摘要
对某型发动机经过等效2500 h试车的DZ406合金定向柱晶燃气涡轮工作叶片不同位置进行了显微组织分析,并与试车前状态叶片的显微组织进行了对比分析,对叶片的剩余寿命进行了推断。结果表明,DZ406合金叶片标准热处理组织主要由块状的碳化物、残留共晶(γ+γ′)和规则立方状的γ′相及γ基体组成,γ′相尺寸约为0.5μm。燃气涡轮工作叶片等效试车2500 h后,心部组织退化程度不高,基体通道无明显变化,γ′相基本保持立方化,尺寸有所长大,平均约0.8μm,未发现TCP相析出。试车叶片外表面组织退化程度高于心部,部分区域基体通道明显变粗,γ′相局部发生连接或合并,高退化区域深度约30μm。根据试车叶片心部组织形貌进行推断,试车叶片剩余寿命为6863 h。
Microstructure analysis of DZ406 superalloy directionally solidified gas turbine blades after 2500 h of equivalent trial run was conducted.The investigation was focused on different regions of the blade and compared these findings with original microstructure of the blades to assess remaining life.The results reveal that the standard heat treated DZ406 superalloy microstructure primarily consists of blocky carbides,residual(γ+γ′)eutectics,regular cubicγ′precipitates,andγmatrix.The size of theγ′phase in the standard condition is approximately 0.5μm.After 2500 h of equivalent trail run,the core microstructure exhibits minimal degradation,with no significant change in the matrix channels,andγ′phases retain its cubic structure,with a slight increase in the average size to about 0.8μm,meanwhile there is no topologically close-packed(TCP)phase precipitated.The microstructure of surface region shows more pronounced degradation compared to the core,with noticeable coarsening of the matrix channels and local merging or linking ofγ′precipitates.The depth of high degradation in the surface region is approximately 30μm.Based on the observed core microstructure characteristics,it is inferred that remaining life of the tested blades is 6863 h.
作者
陈升平
黄秋玉
罗璇
方向
易出山
贾新云
黄朝晖
Chen Shengping;Huang Qiuyu;Luo Xuan;Fang Xiang;Yi Chushan;Jia Xinyun;Huang Zhaohui(Science and Technology on Advanced High Temperature Structural Materials Laboratory,AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;AECC South Industry Co.,Ltd.,Zhuzhou Hunan 412000,China;AECC Hunan Powerplant Research Institute,Zhuzhou Hunan 412002,China)
出处
《金属热处理》
北大核心
2025年第8期80-85,共6页
Heat Treatment of Metals
