小尺寸多级轴流压气机级间干扰现象试验  

Experiment of rotor-stator interaction behaviors in a small multi-stage axial compressor

作　　者：贺象 马宏伟[2] 银越千 单晓明 HE Xiang;MA Hongwei;YIN Yueqian;SHAN Xiaoming(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)

机构地区：[1]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 [2]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

出　　处：《航空动力学报》2020年第11期2378-2384,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(51776011);国家科技重大专项(2017-Ⅳ-0016-0068)。

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。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 1 st rotor tip flow-field agreed well with the typical supersonic-cascade flow features, and only the flow-field at the 1 st 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 1 st 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.

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 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]