GH4169合金自然萌生小裂纹扩展行为的试验研究

doi:10.7527/S1000-6893.2014.0087

固体力学与飞行器总体设计

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

GH4169合金自然萌生小裂纹扩展行为的试验研究

张丽^1,2, 吴学仁³, 黄新跃^1,2

1. 北京航空材料研究院航空材料检测与评价北京市重点实验室, 北京 100095;
2. 北京航空材料研究院先进高温结构材料国防科技重点实验室, 北京 100095;
3. 北京航空材料研究院, 北京 100095

收稿日期:2014-02-27 修回日期:2014-05-05 出版日期:2015-03-15 发布日期:2015-03-31
通讯作者: 吴学仁男, 博士, 研究员, 北京航空材料研究院首席资深高级顾问。主要研究方向: 疲劳与断裂力学、损伤容限技术、材料力学性能。Tel: 010-62496005 E-mail: xrwu621@163.com E-mail:xrwu621@163.com
作者简介:张丽女, 博士,工程师。主要研究方向: 航空发动机材料的小裂纹行为研究与疲劳寿命预测。Tel: 010-62496718 E-mail: zli335@163.com
基金资助:
国家级项目

Experimental investigation on the growth behavior of naturally- initiated small cracks in superalloy GH4169

ZHANG Li^1,2, WU Xueren³, HUANG Xinyue^1,2

1. Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation, Beijing Institute of Aeronautical Materials, Beijing 100095, China;
2. National Key Laboratory of Science and Technology on Advanced High Temperature Structure Materials, Beijing Institute of Aeronautical Materials, Beijing 100095, China;
3. Beijing Institute of Aeronautical Materials, Beijing 100095, China

Received:2014-02-27 Revised:2014-05-05 Online:2015-03-15 Published:2015-03-31
Supported by:
National Level Project

摘要/Abstract

摘要：

为了研究镍基GH4169高温合金自然萌生小裂纹的扩展行为,采用单边缺口拉伸(SENT)试样进行了室温下应力比R=0.1, 0.5的小裂纹扩展试验。在长裂纹近门槛值区域,观察到明显的小裂纹效应,疲劳小裂纹扩展寿命占全寿命的大部分。利用扫描电子显微镜(SEM)和能谱分析仪(EDS)对试样断口表面进行微观分析,结果表明, 疲劳小裂纹起始于合金中的夹杂(Ti(C, N)或Nb(C, N)),并且倾向于以半圆形向试样内部扩展。试样的断裂模式存在由晶体学小平面断裂向疲劳条带断裂的转变,该断裂模式转变处对应小裂纹扩展速率曲线上裂纹加速扩展前的急速降低点。

关键词: 高温合金, 小裂纹效应, 断裂模式, 夹杂, 分散性

Abstract:

The growth behavior of naturally-initiated small cracks in single edge notched tensile (SENT) specimens of nickel-based superalloy GH4169 is studied. Fatigue experiments are conducted under constant amplitude loading with the stress ratios R of 0.1 and 0.5 at room temperature. A significant small crack effect is evident in this alloy, and the major part of total fatigue life is consumed in small crack propagation phase. Fracture mode under cyclic loading is established by scanning electron microscopy (SEM) and energy dispersive spectra (EDS) analysis on specimen fracture surfaces. Small cracks initiate from material inclusions, namely Ti(C, N) or Nb(C, N). A transition of fracture mode from faceted, crystallographic fracture to classical striation type of fracture occurs, corresponding to the minimum growth rate at small crack growth rate curve before crack growth acceleration.

Key words: superalloy, small crack effect, fracture mode, inclusion, scatter

中图分类号:

V216.3

张丽, 吴学仁, 黄新跃. GH4169合金自然萌生小裂纹扩展行为的试验研究[J]. 航空学报, 2015, 36(3): 840-847.

ZHANG Li, WU Xueren, HUANG Xinyue. Experimental investigation on the growth behavior of naturally- initiated small cracks in superalloy GH4169[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(3): 840-847.

