飞机发动机叶片缺陷的差激励涡流传感器检测  

Differential excitation eddy current sensor testing for aircraft engine blades defect

作　　者：于霞[1,2] 张卫民[1] 邱忠超[1] 陈国龙[1] 秦峰[1] 

机构地区：[1]北京理工大学机械与车辆学院,北京100081 [2]中国兵器工业导航与控制技术研究所,北京100089

出　　处：《北京航空航天大学学报》2015年第9期1582-1588,共7页Journal of Beijing University of Aeronautics and Astronautics

基　　金：总装预研项目

摘　　要：针对某型号飞机发动机涡轮叶片上预制的微裂纹缺陷进行了检测研究.基于涡流检测技术设计并研制了一种尺寸小、灵敏度高的差激励探头,应用有限元分析软件开展了叶片微裂纹缺陷仿真分析.为了实现叶片的自动高效检测,设计并采用数控多自由度扫查台来控制采集过程,实现了对叶片表面裂纹缺陷的快速扫查检测.采集信号经过信号调理电路,A/D转换后输入计算机,完成信号的保存、处理和输出.通过对比实验结果与仿真结果发现,研制的差激励式涡流传感器可以有效地实现对叶片类零件表面微裂纹位置的判定,对涡轮叶片类零件微缺陷早期诊断评估具有一定的现实和借鉴意义.The micro-crack detection experiments of the certain model aircraft engine turbine blades were carried out. Based on eddy current testing technology,a small differential excitation probe with high sensitivity and difference from traditional probes was designed and developed. The simulation analysis of micro-crack on aircraft engine turbine blades was completed by finite element analysis software. In order to realize the automatic and efficient detection of engine blades,a computerized numerical control（ CNC） scanner with multidegree of freedom was designed and adopted to control the acquisition process. The detection signals were acquired via the signal conditioning circuit,A/D card and input into computers,where the signals storing,processing and output completed. By comparing the experimental and simulation results,it can be seen that the difference incentive eddy current sensor can effectively and accurately determine the micro-crack position on the blade surface and has practical significance and reference value for evaluating micro-defects of aircraft turbine blade parts during early diagnosis.

关 键 词：发动机叶片 差激励 涡流传感器 裂纹 仿真分析 

分 类 号：TG115.8[金属学及工艺—物理冶金] V263.1[金属学及工艺—金属学]