涡轮带冠叶片共振频率分析  

Analysis for Resonant Frequency of Shrouded Turbine Blade

作　　者：陈香[1] 朱靖[1] 梁恩波[1] 李光辉[1] 滕光蓉[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2014年第1期18-22,52,共6页Gas Turbine Experiment and Research

摘　　要：利用涡轮带冠叶片干摩擦阻尼减振试验系统,分析了阻尼块与叶冠间正压力、阻尼块材料和接触面积及激振力对叶片共振频率的影响。试验结果显示,在特殊正压力加载时,叶片共振频率产生漂移现象,在其它正压力加载条件下,叶片共振频率随正压力增大基本不变;阻尼块面积和材料在不同激振力范围,对叶片共振频率产生不同影响。另外,通过试验还获取了叶片共振频率随外部参数的变化规律及叶片共振频率的大致漂移量,其结果对带冠阻尼减振系统的设计和工程应用都具有参考意义。With a dry friction damping test system of shrouded turbine blades, the effects of positive pres-sure between damping block and blade shroud, material and contact area of damping block and the excita-tion force on resonant frequency of the blade were analyzed. The results show that resonant frequency of the blade loaded special positive pressure has excursion phenomenon, while it will keep changeless when load-ed other increasing positive pressure. In addition, material and contact areas of damping block impose dif-ferent effects on the resonant frequency of the blade loaded different ranges of excitation force. Varying rules of blade resonant frequency by some parameters and approximate excursion value of resonant frequen-cy were obtained, and the results of experiment are referential for design and application of friction damping system of shrouded turbine blades.

关 键 词：航空发动机 涡轮带冠叶片 干摩擦阻尼减振 共振频率 最优正压力 试验 

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]