航空发动机涡轮叶片裂纹的阵列涡流检测仿真

doi:10.7527/S1000-6893.2013.0516

材料工程与机械制造

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航空发动机涡轮叶片裂纹的阵列涡流检测仿真

宋凯¹, 刘堂先¹, 李来平², 危荃², 涂俊²

1. 南昌航空大学无损检测技术教育部重点实验室, 江西南昌 330063;
2. 上海航天精密机械研究所, 上海 201600

收稿日期:2013-09-21 修回日期:2013-12-18 出版日期:2014-08-25 发布日期:2014-01-03
通讯作者: 宋凯，Tel.：0791-87637649，E-mail：Songkai@nchu.edu.cn E-mail:Songkai@nchu.edu.cn
作者简介:宋凯男，博士，副教授。主要研究方向：电磁无损检测，电磁场数值计算。Tel：0791-87637649，E-mail：Songkai@nchu.edu.cn；刘堂先男，硕士研究生。主要研究方向：阵列涡流检测。Tel：0791-87637649，E-mail：laotanglove@gmail.com；李来平男，博士，研究员。主要研究方向：无损检测。Tel：021-37842600，E-mail：llp117@126.com
基金资助:
国家自然科学基金（51265041）；上海航天科技创新基金；江西省教育厅科技项目（GJJ12444）；无损检测技术教育部重点实验室基金（ZD201029003）

Simulation on Aero-engine Turbine Blade Cracks Detection Based on Eddy Current Array

SONG Kai¹, LIU Tangxian¹, LI Laiping², WEI Quan², TU Jun²

1. Key Laboratory of Nondestructive Testing, Ministry of Education, Nanchang Hangkong University, Nanchang 330063, China;
2. Shanghai Spaceflight Precision Machinery Institute, Shanghai 201600, China

Received:2013-09-21 Revised:2013-12-18 Online:2014-08-25 Published:2014-01-03
Supported by:
National Natural Science Foundation of China (51265041);Innovation Fund for Technology Based Aerospace Shanghai;Science and Technology Project in Jiangxi Province Department of Education (GJJ12444);Foundation for Key Laboratory of Nondestructive Testing of Ministry of Education of China (ZD201029003)

摘要/Abstract

摘要：

阵列涡流检测技术因检测范围大和适应性强等诸多优点适合航空发动机涡轮叶片的快速检测。本文建立了发动机涡轮叶片裂纹阵列涡流检测的有限元模型，研究涡轮叶片的叶盆和叶背两种曲面下阵列涡流传感器的检测信号特征。仿真结果表明：当涡流探头与叶身的提离距离不变时，检测线圈的感应电动势随凸面、平面和凹面的次序逐渐增加；检测纵向裂纹时检测线圈电动势敏感度可达激励线圈的12.5倍，其电动势波峰和波谷的距离可表征纵向裂纹的长度且误差小于1.0 mm，而横向裂纹深度也与检测线圈电动势的波谷幅值成单调递减关系，仿真结果可望用于指导发动机涡轮叶片的工程检测实践。

关键词: 涡轮叶片, 阵列涡流, 裂纹, 有限元, 感应电动势

Abstract:

The eddy current array testing technique features a large range of detection, strong adaptability, and many other advantages, which make it suitable for rapid aero-engine turbine blade detecting. In this paper a finite element eddy current array testing model of engine turbine blade cracks is established, and the signal characteristics are studied of the eddy current arrayed sensors for the concave and convex surfaces of the turbine blades. The simulation results show that the electromotive force of the detecting coil increases gradually with convex, plane and concave surfaces when the lift-off distance between the eddy current probe and the blade body is constant. The sensitivity of detecting coil electromotive force for longitudinal cracks can reach 12.5 times that of the excitation coil, and the distance between the peak and trough electromotive force can represent the length of the longitudinal crack with an error of less than 1.0 mm. The transverse crack depth and the trough amplitude of the detecting coil electromotive force show a relationship of monotone decreasing. The simulation results can be used to guide engine turbine blade testing in engineering practice.

Key words: turbine blade, eddy current array, cracks, finite element, electromotive force

中图分类号:

宋凯, 刘堂先, 李来平, 危荃, 涂俊. 航空发动机涡轮叶片裂纹的阵列涡流检测仿真[J]. 航空学报, 2014, 35(8): 2355-2363.

SONG Kai, LIU Tangxian, LI Laiping, WEI Quan, TU Jun. Simulation on Aero-engine Turbine Blade Cracks Detection Based on Eddy Current Array[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(8): 2355-2363.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

航空发动机涡轮叶片裂纹的阵列涡流检测仿真

Simulation on Aero-engine Turbine Blade Cracks Detection Based on Eddy Current Array

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