| 低速压气机设计转速近喘振点流场试验研究 |
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| 引用本文： | 杨海涛,黄洪雁,芦文才.低速压气机设计转速近喘振点流场试验研究[J].航空发动机,2003,29(3):22-26. |
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| 作者姓名： | 杨海涛 黄洪雁 芦文才 |
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| 作者单位： | 哈尔滨工业大学,哈尔滨,150001 |
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| 基金项目： | 国家科技部 973资助项目，国家自然科学基金资助项目 ( 50 1 0 6 0 0 2 ) |
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| 摘 要： | 对某低速压气机在设计转速下从设计工况点向小流量工况点发展直至发生喘振的运行过程进行了试验 ,并在第 2级静叶出口截面进行了详细的流场测量。试验结果表明 ,当流量减小时 ,在测量截面上有明显的大范围分离流动特征。经过对比分析 ,推测出接近喘振时静叶出口的一种分离流动结构
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| 关 键 词： | 多级压气机 试验 喘振 |
| 修稿时间： | 2003年2月16日 |
Experimental Investigation of the Flow Field in Approaching Surge for a Low-Speed Two-Stage Compressor |
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| Authors: | Yang Haitao Huang Hongyan Lu Wencai |
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| Abstract: | Experimental investigation of the flow field in approaching surge was conducted at the design speed for a low-speed two-stage compressor, and the measurements of the flow fi eld were made at the 2nd stage stator row exit. The results show that the separa ted flow is evidently extended with the reduced mass flow. It can be concluded t hat the separated flow with approaching surge occurs at the stator exit. |
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| Keywords: | two-stage compressor approaching surg e test |
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