Volume 34 Issue 10
Oct.  2019
Turn off MathJax
Article Contents
YU Lei, MA Huifang, WANG Weiguo. Analysis and test verification of model rotor sudden nbalanceresponse[J]. Journal of Aerospace Power, 2019, 34(10): 2256-2263. doi: 10.13224/j.cnki.jasp.2019.10.019
Citation: YU Lei, MA Huifang, WANG Weiguo. Analysis and test verification of model rotor sudden nbalanceresponse[J]. Journal of Aerospace Power, 2019, 34(10): 2256-2263. doi: 10.13224/j.cnki.jasp.2019.10.019

Analysis and test verification of model rotor sudden nbalanceresponse

doi: 10.13224/j.cnki.jasp.2019.10.019
  • Received Date: 2019-06-02
  • Publish Date: 2019-10-28
  • Inorder to accurately obtain the transient load caused by fan blade out, contact modeling and transient analysis were carried out by explicit dynamic finite element simulation method. Multi-level calibration and verification test were performed, and these test results were compared with the analysis. The comparison results showed that the explicit dynamic finite element simulation method can provide a feasible simulation method for accurately simulating thedynamic characteristics of sudden unbalance process, and a set of model updating methods from parts, components to whole finite element model, from statics to dynamics were formed. According to the physical quantities such as main path load and sudden unbalanced load defined by the test priority, the selectionof test parameters for model updating was determined. With the calibration results of the model, the peak radial dynamic load can be accurately obtained by using the dynamic strain measurement data of the bearing cone, and the prediction error of peak dynamic load was within 10% compared with thetest observation. This method can be applied to indirect measurement of the impact load, so as to improve the accuracy and simplicity of the measurement.

     

  • loading
  • [1]
    US Department of Transportation Federal Aviation dministration.Federal Aviation Regulation,FAR33:airworthiness standards:aircraft engines[S].Washington DC:Federal Aviation Administration,1983:97-449.
    [2]
    European AviationSafety Agency.CS-25 Amendment 22:certification specifications and acceptable means of compliance for large aero planesS].Cologne,Germany:European Aviation Safety Agency,2018:78-79.
    [3]
    HUSBAND J B.Developing an efficient FEM structural simulation of a fan blade off test in a turbo-fan jet engine[D].Saskatoon,Canada:University of Saskatchewan,2007.
    [4]
    HEIDARI M,CARLSON D L,SINHA S K,et al.An efficient multi-disciplinary simulation of engine fan-blade out event using MD nastran[R].AIAA-2008-2333,2008.
    [5]
    DZENAN H.Mechanical loads on a turbofan engine structure at blade-off[D].Lulea,Sweden:Lulea University of Technology,2009.
    [6]
    SINHA S K,DORBALAS.Dynamic loads in the fan containment structure of a turbofan engine[J].Journal of Aerospace Engineering,2009,22(3):260-269.
    [7]
    SINHA S K,TURNER K E.Dynamic loading on turbofan blades due to bird-strike[J].Journal of Engineering for Gas Turbines and Power,2011,133(12):1-13.
    [8]
    SINHA S K,CZARNECKI G J,HINRICHSEN R L.Dynamic analysis of damage to aircraft propulsion system impacted by exploding missile[J].Journal of Aircraft,2013,50(5):1526-1532.
    [9]
    SINHA S K.Rotor dynamic analysis of asymmetric turbofan rotor due to fanblade-loss event with contact-impact rub loads[J].Journal of Sound and Vibration,2013,332(9):2253-2283.
    [10]
    SENGOZ K,KAN S,ESKANDARIAN A.Development of a generic gas turbine engine fan blade-out full-fan rig model[R].Ashburn,US:The George Washington University Federal Highway Administration/National Highway Traffic Safety Administration (FHWA/NHTSA)National Crash Analysis Center,2015.
    [11]
    洪杰,郝勇,张博,等.叶片丢失激励下整机力学行为及其动力特性[J].航空发动机,2014,40(2):19-23.HONG Jie,HAO Yong,ZHANG Bo,et al.Mechanical behaviors and dynamic characteristics of turbofan engine due to fan blade off[J].Aeroengine,2014,40(2):19-23.(in Chinese)
    [12]
    马艳红,梁智超,王桂华,等.航空发动机叶片丢失问题研究综述[J].航空动力学报,2016,31(3):513-526.MA Yanhong,LIANG Zhichao,WANG Guihua,et al.Review on the blade loss of aeroengine[J].Journal of Aerospace Power,2016,31(3):513-526.(in Chinese)
    [13]
    洪杰,陈成,王永锋,等.突加不平衡激励下高速柔性转子系统振动特性试验[J].航空动力学报,2018,33(1):15-23.HONG Jie,CHEN Cheng,WANG Yongfeng,et al.Vibration test of high speed flexible rotor due to the sudden-unbalance[J].Journal of Aerospace Power,2018,33(1):15-23.(in Chinese)
    [14]
    刘璐璐,赵振华,陈伟,等.叶片丢失后发动机整机响应模拟试验与仿真[J].航空动力学报,2018,33(2):290-298.LIU Lulu,ZHAO Zhenhua,CHEN Wei,et al.Simulated test and numercial simulation of aero-engine whole engine response during blade out event[J].Journal of Aerospace Power,2018,33(2):290-298.(in Chinese)
    [15]
    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)
    [16]
    柴象海,侯亮,王志强,等.航空发动机宽弦风扇叶片鸟撞损伤模型标定[J].航空动力学报,2016,31(5):1032-1038.CHAI Xianghai,HOU Liang,WANG Zhiqiang,et al.Bird strike model calibration for an aero engine wid-chord fan blade[J].Journal of Aerospace Power,2016,31(5):1032-1038.(in Chinese)
    [17]
    陈光.航空发动机结构设计分析[M].2版.北京:北京航空航天大学出版社,2014.
    [18]
    Livemore Software Technology Corporation.LS-DYNA theory manual[EB/OL].[2019-05-26].http://www.lstc.com/download/manuals.
  • 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

    Article Metrics

    Article views (875) PDF downloads(389) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return