On the interaction between corrosion and fatigue which determines the remaining life of bridges

Peng, Daren; Jones, Rhys; Singh, Raman Raghuvir Kumar; Berto, Filippo; McMillan, Alex

doi:10.1111/ffe.12680

Cited by 10 publications

(6 citation statements)

References 23 publications

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“…Indeed, this finding is independently validated via the recent review of atomistic simulation of the growth of small cracks [52,53]. As explained in ASTM E647-13a [54] and [8,19,20,[27][28][29][30][31][32][33][34][35][36][37][38][39][40][41][42]53], for crack growth from small naturally occurring discontinuities there is little R ratio dependence and the value of ∆Kthr is very small . Hence there is little, if any, crack closure associated with the growth of small naturally occurring cracks [8,19,53].…”

Section: Discussion Of Resultsmentioning

confidence: 71%

“…The values of ΔKthr used as well as the initiating discontinuity size are shown in Table 5. The results of this study when taken in conjunction with that in Section 2 and the studies presented in [6,8,19,20,26,4238,41,42] illustrate how the growth of cracks from environmental damage in aircraft structures can be reasonably accurately computed using the Hartman-Schijve crack growth equation and that allowing for experimental error the variability of the crack depth histories can be reasonably well accounted for by allowing for small changes in the value of the term Kthr. We also see that, as per the USAF approach to ris  k assessment [16] and the DST Group formulation [17,18] the growth of the lead cracks, i.e.…”

Section: Crack Growth At Fastener Holes Containing Intergranular Cracmentioning

confidence: 66%

“…Having established how the Hartman-Schijve crack growth equation can be used to accurately compute the growth of cracks at a fastener hole containing intergranular cracking subjected to a measured operational maritime flight load spectrum let us next consider the problem discussed in [20] which involves the growth of cracks from surface pits under a representative civil aircraft spectrum. (Here it should be noted that the ability of this formulation to accurately compute the growth of cracks from surface pits under combat aircraft flight load spectra is shown in [8,19,20,26,41] and its ability to accurately compute the growth of cracks from surface corrosion in a bridge steel is illustrated in [42].) The test coupons discussed in [20] were made from an AA7050-T7451 6" thick plate and had an "hourglass" (dogbone) shape, as shown schematically in Figure 8.…”

Section: Crack Growth At Fastener Holes Containing Intergranular Cracmentioning

confidence: 99%

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Computing the Effect of Environmental Damage on Aircraft Structural Integrity

Jones¹,

Peng²,

Matthews³

et al. 2018

Preprint

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This paper studies the combined effect of corrosion and fatigue on the growth of cracks in aircraft and on the effect of skin corrosion and stress corrosion cracking on the load bearing capacity of rib stiffened aircraft wings. In this context it is shown that the growth of cracks from surface pitting, and also from intergranular cracking at a fastener hole, can be accurately computed using the Hartman-Schijve variant of the NASGRO crack growth equation. The examples studied support the lead crack approach, that has been independently developed by the USAF and the Australian Defence Science Technology Group, in which the growth of lead cracks is often exponential. In the case of skin corrosion it is shown that to be consistent with the US Joint Service Structural Guidelines (JSSG2006) assessment of its effect on the load bearing capacity of the wing should involve an assessment of whether at 115% DLL the remaining material exceeds the yield stress of the material.

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Section: Discussion Of Resultsmentioning

confidence: 71%

Section: Crack Growth At Fastener Holes Containing Intergranular Cracmentioning

confidence: 66%

Section: Crack Growth At Fastener Holes Containing Intergranular Cracmentioning

confidence: 99%

See 1 more Smart Citation

Computing the Effect of Environmental Damage on Aircraft Structural Integrity

Jones¹,

Peng²,

Matthews³

et al. 2018

Preprint

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“…Xu et al [20] also studied the fatigue behavior of corroded steel, which indicated that the fatigue life of corroded steel decreased rapidly due to the increasing rough surface. Peng et al [25,26] combined the uniform corrosion and NASGRO equation to determine the remaining life of structures, the result indicated that the C-F life of the structure was decreased with the assumed initial flaw size increasing.…”

Section: Literature Reviewmentioning

confidence: 99%

Corrosion-Fatigue Evaluation of Uncoated Weathering Steel Bridges

2019

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Uncoated weathering steel (UWS) bridges have been extensively used to reduce the lifecycle cost since they are maintenance-free and eco-friendly. However, the fatigue issue becomes significant in UWS bridges due to the intended corrosion process utilized to form the corrodent-proof rust layer instead of the coating process. In this paper, an innovative model is proposed to simulate the corrosion-fatigue (C-F) process in UWS bridges. Generally, the C-F process could be considered as two relatively independent stages in a time series, including the pitting process of flaw-initiation and the fatigue crack propagation of the critical pitting flaw. In the proposed C-F model, Faraday’s law has been employed at the critical flaw-initiation stage to describe the pitting process, in which the pitting current is applied to reflect the pitting rate in different corrosive environments. At the crack propagation stage, the influence of pitting corrosion is so small that it can be safely ignored. In simulating the crack propagation stage, the advanced NASGRO equation proposed by the NASA is employed instead of the classic Paris’ law, in which a modified fatigue limit is adopted. The fatigue limit is then used to determine the critical size of pitting flaws, above which the fatigue effect joins as a parallel driving force in crack propagation. The model is then validated through the experimental data from published articles at the initiation stage as well as the whole C-F process. Two types of structural steel, i.e., HPS 70W and 14MnNbq steel, have been selected to carry out a case study. The result shows that the C-F life can be notably prolonged in the HPS 70W due to the enhancement in fatigue strength and corrosion resistance. Besides, a sensitivity analysis has been made on the crucial parameters, including the stress range, stress ratio, corrosive environment and average daily truck traffic (ADTT). The result has revealed the different influence of the above parameters on the initiation life and propagation life.

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“…As far as metallic materials are concerned, many structural components experience multiaxial fatigue loading. This is the case, for instance, of metallic parts of bridges cyclically loaded by traveling motor vehicles …”

Section: Introductionmentioning

confidence: 99%

Fatigue assessment of metallic components under uniaxial and multiaxial variable amplitude loading

Carpinteri

Łagoda

Karolczuk

et al. 2018

Fatigue Fract Eng Mat Struct

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In the present paper, the fatigue lifetime of metallic structural components subjected to variable amplitude loading is evaluated by applying 2 different multiaxial high‐cycle fatigue criteria. Such criteria, proposed by some of the present authors, are based on the critical plane approach and aim at reducing a given multiaxial stress state to an equivalent uniaxial stress condition. In particular, the procedure employed by both criteria consists of the following 3 steps: (1) definition of the critical plane; (2) counting of loading cycles; and (3) estimation of fatigue damage. Finally, the previous criteria are validated by comparing the theoretical results with experimental data related to smooth metallic specimens subjected to uniaxial and multiaxial variable amplitude loading.

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On the interaction between corrosion and fatigue which determines the remaining life of bridges

Cited by 10 publications

References 23 publications

Computing the Effect of Environmental Damage on Aircraft Structural Integrity

Computing the Effect of Environmental Damage on Aircraft Structural Integrity

Corrosion-Fatigue Evaluation of Uncoated Weathering Steel Bridges

Fatigue assessment of metallic components under uniaxial and multiaxial variable amplitude loading

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