某型发动机低压压气机转子叶片断裂分析  

Fracture Analysis of Low Pressure Compressor Rotor Blade of an Engine

作　　者：王文杰 蔡文波 Wang Wenjie;Cai Wenbo(Naval Equipment Ministry,Liaoning Dalian 116083,China)

机构地区：[1]海军装备部,辽宁大连116083

出　　处：《燃气轮机技术》2023年第2期57-61,共5页Gas Turbine Technology

摘　　要：针对某型发动机低压压气机第2级转子叶片于飞机起飞时发生的断裂故障,通过外观检查、断口表面检查、成分分析、硬度测试、强度计算以及对叶片修理过程排查等手段,对故障叶片断裂性质和产生原因进行分析。结果表明:叶片故障为疲劳断裂,断口疲劳裂纹起源于叶根转接圆弧处的凹坑损伤边缘。强度计算显示叶片凹坑损伤处叶身最大静应力比正常叶片增加42.8%,振动应力增加58%,应力增加、强度降低是促使故障叶片产生疲劳裂纹的主要原因。在叶片修理转运过程中叶片与转运工装铁质部件发生磕碰造成凹坑损伤,该缺陷在现有修理工艺中具有较强的隐蔽性。提出在叶片喷丸工序前增加表面质量检查,将叶片转运工装用材料由木质和铁质部件结合改为整体塑料成型,以避免类似故障的发生。This paper meanly focused on the fracture failure of the second-stage rotor blade of a certain type of engine during aircraft taking-off.The characteristics of fracture and the reasons were analyzed through visage inspection,fracture surface inspection,composition analysis,hardness test and strength calculation as well as checking the blade repair process.The results show that the cracked blade is fatigue fracture.Fracture fatigue crack originates from the edge of the pit damage at the transition arc of the blade root.Strength calculations show that the maximum static stress of the blade body at the fracture of the blade pits increases by 42.8%compared with the normal blade,and the vibration stress increases by 58%.The increase in stress and decrease in strength at the pit are the main reasons for the fatigue fracture of the cracked blade.In the process of repair and transport,the blade and the iron parts of the transport tooling collide and cause pit damage.This defect has strong concealment in the existing repair process.It is proposed to increase the surface quality inspection before the blade sand blowing process,and change the material of the blade transfer tooling from the combination of wood and iron parts to integral plastic molding to avoid similar failures.

关 键 词：转子叶片 断裂故障 失效分析 发动机 

分 类 号：TK478[动力工程及工程热物理—动力机械及工程]