叶尖定时在压气机转子叶片裂纹故障排除中的应用  

Application of tip timing in fault elimination of compressor rotor blade cracks

作　　者：刘美茹 郜伟强 卫靖澜 王亚南 乔百杰 陈雪峰[1] LIU Mei-ru;GAO Wei-qiang;WEI Jing-lan;WANG Ya-nan;QIAO Bai-jie;CHEN Xue-feng(Xi’an Jiaotong University,School of Mechanical Engineering,Xi’an 7100492,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]西安交通大学机械工程学院,西安710049 [2]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2023年第1期23-29,35,共8页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(52075414)。

摘　　要：介绍了基于叶尖定时的转子叶片振动非接触测试系统的基本原理。将叶尖定时技术成功应用在涡扇发动机压气机第6级转子叶片振动测试中,获取了全转速范围的叶片振动关键信息。测试结果表明,第6级转子叶片在转速10557 r/min时发生共振,通过单自由度和周向傅里叶算法获取叶片振动信息,包括振动频率和幅值。利用叶片有限元模型建立叶尖位移与叶片关键点应力的位移-应力换算系数,实现叶片关键位置动应力重构。结合古德曼曲线完成极限应力转换,明确共振不是导致叶片出现裂纹的原因。通过压气机逼喘试验,确定所有叶片异步振动迅速增加,幅值增长倍数高达233.33倍。综合压气机前期试验情况,认定喘振试验次数过多和喘振时异步振动急剧增加导致动应力过大是叶片产生裂纹的主要原因。The basic theory of the non-contact vibration testing system based on blade tip timing was introduced.The system was succeeded in the blade vibration measurement on the 6st stage of rotor blades of a civil aviation engine high pressure compressor,and key parameters of blades at resonance were obtained for the whole working speeds.The test results show that the 6st stage of rotor blades resonated at the physical speed of 10557 r/min,and the magnitudes and frequencies are obtained with the SDOF and CFF methods.Displacement-strain conversion ratio from blade tip magnitude to the critical points strain was calculated by virtue of the finite element analysis and life predication of the whole blades is realized.Then it can be conclude that the blade crack is not leaded by the resonance.Meanwhile,the Non-integral vibration amplitude increased rapidly which was up to 233.33 fold.Synthesizing the previous test situation,it can be sure that the main cause of the crack of the blades are overmuch times of surge and too large Non-integral vibration at surge which leads to large stress.

关 键 词：航空发动机 叶尖定时 非接触式测量 动频 喘振 压气机转子叶片 

分 类 号：V263.6[航空宇航科学与技术—航空宇航制造工程]