摘要
高温合金作为航空紧固件的主要原材料,其力学性能直接影响着航空装备构件的紧固性能。以GH4141高温合金为试验材料,分析不同热处理后GH4141试样的金相组织、显微硬度、力学性能和断口形貌等特征,研究结果表明了固溶温度对晶粒尺寸影响较大,且随着固溶温度的升高,显微硬度降低;热处理后试样表面形成的残余应力为压缩状态;试样在1080℃固溶760℃时效处理后的拉伸强度最大为1214 MPa,其拉伸断口表现出明显的析出相强化诱导的颈缩和韧窝特征。
As the main raw material of aviation fasteners,the mechanical properties of superalloy directly affect the fastening properties of aviation equipment components.In this study,the microstructure,microhardness,mechanical properties and fracture morphology of GH4141 superalloy after different heat treatments were analyzed.The results show that the solution temperature has a great effect on the grain size,and the microhardness decreases with the increase of solution temperature.The residual compressive stress formed on the surface of the samples after heat treatment.The maximum tensile strength of the sample after solution at 1080℃and aging at 760℃was 1214 MPa,and the tensile fracture showed obvious features of precipitated phase strengthening induced neck shrinkage and dimples.
作者
孙晓军
刘乐
付建建
杨晨辉
孙志擎
张亚龙
SUN Xiaojun;LIU Le;FU Jianjian;YANG Chenhui;SUN Zhiqing;ZHANG Yalong(Henan Provincial Key Laboratory of Fastening Technology,Xinyang 464000,CHN;School of Aerospace Engineering,Zhengzhou University of Aeronautics,Zhengzhou 450046,CHN;School of Mechanical and Automotive Engineering,South China University of Technology,Guangzhou 510640,CHN)
出处
《制造技术与机床》
北大核心
2023年第4期85-88,共4页
Manufacturing Technology & Machine Tool
基金
河南省紧固连接技术重点实验室开放课题(JGLJ2202)
中国博士后科学基金(2022M712920)。
