| 不同缝槽进气孔间距的纯气膜绝热温比试验研究 |
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| 引用本文： | 张弛,许全宏,林宇震.不同缝槽进气孔间距的纯气膜绝热温比试验研究[J].航空动力学报,2006,21(3):533-537. |
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| 作者姓名： | 张弛 许全宏 林宇震 |
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| 作者单位： | 北京航空航天大学,航空航天大学能源与动力工程学院,航空发动机气动热力重点实验室,北京,100083 |
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| 摘 要： | 通过传热试验法对不同缝槽进气孔间距的纯气膜冷却效率进行研究.研究所用气膜缝槽结构无收缩,进气孔与舌片垂直.试验中主流湍流强度在10%以上,测量气膜绝热壁温以确定其重要冷却效率描述参数--绝热温比.试验结果表明:缝槽进气孔间距对气膜冷却效率影响很大,减小进气孔间距,可以减小缝槽几何特征参数MIXN,明显提高气膜的绝热温比.
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| 关 键 词： | 航空、航天推进系统 航空发动机 燃烧室 气膜冷却 绝热温比 缝槽几何特征参数 |
| 文章编号： | 1000-8055(2006)03-0533-05 |
| 收稿时间： | 2005/6/22 0:00:00 |
| 修稿时间： | 2005年6月22日 |
Experimental Investigation on the Film-Cooling Adiabatic Effectiveness with Different Slot Inlet Hole Pitches |
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| ZHANG Chi,XU Quan-hong and LIN Yu-zhen.Experimental Investigation on the Film-Cooling Adiabatic Effectiveness with Different Slot Inlet Hole Pitches[J].Journal of Aerospace Power,2006,21(3):533-537. |
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| Authors: | ZHANG Chi XU Quan-hong and LIN Yu-zhen |
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| Institution: | National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | The film-cooling adiabatic effectiveness was investigated by the heat-transfer experimental method with different pitch between inlet holes of the slot film.The adiabatic wall temperature was measured to calculate the important parameter for film-cooling effectiveness,defined as adiabatic effectiveness.The slot film configurations featured no convergence and inlet holes perpendicular to slot lip.The main stream turbulent level was higher than 10% in all experiments.The experimental results indicate that the pitch between inlet holes plays important role in film-cooling effectiveness.The adiabatic film-cooling effectiveness increases with the decrease of the pitch between the inlet holes and the slot geometric parameter MIX_N. |
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| Keywords: | aerospace propulsion system aircraft engine combustion chamber film cooling film-cooling adiabatic effectiveness slot geometric parameter |
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