Experimental investigation on damage evolution in pre-corroded aluminum alloy 7075-T7651 under fatigue loading

Song, Hang; Liu, Changchun; Zhang, Hao; Yang, Xudong; Chen, Yajun; Leen, Seán B.

doi:10.1016/j.msea.2020.140206

Cited by 27 publications

(21 citation statements)

References 31 publications

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“…Whether fatigue cracking occurs in hazardous detail part is independent, and the cracking probability is set as p. The similar details number x of fatigue cracking follows binomial distribution, namely X ∼ Bðn, pÞ. The probability P N 0 of fatigue cracking of k hazardous detail parts under specified load cycle N 0 is defined as equation (2). It also works when n = 1…”

Section: Quantifying Damage Probability For Similar Detail Groupmentioning

confidence: 99%

“…The probability distribution characteristics of similar details number of fatigue cracking in different load cycles are shown in Figures 1(a) to (e)), respectively. The y-axial in the figure below represents the result of equation (2), that is, the probability of similar details number of fatigue cracking. It can be seen what is the maximum probability P N 0 when the similar details number x of fatigue cracking is taken, which indicates the correctness of the binomial distribution maximum probability rule proposed above.…”

Section: Failure Probability Of the Similar Details Number Of Fatigue...mentioning

confidence: 99%

“…So far, researchers have done a lot of research on the fatigue behavior of materials. The mechanism of fatigue crack initiation 2,3 and the characteristics of crack propagation 4,5 were explained from the microscopic perspective, and the influencing factors of fatigue behavior were analyzed. 6 In addition, more studies have been conducted on the prediction of fatigue life.…”

Section: Introductionmentioning

confidence: 99%

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Investigation on fatigue damage equivalence probability for the structure with similar fatigue hazardous detail parts

Qin

Dui³

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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Fatigue damage of a whole structure with multiple similar fatigue hazardous detail parts is unclear. This paper focuses on the concept of quantified fatigue damage for the structure with similar fatigue hazardous detail parts by using the probability method and fatigue failure probability of the severe load spectrum. The probability criterion and calculation method of equivalent damage with different load spectra were proposed. The fatigue life probability distribution of the severe load spectrum was analyzed, and the acceleration ratio was defined by the similar details number of fatigue cracking in combination with the fatigue failure probability characteristics of the severe load spectrum. The results show that there is good agreement between the similar details number range of fatigue cracking in two load spectra, which means they are considered to be equivalent. The ratio of the sum of two similar details number ranges is used as acceleration ratio to evaluate the severe load spectrum. The application of this study in the statistical sense of engineering structure fatigue failure is more convincing.

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Section: Quantifying Damage Probability For Similar Detail Groupmentioning

confidence: 99%

Section: Failure Probability Of the Similar Details Number Of Fatigue...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Investigation on fatigue damage equivalence probability for the structure with similar fatigue hazardous detail parts

Qin

Dui³

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…The flow behavior of titanium alloy under hot working conditions was investigated using an extrapolated model that was based on the Linear and Ludwick hardening laws [ 24 ]. A practical approach to extend typical stress—strain curves and obtain the mechanical properties of material is the digital image correlation (DIC) method, which has been effectively applied in acquiring the deformation field on the surface of the material and the structure [ 25 , 26 , 27 , 28 ]. 3D deformation measurement data and finite element (FE) analysis of expansion tests were utilized to determine the parameters of the Swift and Hollomon hardening laws of aerospace alloys [ 29 ].…”

Section: Introductionmentioning

confidence: 99%

Investigation on Strain Hardening and Failure in Notched Tension Specimens of Cold Rolled Ti6Al4V Titanium Alloy

Zhang,

Gao,

Chen

et al. 2022

Materials

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Uniaxial and notched tension samples are utilized to investigate the damage and failure of titanium alloy Ti6Al4V. The strain fields on the samples are obtained by the digital image correlation (DIC) method. Strain localization occurs before fracturing in all samples, and the width and size of the localized zone are characterized. Slant fractures are observed in uniaxial and notched tension specimen, which indicate that the initiation and propagation of cracks in thin sheet specimens are highly affected by the shear stress. Numerical simulations were performed for identification of hybrid hardening laws, and the results were compared with the experiments. The influence of the stress triaxiality on damage mechanism of Ti6Al4V was analyzed by observation of the specimen fracture surfaces using SEM. The results show that a higher stress triaxiality facilitates the formation and growth of micro-voids, which leads to a decrement of strain at failure.

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“…To date, many studies have been performed elucidating the effects of pre-corrosion on the fatigue performance of 7075 aluminum alloy [10][11][12][13][14][15][16][17][18][19][20][21][22]. For instance, Sankaran et al [12] investigated the effects of pitting pre-corrosion on the fatigue behavior of aluminum alloy 7075-T6 using cyclic fog-dry salt spray tests, and found that the fatigue lives of aluminum alloys could be dramatically reduced by pitting corrosion.…”

Section: Introductionmentioning

confidence: 99%

Actual Marine Atmospheric Pre-Corrosion Fatigue Performance of 7075-T73 Aluminum Alloy

Shi

Xiang²,

Tao³

et al. 2022

Metals

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Actual marine atmospheric pre-corrosion behavior and its effect on the fatigue performance of 7075-T73 aluminum alloy were studied by means of marine atmospheric outdoor exposure testing and fatigue testing. The surface and cross-sectional microstructures of aluminum alloy specimens after different numbers of days of exposure were analyzed. Localized pitting, and intergranular and exfoliation corrosion occurred during the outdoor exposure of aluminum alloy specimens in a marine atmosphere. The degree of severity of atmospheric corrosion increased with increasing duration of exposure. The effects of Fe-rich constituent particles (Al23CuFe4) and grain boundary precipitates (MgZn2) on the marine atmospheric corrosion behavior were discussed. In addition, when the exposure time was increased from 0 days to 15 days, the average fatigue life of aluminum alloy specimens decreased dramatically from about 125.16 × 104 cycles to 16.58 × 104 cycles. As the exposure time was further increased to 180 days, the average fatigue life slowly decreased to about 6.21 × 104 cycles. The fatigue fracture characteristics and the effect mechanism of marine atmospheric pre-corrosion on the fatigue life of 7075-T73 aluminum alloy were also analyzed.

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Experimental investigation on damage evolution in pre-corroded aluminum alloy 7075-T7651 under fatigue loading

Cited by 27 publications

References 31 publications

Investigation on fatigue damage equivalence probability for the structure with similar fatigue hazardous detail parts

Investigation on fatigue damage equivalence probability for the structure with similar fatigue hazardous detail parts

Investigation on Strain Hardening and Failure in Notched Tension Specimens of Cold Rolled Ti6Al4V Titanium Alloy

Actual Marine Atmospheric Pre-Corrosion Fatigue Performance of 7075-T73 Aluminum Alloy

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