涡轮带冠叶片干摩擦阻尼减振试验  

Experiment on dry friction damping of shrouded turbine blades

作　　者：陈香[1] 朱靖[1] 李光辉[1] 王春健[1] 

机构地区：[1]中国航空工业集团公司中国燃气涡轮研究院,四川江油621703

出　　处：《航空动力学报》2012年第4期817-823,共7页Journal of Aerospace Power

摘　　要：设计一套涡轮带冠叶片干摩擦阻尼减振试验系统,并利用该试验系统对阻尼块与叶冠之间不同接触紧度、不同接触面积以及采用不同材料阻尼块时涡轮叶片动力特性和减振效果进行了分析研究.结果表明接触紧度、阻尼块的接触面积、材料以及外部激振力共同影响涡轮叶片的减振效果,共同决定该系统是否存在最优正压力以及最优正压力存在时的范围或大小.另外,激振力的变化将导致叶片的响应、系统阻尼比、共振频率以及最优正压力等一系列参数变化.试验结果能够为理论计算提供数据验证,为指导涡轮带冠叶片的减振设计提供依据.A dry friction damping test system of shrouded turbine blades was designed.The effects of different mounting tightness and contact areas between damping block,blade shroud and different materials of damping block on dynamical characteristic and damping of the turbine blades were studied with this system.The results show that damping of the turbine blades is affected by mounting tightness,contact area,materials of damping block and excitation force,which also determin whether the damping system has best vertical press,and dominates its range and domain under the existence of best vertical press.Moreover,change of the excitation force can induce the changing a series of experimental parameters,such as response of the turbine blades,damping ratio of the system,resonance frequency and best vertical press.Those results can provide the experimental verification for theoretical arithmetic and provide further insight into damping design of the shrouded turbine blades.

关 键 词：涡轮叶片 干摩擦 阻尼 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]