| 高位垂直进气径向出流旋转盘腔换热的实验研究 |
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| 引用本文： | 徐国强,张笙,罗翔,丁水汀,陶智,雷斌.高位垂直进气径向出流旋转盘腔换热的实验研究[J].航空动力学报,2006,21(5):820-823. |
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| 作者姓名： | 徐国强 张笙 罗翔 丁水汀 陶智 雷斌 |
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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空发动机气动热力重点实验室,北京,100083 |
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| 摘 要： | 用实验的方法对高位垂直进气转静系旋转盘附近冷气换热特性的基础数据进行补充和拓展研究,建立了高速旋转换热实验台,并运用遥测技术采集温度信号,得到了转盘表面温度、局部努赛尔特数的分布及平均努赛尔特数,主要结论为:(1)转盘表面温度呈外高内低分布.(2)转盘表面的局部努赛尔特数在r＜0.4b的区域基本不变,r＞0.4b的区域里,局部努赛尔特数随半径的增加而迅速增大.(3)其它条件不变时,随流量系数的提高,平均努赛尔特数大幅度上升.
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| 关 键 词： | 航空、航天推进系统 高位进气 旋转盘 换热 |
| 文章编号： | 1000-8055(2006)05-0820-04 |
| 收稿时间： | 8/4/2005 12:00:00 AM |
| 修稿时间： | 2005年8月4日 |
Experimental investigation on heat transfer in shrouded rotating disk with high-positioned air inflow |
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| XU Guo-qiang,ZHANG Sheng,LUO Xiang,DING Shui-ting,TAO Zhi and LEI Bin.Experimental investigation on heat transfer in shrouded rotating disk with high-positioned air inflow[J].Journal of Aerospace Power,2006,21(5):820-823. |
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| Authors: | XU Guo-qiang ZHANG Sheng LUO Xiang DING Shui-ting TAO Zhi and LEI Bin |
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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 heat transfer characteristics of the rotor-stator disk system were investigated experimentally.The distributions of temperature on the rotating disk surface,local and averaged Nusselt number of the rotating disk were obtained from the test.Conclusions are drawn as follows:The temperature gradient near disk center is insignificant;the Nusselt number at the inner radial position is almost invariable;and at outer radial position is increased with the increase of inlet mass flow coefficient.The averaged Nusselt number is dramatically increased with the increase of inlet mass flow coefficient. |
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| Keywords: | aerospace propulsion system high-positioned air inflow rotating disk heat transfer |
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