Comparison of fatigue crack retardation methods

Domazet, Željko

doi:10.1016/1350-6307(96)00006-4

Cited by 76 publications

(21 citation statements)

References 2 publications

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“…The aim of these methods is to extend the fatigue lives of cracked structural components that cannot be replaced as soon as the cracks are observed; this situation commonly happens when the replacement of new parts are time consuming and costly. Various methods for crack growth retardation have been proposed by researchers [1], for example, crack filling [2][3][4], application of the composite or metal patches on the cracked area, welding repair [5][6][7], and applying the residual compressive stresses.…”

Section: Introductionmentioning

confidence: 99%

Mixed mode fatigue crack initiation and growth in a CT specimen repaired by stop hole technique

Ayatollahi

Razavi

Yahya

2015

Engineering Fracture Mechanics

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Section: Introductionmentioning

confidence: 99%

Mixed mode fatigue crack initiation and growth in a CT specimen repaired by stop hole technique

Ayatollahi

Razavi

Yahya

2015

Engineering Fracture Mechanics

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“…Use of bonded repairs and crack retardation methods may be the easiest and cheapest solution to overcome these problems. Use of adhesively bonded repair with either metal or composites patches on 2024-T3 has received a lot of attention [8,9]. Disadvantages include material compatibility problems.…”

Section: Introductionmentioning

confidence: 99%

The response of aluminium/GLARE hybrid materials to impact and to in-plane fatigue

Bagnoli¹,

Bernabei²,

Figueroa-Gordon

et al. 2009

Materials Science and Engineering: A

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a b s t r a c tFibre metal laminates (FMLs), such as glass reinforced aluminium (GLARE), are a family of materials with excellent damage tolerance and impact resistance properties. This paper presents an evaluation of the low velocity impact behaviour and the post-impact fatigue behaviour of GLARE laminate adhesively bonded to a high strength aluminium alloy substrate as a fatigue crack retarder. The damage initiation, damage progression and failure modes under impact and fatigue loading were examined and characterised using an ultrasonic phased array C-scan together with metallography and scanning electron microscopy (SEM). After impact on the substrate, internal damage to the GLARE bonded on the opposite side of the substrate occurred in the form of fibre and matrix cracking. No delamination was detected at the GLARE/substrate bond. Before impact the bonded GLARE strap caused reductions in substrate fatigue crack growth rate of up to a factor of 5. After impact the retardation was a factor of 2. The results are discussed in terms of changes to the GLARE stiffness promoted by the impact damage.

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“…Several different approaches (experimental, analytical and numerical) have been proposed in order to characterize the fatigue behaviour of the structure. Generally, when a crack is detected in a engineering component, the problem for an engineer is to propose an appropriate repair method in order to increase the lifetime of this component 1 , 2 . Up to now, many crack repair techniques have been proposed for inhibiting crack propagation in structural components.…”

Section: Introductionmentioning

confidence: 99%

“…However, a high overload amplitude may lead to sudden fracture. On the other hand, other repair techniques have been developed such as: crack infiltration, 1 repair welding and metal reinforcement, 2 drilling a hole at or near a crack tip 4 and hole expansion 5 …”

Section: Introductionmentioning

confidence: 99%

Fatigue life estimation after crack repair in 6005 A‐T6 aluminium alloy using the cold expansion hole technique

Ghfiri

Amrouche

Imad

et al. 2000

Fatigue Fract Eng Mat Struct

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In this paper, the hole drilling (HD) and the cold expansion (CE) processes, which were used as a technique for crack repair, were investigated in order to estimate the beneficial effects on fatigue crack initiation (FCI). The FCI life is defined as the number of cycles to initiate a new crack of 0.2 mm on the surface of the specimen. Three hole radii and three degrees of cold expansion (DCE%) values were tested after a crack propagation period. Crack retardation after the CE process was observed. This phenomenon is due to two mechanisms: retardation owing to both geometric and mechanical effects, which is produced by the stress concentration at the drilled hole, and the large strain‐induced compressive residual stresses around the hole. In this report, the influence of the loading conditions was studied. For high values of the stress intensity factor range ΔKρ around the hole (based on the pseudo crack length a + ρ), the number of cycles corresponding to crack initiation Ni is low. At the edge of the hole, the maximum stress range can be approximated by the following formula: Δσmax = 2ΔKρ /√πρ , where ρ is the hole radius and ΔKρ is the related stress intensity factor range.The FCI life extension, defined by the number of cycles corresponding to crack re‐initiation Ni , is related to the relative maximum stress range ratio Rσ = [(Δσmax )/(Δσmax )th ] where (Δσmax )th is the value of the threshold maximum stress range obtained when Ni = 2 × 106 cycles. The relationship between Ni and Rσ may be written as a power function.

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Comparison of fatigue crack retardation methods

Cited by 76 publications

References 2 publications

Mixed mode fatigue crack initiation and growth in a CT specimen repaired by stop hole technique

Mixed mode fatigue crack initiation and growth in a CT specimen repaired by stop hole technique

The response of aluminium/GLARE hybrid materials to impact and to in-plane fatigue

Fatigue life estimation after crack repair in 6005 A‐T6 aluminium alloy using the cold expansion hole technique

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