| 一个扩压叶栅角区流向涡的物理模式 |
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| 引用本文： | 唐燕平,陈芳.一个扩压叶栅角区流向涡的物理模式[J].航空学报,1989,10(2):36-43. |
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| 作者姓名： | 唐燕平 陈芳 |
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| 作者单位： | 北京航空航天大学
(唐燕平)，北京航空航天大学(陈芳) |
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| 摘 要： | 本文采用烟显示和三维流场测量的方法,研究扩压叶栅角涡的物理模式。试验结果揭示了角涡发生、发展程中的流动形态和结构特点,以及角涡与叶面附面层相互作用的物理过程。在这个物理模式的基础上讨论了角涡引起高流动损失的物理机制。
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| 关 键 词： | 压气机 叶栅 拐角流 |
| 收稿时间： | 1987-09-05; |
A PHYSICAL MCDEL OF THE STREAMWISE CORNER VORTEXES IN A COMPRESSOR CASCADE |
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| Beijing University of Aeronautics and Astronautics Trag Yanping and Chen Fang.A PHYSICAL MCDEL OF THE STREAMWISE CORNER VORTEXES IN A COMPRESSOR CASCADE[J].Acta Aeronautica et Astronautica Sinica,1989,10(2):36-43. |
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| Authors: | Beijing University of Aeronautics and Astronautics Trag Yanping and Chen Fang |
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| Institution: | Beijing University of Aeronautics and Astronautics Trag Yanping and Chen Fang |
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| Abstract: | The flow visualization by means of smoke and measurement of 3 -D flow field are conducted to investigate physical model of the streamwise corner vortexes in a compressor cascade.The exoerimental results describe not only the flow pattern and structural characteristics,but also the iateraction of the corner vortexes with the blade surface boundary layers in the cascade.Based on this physical model, the mechanism has been discussed that high losses are caused by the corner vortexes. |
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| Keywords: | compressor cascades earner flow |
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