| 叶片端弯技术机理探讨 |
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| 引用本文： | 黄力希,魏星禄,彭泽琰.叶片端弯技术机理探讨[J].航空动力学报,1988,3(3):219-222,281-282. |
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| 作者姓名： | 黄力希 魏星禄 彭泽琰 |
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| 作者单位： | 北京航空航天大学
(黄力希，魏星禄)，北京航空航天大学(彭泽琰) |
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| 摘 要： | 本文首次以数值计算,理论分析以及试验分析的综合手段探讨叶片端弯的气动机理,分析表明;端弯会导致整个流场再分布,主流场变化可能是影响叶片性能改进的重要因素。
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| 收稿时间： | 1987/11/1 0:00:00 |
APPROACH TO BLADE END-BEND MECHANISM |
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| Huang Lixi,Wei Xinglu and Peng Zeyan.APPROACH TO BLADE END-BEND MECHANISM[J].Journal of Aerospace Power,1988,3(3):219-222,281-282. |
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| Authors: | Huang Lixi Wei Xinglu and Peng Zeyan |
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| Institution: | Beijing Institute of Aeronautics and Astronautics;Beijing Institute of Aeronautics and Astronautics;Beijing Institute of Aeronautics and Astronautics |
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| Abstract: | Blade end-bend is a new technique to improve the performance of compressors. A comprehensive study of two multistage compressors has been completed with numerical calculation, theoretical analysis and experimental investigation.It is shown that the end-bend causes redistribution of the whole flowfield,and the changes of characteristics in main flow region may be a vital factor to improve the engine performance. A comparative study of several end-bend patterns shows that the character of redistribution differs for each from other. It is important to choose the end-bend pattern suitable for the specific compressor. |
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