| 带肋变截面回转通道内沿程有效压力分布特性的实验研究 |
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| 引用本文： | 刘浪,丁水汀,陶智,徐国强.带肋变截面回转通道内沿程有效压力分布特性的实验研究[J].航空动力学报,2003,18(3):353-357. |
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| 作者姓名： | 刘浪 丁水汀 陶智 徐国强 |
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| 作者单位： | 北京航空航天大学,能源与动力工程学院,北京,100083 |
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| 基金项目： | 航空发动机气动热力重点实验室基金(99JS48.3.1) |
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| 摘 要： | 以某型航空发动机的实际涡轮叶片内部的带肋变截面180°回转通道为研究对象,以实验的方法分别研究了带90°直肋和带60°斜肋的通道内的流体流动的特性。根据研究问题的特点,定义了壁面有效压力及局部有效压力系数,并得到了其沿程分布及两种通道内有效压力系数的经验公式。实验发现,对于带90°直肋和带60°斜肋的矩形回转通道沿程有效压力的分布趋势基本一致,由于流道截面积的不规则变化,导致有效压力有沿程逆增现象。
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| 关 键 词： | 航空、航天推进系统 冷却叶片 回转通道 流动与换热 有效压力 |
| 文章编号： | 1000-8055(2003)03-0353-05 |
| 收稿时间： | 7/8/2002 12:00:00 AM |
| 修稿时间： | 2002年7月8日 |
An Experimental Study of Efficient Pressure Distribution in a Turn-Over Channel with Ribs |
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| LIU Lang,DING Shui-ting,TAO Zhi and XU Guo-qiang.An Experimental Study of Efficient Pressure Distribution in a Turn-Over Channel with Ribs[J].Journal of Aerospace Power,2003,18(3):353-357. |
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| Authors: | LIU Lang DING Shui-ting TAO Zhi and XU Guo-qiang |
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| Institution: | Beijing University of Aeronautics and Astronautics,Beijing 100083,China;Beijing University of Aeronautics and Astronautics,Beijing 100083,China;Beijing University of Aeronautics and Astronautics,Beijing 100083,China;Beijing University of Aeronautics and Astronautics,Beijing 100083,China |
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| Abstract: | The turn-over channel of turbine blade is an important part of the internal cooling structure of the turbine blade. Its flow performance is important for the design of cooling structure of the turbine blade. In this paper,a real turn-over channel of turbine blade is simplified and experimental study has been conducted. The paper demonstrates the investigation of the flow performance in a 180° turn-over channel with 90° parallel ribs and 60° parallel ribs respectively. The efficient pressure distribution was obtained along the channel in the inner part of these two turnover channels with 90° and 60° ribs is similar. Some efficient pressure increases along the channel due to irregular change of the channel shape. Correlation formulas of the coefficient of the efficient pressure are derived in the paper. |
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| Keywords: | aerospace propulsion system cooling blade turn-over channel heat transfer and flow efficient pressure |
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