涡扇发动机二级转子叶片超温断裂分析  

Fracture Analysis for Second Stage Rotor Turbine Blade in Aero-engine

作　　者：赵文侠[1,2,3] 李莹[1,2,3] 范映伟[1,2,3] 郑运荣[1] 

机构地区：[1]北京航空材料研究院,北京100095 [2]中航工业失效分析中心,北京100095 [3]中航工业试金石检测公司,北京100095

出　　处：《材料工程》2012年第8期39-44,共6页Journal of Materials Engineering

摘　　要：运用光学显微镜、扫描电子显微镜、电子探针微束分析仪对断裂叶片表面进行了宏观形貌、叶片断口宏观、微观形貌及显微组织分析,推断出叶片使用时不同部位所承受的温度范围,并对断裂原因进行了探讨。结果表明:启动超温致使叶片γ′相回溶甚至过烧至初熔状态,局部枝晶间和晶界出现明显液化现象,叶片前缘和后缘过烧程度严重,该区承受的温度达到甚至超过了1260℃,距叶片前缘约6mm中心区,其承温在1220℃左右,离叶片前缘8mm处,其短时承温在1180℃以下;超温使叶片处于严重过载状态,最终造成多个叶片瞬间断裂。The macrostructure, micromorphology and microstructure were detected by optical micro scope, scanning electrical microscope and electrical probe microanalyzer. The temperature range on different areas of turbine blade was deduced during. And the reason that caused blade fractured was discussed. The results show that,during the starting stage of engine, 7＇phase dissolved or even turn out to be incipient melting caused by overheat, liquefaction was found in parts of interdendritic and grain boundary, leading edge and trailing edge of blade overburned seriously where the temperature reached more than 1260°C, temperature of central area on the blade was around 1220°C where away from leading edge about 6mm, temperature of area was under 1180°C in short time where away from leading edge about 8mm. Overload state on blade caused by overheat, and finally some of blade frac tured instantly.

关 键 词：涡轮叶片 超温 初熔 过载断裂 失效分析 

分 类 号：TG115[金属学及工艺—物理冶金]