Fatigue crack growth from foreign object damage under combined low and high cycle loading. Part I: Experimental studies

Ding, Jian; Hall, Richard F.; Byrne, J.; Tong, Jie

doi:10.1016/j.ijfatigue.2006.10.020

Cited by 48 publications

(40 citation statements)

References 19 publications

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“…Off-angle impacts were found to be more detrimental than head-on, and up to 50% loss in fatigue strength [2] were reported due to FOD. Impacts using hard cubes were carried out on plates [2], generic aerofoil specimens [15] and a more realistic aerofoil shape resembling real compressor blades [17][18][19]. The cubical projectile was considered more representative of "worst case" damage seen in service.…”

Section: Introductionmentioning

confidence: 99%

Characterisation of foreign object damage (FOD) and early fatigue crack growth in laser shock peened Ti–6Al–4V aerofoil specimens

Spanrad

Tong

2011

Materials Science and Engineering: A

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102

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Section: Introductionmentioning

confidence: 99%

Characterisation of foreign object damage (FOD) and early fatigue crack growth in laser shock peened Ti–6Al–4V aerofoil specimens

Spanrad

Tong

2011

Materials Science and Engineering: A

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102

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Section: Discussionmentioning

confidence: 80%

“…11. This may be an important reason why crack growth rates from FOD are higher than those obtained from long crack growth data under the corresponding applied stress ratios, as observed from experimental work [9,10].For future study, one important issue is to experimentally measure the residual stress relaxation after FOD to validate the present model. Boyce et al [3] has reported both experimental and numerical results on the relaxation of residual stresses induced by a static indentation.…”

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confidence: 86%

“…Analysis was then carried out to determine when and to what extent the residual stresses and stress concentrations caused by FOD reduce the critical crack size associated with the threshold for fatigue crack growth. More recently, Ding et al [8,9] studied FOD-induced small crack growth in rolled Ti-6Al-4V plates subjected to combined LCF and HCF loadings, and suggested a two-parameter crack growth model together with a corrected stress intensity solution to correlate the experimental data.Impact-induced stress is expected to relax under the subsequent fatigue loading. Torres and Voorwald [14] reported significant relaxation of the compressive residual stress field for shotpeened AISI 4340 steel under fatigue loading.…”

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confidence: 99%

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Computational simulation of the relaxation of local stresses due to foreign object damage under cyclic loading

Davis

Ding²,

Sun

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part L:

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In this study, the phenomenon of residual stress relaxation from foreign object damage (FOD) is numerically simulated using a hybrid explicit-implicit finite element method. The effects of both low-cycle and high-cycle fatigue loadings on stress relaxation were studied. FOD is first simulated by firing a 3mm cube impacting onto a plate of Ti-6Al-4V at 200m/s. The FOD impact produces two distinct stress concentrations: one is compressive directly beneath the impact site, the other is tensile around the outer edge of the impact. The plate was then assumed to be subjected to a cyclic fatigue loading. The stress relaxation was investigated under a range of stress ratios and maximum applied stresses. Two different material models were considered for the simulations, namely an elastic-perfectly plastic model and a non-linear kinematic hardening model. Keywords: finite element; impact; foreign object damage (FOD); residual stress; stress relaxation. normal stress component in x-direction, i.e. in the direction of applied load σ ys yield stress 2 σ ys (  ) strain rate sensitive yield stress σ y stress component in y-direction σ z stress component in z-direction 1. Introduction Dynamic impact and subsequent fatigue under cyclic loading conditions demonstrate a very demanding failure mode, which occurs in a number of mechanical applications. Impact leads to either beneficial or detrimental effects on the fatigue performance. For example, the cold working process of shot-peening is used to create a beneficial compressive residual stress field over the surface of the component. This compressive residual stress inhibits surface crack growth and thereby leads to an increase in fatigue life. Spherical shots made from hardened materials are typically used for the shot peening, fired at velocities in the range of 40-100 m/s. [1]. The detrimental effects of impacts are observed in such a phenomenon as Foreign Object Damage (FOD), which occurs primarily during the takeoff and landing periods of aircraft flights, where millimetre sized debris in the form of hard particles such as sand and grit are ingested into aero engines [2][3][4]. These particles impact the fan and early stage compressor blades, typically made from the titanium alloy Ti-6Al-4V, at speeds in the range of 200 to 350 m/s. Impacts on the leading edge of the blades cause the most severe damage, which is in the form of notch like craters and gives rise to stress concentrations, residual stresses, microcracks around the impact site and distortion of the materials microstructure [3]. The combination of the fatigue loading and the residual stress field induced by the impact can make the impact region a preferential site for both fatigue crack initiation and growth. This reduces the fatigue resistance of the blades and in some cases causes them to fail prematurely. It has been reported that the cost of FOD to both the civil and military aircraft industries is greater than $4 billion annually [4]. NotationTo gain insight into the interaction between FOD and fati...

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“…Powell et al [22] explains that at lower values of DK, only the LCF contributes to the crack growth. As soon as DK onset , the threshold for pure HCF, is surpassed, the crack growth rate is dictated by both LCF and HCF [23][24][25], generally by a simple linear summation relationship. Because of a high number of HCF cycles, when DK onset is reached, the crack growth rate increases drastically, leading to a rapid failure.…”

Section: Introductionmentioning

confidence: 99%

Crack propagation methodology under complex loadings

Dompierre

Mesbah

Wyart

2015

Engineering Fracture Mechanics

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Fatigue crack growth from foreign object damage under combined low and high cycle loading. Part I: Experimental studies

Cited by 48 publications

References 19 publications

Characterisation of foreign object damage (FOD) and early fatigue crack growth in laser shock peened Ti–6Al–4V aerofoil specimens

Characterisation of foreign object damage (FOD) and early fatigue crack growth in laser shock peened Ti–6Al–4V aerofoil specimens

Computational simulation of the relaxation of local stresses due to foreign object damage under cyclic loading

Crack propagation methodology under complex loadings

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