Dynamic Response Characteristics Analysis of 3D Blade Tip Clearance for Turbine Blade Crack Azimuth Angle

FAN Bochao; ZHANG Xiaodong; XIONG Yiwei; HUANG Xin; DAI Fei

doi:10.7652/xjtuxb202407016

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Dynamic Response Characteristics Analysis of 3D Blade Tip Clearance for Turbine Blade Crack Azimuth Angle

更新时间：2025-07-28

- Dynamic Response Characteristics Analysis of 3D Blade Tip Clearance for Turbine Blade Crack Azimuth Angle
- Vol. 58, Issue 7, Pages: 170-178(2024)
- 作者机构：
  
  1. 西安交通大学机械工程学院,西安,710049
  2. 西安交通大学现代设计及转子轴承系统教育部重点实验室,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202407016
  CLC： V232.4
- Published：2024
- 稿件说明：
移动端阅览
FAN Bochao, ZHANG Xiaodong, XIONG Yiwei, et al. Dynamic Response Characteristics Analysis of 3D Blade Tip Clearance for Turbine Blade Crack Azimuth Angle[J]. 2024, 58(7): 170-178.
DOI：

FAN Bochao, ZHANG Xiaodong, XIONG Yiwei, et al. Dynamic Response Characteristics Analysis of 3D Blade Tip Clearance for Turbine Blade Crack Azimuth Angle[J]. 2024, 58(7): 170-178. DOI： 10.7652/xjtuxb202407016.

摘要

针对叶尖定时故障诊断方法在检测叶片裂纹时仅关注一维信息、提取故障特征有限的不足

利用叶尖间隙具有三维特征的特点

提出了航空发动机涡轮叶-盘-轴耦合系统的三维叶尖间隙(3D-BTC)有限元模型。以该模型为基础

分析了航空发动机涡轮叶片裂纹方位角对三维叶尖间隙的影响规律。首先

建立了航空发动机涡轮叶-盘-轴耦合系统有限元模型; 其次

在叶片尾缘处引入贯穿裂纹

通过瞬态动力学分析计算了在不同横滚角、俯仰角裂纹作用下叶片的变形; 最后

采用三维叶尖间隙计算方法获取了叶片三维叶尖间隙时域波形及频谱

研究了航空发动机涡轮叶片裂纹方位角的三维叶尖间隙动态响应特性。计算结果表明:裂纹的出现会降低叶片刚度

从而影响叶片的三维叶尖间隙; 叶片三维叶尖间隙随裂纹横滚角的增大而减小

随裂纹俯仰角的增大先减小后增大; 随着裂纹两类方位角变化

不同测点位置的叶尖径向间隙基本谐波分量峰值变化率的差值最大为6.1%

周向滑移角和轴向偏转角基本谐波分量峰值变化率的差值小于0.12%

可见综合三维叶尖间隙能够更准确地反映裂纹信息。

Abstract

In view of the insufficiency that blade tip timing(BTT)fault diagnosis method only focuses on one-dimensional information and has limited extraction of fault features in detecting blade cracks

a three-dimensional blade tip clearance(3D-BTC)finite element model of aero-engine turbine blade-disk-shaft coupling system is proposed based on the 3D characteristics of blade tip clearance(BTC). Based on this model

the effect of aero-engine turbine blade crack azimuth angle on 3D-BTC is analyzed. Firstly

a finite element model of an aero-engine turbine blade-disk-shaft coupling system is established. Then the through crack is introduced at the trailing edge of the blade

and the blade deformation under the influence of cracks at different roll angles and pitch angles is calculated through transient dynamics analysis. Finally

the 3D-BTC calculation method is used to obtain the time domain waveform and spectrum of the 3D-BTC and study the 3D-BTC dynamic response characteristics of the aero-engine turbine blade crack azimuth angle. The results show that the crack reduces the blade stiffness and affects the 3D-BTC. The 3D-BTC decreases with the increase of crack roll angle

and decreases first and then increases with the increase of crack pitch angle. With the change of the crack azimuth angles

the difference of the basic harmonic component peak change rate of radial tip clearance at different measuring points is up to 6.1%. The difference of the basic harmonic component peak change rate of circumferential deflection angle and axial deflection angle is less than 0.12%. The information on blade cracks can be obtained more accurately based on the 3D-BTC.

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references

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