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2222材料工程  2020, Vol. 48 Issue (6): 156-162    DOI: 10.11868/j.issn.1001-4381.2018.001058
  研究论文 本期目录 | 过刊浏览 | 高级检索 |
冷挤压GH4169合金孔结构疲劳性能与断口分析
王欣1,2,*(), 陈星3, 胡仁高4, 胡博4, 许春玲1,2, 汤智慧1,2, 古远兴4
1 中国航发北京航空材料研究院 表面工程研究所, 北京 100095
2 中国航发北京航空材料研究院 航空材料先进腐蚀与防护航空科技重点实验室, 北京 100095
3 中国航发北京 航空材料研究院检测研究中心, 北京 100095
4 中国航发四川燃气涡轮研究院, 成都 610500
Fatigue property and fracture analysis on cold-expanded hole structure of GH4169 alloy
Xin WANG1,2,*(), Xing CHEN3, Ren-gao HU4, Bo HU4, Chun-ling XU1,2, Zhi-hui TANG1,2, Yuan-xing GU4
1 Surface Engineering Institution, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China
2 Aviation Key Laboratory of Advanced Corrosion and Protection on Aviation Materials, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China
3 Testing Research Center, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China
4 AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China
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摘要 

对GH4169合金中心孔板材进行冷挤压强化，研究其挤压前后825 MPa/600℃/R=0.1疲劳寿命，分析挤压前后表面粗糙度变化和疲劳过程中的残余应力场演化，并细致观察两件挤压试样不同寿命（分别为25105周次和10719周次）断口以分析表面完整性对疲劳过程的作用。结果表明：相比原始试样，冷挤压强化后试样中值疲劳寿命估计量提高了1倍，挤压后较低的表面粗糙度和疲劳过程中稳定的残余应力场是疲劳寿命提高的主要原因。同时，挤压后疲劳寿命标准差增大。由断口定量分析可知，两件试样距疲劳源区0.1 mm之后的扩展寿命相当，而萌生寿命（分别为18786周次和5915周次）却相差巨大。造成孔挤压后寿命分散性大的原因是0.1 mm以内的裂纹萌生寿命差别。为提高孔结构疲劳性能稳定性，挤压时应注意近表层表面完整性的控制。
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王欣
陈星
胡仁高
胡博
许春玲
汤智慧
古远兴
关键词 ： 冷挤压,  孔结构,  疲劳,  断口定量分析    
Abstract：

Cold expansion (CE) was applied on the centre-hole plate of GH4169 alloy. The fatigue lives, as received and after CE, were investigated at 825 MPa/600 ℃/R=0.1. Surface roughness before and after CE, residual stress profiles during fatigue cycles were studied. And the influence of surface integrity on fatigue process was analyzed by the careful fracture observation with two CE samples of different lives (25105 cycles and 10719 cycles). The results show that the median fatigue life estimation of specimens after CE doubles compared with as-received. The lower surface average roughness after CE and the stable residual stress profile during fatigue process are the main reasons for fatigue life promotion. However, the standard deviation of fatigue lives increases after CE. The fractographic quantitative analysis shows the propagation lives of two specimens beyond 0.1 mm from fatigue source are considered, but initiation lives (18786 cycles and 5915 cycles, respectively) are of great difference. As a contrast, the reason of the big dispersion about CE fatigue lives is the different initiation life within 0.1 mm from the source. Therefore, the attention should be paid to the surface integrity control of near surface during cold expansion to improve the stability of hole structure fatigue property.
Key words： cold expansion    hole structure    fatigue    fractographic quantitative analysis
收稿日期: 2018-08-31      出版日期: 2020-06-15
中图分类号:  TG668  
通讯作者: 王欣     E-mail: rasheed990918@163.com
作者简介: 王欣(1983-), 男, 研究员, 研究方向为抗疲劳的表面强化技术, 联系地址:北京市81信箱5分箱(100095), E-mail:rasheed990918@163.com
引用本文:   
王欣, 陈星, 胡仁高, 胡博, 许春玲, 汤智慧, 古远兴. 冷挤压GH4169合金孔结构疲劳性能与断口分析[J]. 材料工程, 2020, 48(6): 156-162.