参考文献

[1] Aeronautical Systems Division, Wright-Patterson Air Force Base. Military Standard 1783 United States Air Force Engine Structural Integrity Program[S]. OH: Aeronautical Systems Division, Wright-Patterson Air Force Base, 1984.

[2] Ghonem H, Nicholas T, Pineau A. Elevated temperature fatigue crack growth in alloy 718—Part Ι: effects of mechanical variables[J]. Fatigue and Fracture of Engineering Material and Structures, 1993, 16(5): 565-576.

[3] The Compile Commitee of Materials Mechanical Data Handbook for Aircraf Engine Design. Materials mechanical data handbook for aircraft engine design (4) [M]. Beijing: Aviation Industry Press, 2010:151-153 (in Chinese). 《航空发动机设计用材料数手册》编委会. 航空发动机设计用材料数据手册(第四册)[M]. 北京: 航空工业出版社, 2010: 151-153.

[4] Miller K J. The short crack problem[J]. Fatigue and Fracture of Engineering Materials and Structures, 1982, 5(3): 223-232.

[5] Wu X R, Newman J C, Zhao W, et al. Small crack growth and fatigue life predictions for high-strength aluminum alloys: Part Ι—experimental and fracture mechanics analysis[J]. Fatigue and Fracture of Engineering Material and Structures, 1998, 21(11): 1289-1306.

[6] Wu X R, Liu J Z. Total fatigue prediction for aeronautical materials by using small-crack theory[J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(2): 219-226 (in Chinese). 吴学仁, 刘建中. 基于小裂纹理论的航空材料疲劳全寿命预测[J]. 航空学报, 2006, 27(2): 219-226.

[7] Luo J, Bowen P. Small and long fatigue crack growth behavior of a PM Ni-based superalloy, Udimet 720[J]. International Journal of Fatigue, 2004, 26(2): 113-124.

[8] Polak J. Cyclic deformation, crack initiation, and low-cycle fatigue[M]//Ritchie R O, Murakami Y. Comprehensive Structural Integrity: Cyclic Loading and Fracture. Amsterdam: Elsevier, 2003: 1-39.

[9] Connolley T, Reed P A S, Starink M J. Short crack initiation and growth at 600 ℃ in notched specimens of inconel 718[J]. Materials Science and Engineering: A, 2003, 340(1-2): 139-154.

[10] Romanoski G R, Jr. The fatigue behavior of small cracks aircraft turbine disk alloys[D]. Massachusetts, MA: Massachusetts Institute of Technology, 1990.

[11] Bache M R, Evans W J, Hardy M C. The effects of environment and loading waveform on fatigue crack growth in inconel 718[J]. International of Fatigue, 1999, 21(Supplement): S69-S77.

[12] Connolley T, Starink M J, Reed P A S. Effect of oxidation on high temperature fatigue crack initiation and short crack growth in inconel 718[C]//Pollock T M, Kissinger RD, Bowman R R, et al., editors. Proceedings of the 9th International Symposium on Superalloys (Superalloys 2000). Warrendale, PA: The Minerals, Metals & Materials Society (TMS). 2000: 435-444.

[13] Xie X S, Zhang L N, Zhang M C, et al. Micro-mechanical behavior study of non-metallic inclusions in nickel-base P/M superalloy[J]. Acta Metallurgica Sinica, 2002, 38(6): 635-642 (in Chinese). 谢锡善, 张丽娜, 张麦仓, 等. 镍基粉末高温合金中夹杂物的微观力学行为研究[J]. 金属学报, 2002, 38(6): 635-642.

[14] Ma X F, Shi H J. On the fatigue small crack behaviors of directionally solidified superalloy DZ4 by in situ SEM observations[J]. International Journal of Fatigue, 2012, 35(1): 91-98.

[15] Huang X Y, Yu H C, Xu M Q, et al.Experimental investigation on microcrack initiation process in nickel-based superalloy DAGH4169[J]. International Journal of Fatigue, 2012, 42: 153-164.

