| 交错肋通道换热和流阻特性的研究 |
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| 引用本文： | 丁水汀,秦岭,邓宏武,陶智,徐国强,林宇震.交错肋通道换热和流阻特性的研究[J].航空动力学报,2007,22(2):205-209. |
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| 作者姓名： | 丁水汀 秦岭 邓宏武 陶智 徐国强 林宇震 |
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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航空发动机气动热力重点实验室,北京,100083 |
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| 基金项目： | 教育部跨世纪优秀人才培养计划 |
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| 摘 要： | 针对布有交错肋的涡轮叶片尾缘内冷通道进行了换热以及流阻的实验研究.实验结果表明,变截面带肋通道的换热效果和流阻都高于等截面带肋通道.等截面通道和变截面通道相对于光通道而言Nu数分别提升了4～6倍和7倍,但其流阻系数相应的也分别提高了400倍和600倍左右.变截面带肋通道的综合换热效果同样优于等截面通道.
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| 关 键 词： | 航空、航天推进系统 涡轮叶片 交错肋 换热 流阻 |
| 文章编号： | 1000-8055(2007)02-0205-05 |
| 收稿时间： | 2006/1/20 0:00:00 |
| 修稿时间： | 2006年1月20日 |
Experimental investigation of heat transfer and flow resistance in a crossed-rib channel |
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| DING Shui-ting,QIN Ling,DENG Hong-wu,TAO Zhi,XU Guo-qiang and LIN Yu-zhen.Experimental investigation of heat transfer and flow resistance in a crossed-rib channel[J].Journal of Aerospace Power,2007,22(2):205-209. |
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| Authors: | DING Shui-ting QIN Ling DENG Hong-wu TAO Zhi XU Guo-qiang 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;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 investigation of heat transfer and flow resistance in a crossed-rib channel located in turbine blade was conducted experimentally.Experimental results show that the Nusselt Number in the rectangular channel and the variable channel is 4~6 times and 7 times higher than that in a smooth channel,while flow resistance coefficient was enlarged by about 400 and 600 times.The total thermal performance in the variable channel is about 1.2 times higher than that in the rectangular channel. |
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| Keywords: | aerospace propulsion system turbine blade crossed-rib heat transfer flow resistance |
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