固溶处理对长期服役燃机透平叶片组织和力学性能的影响

doi:10.13251/j.issn.0254-6051.2023.08.016

金属热处理 ›› 2023, Vol. 48 ›› Issue (8): 99-105.DOI: 10.13251/j.issn.0254-6051.2023.08.016

固溶处理对长期服役燃机透平叶片组织和力学性能的影响

施峰¹, 姚伟民¹, 沈俭¹, 殷春宏¹, 曹琦¹, 洪亚光¹, 许辉², 丁阳²

1.江苏华电吴江热电有限公司, 江苏苏州 215221;
2.华电电力科学研究院有限公司, 浙江杭州 310030

收稿日期:2023-02-02 修回日期:2023-06-19 出版日期:2023-08-25 发布日期:2023-10-10
作者简介:施峰(1982—),男,高级工程师,硕士,主要研究方向为重型燃机热通道部件服役寿命管理,E-mail: sf@chd.com.cn
基金资助:
华电集团中央研究院项目(ZYYJY21-01)

Effect of solution treatment on microstructure and mechanical properties of turbine blade after long-term service

Shi Feng¹, Yao Weimin¹, Shen Jian¹, Yin Chunhong¹, Cao Qi¹, Hong Yaguang¹, Xu Hui², Ding Yang²

1. Jiangsu Huadian Wujiang Thermal Power Co., Ltd., Suzhou Jiangsu 215221, China;
2. Huadian Electric Power Research Institute Co., Ltd., Hangzhou Zhejiang 310030, China

Received:2023-02-02 Revised:2023-06-19 Online:2023-08-25 Published:2023-10-10

摘要/Abstract

摘要： 对服役约27 000 h的重型燃机透平一级动叶进行了1180 ℃×2 h/ArC(ArC:吹氩冷却)固溶处理,对比分析了此GTD111合金叶片不同区域的微观组织和力学性能变化。结果表明,叶片前缘区和中部区保持着树枝晶形态,晶界、碳化物及γ′相无明显老化。而尾缘区树枝晶消失,晶界存在粗化,碳化物明显退化,γ′相发生了粗化和筏化。叶片尾缘区硬度整体上高于前缘,在25~871 ℃下叶顶到榫头试样的抗拉强度总体上呈先增加后降低的趋势,而在982 ℃下不同位置试样的抗拉强度趋近相同。对于服役后的GTD111合金透平叶片,1180 ℃下固溶处理未能完全消除老化组织,与固溶温度较低或保温时间不足有关。

关键词: GTD111合金, 透平叶片, 固溶处理, γ′相, 碳化物, 力学性能

Abstract: A first stage rotor blade made of GTD111 alloy in heavy gas turbine after service for 27 000 h was solution treated at 1180 ℃ for 2 h and then argon blowing cooled, the microstructure and mechanical properties of different regions of the blade were compared and analyzed. The results show that dendrite morphology is maintained in the leading edge and middle region of the blade, meanwhile grain boundaries, carbides and γ′ phase are not aged obviously. In the trailing edge of the blade, however, the dendrites disappear, the grain boundaries are coarsened, the carbides degrade obviously, and the γ′ phase is coarsened and rafted. The hardness of trailing edge in the blade as a whole is higher than that of leading edge, the tensile strength of the specimens varying from blade tip to tenon increases first and then decreases on the whole at 25-871 ℃, while that of the specimens at different positions tends to be the same at 982 ℃. For the GTD111 alloy turbine blades after long-term service, the solution treatment at 1180 ℃ cannot completely eliminate the aged microstructure, which is related to the insufficient solution temperature or holding time.

Key words: GTD111 alloy, turbine blade, solution treatment, γ′ phase, carbide, mechanical properties

中图分类号:

TG113.12

施峰, 姚伟民, 沈俭, 殷春宏, 曹琦, 洪亚光, 许辉, 丁阳. 固溶处理对长期服役燃机透平叶片组织和力学性能的影响[J]. 金属热处理, 2023, 48(8): 99-105.

Shi Feng, Yao Weimin, Shen Jian, Yin Chunhong, Cao Qi, Hong Yaguang, Xu Hui, Ding Yang. Effect of solution treatment on microstructure and mechanical properties of turbine blade after long-term service[J]. Heat Treatment of Metals, 2023, 48(8): 99-105.

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固溶处理对长期服役燃机透平叶片组织和力学性能的影响

Effect of solution treatment on microstructure and mechanical properties of turbine blade after long-term service

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