[16] Caton M J, Jha S K. Small fatigue crack growth and failure mode transitions in Ni-base superalloy at elevated temperature[J]. International Journal of Fatigue, 2010, 32(9): 1461-1472.

[17] Mercer C, Soboyejo A B O, Soboyejo W O. Micromechanisms of fatigue crack growth in a forged inconel 718 nickel-based superalloy[J]. Materials Science and Engineering: A, 1999, 270(2): 308-322.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

GH4169合金自然萌生小裂纹扩展行为的试验研究

Experimental investigation on the growth behavior of naturally- initiated small cracks in superalloy GH4169

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	杨斯媛, 王颖, 王纪来, 杨振文, 王东坡. Al₂O₃陶瓷与GH3536真空钎焊接头界面组织与力学性能[J]. 航空学报, 2022, 43(4): 525806-525806.
[2]	武鑫磊, 刘永红, 亓梁, 赵莅龙, 纪仁杰. 镍基高温合金电火花辅助电弧高效铣削技术[J]. 航空学报, 2022, 43(4): 525615-525615.
[3]	彭振龙, 张翔宇, 张德远. 航空航天难加工材料高速超声波动式切削方法[J]. 航空学报, 2022, 43(4): 525587-525587.
[4]	王常宇, 徐可君, 秦海勤, 马中原, 谢静, 谢镇波. 一种广义Bodner-Partom黏塑性本构模型[J]. 航空学报, 2022, 43(12): 426009-426009.
[5]	尚勇, 冯阳, 刘巧沐, 王君武, 杨惠君, 茹毅, 张恒, 赵文月, 裴延玲, 李树索, 宫声凯. 大型科学装置在航空发动机高温结构材料和涂层上的研究与应用[J]. 航空学报, 2022, 43(10): 527481-527481.
[6]	吕培森, 高强, 李常金, 刘丽荣, 张明俊, 彭志江. 应力对DD5单晶高温合金持久过程中析出相的影响[J]. 航空学报, 2021, 42(6): 424073-424073.
[7]	徐可君, 肖阳, 秦海勤, 贾明明. 基于循环应变特征的疲劳-蠕变寿命预测方法[J]. 航空学报, 2021, 42(5): 524109-524109.
[8]	肖阳, 秦海勤, 徐可君, 贾明明, 张柱柱. 基于改进SWT模型的FGH96合金低周疲劳寿命预测[J]. 航空学报, 2021, 42(5): 524360-524360.
[9]	李茜, 张福禄, 赵子华. 镍基单晶/柱晶高温合金超高周疲劳研究进展[J]. 航空学报, 2021, 42(5): 524340-524340.
[10]	胡胜鹏, 李文强, 付伟, 宋晓国, 龙伟民, 曹健. BNi-2非晶钎料钎焊高铌TiAl合金与GH3536合金接头组织与性能[J]. 航空学报, 2021, 42(3): 423846-423846.
[11]	孔豪豪, 杨树峰, 曲敬龙, 杜金辉, 黄燕成. GH4169铸锭中夹杂物的类型及分布规律[J]. 航空学报, 2020, 41(4): 423306-423306.
[12]	胡晓安, 石多奇, 杨晓光, 于慧臣. TMF本构和寿命模型:从光棒到涡轮叶片[J]. 航空学报, 2019, 40(3): 422494-422494.
[13]	王曼, 杨家勇, 何二锋, 涂冰. 高温合金前缘热防护结构隔热性能分析[J]. 航空学报, 2016, 37(S1): 53-58.
[14]	荆甫雷, 王荣桥, 胡殿印, 蒋康河. 单晶高温疲劳损伤参量的选取与寿命建模[J]. 航空学报, 2016, 37(9): 2749-2756.
[15]	何卫锋, 李应红, 聂祥樊, 李志丰, 周留成. 激光冲击叶片榫头变形控制与疲劳试验[J]. 航空学报, 2014, 35(7): 2041-2048.