Xin WANG, Xing CHEN, Ren-gao HU, Bo HU, Chun-ling XU, Zhi-hui TANG, Yuan-xing GU. Fatigue property and fracture analysis on cold-expanded hole structure of GH4169 alloy. Journal of Materials Engineering, 2020, 48(6): 156-162.
链接本文:  
http://jme.biam.ac.cn/CN/10.11868/j.issn.1001-4381.2018.001058      或      http://jme.biam.ac.cn/CN/Y2020/V48/I6/156
Fig.1  中心孔板材疲劳试样
(a)正视图；(b)侧视图
C Cr Ni Co Mo Al Ti Fe
0.04 19.0 53.0 ≤1.0 3.0 0.5 1.0 Bal
Table 1  GH4169合金化学成分(质量分数/%)
Temperature/
℃		 σb/
MPa		 σ0.2/
MPa		 δ4/
%		 ψ/
%
20 1345-1430 1140-1200 12-22 20-37
650 1100-1165 930-995 12-30 25-38
Table 2  GH4169合金力学性能
State Sample No σmax/ MPa Fatigue life/ cycle Logarithmic fatigue life/cycle Median fatigue life/cycle Median fatigue life estimation/cycle Standard deviation
As-received 169-K-23 825 7574 3.88 3.9 7362 0.03
169-K-25 7038 3.85
169-K-26 8020 3.90
169-K-38 7412 3.87
169-K-55 6447 3.81
169-K-59 7752 3.89
169-K-62 7121 3.85
Cold expansion 169-K-17 825 15098 4.18 4.2 14927 0.13
169-K-31 25105 4.40
169-K-34 13844 4.14
169-K-52 9245 3.97
169-K-61 12554 4.10
169-K-67 10719 4.03
169-K-68 15726 4.20
Table 3  825 MPa/600 ℃/R=0.1条件下挤压和原始试样的疲劳寿命
NoRa/μm
As-received Cold expansion
1 0.46 0.21
2 0.42 0.18
3 0.47 0.17
Table 4  原始试样和冷挤压试样表面粗糙度
Fig.2  挤压和不同疲劳周次下的孔边残余压应力场
Fig.3  中心孔板材疲劳试样断裂外观
Fig.4  中心孔板材疲劳试样断口宏观形貌
(a)169-K-67;(b)169-K-31
Fig.5  169-K-67试样左侧断面微观形貌
(a)源区形貌；(b)放大源区形貌；(c), (d), (e)前/中/后期疲劳条带；(f)瞬断区
Fig.6  169-K-31试样左侧断面微观形貌
(a)源区形貌；(b)放大源区形貌；(c), (d), (e)前/中/后期疲劳条带；(f)瞬断区
No Crack length/ mm Average spacing of fatigue bands/μm N′i/ cycle Ni/ cycle
1 0.100 0.65 1875 1875
2 1.319 0.65 1202 1202
3 2.082 0.62 543 543
4 2.457 0.76 932 932
5 3.235 0.91 504 252
6 3.747 1.12 ∑Nn =5056 ∑Nn =4804
Table 5  169-K-67试样左侧断面疲劳条带测量结果
Fig.7  169-K-67试样左侧断面裂纹扩展速率与裂纹长度的关系
No Crack length/mm Average spacing of fatigue bands/μm N′i/cycle
1 0.100 0.48 743
2 0.468 0.51 1016
3 1.037 0.61 1026
4 1.668 0.62 1035
5 2.460 0.91 928
6 3.388 1.09 551
7 3.931 0.88 717
8 4.634 1.08 213
9 4.868 1.12 ∑Nn=6229
Table 6  169-K-31试样左侧断面疲劳条带测量结果
Fig.8  169-K-31试样左侧断面裂纹扩展速率与裂纹长度的关系
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