| 直通道和弯曲通道中超声速气膜冷却研究 |
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| 引用本文： | 彭威,姜培学. 直通道和弯曲通道中超声速气膜冷却研究[J]. 航空动力学报, 2008, 23(3): 406-409 |
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| 作者姓名： | 彭威 姜培学 |
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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 100084 |
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| 摘 要： | 对直通道和弯曲通道两种不同几何形状中的二维平行缝槽形式的超声速气膜冷却进行了数值模拟,分析了在有、无斜激波入射冷却层时的冷却效果.计算结果表明,斜激波的入射使壁面的冷却效率较无斜激波入射时要低.在该计算模型中,无斜激波入射时,弯曲通道壁面的冷却效果好于直通道壁面,而有斜激波入射时,弯曲通道壁面的冷却效果不如直通道壁面.
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| 关 键 词： | 航空、航天推进系统 超声速 气膜冷却 激波 直通道 弯曲通道 |
| 文章编号： | 1000-8055(2008)03-0406-04 |
| 收稿时间： | 2007-03-12 |
| 修稿时间： | 2007-03-12 |
Investigation of supersonic film cooling in flat and convex channels |
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| PENG Wei and JIANG Pei-xue. Investigation of supersonic film cooling in flat and convex channels[J]. Journal of Aerospace Power, 2008, 23(3): 406-409 |
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| Authors: | PENG Wei and JIANG Pei-xue |
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| Affiliation: | Key Laboratory for Thermal Science and Power Engineering of Ministry of Educations, Department of Thermal Engineering, Tsinghua University, Beijing 100084, China |
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| Abstract: | Film cooling with supersonic,tangential-slot injection of cooling air into supersonic air flow was numerically investigated.The effect of impingement of oblique shock wave was studied and its impacts on a flat surface and on a convex surface were compared.The results indicate that the adiabatic effectiveness of both the surfaces is reduced by the impingement of the oblique shock wave.The adiabatic effectiveness of convex surface is higher than that of flat surface when oblique shock wave is absent whereas the opposite is the case when it is present. |
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| Keywords: | aerospace propulsion system supersonic film cooling shock wave flat channel convex channel |
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