Fatigue strength assessment of initial semi-elliptical cracks located at a hole

被引:12
作者
Boljanovic, Slobodanka [1 ]
Maksimovic, Stevan [2 ]
Djuric, Mirjana [2 ]
机构
[1] Serbian Acad Arts & Sci, Math Inst, Kneza Mihaila 36, Belgrade, Serbia
[2] VTI Aeronaut Dept, Ratka Resanovica 1, Belgrade, Serbia
关键词
Crack path; Fatigue; FEM; Semi-elliptical crack; Strength calculation; STRESS INTENSITY FACTORS; SURFACE CRACKS; ROUND BARS; NOTCHED SHELLS; DRIVING-FORCE; GROWTH; PARAMETER;
D O I
10.1016/j.ijfatigue.2016.04.011
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
In the present paper, the residual strength of a pin-loaded lug and a finite plate, both with a semi elliptical crack emanating from a hole, is examined. A new analytical methodology, based on Fracture Mechanics concepts, is proposed to analyse the crack propagation process in terms of life estimation and crack front evolution. Firstly, the stress field and the stress intensity factor are computed by applying both analytical and numerical approaches. Then, the two-parameter driving force model proposed by Kujawski is implemented for the fatigue life estimation and the crack front evolution. The validity of model here employed is assessed through the comparison between crack growth calculations and experimental data available in the literature, such comparison shows a quite good correlation for the crack and geometrical configurations here examined. (C) 2016 Elsevier Ltd. All rights reserved.
引用
收藏
页码:548 / 556
页数:9
相关论文
共 38 条
[21]  
Forman R. G., 1972, Engineering Fracture Mechanics, V4, P333, DOI 10.1016/0013-7944(72)90048-3
[22]  
Grandt AF, 1982, AFWALTR833043
[23]   DETERMINATION OF STRESS INTENSITY FACTORS FOR CORNER CRACKED HOLE USING ISOPARAMETRIC SINGULARITY ELEMENT [J].
HECHMER, JL ;
BLOOM, JM .
INTERNATIONAL JOURNAL OF FRACTURE, 1977, 13 (05) :732-735
[24]  
Heliot J, 1980, ASME CTPVP C SAN FRA
[25]  
Hellen T. K., 1975, International Journal for Numerical Methods in Engineering, V9, P187, DOI 10.1002/nme.1620090114
[26]  
Impellizzeri L.F., 1976, ASTM STP 595, P320
[27]   Fatigue crack growth behavior of Al7050-T7451 attachment lugs under flight spectrum variation [J].
Kim, JH ;
Lee, SB ;
Hong, SG .
THEORETICAL AND APPLIED FRACTURE MECHANICS, 2003, 40 (02) :135-144
[29]   Total Fatigue Life Estimation of Notched Structural Components Using Low-Cycle Fatigue Properties [J].
Maksimovic, S. ;
Posavljak, S. ;
Maksimovic, K. ;
Nikolic, V. ;
Djurkovic, V. .
STRAIN, 2011, 47 :341-349
[30]   Analysis of fatigue crack growth in an attachment lug based on the weight function technique and the UniGrow fatigue crack growth model [J].
Mikheevskiy, S. ;
Glinka, G. ;
Algera, D. .
INTERNATIONAL JOURNAL OF FATIGUE, 2012, 42 :88-94