FARAHANI H K , KETABCHI M , ZANGENEH S , et al . Characterization of damage induced by impacting objects in Udimet-500 alloy [J ] . Journal of Failure Analysis and Prevention , 2016 , 16 ( 4 ): 629 - 634 . DOI: 10.1007/s11668-016-0129-7 http://doi.org/10.1007/s11668-016-0129-7 http://link.springer.com/10.1007/s11668-016-0129-7 http://link.springer.com/10.1007/s11668-016-0129-7

关玉璞 , 陈伟 , 高德平 . 航空发动机叶片外物损伤研究现状 [J ] . 航空学报 , 2007 , 28 ( 4 ): 851 - 857 . 全面地介绍了航空发动机叶片外物损伤研究的现状。叶片鸟撞击损伤是一种软物损伤。从鸟撞击叶片过程的理论研究、计算研究和试验研究三个方面进行了详细地介绍。叶片冰撞击损伤既可能是软物损伤又可能是硬物损伤。叶片冰损伤的研究文献较少，对此进行了简要地介绍。叶片硬物损伤包括金属块、石块和冰块三种形式。对叶片硬物损伤研究的各个方面，包括叶片硬物损伤的形成、叶片硬物损伤后的疲劳强度、叶片由于硬物损伤而产生微裂纹和微裂纹增长等，进行了详细地介绍。最后，提出了国内进行叶片外物损伤的研究方向。

GUAN Y P , CHEN W , GAO D P . Present status of investigation of foreign object to blade in aero-engine [J ] . Acta Aeronautica et Astronautica Sinica , 2007 , 28 ( 4 ): 851 - 857 . (in Chinese)

马超 , 王玉娜 , 武耀罡 , 等 . 航空发动机风扇叶片硬物冲击损伤特征 [J ] . 航空动力学报 , 2017 , 32 ( 5 ): 1105 - 1111 .

MA C , WANG Y N , WU Y G , et al . Hard object impact damage characteristic of aero-engine fan blade [J ] . Journal of Aerospace Power , 2017 , 32 ( 5 ): 1105 - 1111 . (in Chinese)

舒畅 , 程铭 , 许煜 , 等 . 航空发动机压气机叶片外物损伤规律研究 [J ] . 机械工程学报 , 2019 , 55 ( 13 ): 87 - 94 . DOI: 10.3901/JME.2019.13.087 http://doi.org/10.3901/JME.2019.13.087 通过对某型航空发动机压气机转子叶片外物损伤数据进行深入分析，揭示出损伤类型、缺口尺寸和位置沿压气机轴向和径向的分布规律。研究结果表明：在缺口、撕裂、凹坑和卷曲四类典型损伤中，缺口损伤所占的比重最大；低压压气机损伤率较高，且各级叶片损伤率随压气机级数的增加呈现下降趋势，高压压气机各级叶片中，各损伤类型表现出显著差异性，该特点与叶片材料、冲击能量等因素的变化有关；缺口损伤尺寸沿压气机的轴向分布差异性不明显，在高、低压气机中满足不同的分布形式，且损伤位置仅与深度尺寸存在显著关联；低压一级叶片大多数缺口损伤位于距离叶根高度80%以上区域，其损伤位置与损伤尺寸没有显著关联，但损伤宽度和损伤深度存在线性相关性。

SHU C , CHENG M , XU Y , et al . Study on foreign object damage regular pattern of aero engine compressor blades [J ] . Journal of Mechanical Engineering , 2019 , 55 ( 13 ): 87 - 94 . (in Chinese) DOI: 10.3901/JME.2019.13.087 http://doi.org/10.3901/JME.2019.13.087 Based on the analysis of foreign object damage on certain aero engine compressor blades,the distribution regular pattern of the damage type, notch size and position along the axial and radial directions of the compressor is revealed.The results indicate that the notch is the main type of four typical damages which include notches,tears,pits and curls. The damage rates on low pressure compressor blades are relatively high, and they have a downward trend with the increase of compressor stages, while the damage types on high pressure compressor blades are quite different, because of many changing factors such as blade material and impact energy. Furthermore, there is no obvious difference in the distribution of notch sizes along the axial direction of compressors, but their distribution characteristics are quite different between high and low pressure compressors, the damage location only has a significant correlation with the depth sizes. As far as the first blade of the low pressure compressors is concerned, most of notch damages are located more than 80% of the height above the blade root, there is no significant correlation between the notch position and the size, but there is a linear correlation between the notch width and depth.

