航空发动机风扇叶片振动特性分析

寇海军; 张俊红; 林杰威

doi:10.7652/xjtuxb201411019

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航空发动机风扇叶片振动特性分析

更新时间：2025-07-09

- 航空发动机风扇叶片振动特性分析
- Aero-Engine Fan Blade Vibration Characteristic Analysis
- 西安交通大学学报 2014年48卷第11期页码：109-114
- 作者机构：
  
  天津大学内燃机燃烧学国家重点实验室,天津,300072
- 作者简介：
- 基金信息：
  
  : 2014-01-23。作者简介: 寇海军(1984—),男,博士生;张俊红(通信作者),女,教授,博士生导师。基金项目: 国家自然科学基金委员会与中国民用航空局联合资助重点项目(U1233201);教育部高等学校博士学科点专项科研基金资助项目(20130032130005);天津科技支撑计划重点项目(13ZCZDGX00200)
- DOI：10.7652/xjtuxb201411019
  中图分类号： V232.4
- 网络首发：2014-11-10，
  
  纸质出版：2014
- 稿件说明：
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寇海军, 张俊红, 林杰威. 航空发动机风扇叶片振动特性分析[J]. 西安交通大学学报, 2014,48(11):109-114.

Aero-Engine Fan Blade Vibration Characteristic Analysis[J]. 2014, 48(11): 109-114.
寇海军, 张俊红, 林杰威. 航空发动机风扇叶片振动特性分析[J]. 西安交通大学学报, 2014,48(11):109-114. DOI： 10.7652/xjtuxb201411019.

Aero-Engine Fan Blade Vibration Characteristic Analysis[J]. 2014, 48(11): 109-114. DOI： 10.7652/xjtuxb201411019.

摘要

针对叶片的振动失效关系到整台发动机的工作可靠性的问题

基于振动分析理论

在风扇叶片模态试验的基础上

结合有限元方法建立了叶片振动分析模型; 考虑气体与叶片的耦合作用

建立了旋转叶片流道模型; 利用计算流体动力学计算了额定工况下的叶片表面气动载荷

并将其引入旋转叶片有限元振动分析中进行了叶片静频、动频和振动响应分析

从而得到叶片在不同转速下的动态响应。分析发现

叶片转速在2 000～3 600 r/min范围内的10个转速点存在谐共振。通过进一步分析10个转速下的叶片振型与动态应力得出:临界转速工况下的振动应力明显高于相邻转速

但共振应力峰值与临界转速并无正相关性; 共振应力集中位置受叶片模态振型影响较大

始终出现于叶片前缘并沿叶高方向变化

表明叶片前缘最易发生振动疲劳。研究结果对叶片振动疲劳设计和维护维、修均有一定的指导意义。

Abstract

Vibration failure of blade affects the reliability of aero-engine. According to vibration analysis and modal test

a vibration calculation model of blade was established with the finite element method. Considering the fluid-solid interaction

a flow channel model of the rotating blade was constructed

and computational fluid dynamics was employed to compute the aerodynamic load on the blade surface under some rated conditions then was imported to the vibration model to calculate the static frequency

dynamic frequency and vibration responses of the blade at different rotational speeds. It is found that the resonance appears for several times between 2 000 and 3 600 r/min. And the further analyses for the blade vibration mode as well as dynamic stress at these speeds show that the vibration stress at critical speed is obviously higher than those at the adjacent speeds when the blade resonates

but there is no positive correlation between the peak vibration stress and critical speed. The peak vibration stress distribution is closely related to the modal shape of the blade

however

it always appears at the leading edge and changes along the blade height

and the leading edge of the blade is most prone to vibration fatigue.

关键词

Keywords

references

蔡肇云, 金六周. 航空发动机强度设计、试验手册: 叶片强度与振动计算[M]. 北京: 第三机械工业部第六研究院, 1980: 34-50.

SUBRAHMANYAM K B, KULKARNI S V, RAO J S. Coupled bending-bending vibrations of pre-twisted cantilever blading allowing for shear deflection and rotary inertia by the Reissner method[J]. International Journal of Mechanical Sciences, 1981, 23(9): 517-530.

SRINIVASIN A V. Flutter and resonant vibration characteristics of engine blades[J]. Journal of Engineering for Gas Turbines and Power, 1997, 119(4): 742-775.

POURSAEIDI E, BABAEI A. Effects of natural frequencies on the failure of R1 compressor blades[J]. Engineering Failure Analysis, 2012, 25: 304-315.

XU C, AMANO R S, LEE E K. Investigation of an axial fan-blade stress and vibration due to aerodynamic pressure field and centrifugal effects[J]. JSME International Journal Series: B, 2004, 47(1): 75-90.

郭强, 竺晓程. 高速离心压缩机旋转失速的全流场数值模拟[J]. 机械工程学报, 2009, 45(6): 284-289.

GUO Qiang, ZHU Xiaocheng. Numerical simulation of rotating stall inside high speed centrifugal compressor using entire geometry mesh[J]. Chinese Journal of Mechanical Engineering, 2009, 45(6): 284-289.

HOU J, WICKS B J. An investigation of fatigue failures of turbine blades in a gas turbine engine by mechanical analysis[J]. Engineering Failure Analysis, 2002, 9(2): 201-211.

曾庆华. 模态试验中跑点测量时传感器附加质量影响的消除[J]. 南京航空航天大学学报, 1994, 26(5): 692-695.

ZENG Qinghua. Elimination of effects of transducer mass on modal parameters in moving-point measurements[J]. Journal of Nanjing University of Aeronautics Astronautics, 1994, 26(5): 692-695.

POURSAEIDI E, AIENERAVAIE M. Failure analysis of a second stage blade in a gas turbine engine[J]. Engineering Failure Analysis, 2008, 15(8): 1111-1129.

KIM K K, LEE Y S. Modal characteristics according to the tip shape and assembly condition of the turbine blade[J]. Journal of Mechanical Science and Technology, 2013, 27(11): 3409-3417.

KOSMATKA J B, FRIEDMANN P. Vibration analysis of composite turbo propellers using a nonlinear beam-type finite-element approach[J]. AIAA Journal, 1989, 27(11): 1606-1614.

杨雯, 杜发荣. 宽弦空心风扇叶片动力响应特性研究[J]. 航空动力学报, 2007, 22(3): 444-449.

YANG Wen, DU Farong. Investigation of dynamic response property of wide-chord hollow fan blade[J]. Journal of Aerospace Power, 2007, 22(3): 444-449.

徐鹤山. 发动机叶片工程应用分析[M]. 北京: 航空工业出版社, 2011: 154-177.

航空发动机设计手册总编委会. 航空发动机设计手册:18册[M]. 北京: 北京航空工业出版社, 2000: 568-570.

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