DZ406合金燃气涡轮工作叶片服役后的显微组织

doi:10.13251/j.issn.0254-6051.2025.08.014

金属热处理 ›› 2025, Vol. 50 ›› Issue (8): 80-84.DOI: 10.13251/j.issn.0254-6051.2025.08.014

DZ406合金燃气涡轮工作叶片服役后的显微组织

陈升平¹, 黄秋玉², 罗璇², 方向³, 易出山², 贾新云¹, 黄朝晖¹

1.中国航发北京航空材料研究院先进高温结构材料重点实验室, 北京 100095;
2.中国航发南方工业有限公司, 湖南株洲 412000;
3.中国航发湖南动力机械研究所, 湖南株洲 412002

收稿日期:2025-04-01 修回日期:2025-06-12 出版日期:2025-08-25 发布日期:2025-09-10
作者简介:升平(1989—),男,工程师,硕士,主要研究方向为铸造高温合金,E-mail:willofforsaken@hotmail.com。

Microstructure of DZ406 superalloy gas turbine blades after service

Chen Shengping¹, Huang Qiuyu², Luo Xuan², Fang Xiang³, Yi Chushan², Jia Xinyun¹, Huang Zhaohui¹

1. Science and Technology on Advanced High Temperature Structural Materials Laboratory, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China;
2. AECC South Industry Co., Ltd., Zhuzhou Hunan 412000, China;
3. AECC Hunan Powerplant Research Institute, Zhuzhou Hunan 412002, China

Received:2025-04-01 Revised:2025-06-12 Online:2025-08-25 Published:2025-09-10

摘要/Abstract

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0.5 μm。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0.8 μm,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30 μm。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。

关键词: DZ406合金, 工作叶片, 服役, 显微组织, 剩余寿命

Abstract: 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 cubic γ' precipitates, and γ matrix. The size of the γ' phase in the standard condition is approximately 0.5 μm. After 2500 h of equivalent trail run, the core microstructure exhibits minimal degradation, with no significant change in the matrix channels, and γ' phases retain its cubic structure, with a slight increase in the average size to about 0.8 μm, 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 of γ' precipitates. The depth of high degradation in the surface region is approximately 30 μm. Based on the observed core microstructure characteristics, it is inferred that remaining life of the tested blades is 6863 h.

Key words: DZ406 superalloy, turbine blades, service, microstructure, remaining life

中图分类号:

TG146.1

陈升平, 黄秋玉, 罗璇, 方向, 易出山, 贾新云, 黄朝晖. DZ406合金燃气涡轮工作叶片服役后的显微组织[J]. 金属热处理, 2025, 50(8): 80-84.

Chen Shengping, Huang Qiuyu, Luo Xuan, Fang Xiang, Yi Chushan, Jia Xinyun, Huang Zhaohui. Microstructure of DZ406 superalloy gas turbine blades after service[J]. Heat Treatment of Metals, 2025, 50(8): 80-84.

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DZ406合金燃气涡轮工作叶片服役后的显微组织

Microstructure of DZ406 superalloy gas turbine blades after service

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