On the strain energy release rate and fatigue crack growth rate in metallic alloys

被引:9
作者
Amsterdam, Emiel [1 ]
Wiegman, Jan Willem E. [1 ]
Nawijn, Marco [2 ]
De Hosson, Jeff Th. M. [3 ]
机构
[1] Royal Netherlands Aerosp Ctr NLR, Marknesse, Netherlands
[2] Colosso, Uffelte, Netherlands
[3] Univ Groningen, Zernike Inst Adv Mat, Dept Appl Phys, Groningen, Netherlands
关键词
Linear elastic fracture mechanics; Fatigue; Design; Engineering; Metals; INCOMPLETE SELF-SIMILARITY; ALUMINUM-ALLOYS; PROPAGATION; STRESS; THRESHOLD; FRACTURE; MICROMECHANISMS; PLASTICITY; PARAMETERS; TI-6AL-4V;
D O I
10.1016/j.engfracmech.2023.109292
中图分类号
O3 [力学];
学科分类号
08 ; 0801 ;
摘要
The field of fracture mechanics started with Griffith's energy concept for brittle fracture in 1920. In 1963, Paris et al. used a fracture mechanics' parameter to introduce an equation for the fatigue crack growth rate in ductile materials and this equation is now commonly known as the 'Paris law'. However, the Paris law and the semi-empirical models that followed ever since do not fully account for the main intrinsic and extrinsic properties involved with fatigue crack growth in metallic alloys. In contrast, here a dimensionally correct fatigue crack growth rate equation is introduced that is based on the original crack driving force as introduced by Griffith and the presence of plasticity in a metal to withstand crack propagation. In particular it is shown that the fatigue crack growth rate shows a power law relationship with the cyclic strain energy release rate over the maximum stress intensity factor. The new description corrects for the ratio between the minimum and maximum stress in a cycle during constant amplitude loading and for crack growth retardation under variable amplitude loading. The method has been successfully applied to variable amplitude crack growth with spectra that are representative of different fatigue dominated aircraft locations. As such, it allows for accurate predictions of variable amplitude fatigue crack growth life in aerospace structures.
引用
收藏
页数:17
相关论文
共 91 条
[21]  
Dowling N., 1973, MECH CRACK GROWTH AS, V590, P82, DOI [10.1520/STP33940S, DOI 10.1520/STP33940S]
[22]   YIELDING OF STEEL SHEETS CONTAINING SLITS [J].
DUGDALE, DS .
JOURNAL OF THE MECHANICS AND PHYSICS OF SOLIDS, 1960, 8 (02) :100-104
[23]  
E08 Committee, Test method for measurement of fatigue crack growth rates, DOI [10.1520/E0647-15E01, DOI 10.1520/E0647-15E01]
[24]  
El Haddad M, 1983, FRACTURE RESISTANCE, DOI [10.1520/STP36793S, DOI 10.1520/STP36793S]
[25]  
Elber W, 1971, Damage Tolerance in Aircraft Structures. ASTM STP 486, P230
[26]   J-INTEGRAL APPLICATIONS FOR SHORT FATIGUE CRACKS AT NOTCHES [J].
ELHADDAD, MH ;
DOWLING, NE ;
TOPPER, TH ;
SMITH, KN .
INTERNATIONAL JOURNAL OF FRACTURE, 1980, 16 (01) :15-30
[27]   FATIGUE CRACK-PROPAGATION OF SHORT CRACKS [J].
ELHADDAD, MH ;
SMITH, KN ;
TOPPER, TH .
JOURNAL OF ENGINEERING MATERIALS AND TECHNOLOGY-TRANSACTIONS OF THE ASME, 1979, 101 (01) :42-46
[28]   OVERVIEW NO 112 - THE CYCLIC PROPERTIES OF ENGINEERING MATERIALS [J].
FLECK, NA ;
KANG, KJ ;
ASHBY, MF .
ACTA METALLURGICA ET MATERIALIA, 1994, 42 (02) :365-381
[29]   FATIGUE DAMAGE AND CRACK GROWTH IN ALUMINIUM ALLOYS [J].
FORSYTH, PJE .
ACTA METALLURGICA, 1963, 11 (07) :703-&
[30]  
Forsyth PJE, 1961, CRACK PROP P CRANF S, P76