首页 | 本学科首页   官方微博 | 高级检索  
     检索      

细长柔性转子高速动平衡方法
引用本文:邓旺群,李上福,高德平,廖学军.细长柔性转子高速动平衡方法[J].航空动力学报,2004,19(4):506-511.
作者姓名:邓旺群  李上福  高德平  廖学军
作者单位:南京航空航天大学,能源与动力学院,江苏,南京,210016;中国航空动力机械研究所,湖南,株洲,412002
基金项目:国家航空预研资助项目(24.8.3)
摘    要:提出了一种通过平衡辅助工装——平衡卡箍来进行细长柔性转子高速动平衡的新工艺方法。按照设计准则设计加工了一组精密平衡卡箍并用有限元法进行了强度校核,卡箍的验证考核试验在两个模拟轴上完成,结果表明:卡箍的平衡性能良好,对模拟轴的临界转速和振动特性的影响甚微,在此基础上完成了装机动力涡轮转子的高速动平衡试验,效果良好。 

关 键 词:航空、航天推进系统  涡轴发动机  细长柔性转子  高速动平衡  平衡卡箍  临界转速
文章编号:1000-8055(2004)04-0506-06
收稿时间:2003/7/18 0:00:00
修稿时间:2003年7月18日

Method of High Speed Dynamic Balance to Balance a Slender Flexible Rotor
DENG Wang-qun,LI Shang-fu,GAO De-ping and LIAO Xue-jun.Method of High Speed Dynamic Balance to Balance a Slender Flexible Rotor[J].Journal of Aerospace Power,2004,19(4):506-511.
Authors:DENG Wang-qun  LI Shang-fu  GAO De-ping and LIAO Xue-jun
Institution:1.College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing210016,China2.China Aviation Powerplant Research Institute,Zhuzhou412002,China
Abstract:A new technology method of high speed dynamic balance to balance a slender flexible rotor is presented by using auxiliary tool of balance-balance collars in this paper.A set of precise balance collars are designed and processed according to design criteria and their strength calibration is completed by using finite element method.The experiments of checking and verifying balance collars are accomplished through two simulating shafts.The results of experiments show that the balance behavior of the collars is good and they have little influence on critical speed and vibration characteristics of each simulating shaft.Based on this,high speed dynamic balance of power turbine rotor of turbine shaft engine is satisfactorily conducted by using these balance collars and the effect is very ideal.
Keywords:aerospace propulsion system  turbine shaft engine  slender flexible rotor  high speed dynamic balance  balance collar  design criterion  balance behavior  critical speed
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号