Volume 36 Issue 4
Apr.  2021
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2021  >  36(4): 826-838
TIAN Shaojie, QI Wenkai, XU Zhenghua. Method of blade vibration response analysis under airflow excitation[J]. Journal of Aerospace Power, 2021, 36(4): 826-838. doi: 10.13224/j.cnki.jasp.2021.04.015
Citation: TIAN Shaojie, QI Wenkai, XU Zhenghua. Method of blade vibration response analysis under airflow excitation[J]. Journal of Aerospace Power, 2021, 36(4): 826-838. doi: 10.13224/j.cnki.jasp.2021.04.015
shu

Method of blade vibration response analysis under airflow excitation

doi: 10.13224/j.cnki.jasp.2021.04.015

  • College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

  • Received Date: 2020-06-20
  • Publish Date: 2021-04-28
    Abstract
  • In order to study the method of blade vibration response analysis under airflow excitation, the aerodynamic excitation force prediction method was established. The nonlinear harmonic method was used to conduct three-dimensional unsteady flow analysis of the blades, obtain the fluctuating pressure on the blade surface, compile the flow-solid conversion program, and calculate the aerodynamic excitation force on the blade. The aerodynamic damping analysis method for blades was established. Based on the energy method and the weak coupling analysis method, the fluid-solid weak coupling analysis was carried out for blades and flow fields. The aerodynamic negative work done by aerodynamic forces on moving blades was equivalent to the work done by viscous damping force, and the modal aerodynamic damping ratio of rotor blades was obtained. The vibration response analysis method of blade excited by airflow was established, and based on aerodynamic excitation force and modal aerodynamic damping ratio of blade, modal superposition method was adopted. Using this method, the aerodynamic excitation force, the modal aerodynamic damping ratio of the first eight modes and the vibration response of the rotor blade under the combined action of the aerodynamic excitation force and the aerodynamic damping were calculated for the rotor stator blade array model of the 1.5-stage compressor in the engine. The results showed that the vibration stress reached 100 MPa.

     