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HU X T , SONG Y D . Research on effect of foreign object damage on high cycle fatigue performance for fan/compressor blades [J ] . Aeroengine , 2017 , 38 ( 3 ): 18 - 23 . (in Chinese)

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李静 , 孙强 , 李春旺 , 等 . 某型航空发动机压气机叶片振动疲劳寿命研究 [J ] . 应用力学学报 , 2011 , 28 ( 2 ): 189 - 193 .

LI J , SUN Q , LI C W , et al . Study on the vibration fatigue life for aero-engine compressor blade [J ] . Chinese Journal of Applied Mechanics , 2011 , 28 ( 2 ): 189 - 193 . (in Chinese)

MAJILA A N , RAMACHANDRA A S , MANNAN S L , et al . Influence of foreign object damage on high cycle fatigue of Ti-6Al-4V [J ] . Transactions of The Indian Institute of Metals , 2015 , 68 ( 8 ): 1 - 7 .

于霞 , 张卫民 , 邱忠超 , 等 . 航空发动机涡轮叶片裂纹检测信号特征提取 [J ] . 兵工学报 , 2014 , 35 ( 8 ): 1267 - 1274 . DOI: 10.3969/j.issn.1000-1093.2014.08.020 http://doi.org/10.3969/j.issn.1000-1093.2014.08.020 航空发动机涡轮叶片是高精密重要器件，其表面微裂纹检测属于不规则曲面检测的一种,是无损检测领域研究的热点和难点。考虑到涡流检测的特有优势，设计了一种不同于传统方式的简单实用且有效的差激励涡流探头，实现对涡轮叶片预制微裂纹的识别。由于叶片表面为曲率变化的弧面，检测过程难免会发生提离,因此获得的检测信号中包含噪声和多个奇异点等多种干扰因素。为保证缺陷位置重要信息不丢失，采用镜像延拓经验模态分解（EMD）重构与小波奇异性检测相结合的方法对得到的微裂纹信号进行处理，滤除了非裂纹位置的多处畸变点影响，有效准确地实现了叶片微裂纹位置的判定。实验结果表明，该方法可以有效降低检测信号的噪声和干扰，准确提取裂纹信号特征信息，对飞机涡轮叶片类零件微缺陷的早期检测和完整有效性评估具有一定的借鉴意义。

YU X , ZHANG W M , QIU Z C , et al . Signal feature extraction of aero-engine turbine blade crack detection [J ] . Acta Armamentarii , 2014 , 35 ( 8 ): 1267 - 1274 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2014.08.020 http://doi.org/10.3969/j.issn.1000-1093.2014.08.020 The aero-engine turbine blade is a high precision part. Blade surface crack detection belongs to an irregular surface detection, and is a hotspot and difficulty in the field of non-destructive testing. Taking the unique advantage of eddy current testing into account, a simple，practical and effective differential incentive eddy current probe is designed to detect the prefabricated micro-cracks of aero-engine turbine blades. Since the surface curvature of turbine blade varies, the lift-off effect exists inevitably in the detection process. Therefore, the test results of the detection signal contain noise and multiple singular points. In order to ensure that the important information of defect location is not lost, the combination of the mirror extension empirical mode decomposition（EMD）reconstruction and wavelet singularity detection method is used to process the detected micro-crack signals, filter out the influence of several distortion points on non-cracked positions, and achieve an accurate and effective determination of the micro-crack position of turbine blade. The results show that the method can effectively reduce the noise and interference of detection signal, and extract accurately the feature information of crack signal.

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HU X T , JIA X , ZHU Z J , et al . Effect of dent-type foreign object damage on fatigue strength of TC4 material [J ] . Journal of Aerospace Power , 2018 , 33 ( 4 ): 969 - 979 . (in Chinese)

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