固体力学与飞行器总体设计

GH4169合金自然萌生小裂纹扩展行为的试验研究

  • 张丽 ,
  • 吴学仁 ,
  • 黄新跃
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  • 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
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

收稿日期: 2014-02-27

  修回日期: 2014-05-05

  网络出版日期: 2015-03-31

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 ,
  • WU Xueren ,
  • HUANG Xinyue
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  • 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 date: 2014-02-27

  Revised date: 2014-05-05

  Online published: 2015-03-31

Supported by

National Level Project

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。

本文引用格式

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 . DOI: 10.7527/S1000-6893.2014.0087

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.

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.

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