    • FullText(HTML)
  • loading
    • References(25)
  • [1]
    罗楚威,陈江.轴流压气机非定常数值模拟方法精度分析［J］.航空动力学报,2017,32(11):2808-2816. LUO Chuwei,CHEN Jiang.Accuracy analysis of numerical simulation method for unsteady axial flow compressor［J］.Journal of Aerospace Power,2017,32(11):2808-2816.(in Chinese)
    [2]
    SMITH N R,KEY N L.Blade-row in-teraction effects on unsteady stator loading in an em-bedded compressor stage［J］.Journal of Propulsion and Power,2017,33(1):248-255.
    [3]
    KULISA P,DANO C.Numerical simulation of unsteady blade row interactions induced by passing wakes［J］.European Journal of Mechanics:B Fluids,2005,25(3):379-392.
    [4]
    刘锡阳,于海力,赵晓路,等.相位延迟法在双排涡轮三维非定常流动数值模拟中的应用［J］.工程热物理学报,2005,26(6):46-48. LIU Xiyang,YU Haili,ZHAO Xiaolu,et al.Accuracy analysis of numerical simulation method for unsteady axial flow compressor［J］.Journal of Engineering Thermophysics,2005,26(6):46-48.(in Chinese)
    [5]
    WANG Xiangpeng,WANG Yanrong,TIAN Aimei.Effect of axial spacing between rotor-stator on vibration stress of blade［J］.Journal of Aerospace Power,2016,31(6):1427-1434.
    [6]
    ARNONE A.Rotor-stator interaction analysis using the Navier-Stokes equations and a multi-grid method［J］.Journal of Turbomachinery,1996,118(4):1-15.
    [7]
    李亚,黄秀全,王远刚.叶片数约化对叶片气动载荷的影响研究［J］.科学技术与工程,2013,13(11):3190-3194. LI Ya,HUANG Xiuquan,WANG Yuangang.Study on the influence of blade reduction on blade aerodynamic load［J］.Science Technology and Engineering,2013,13(11):3190-3194.(in Chinese)
    [8]
    FENG Wang,DI MARE L.Favre-averaged nonlinear harmonic method for compressible periodic flows［J］.AIAA Journal,2019,57(3):1133-1142.
    [9]
    BURON J D,HOUDE S,LESTRIEZ R,et al.Application of the non-linear harmonic method to study the rotor-stator interaction in Francis-99 test case［J］.Journal of Physics Conference Series,2015,579(1):156-169.
    [10]
    药晓江,董景新,尚捷,等.非线性谐波法在叶轮机械非定常计算中的应用［J］.推进技术,2016,37(4):632-639. YAO Xiaojiang,DONG Jingxin,SHANG Jie,et al.Application of nonlinear har-monic method in unsteady calculation of turbomachinery［J］.Journal of Propulsion Technology,2016,37(4):632-639.(in Chinese)
    [11]
    王翔鹏.叶片尾迹激励及其强迫振动响应［D］.北京:北京航空航天大学,2015. WANG Xiangpeng.Blade wake excitation and its forced vibration response［D］.Beijing:Beijing University of Aeronautics and Astronautics,2015.(in Chinese)
    [12]
    VILMIN S P,LORRAIN  R,TARTINVILLE B T,et al.The nonlinear harmonic method:from single stage to multi-row effects［J］.International Journal of Computational Fluid Dynamics,2013,27(2):88-99.
    [13]
    SEINTURIER E,LOMBARD J P,DUMAS M,et al.Forced response prediction:methodology for the design of HP compressors bladed disks［R］.ASME Paper GT2004-53372,2004.
    [14]
    SRIVASTAVA R,BAKHLE M A,KEITH T G.Numerical simulation of aerodynamic damping for flutter analysis of turbomachinery blade rows［J］.Journal of Propulsion and Power,2003,19(2):260-267.
    [15]
    郭雪莲,李琳.航空发动机叶片气动阻尼的研究［C］∥第十一届全国空气弹性学术交流会会议论文集.昆明:中国空气动力学学会空气弹性力学专业委员会、中国力学学会流固耦合力学专业委员会、中国力学学会,2009:475-479.
    [16]
    张陈安,张伟伟,叶正寅.一种高效的叶轮机叶片气动阻尼计算方法［J］.力学学报,2011,43(5):826-833. ZHANG Chenan,ZHANG Weiwei,YE Zhengyin.An efficient calculation method for aerodynamic damping of turbine blades［J］.Chinese Journal of Theoretical and Applied Mechanics,2011,43(5):826-833.(in Chinese)
    [17]
    肖军,杨启超,王乐.离心叶轮气动阻尼的数值分析［J］.航空动力学报,2018,33(9):2129-2138. XIAO Jun,YANG Qichao,WANG Le.Numerical analysis of aerodynamic damping of centrifugal impeller［J］.Journal of Aerospace Power,2018,33(9):2129-2138.(in Chinese)
    [18]
    于航.叶轮机械振动的气动阻尼研究［D］.北京:北京航空航天大学,2006. YU Hang.Study on aerodynamic damping of turbomachinery vibration［D］.Beijing:Beijing University of Aeronautics and Astronautics,2006.(in Chinese)
    [19]
    郑赟,余永博.轴向间距对转子叶片颤振特性的影响机理［J］.北京航空航天大学学报,2018,44(4):709-716. ZHENG Yun,YU Yongbo.Mechanism of the influence of axial spacing on the flutter characteristics of rotor blades［D］.Journal of Beijing University of Aeronautics and Astronautics,2018,44(4):709-716.(in Chinese)
    [20]
    PALAZOTTO A,SHIPMAN W.The consideration of high cycle fatigue in a turbine blade［R］.AIAA-2002-1537,2002.
    [21]
    王梅.非定常流场分析结果向结构载荷压力场转化问题的解决［J］.燃气涡轮试验与研究,2005,18(3):15-18. WANG Mei.The solution to the problem of transforming the results of unsteady flow field analysis into structural load pressure field［J］.Gas Turbine Experiment and Research,2005,18(3):15-18.(in Chinese)
    [22]
    PIRACCINI F,LORUSSO S,MACELI N,et al.Forced response analysis of a steam turbine shrouded blade:numerical analysis and experiments［R］.ASME Paper GT2013-95703,2013.
    [23]
    王立刚,沈艳,杨丽宏.高等数值计算［M］.北京:清华大学出版社,2014:114-119.
    [24]
    赵军,刘宝杰.非线性谐波法的进一步校验分析［J］.航空动力学报,2008,23(4):680-686. ZHAO Jun,LIU Baojie.Further verification of nonlinear harmonic method［J］.Journal of Aerospace Power,2008,23(4):680-686.(in Chinese)
    [25]
    于航.叶轮机械振动叶片的气动阻尼研究［D］.北京:北京航空航天大学,2008. YU Hang.Study on aerodynamic damping of vibrating blades of turbomachinery［D］.Beijing:Beijing University of Aeronautics and Astronautics,2008.(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(4461.0KB)
    XML

    Article Metrics

    Article views (665) PDF downloads(390) 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