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| 轴流压气机气动扩稳一类新措施的实验探索 | |
| 引用本文： | 李志平,李秋实,袁巍,陆亚钧,蒋华兵. 轴流压气机气动扩稳一类新措施的实验探索[J]. 航空动力学报, 2006, 21(3): 485-491 |
| 作者姓名： | 李志平 李秋实 袁巍 陆亚钧 蒋华兵 |
| 作者单位： | 北京航空航天大学,航空航天大学能源与动力工程学院,航空发动机气动热力重点实验室,北京,100083 |
| 摘 要： | 采用外部绕流激励的方法研究非定常绕流对压气机气动稳定性的影响规律,并在此基础上探索了该措施的工程应用前景.通过模型实验验证了利用压气机内叶排间绕流的非定常耦合作用,优化匹配其周向气动布局方案,可有效的提升压气机稳定工作裕度,并改善其气动稳定性.结果表明:当绕流撞击强度达到某一阈值,并且当非定常绕流频率与非定常旋涡脱落特征频率发生耦合时,可较大幅度的提高压气机稳定工作裕度,其相对值可提高约22.1%.这一结论在压气机不同的折合转速工作状态下仍然得到了验证. |
| 关 键 词： | 航空、航天推进系统 轴流压气机 旋转失速 非定常分离流 声激励 尾流撞击效应 |
| 文章编号： | 1000-8055(2006)03-0485-07 |
| 收稿时间： | 2005-04-22 |
| 修稿时间： | 2005-04-22 |
The Experimental Research on a New Method for Extending the Axial-Compressor''''s Stall Margin |
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| LI Zhi-ping,LI Qiu-shi,YUAN Wei,LU Ya-jun and JIANG Hua-bing. The Experimental Research on a New Method for Extending the Axial-Compressor''''s Stall Margin[J]. Journal of Aerospace Power, 2006, 21(3): 485-491 | |
| Authors: | LI Zhi-ping LI Qiu-shi YUAN Wei LU Ya-jun JIANG Hua-bing |
| Affiliation: | 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 |
| Abstract: | Firstly,investigating the influences of unsteady disturbance on compressor's aerodynamic stability by exterior excitation,and then exploring the new method's outlook for engineering application by utilizing the unsteady wake impact cooperative effect in adjacent blades of compressor.Furtherly,the model experiment proved that the goal which increasing the compressor's aerodynamic performance and aerodynamic stability can be realized by optimizing the unsteady aerodynamic circumference configuration technique in compressor.The experiment results indicated that the stall margin can be increased greatly when excitation amplitude exceeded the threshold value and excitation frequency cooperated with the typical vortex shedding frequency,the stall margin can be increased 22.1% relatively.On the other hand,the cooperative effects of WIE(Wake Impact Effect,WIE) at different correct rotating speed were investigated in detail. |
| Keywords: | aerospace propulsion system axial-compressor rotating stall unsteady separated flow acoustic excitation Wake Impact Effect(WIE) |
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