| 旋转畸变对模态波发展过程影响试验 |
| |
| 引用本文： | 严伟,胡骏,杨帆,王志强,尹超.旋转畸变对模态波发展过程影响试验[J].航空动力学报,2014,29(10):2443-2449. |
| |
| 作者姓名： | 严伟 胡骏 杨帆 王志强 尹超 |
| |
| 作者单位： | 南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191;南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191;南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191;南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191;南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191 |
| |
| 基金项目： | 高等学校博士学科点专项科研基金（20123218120009） |
| |
| 摘 要： | 为探究"危险频率"的物理机制,设计了旋转畸变发生器,对旋转畸变条件下两级低速轴流压气机的失速起始过程进行了试验研究.结果表明:该旋转畸变发生器在不同转速下均能输出类方波状的总压分布.旋转畸变导致压气机总静压升特性下降和稳定裕度损失,并且存在使压气机稳定裕度损失最大的畸变旋转频率.失速起始过程中模态波产生于畸变区,传播到非畸变区时会受到抑制.当畸变旋转频率等于模态波的传播频率时,模态波发展为旋转失速所需的时间最短,压气机稳定裕度损失最大.对失速起始信号的时频分析显示"危险频率"在数值上等于模态波的传播频率.
|
| 关 键 词： | 旋转畸变 危险频率 时频分析 模态波 旋转失速 |
| 收稿时间： | 2013/6/15 0:00:00 |
Effect experiment of rotating distortion on the development of modal wave |
| |
| YAN Wei,HU Jun,YANG Fan,WANG Zhi-qiang and YIN Chao.Effect experiment of rotating distortion on the development of modal wave[J].Journal of Aerospace Power,2014,29(10):2443-2449. |
| |
| Authors: | YAN Wei HU Jun YANG Fan WANG Zhi-qiang and YIN Chao |
| |
| Institution: | Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China |
| |
| Abstract: | In order to explorer the mechanism of the "dangerous frequency", a rotating distortion generator was designed to investigate the effects of rotating distortion on the stall inception of a two-stage low speed axial flow compressor. Experiment results show that the rotating distortion generator can output a rectangle-like total pressure distribution at different rotating speeds. The compressor exhibited significant loss in total-static pressure rise and stability margin arising from rotating distortion, especially when it rotated at a particular speed. Detailed measurements and analysis suggest that the modal wave appears firstly in the distorted area and is restrained when it spreads into un-distorted zone. When transmit frequency of modal wave is equal to the distortion rotating frequency, the modal wave needs least time to develop into rotating stall, the loss in stability margin is the maximum. The time-frequency analysis of the stall inception signal suggests that the "dangerous frequency" is equal to the transmit frequency of the modal wave. |
| |
| Keywords: | rotating distortion dangerous frequency time-frequency analysis modal wave rotating stall |
| 本文献已被 CNKI 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
