| 新型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,魏晓峰.新型孔结构对气膜冷却效率的影响[J].航空动力学报,2010,25(10). |
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| 作者姓名： | 吴宏 孟恒辉 魏晓峰 |
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| 作者单位： | 能源与动力工程学院工程热物理系,中国空间技术研究院飞行器设计总体部,能源与动力工程学院 |
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| 摘 要： | 通过对不同孔间距模型的气膜冷却现象的流动和换热进行数值计算，得到了不同吹风比下，展向和流向间距对冷却效率的影响规律。研究结果表明，在主流雷诺数为4797,吹风比在0.2~2.0 条件下，(1)展向方向上，存在最佳布局；(2)流向方向上，辅助孔在主孔下游较好；(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，数值计算，冷却效率 |
| 收稿时间： | 9/15/2009 6:53:26 PM |
Numerical investigation on the effect of different new configurations on film cooling effectiveness |
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| wuhong,menghenghui and weixiaofeng.Numerical investigation on the effect of different new configurations on film cooling effectiveness[J].Journal of Aerospace Power,2010,25(10). |
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| Authors: | wuhong menghenghui and weixiaofeng |
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| Institution: | Beihang University,Beijing institute of Spacecraft System Engineering, China Academy of Space Technology,School of Jet Propulsion, Beihang University |
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| Abstract: | The flow fields and cooling effectiveness of the film cooling from the new holes embedded in different space distribution were investigated numerically in several blowing ratios , 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 4797, and the blowing ratio(M) alters from 0 to 0.0239. Results showed that: (1)in different span space models, the optimal span space is 1D; (2) more 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 keep constant under the flow spaces, while the value and direction changes sharply. |
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| Keywords: | film cooling numerical simulation adiabatic effectiveness |
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