| 蔡苏阳,陈振华,冯萍,张浩喆,何喜,方雨婷,卢超.涡轮叶片热障涂层中微小缺陷的阵列超声瑞利波检测[J].电子测量与仪器学报,2025,39(8):22-29 |
| 涡轮叶片热障涂层中微小缺陷的阵列超声瑞利波检测 |
| Array ultrasonic Rayleigh wave detection of small defects inthermal barrier coatings of turbine blade |
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| DOI： |
| 中文关键词: 涡轮叶片 热障涂层 瑞利波 微裂纹 |
| 英文关键词:turbine blade thermal barrier coatings Rayleigh wave micro-crack |
| 基金项目:国家自然科学基金（12464059）、航发技术委托项目（HFDL-KYZ-JSZ-202308-40）资助 |
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| Author | Institution |
| Cai Suyang | Key Laboratory of Nondestructive Testing of Ministry of Education, Nanchang Hangkong University, Nanchang 330063, China |
| Chen Zhenhua | Key Laboratory of Nondestructive Testing of Ministry of Education, Nanchang Hangkong University, Nanchang 330063, China |
| Feng Ping | AECC Aviation Power Co., Ltd., Xi′an 710021, China |
| Zhang Haozhe | AECC Aviation Power Co., Ltd., Xi′an 710021, China |
| He Xi | AECC Aviation Power Co., Ltd., Xi′an 710021, China |
| Fang Yuting | Key Laboratory of Nondestructive Testing of Ministry of Education, Nanchang Hangkong University, Nanchang 330063, China |
| Lu Chao | Key Laboratory of Nondestructive Testing of Ministry of Education, Nanchang Hangkong University, Nanchang 330063, China |
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| 中文摘要: |
| 航空涡轮叶片的热障涂层可降低叶片表面温度、防止表面高温腐蚀，涂层缺陷严重影响叶片使用性能，复杂的叶片曲面形状及其基体结构导致涂层缺陷的无损检测困难。鉴于瑞利波对表面应力和表面微裂纹等损伤变化敏感的特性，提出了基于广义瑞利波传播的涡轮叶片热障涂层表面微裂纹缺陷无损检测方法。设计了专用超声阵列换能器并搭建了瑞利波检测系统，提取沿叶片宽度方向上叶背涂层中传播的瑞利波检测信号，分析叶片幅度的分布特征与叶片内部复杂结构的关联；最后，分析叶片中人工窄槽对瑞利波传播特征的影响，并提出涂层缺陷的广义瑞利波检测方法。结果表明，涡轮叶片复杂表面轮廓、内腔导流结构导致对瑞利波幅度具有显著影响；将完好叶片涂层的瑞利波幅度分布与带窄槽（500 μm×80 μm×20 μm）的叶片涂层瑞利波幅度分布特征相对比表明，含窄槽路径上传播的超声波幅度明显上升，平均增大了54.3 mV，该特征可用于涡轮叶片热障涂层表面微裂纹缺陷损伤的无损检测。 |
| 英文摘要: |
| The thermal barrier coating of aviation turbine blades can reduce the surface temperature of the blades and prevent high temperature corrosion on the surface. The coating defects affect the performance of the blades seriously. The complex blade surface shape and its matrix structure lead to the difficulty of non-destructive testing of coating defects. In view of the sensitivity of Rayleigh wave to damage changes such as surface stress and surface micro-cracks, a non-destructive testing method for micro-crack defects on the surface of turbine blade thermal barrier coating based on generalized Rayleigh wave propagation is proposed. A special ultrasonic array transducer was designed and a Rayleigh wave detection system was built. The Rayleigh wave detection signal propagating in the back coating along the width direction of the blade was extracted, and the correlation between the distribution characteristics of the blade amplitude and the complex structure inside the blade was analyzed. Finally, the influence of artificial narrow slots in the blade on the propagation characteristics of Rayleigh waves is analyzed, and a generalized Rayleigh wave detection method for coating defects is proposed. The results show that the complex surface profile and the inner cavity diversion structure of the turbine blade have a significant effect on the amplitude of the Rayleigh wave. The Rayleigh wave amplitude distribution of the intact blade coating is compared with the Rayleigh wave amplitude distribution characteristics of the blade coating with a narrow groove (500 μm×80 μm×20 μm). The results show that the ultrasonic amplitude propagating on the path with a narrow groove increases significantly, with an average increase of 54.3 mV. This feature can be used for non-destructive testing of micro-crack defect damage on the surface of turbine blade thermal barrier coating. |
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