固溶时效对激光沉积修复<strong>ZM6</strong>合金组织及力学性能的影响

doi:10.11900/0412.1961.2023.00330

金属学报

2025, Vol. 61

Issue (6): 875-886 DOI: 10.11900/0412.1961.2023.00330

研究论文

本期目录 | 过刊浏览

固溶时效对激光沉积修复ZM6合金组织及力学性能的影响

钦兰云¹, 张健¹, 伊俊振²^,³(

), 崔岩峰⁴, 杨光¹(

), 王超³

1 沈阳航空航天大学机电工程学院沈阳 110136
2 沈阳航空航天大学材料科学与工程学院沈阳 110136
3 沈阳航空航天大学航空制造工艺数字化国防重点学科实验室沈阳 110136
4 中国航发哈尔滨东安发动机有限公司哈尔滨 150066

Effects of Solution Aging on Microstructural Evolution and Mechanical Properties of Laser Deposition Repairing ZM6 Alloy

QIN Lanyun¹, ZHANG Jian¹, YI Junzhen²^,³(

), CUI Yanfeng⁴, YANG Guang¹(

), WANG Chao³

1 School of Mechatronics Engineering, Shenyang Aerospace University, Shenyang 110136, China
2 School of Materials Science and Engineering, Shenyang Aerospace University, Shenyang 110136, China
3 Key Laboratory of Fundamental Science for National Defense of Aeronautical Digital Manufacturing Process, Shenyang Aerospace University, Shenyang 110136, China
4 AECC Harbin Dongan Engine Co. Ltd., Harbin 150066, China

引用本文:

钦兰云, 张健, 伊俊振, 崔岩峰, 杨光, 王超. 固溶时效对激光沉积修复ZM6合金组织及力学性能的影响[J]. 金属学报, 2025, 61(6): 875-886.
Lanyun QIN, Jian ZHANG, Junzhen YI, Yanfeng CUI, Guang YANG, Chao WANG. Effects of Solution Aging on Microstructural Evolution and Mechanical Properties of Laser Deposition Repairing ZM6 Alloy[J]. Acta Metall Sin, 2025, 61(6): 875-886.

全文: PDF(6064 KB) HTML

摘要:

为了提高镁合金航空构件修复质量、延长服役寿命，本工作针对航空镁合金构件的冶金缺陷及服役损伤开展了ZM6合金激光沉积修复研究，对比分析了固溶时效(T6：520 ℃、8 h + 220 ℃、14 h)处理前后修复试样微观组织及力学性能的变化。结果表明，沉积态试样修复区组织由细小的α-Mg相和第二相组成，第二相主要以连续网状分布在晶界处，少量以点状及棒状分布在晶粒内部。修复区平均硬度为(60 ± 2) HV_0.1，修复试样的抗拉强度、屈服强度和延伸率分别为137.47 MPa、111.61 MPa和5.57%，其断裂位置在基材部分，断裂模式为沿晶-穿晶混合的脆性断裂；经T6处理后，修复区组织由细小的α-Mg晶粒和异常粗大晶粒组成，且晶粒内部析出了β′相。T6处理后试样修复区的平均硬度提高17.5%，异常粗大晶粒和细小晶粒导致硬度波动范围较大，抗拉强度和屈服强度分别提升了49.8%和75.6%，但延伸率有所下降。拉伸试样断裂位置在修复区，异常粗大晶粒是引起断裂的主要原因。

