness numerical simulation anti-vortex configuration film hole heat transfer |
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