非接触叶尖振动参数辨识方法验证试验  

Verification Test on Identification Method of Non-Contact Blade Tip Vibration Parameters

作　　者：许艳芝[1] 冯少鹏[1] 郭政波 XU Yan-zhi;FENG Shao-peng;GUO Zheng-bo(Engine Department of Chinese Flight Test Establishment, Xi′anShaanxi 710089, China)

机构地区：[1]中国飞行试验研究院发动机所,陕西西安710089

出　　处：《机械研究与应用》2019年第2期68-71,77,共5页Mechanical Research & Application

摘　　要：为检验非接触叶尖振动参数辨识方法在工程上的应用效果,在某航空风扇转子试验器上开展了相关试验研究。首先利用外物撞击试验方法得出不同转速下叶片一阶弯曲振动频率,在3 000 r/min、3 500 r/min、4 020 r/min、4 450 r/min四个稳态转速下测量了风扇叶片叶尖振动数据,利用同步振动和异步振动参数辨识方法对叶尖振动数据进行了分析研究,总结得出不同叶片编号、转速下叶尖振动数据的规律。分析发现:该方法在大部分情况下辨识的振动参数是错误的,进一步分析得出辨识方法出错的主要原因。这些分析结论为非接触叶尖振动参数辨识方法的工程化提供了指导。In order to test the application effect of non-contact blade tip vibration parameter identification method in engineering, the related experimental research was carried out on an aviation fan rotor tester. First, the first-order bending vibration frequency of the blade at different rotating speeds is obtained by means of the external impact test;the vibration data of fan blade tip is measured at these four steady speed:3 000 r/min,3 500 r/min, 4 020 r/min and 4 450 r/min;then, the blade tip vibration data is analyzed by using the method of synchronous and asynchronous vibration parameter identification, thus the law of tip vibration data under different blade number and rotation speed is summarized. It is found that the vibration parameters identified by this method are wrong in most cases;and the main reasons for error of the identification method are obtained through further analysis. These analysis results provide guidance for the engineering of non-contact blade tip vibration parameter identification method.

关 键 词：非接触叶尖振动 振动参数辨识 叶尖定时原理 同步振动 异步振动 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]