Aero-Engine Fan Blade Vibration Characteristic Analysis

doi:10.7652/xjtuxb201411019

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Aero-Engine Fan Blade Vibration Characteristic Analysis

更新时间：2025-07-09

- Aero-Engine Fan Blade Vibration Characteristic Analysis
- Vol. 48, Issue 11, Pages: 109-114(2014)
- 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：
- DOI：10.7652/xjtuxb201411019
  CLC： V232.4
- Online First：10 November 2014，
  
  Published：2014
- 稿件说明：
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Aero-Engine Fan Blade Vibration Characteristic Analysis[J]. 2014, 48(11): 109-114.
DOI：

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

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