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带交叉肋变截面回转通道内换热的实验研究
引用本文:魏喆,邓宏武,陶智,丁水汀,徐国强.带交叉肋变截面回转通道内换热的实验研究[J].航空动力学报,2004,19(5):645-649.
作者姓名:魏喆  邓宏武  陶智  丁水汀  徐国强
作者单位:北京航空航天大学,能源与动力工程学院,北京,100083
摘    要:以航空发动机涡轮叶片内部回转通道为设计原型,实验研究了三种不同入口宽高比的带60°交叉肋变截面180°回转通道壁面的换热特性。分析了几何无因次参数和气流雷诺数对通道带肋表面换热的影响。结果表明:通道壁面的换热效果是随着进口雷诺数的增大而增加的,其分布趋势基本一致;对于不同宽高比的通道,低雷诺数时通道平均换热效果是基本相同的,在高雷诺数时宽高比小的通道要好于宽高比大的通道,而换热系数在整体通道上的分布情况基本相同。

关 键 词:航空、航天推进系统  交叉肋  回转通道  宽高比  换热
文章编号:1000-8055(2004)05-0645-05
收稿时间:2003/10/14 0:00:00
修稿时间:2003年10月14

Experimental Investigation of Heat Transferin Turn-Over Variable Cross-Section Channels with Interleaving Ribs
WEI Zhe,DENG Hong-wu,TAO Zhi,DING Shui-ting and XU Guo-qiang.Experimental Investigation of Heat Transferin Turn-Over Variable Cross-Section Channels with Interleaving Ribs[J].Journal of Aerospace Power,2004,19(5):645-649.
Authors:WEI Zhe  DENG Hong-wu  TAO Zhi  DING Shui-ting and XU Guo-qiang
Institution:School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Jet Propulsion,Beijing University of Aeronautics and Astronautics,Beijing100083,China
Abstract:Measurements has been carried out on a 180° turnover variable cross-section channel with 60° interleaving ribs.The design of the channel inner configuration was referred to an actual aero-engine turbine blade.Heat transfer characteristics were investigated at three different inlet widths to heights ratio channels. The influence of non-dimensional parameters on heat transfer of the surfaces with ribs was analyzed.The results show that at high Renolds number,the channels with large width to height ratio have better average heat transfer effect,but at low Reynolds number,the effect does not vary much with width to height ratio.Heat transfer coefficient distribution in the whole channel is basically the same for all the cases studied.
Keywords:aerospace propulsion system  interleaving ribs  turnover channel  aspect ratio  heat transfer
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