Volume 33 Issue 1
Jan.  2018
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2018  >  33(1): 15-23
Vibration test of high speed flexible rotor due to the suddenunbalance[J]. Journal of Aerospace Power, 2018, 33(1): 15-23. doi: 10.13224/j.cnki.jasp.2018.01.002
Citation: Vibration test of high speed flexible rotor due to the suddenunbalance[J]. Journal of Aerospace Power, 2018, 33(1): 15-23. doi: 10.13224/j.cnki.jasp.2018.01.002
shu

Vibration test of high speed flexible rotor due to the suddenunbalance

doi: 10.13224/j.cnki.jasp.2018.01.002
  • Received Date: 2016-06-14
  • Publish Date: 2018-01-28
    Abstract
  • A high speed flexible cantilever rotor test rig was established to investigate the vibration response of the turbofan rotor in time domain and frequency domain under the suddenunbalance and the rubimpact caused by blade loss, based on the equivalence principle of structural/mechanical characteristics. The research showed that, suddenunbalance led to significant impact on rotor, the aggravation of the rotors transient response, and flexural resonance of rotor; the rubimpact between rotor and stator resulted in the increase of the critical speed of rotor and the nonlinear vibration with the super harmonic frequencies.

     

    • FullText(HTML)
  • loading
    • References(19)
  • [1]
    COSME N,CHEVROLET D,BONINI J,et al.Prediction of engine loads and damages due to fan blade off event［R］.AIAA2002-1666，2002.
    [2]
    Federal Aviation Administration.Airworthiness standards aircraft engines:14 CFR Part 33［S］.Washington DC:Federal Aviation Administration,1993:81-99.
    [3]
    European Aviation Safety Agency.Certification specifications for engines:CSE［S］.Munich,Germany:EASA,2009:140-141.
    [4]
    SINHA S K.Rotordynamic analysis of asymmetric turbofan rotor due to fan bladeloss event with contactimpact rub loads［J］.Journal of Sound and Vibration,2013,332(9):2253-2283.
    [5]
    宣海军,陆晓,洪伟荣,等.航空发动机机匣包容性研究综述［J］.航空动力学报,2010,25(8):1860-1870.XUAN Haijun,LU Xiao,HONG Weirong,et al.Review of aeroengine case containment research［J］.Journal of Aerospace Power,2010,25(8):1860-1870.(in Chinese)
    [6]
    NAIK D,SANKARAN S,MOBASHER B,et al.Development of reliable modeling methodologies for fan blade out containment analysis:Part Ⅰ experimental studies［J］.International Journal of Impact Engineering,2009,36(1):111.
    [7]
    徐春雨.民用飞机发动机安装节设计载荷要求研究［J］.科技视界,2015(27):135-135.XU Chunyu.Research on design load requirement of civil aircraft engine installation section［J］.Science and Technology Vision,2015(27):135-135.(in Chinese)
    [8]
    JACQUETRICHARDET G,TORKHANI M,CARTRAUD P,et al.Rotor to stator contacts in turbomachines：review and application［J］.Mechanical Systems and Signal Processing,2013,40(2):401-420.
    [9]
    GROLL G V,EWINS D J.On the dynamics of windmilling in aeroengines［R］.London:International Conference on Vibrations in Rotating Machinery,2000.
    [10]
    HIBNER D R,BZLONO D F.Experimental study of transient dynamics of a flexible rotor［R］.NASA CR-2703,1976.
    [11]
    KALINOWSKI P,BARGEN O,LIEBICH R.Vibrations of rotating machinery due to sudden mass loss［C］∥The Proceedings of 8th IFToMM International Conference on Rotor Dynamics.Seoul,Korea:IFToMM,2010:584-590.
    [12]
    李其汉,赵福安,张世平.带弹性阻尼支承的转子系统丢失叶片瞬态响应试验研究［J］.航空动力学报,1992,7(2):103-107.LI Qihan,ZHAO Fuan,ZHANG Shiping.Experimental investigation on blade loss transient response of rotor with flexible damped support［J］.Journal of Aerospace Power,1992,7(2):103-107.(in Chinese)
    [13]
    张力,马艳红,梁智超,等.转子系统碰摩约束模型与振动响应分析［J］.北京航空航天大学学报,2015,41(9):1631-1637.ZHANG Li,MA Yanhong,LIANG Zhichao,et al.Constraint model and vibration response analysis of rotor rubimpact［J］.Journal of Beijing University of Aeronautics and Astronautics,2015,41(9):1631-1637.(in Chinese)
    [14]
    KIM Y,NOAH S T.Quasiperiodic response and stability analysis for a nonlinear Jeffcott rotor［J］.Journal of Sound and Vibration,1996,190(2):239-253.
    [15]
    KHANLO H M,GHAYOUR M,ZIAEIRAD S.Chaotic vibration analysis of rotating flexible continuous shaftdisk system with a rubimpact between the disk and the stator［J］.Communications in Nonlinear Science and Numerical Simulation,2011,16(1):566-582.
    [16]
    JOHN J Y.On occurrence of reverse full annular rub［J］.Journal of Engineering for Gas Turbines and Power,2012,134(1):12505-12512.
    [17]
    PATEL T H,DARPE A K.Coupled bendingtorsional vibration analysis of rotor with rub and crack［J］.Journal of Sound and Vibration,2009,326(3):740-752.
    [18]
    高艳蕾,李勇,王德友.转子机匣系统碰摩故障特征试验研究［J］.航空发动机,2002,28(4):16-21.GAO Yanlei,LI Yong,WANG Deyou.Experimental investigation of rotortocasing rubbing fault［J］.Aeroengine,2002,28(4):16-21.(in Chinese)
    [19]
    梁智超,张振波,刘书国,等.转子支承机匣系统碰摩试验及特征提取［J］.航空动力学报,2014,29(3):604-611.LIANG Zhichao,ZHANG Zhenbo,LIU Shuguo,et al.Experiment and characteristics extraction of rubimpact in rotorsupportcase system［J］.Journal of Aerospace Power,2014,29(3):604-611.(in Chinese)
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(1410.0KB)
    XML

    Article Metrics

    Article views (1446) PDF downloads(879) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return