基于磨粒流处理高涡工作叶片振动疲劳断裂损伤行为研究  

Study on Vibration Fatigue of Working Blades with High Vortexes Based on Abrasive Flow

作　　者：陈星 刘新灵 张金刚 胡春燕 范浩 陈焕圳 CHEN Xing;LIU Xin-ling;ZHANG Jin-gang;HU Chun-yan;FAN Hao;CHEN Huan-zhen(AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;AVIC Failure Analysis Center,Beijing 100095,China;Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation,Beijing 100095,China;Key Laboratory of Aeronautical Materials Testing and Evaluation,Aero Engine Corporation of China,Beijing 100095,China;College of Materials Science and Engineering,Nanchang Hangkong University,Nanchang 330063,China;AECC South Industry Co.,Ltd.,Hunan Zhuzhou 412002,China)

机构地区：[1]中国航发北京航空材料研究院,北京100095 [2]航空工业失效分析中心,北京100095 [3]航空材料检测与评价北京市重点实验室,北京100095 [4]中国航空发动机集团材料检测与评价重点实验室,北京100095 [5]南昌航空大学材料科学与工程学院,南昌330063 [6]中国航发南方工业有限公司,湖南株洲412002

出　　处：《失效分析与预防》2023年第1期29-36,共8页Failure Analysis and Prevention

基　　金：国家科技重大专项项目(J2019-IV-0011-0079);国防科工局重点项目(KZ5C200778)。

摘　　要：高涡工作叶片在电火花和大功率飞秒激光制孔状态下孔边存在重熔层和棱状痕迹等缺陷,磨粒流可有效去除重熔层和改善孔边导圆。对通过磨粒流处理前后的模拟件和叶片的振动疲劳性能和断裂损伤行为进行对比研究,结果表明:叶片高温振动疲劳失效位于叶根一弯应力较大区,磨粒流处理前后并未改变结构应力。磨粒流处理后,叶片裂纹起源发生改变,由原来的气膜孔内壁入口侧角源和孔壁中部制孔缺陷小线源,转变为仅从气膜孔内壁入口侧角源,且孔边存在导圆,改善局部应力,提升叶片高周疲劳可靠性;磨粒流处理前后裂纹扩展方式相似,均为裂纹萌生后沿叶片厚度和叶宽方向斜向45°扩展,与单晶材料或板型试样振动疲劳扩展方式相同,之后沿着前缘、尾缘、加强筋多向扩展,扩展前期呈类解理特征,扩展中后期可见较宽的疲劳条带。The high vortex working blade has defects such as remelted layer and prismatic marks on the edge of the hole under the state of electrical discharge machining and high-power femtosecond laser drilling.The abrasive flow treatment can effectively remove the remelted layer and improve the rounding of the hole edge.The study was performed by comparing the vibration fatigue performance and fracture damage behavior of simulated parts and blades before and after the abrasive flow treatment.The results show that the high-temperature vibration fatigue failure of the blade is located in the relatively large bending stress area of the blade root,and the structural stress does not change before and after the abrasive flow treatment.After the abrasive flow treatment,the origin of the blade cracks changed from the original angle source on the inlet side of the inner wall in the air film hole and the small line source of the hole-making defect in the middle of the hole wall to only the angle source on the inlet side of the inner wall in the air film hole.Also,there is a guide hole at the edge,which improves the local stress and improves the high-cycle fatigue reliability of the blade.The crack propagation mode before and after the abrasive flow treatment is similar:they both propagated obliquely at 45°along the thickness and width of the blade after the initiation of crack,which is the same with the vibration fatigue expansion mode of single crystal materials or plates.After that,it expands in multiple directions along the leading edge,trailing edge,and ribs.The early expansion shows a cleavage-like feature,and a wide fatigue strip can be seen in the middle and late expansion.

关 键 词：磨粒流 涡轮工作叶片 振动疲劳 损伤评价 断裂损伤行为 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]