关键词 ：激光沉积修复, ZM6合金, 固溶时效, 异常粗大晶粒, 力学性能

Abstract：

ZM6 (Mg-Nd-Zn-Zr) alloy is a typical casting magnesium alloy with low density, high specific strength and stiffness, good vibration damping performance, good machinability, and good heat resistance. It is widely used in aerospace and aviation fields. However, metallurgical or machining defects are inevitable while processing due to the complicated shapes and large scales of aviation components. Failure to repair them may lead to significant economic loss. Laser deposition repair can be applied to aerospace components because of the advantages of small heat input and high molding accuracy. This work focuses on repairing the aerospace ZM6 magnesium alloy components using laser deposition, addressing the metallurgical defects and service damage to the components. The changes in the microstructure and mechanical properties of the repaired ZM6 samples before and after solution aging (T6: 520 ^oC, 8 h + 220 ^oC, 14 h) treatment were compared. The results show that the microstructure of the repaired zone of the as-deposited sample consists of fine α-Mg grains. The secondary phases distributed mainly at grain boundaries showed a continuous network, and a small number of the dot- and rod-shaped secondary phases were distributed inside Mg grains. The average hardness of the repaired zone is (60 ± 2) HV_0.1, and the tensile strength, yield strength, and elongation were 137.47 MPa, 111.61 MPa, and 5.57%, respectively. The fracture occurred in the base metal, and the tensile fracture mode comprised transgranular and intergranular brittle fractures. After T6 treatment, the microstructure of the repaired zone comprised fine α-Mg grains and abnormally coarse grains, and β′ phase was precipitated inside the grains. The average hardness of the repaired zone increased by 17.5% compared to that of the as-deposited samples, and the abnormally coarse and fine grains led to various hardness fluctuations. The tensile strength and yield strength of the T6-treated samples increased by 49.8% and 75.6%, respectively, but the elongation decreased. The fracture location of the tensile sample was in the repaired zone because of the formation of abnormally coarse grains.

Key words： laser deposition repairing ZM6 alloy solution aging abnormally coarse grain mechanical property

收稿日期: 2023-08-10

ZTFLH:

TG146.2

基金资助:国家重点研发计划项目(2022YFE0122600);中国航空发动机集团产学研合作项目(HFZL2021CXY025-1);辽宁省教育厅基金项目(JYT2020061);沈阳航空航天大学航空制造工艺数字化国防重点学科实验室开放基金项目(SHSYS202001)

通讯作者: 伊俊振，jzyi@sau.edu.cn，主要从事激光沉积制造、激光沉积修复方面的研究；
杨光，yangguang@sau.edu.cn，主要从事金属激光沉积制造方面的研究

Corresponding author: YI Junzhen, associate professor, Tel: 18004024448, E-mail: jzyi@sau.edu.cn;
YANG Guang, professor, Tel: 18040037100, E-mail: yangguang@sau.edu.cn

作者简介: 钦兰云，女，1977年生，教授，博士

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https://www.ams.org.cn/CN/10.11900/0412.1961.2023.00330 或 https://www.ams.org.cn/CN/Y2025/V61/I6/875

图1 ZM6合金基材及梯形凹槽尺寸示意图

图2 激光沉积制造系统示意图

图3 激光沉积修复(LDR)过程及拉伸试样的取样位置和尺寸示意图

图4 ZM6合金基材的OM像、晶粒尺寸分布、SEM像及EDS分析

图5 LDR试样的OM像、低/高倍下熔合线附近的SEM像、修复区晶粒尺寸分布和EDS分析

图6 LDR-T6试样熔合线附近的OM像、修复区晶粒尺寸分布、SEM像及EDS分析

图7 LDR与LDR-T6试样修复区的XRD谱

图8 LDR与LDR-T6试样不同区域的显微硬度分布

图9 基材、LDR与LDR-T6试样的工程应力-应变曲线、断裂位置及室温拉伸性能

图10 LDR与LDR-T6试样拉伸断口的SEM像

图11 LDR与LDR-T6试样拉伸断口截面的OM像

图12 LDR试样修复区、LDR-T6试样修复区和熔合线附近的反极图(IPF)，及LDR试样修复区的局部取向差(KAM)图和LDR试样的SEM像

图13 LDR与LDR-T6试样修复区晶界分布图及取向差统计图

图14 LDR与LDR-T6拉伸试样的断裂机制示意图

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