Fatigue crack growth in laser-shock-peened Ti–6Al–4V aerofoil specimens due to foreign object damage

Lin, Bing; Lupton, Colin; Spanrad, Sven; Schofield, John; Tong, Jie

doi:10.1016/j.ijfatigue.2013.10.001

Cited by 67 publications

(27 citation statements)

References 65 publications

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“…As plasticity-induced crack closure leads to compressive residual stresses in the plastic wake, the concept of residual stresses may be utilised to treat the cases of crack closure [31]. The effects of crack closure on J--integral may be considered by introducing the initial strains due to residual stresses into the Rice's J--integral equation [1] and the path--independent J--integral is then obtained [32,33]. The modified path--independent J--integral expression introducing initial strains !"…”

Section: Crack Driving Forcementioning

confidence: 99%

Characterisation of fatigue crack tip field in the presence of significant plasticity

Lin¹,

Alshammrei

Wigger

et al. 2019

Theoretical and Applied Fracture Mechanics

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Characterisation of a fatigue crack tip in the presence of significant plasticity has been challenging due to the lack of suitable tools and lack of knowledge of material constitutive information under cyclic loading. In this paper, Digital Image Correlation (DIC) and integrated finite element (FE) analyses have been used to characterise the crack-tip field beyond the small-scale yielding (SSY) regime in a stainless steel 316L of a compact-tension (CT) specimen under mode I loading conditions. The non-linear characteristics of the near-tip deformation field were verified by the poor fit to the William's regression and the overestimation of the stress intensity factor K. The extent of the crack tip plasticity was estimated using a detailed constitutive material model and compared with the estimated by Irwin. The displacement fields local to a stationary fatigue crack were mapped using DIC, and inputted into the FE model as boundary conditions so that an integrated FE analysis was carried out. Fatigue pre-cracking was simulated in the FE analysis prior to the full-field analysis of the fatigue crack tip, including stress/strain distributions ahead of the crack tip and the crack opening displacement (COD) under selected loading conditions. Although a distinct "knee" was captured from the compliance curves in both the DIC measurements and the FE analyses, consistent with the existing knowledge on the phenomenon of crack closure, it does not appear to correlate with the crack driving force measured by the J-integral.

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Section: Crack Driving Forcementioning

confidence: 99%

Characterisation of fatigue crack tip field in the presence of significant plasticity

Lin¹,

Alshammrei

Wigger

et al. 2019

Theoretical and Applied Fracture Mechanics

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“…Multiple failure modes were observed, including materials pile-up, folding and fretting debris for head-on impact; and lost of materials by shearing, formation of shear-bands and microcracks for 45°impact. These gave rise to multiple crack initiation sites and prompted accelerated crack growth under simulated service loads, such as low cycle, high cycle and combined low and high cycle fatigue (Lin et al, 2014). Prediction of such crack growth requires considerable confidence in the description of residual stress field due to both surface treatment (LSP) and FOD.…”

Section: Physical Damages Due To Fodmentioning

confidence: 99%

Residual stresses due to foreign object damage in laser-shock peened aerofoils: Simulation and measurement

Lin

Zabeen

Tong

et al. 2015

Mechanics of Materials

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a b s t r a c tForeign object damage (FOD) to the leading edge of aerofoils has been identified as one of the main life-limiting factors for aeroengine compressor blades. Laser-shock peening (LSP) has been proposed as a means of increasing the material's resistance to such impact damage. In this work, a three-dimensional finite element (FE) model has been developed to simulate the residual stresses due to head on (0°) and 45°impacts by a cuboidal projectile on aerofoil specimens treated with LSP. The Johnson-Cook (JC) material model was employed to describe the strain rate-dependent material behaviour; whilst the JohnsonCook dynamic failure model was considered in 45°FOD simulation, where significant loss of material occurred. The strain rate sensitivity of the model at selected high strain rates was assessed against the data from the literature. The numerical results from the simulation of head-on impact were compared with the measurements by depth-resolved synchrotron X-ray diffraction on the mid-plane. The models were then used to predict the 3D residual stress distributions due to 0°and 45°FOD impacts, and the results were compared with the strain maps obtained from high-energy synchrotron X-ray diffraction. Good to excellent correlations between the simulations and the measurements have been found.

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“…Therefore, a significant improvement in the fatigue behaviour and lifetime prolongation can be achieved for components and structures with surface cracks 27,28,31,34 as well as through‐thickness cracks 29,30,32,33 . Lin et al have investigated the effect of LSP on the fatigue strength of engine components subjected to foreign object damage (FOD), where LSP is applied before FOD 35 . A delayed crack onset and reduced early fatigue crack growth rates for Ti–6Al–4V specimens with LSP treatment compared with specimens without LSP treatment are reported.…”

Section: Introductionmentioning

confidence: 99%

On the application of laser shock peening for retardation of surface fatigue cracks in laser beam‐welded AA6056

Kashaev

Ushmaev

Ventzke

et al. 2020

Fatigue Fract Eng Mat Struct

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The present study aims to investigate the extent to which the fatigue behaviour of laser beam-welded AA6056-T6 butt joints with an already existing crack can be improved through the application of laser shock peening. Ultrasonic testing was utilized for in situ (nondestructive) measurement of fatigue crack growth during the fatigue test. This procedure allowed the preparation of welded specimens with surface fatigue cracks with a depth of approximately 1.2 mm. The precracked specimens showed a 20% reduction in the fatigue limit compared with specimens without cracks in the as-welded condition. Through the application of laser shock peening on the surfaces of the precracked specimens, it was possible to recover the fatigue life to the level of the specimens tested in the as-welded condition. The results of this study show that laser shock peening is a very promising technique to recover the fatigue life of welded joints with surface cracks, which can be detected by nondestructive testing. K E Y W O R D Saluminium alloys, fatigue crack, laser beam welding, laser shock peening, residual stress, ultrasonic crack tip diffraction

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Fatigue crack growth in laser-shock-peened Ti–6Al–4V aerofoil specimens due to foreign object damage

Cited by 67 publications

References 65 publications

Characterisation of fatigue crack tip field in the presence of significant plasticity

Characterisation of fatigue crack tip field in the presence of significant plasticity

Residual stresses due to foreign object damage in laser-shock peened aerofoils: Simulation and measurement

On the application of laser shock peening for retardation of surface fatigue cracks in laser beam‐welded AA6056

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