| 小尺寸多级轴流压气机级间干扰现象试验 |
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| 引用本文： | 贺象,马宏伟,银越千.小尺寸多级轴流压气机级间干扰现象试验[J].航空动力学报,2020,35(11):2378-2384. |
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| 作者姓名： | 贺象 马宏伟 银越千 |
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| 作者单位： | 中国航空发动机集团有限公司湖南动力机械研究所中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002,北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191,中国航空发动机集团有限公司湖南动力机械研究所中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002,中国航空发动机集团有限公司湖南动力机械研究所中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002 |
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| 基金项目： | 国家自然科学基金（51776011）； 国家科技重大专项（2017-Ⅳ-0016-0068） |
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| 摘 要： | 针对某小尺寸多级轴流压气机,利用Kulite动态压力传感器以及高频压力探针,测量不同转速下转子叶顶动态静压分布以及级间流场,并对测得的动态压力信号进行分析,研究多级压气机转/静干扰作用。结果表明:高转速下,首级转子叶顶测得的流场能够反映典型的超声叶栅流动特征,多级压气机存在的级间干扰作用只影响到首级转子出口流场;中等转速下,级间干扰作用非常显著,影响到首级转子进口,并随压气机节流级间扰动强度增大。对这些级间扰动的对应频率进行模态分析,从而获得了非定常级间扰动的传播速度和模态数。
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| 关 键 词： | 多级轴流压气机 超声叶栅流动 动态压力测量 级间干扰 模态分析 |
| 收稿时间： | 2020/4/13 0:00:00 |
Experiment of rotor-stator interaction behaviors in ,a small multi-stage axial compressor |
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| HE Xiang,MA Hongwei,YIN Yueqian.Experiment of rotor-stator interaction behaviors in ,a small multi-stage axial compressor[J].Journal of Aerospace Power,2020,35(11):2378-2384. |
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| Authors: | HE Xiang MA Hongwei YIN Yueqian |
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| Institution: | Hunan Key Laboratory of Turbomachinery on Small and Medium Aero-Engine,,Hunan Aviation Powerplant Research Institute,,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China;;National Key Laboratory of Science and Technology on Aero-Engine ,Aero-thermodynamics,School of Energy and Power Engineering,,Beijing University of Aeronautics and Astronautics,Beijing 100191,China |
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| Abstract: | The dynamic pressure signals were measured and analyzed by the Kulite transducers and the fast response pressure probes to investigate the rotor-stator interaction phenomenon in small multistage axial compressor. Results indicated that, at higher rotor speed, the 1st rotor tip flow-field agreed well with the typical supersonic-cascade flow features, and only the flow-field at the 1st rotor trailing-edge was disturbed by the rotor-stator interactions. However, at lower rotor speed, the rotor-stator interaction obviously increased in intensity and appeared at the 1st rotor leading-edge with the compressor throttling. Modal analysis was carried out for these frequency components of rotor-stator interactions, and then the propagation speed and modal number were obtained finally. |
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| Keywords: | multistage axial-compressor supersonic cascade flow dynamic pressure measurement rotor-stator interaction modal analysis |
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