摘要
为建立叶尖振幅与叶根关键点动应变映射关系,开展了模拟转子叶片叶尖振幅与叶根动应变测量试验。采用叶尖定时测试系统测量叶尖振幅,同时利用应变片测试系统测量叶根关键点动应变,研究模拟转子叶片不同共振转速下,叶尖定时技术所测叶尖振幅与应变片所测动应变之间的映射关系。试验数据分析结果表明,叶尖定时技术所测转子叶片频率与应变片测量结果相比,误差在1.0%以内;转子叶片叶根动应变与叶尖振幅的比值误差最大为14.4%。研究成果为叶尖定时技术在航空发动机压气机和涡轮转子叶片振动测试中的应用提供了依据。
In order to set up mapping relationship between blade tip vibration amplitude and dynamic strain of critical points at the blade root,vibration experiment of simulating rotor blade was carried out.In the ex⁃periment,the blade tip timing system and the strain gage were respectively used to measure blade tip dis⁃placement and root strain.The mapping relationship between the tip displacement and the root strain was developed at different resonance speeds.Results showed that the relative errors of the identified natural fre⁃quencies by the blade tip timing and strain gage measurement were less than 1.0%.The maximum measure⁃ment error of ratio of the root dynamic strain to the tip displacement magnitude was 14.4%.Furthermore,this work provides the basis of the extension for the non-contact dynamic stress measurement of the com⁃pressor and turbine blades of aero-engine.
作者
肖潇
刘美茹
焦江昆
郜伟强
敖春燕
乔百杰
XIAO Xiao;LIU Mei-ru;JIAO Jiang-qun;GAOWei-qiang;AO Chun-yan;QIAO Bai-jie(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China;Xi’an Jiaotong University,School of Mechanical Engineering,Xi’an 710049,China)
出处
《燃气涡轮试验与研究》
2021年第6期6-11,共6页
Gas Turbine Experiment and Research
基金
国家科技重大项目(2017-V-0009)。
关键词
航空发动机
转子叶片
非接触测试
叶尖定时
动应变测量
动频
aero-engine
rotor blade
non-contact measurement
blade tip timing
dynamic strain measurement
dynamic frequency
