摘要
针对R20燃气轮机第三级涡轮工作叶片断裂事故,对叶片断裂部位开展宏观、微观形貌分析和力学性能检测,得出叶片断裂的原因。结果显示:叶片的失效原因为疲劳,疲劳源在叶盆侧距离进气边3~4 mm的表面研磨区域交界处,对比2和3号叶片的相同位置,1号叶片第一榫齿面研磨情况较为严重,研磨区域内含有较高的铁和氧元素,与榫齿面和涡轮盘榫槽面发生微动磨损有关,导致疲劳裂纹过早地萌生;从宏观上观察断口的疲劳扩展区比例、疲劳条纹宽度和疲劳条纹出现位置,判断为高周疲劳且疲劳裂纹扩展应力较高。
Aiming at the fracture of the third-stage turbine working blade of the R20 gas turbine,inspect the macroscopic and microscopic morphology analysis of the blade fracture part,and the mechanical performance detection,obtain the reason why blade fracture.The results show that the failure property of the blade is fatigue,the fatigue source is the line source,where at the junction of the surface grinding area 3~4 mm away from the air intake edge which on the side of the leaf basin.Compared with the same position of No.2 and No.3 blades,the grinding situation of the first tenon surface of blade No.1 is relatively serious.The grinding area contains high iron and oxygen,which are related the fretting wear of tenon surface and turbine plate tenon groove surface,resulting in premature fatigue cracks problem.According to the proportion of fatigue expansion area,fatigue fringe width and fatigue fringe occurrence position on macro fractures,it is judged to be high cycle fatigue and fatigue crack propagation stress is high.
作者
王辉
Wang Hui(AECC Gas Turbine(Zhuzhou)Co.,Ltd.,Hunan Zhuzhou 412000,China)
出处
《燃气轮机技术》
2023年第2期62-67,72,共7页
Gas Turbine Technology
