航空发动机用镍基单晶高温合金涡轮叶片服役后的显微组织损伤  

Microstructure Damage of Nickel-Based Single Crystal Superalloy Turbine Blade for Aircraft Engine after Service

作　　者：冷玉潇 曹铁山[1] 陈家万 程从前[1] 赵杰[1] LENG Yuxiao;CAO Tieshan;CHEN Jiawan;CHENG Congqian;ZHAO Jie(School of Materials Science and Engineering,Dalian University of Technology,Dalian 116024,China)

机构地区：[1]大连理工大学材料科学与工程学院,大连116024

出　　处：《机械工程材料》2025年第2期34-42,共9页Materials For Mechanical Engineering

摘　　要：在服役一定时间的航空发动机用镍基单晶高温合金高压涡轮叶片不同叶片高度(叶根,49%叶高,60%叶高,85%叶高)的横截面上取样进行显微组织观察和硬度测试,以榫头部位显微组织为基准研究了叶片不同区域(叶片前缘、叶盆、尾缘、叶背)的显微组织损伤及其与硬度变化的关系。结果表明:叶片相同高度处的前缘和尾缘区域由于承受更高的温度和应力,组织损伤程度较叶背和叶盆区域更显著。49%和60%叶高处前缘和尾缘区域的显微组织损伤最为严重,尤其是在尾缘区域,γ'相的退化现象显著,表现为面积分数明显降低、颗粒边角出现钝化以及部分γ'相发生回溶。49%和60%叶高处尾缘区域的硬度明显低于叶背和叶盆区域。γ'相的回溶和颗粒粗化会使硬度下降,而在较低温度区域或较低应力条件下,γ'相颗粒相对稳定,回溶和粗化现象较少,硬度较高。The cross-sections of different blade heights(blade root,49%blade height,60%blade height,85%blade height)of nickel-based single crystal superalloy high-pressure turbine blade for the aircraft engine after service for a certain period of time were sampled,and the microstructure observation and microhardness test were carried out.Based on the microstructure of the tenon,the microstructure damage at different areas(blade leading edge,blade basin,railing edge,blade back)of the blade and its relationship with the microhardness change were studied.The results show that the leading edge and trailing edge of the blade at the same height were subjected to higher temperature and stress,and the degree of microstructure damage was more significant than that in the blade back and blade basin.The microstructure damage of the leading edge and trailing edge at 49%and 60%blade height was the most serious,especially in the trailing edge area.The degradation of γ' phase in the trailing edge area at 49%and 60%blade height was significant,which was manifested by the decrease of γ' phase area fraction,the passivation of particle edges and the re-dissolution of some γ' phases.The microhardness of the trailing edge area at 49%and 60%blade height was significantly lower than that of the blade back and the blade basin.The re-dissolution and coarsening process of γ' phase would reduce the microhardness.Under relatively low temperatures or relatively low stresses,γ' phase particles were relatively stable,the re-dissolution and coarsening phenomenon was relatively rare,and the hardness was relatively high.

关 键 词：镍基单晶高温合金 涡轮叶片 服役损伤 组织退化 硬度降低 

分 类 号：TG132.3[一般工业技术—材料科学与工程]