Effect of grain size on fatigue-crack growth in 2524 aluminium alloy

Yin, Dong; Liu, Huiqun; Chen, Yuqiang; Yi, Danqing; Wang, Bo; Wang, Bin; Shen, Fanghua; Fu, Shang; Tang, Chaojun; Pan, Suping

doi:10.1016/j.ijfatigue.2015.11.011

Cited by 106 publications

(42 citation statements)

References 30 publications

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“…13f). The phenomenon of crack closure delaying fatigue crack propagation has been observed and reported in the previous studies as well [34,35]. Thus, the crack closure observed in this study may be related to the high Schmid factors and large sizes of the grains, as per the statistical chart of the Schmid factors (see in Fig.…”

Section: Fatigue Crack Path Analysissupporting

confidence: 81%

Effects of heating rate during solid-solution treatment on microstructure and fatigue properties of AA2524 T3 Al–Cu–Mg sheet

Shen

Wang

et al. 2016

Materials & Design

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Section: Fatigue Crack Path Analysissupporting

confidence: 81%

Effects of heating rate during solid-solution treatment on microstructure and fatigue properties of AA2524 T3 Al–Cu–Mg sheet

Shen

Wang

et al. 2016

Materials & Design

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“…Furthermore, as stress ratio increases, the fatigue threshold value decreases for both sensitized conditions of alloy. In the threshold regime, the combined effect of segregation of precipitate particles near to grain boundaries, plasticity induced crack closure, and crack driving force significantly affects the FCG properties of sensitized alloy …”

Section: Resultsmentioning

confidence: 99%

Investigation of fatigue and fracture behaviour of sensitized marine grade aluminium alloy AA 5754

Kumar

Singh

2019

Fatigue Fract Eng Mat Struct

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In the present study, fatigue and fracture characteristics of sensitized marine grade Al‐Mg (AA 5754) alloy are experimentally evaluated. Received alloy is sensitized at temperatures of 150°C (SENS50) and 175°C (SENS75) for 100 hours. Fracture parameters, KIc and JIc, are experimentally evaluated. Slow strain rate tensile tests at a crosshead speed of 0.004, 0.006, and 0.01 mm/min; fatigue crack growth tests at load ratios (R = Pmin/Pmax) of 0.1, 0.2, and 0.5; and low cycle fatigue tests at four strain amplitudes of (0.3‐0.6)% are performed for SENS50 and SENS75 alloys. Relatively lower magnitude of fracture toughness values are observed for SENS75 specimen. Severe degradation in tensile properties, fatigue crack growth characteristics, and low cycle fatigue lives are observed for SENS75 samples. Extended finite element method is adopted to simulate the elasto‐plastic crack growth during fracture toughness evaluation. Scanning electron microscopy (SEM) is used to understand the failure mechanism of sensitized alloys.

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“…The fatigue crack propagation (FCP) resistance of aerospace structural components is an extremely important indicator. Yin [16] and Shou [17] et al discussed the influence of grain size on the crack growth rate of 2524 aluminum alloy. Yin suggested that within the range of low stress intensity factor ΔK, the crack closure effect of the coarse grain samples was greater than that of the fine grain samples, and the grain refinement degraded the fatigue resistance.…”

Section: Introductionmentioning

confidence: 99%

Precipitate Evolution and Fatigue Crack Growth in Creep and Artificially Aged Aluminum Alloy

Liu

et al. 2018

Metals

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The fatigue performance of high-strength Al-Cu-Mg alloys is generally influenced by the process of creep age formation when applied to acquire higher strength. The results show that creep aging accelerates the precipitation process, leading to a more uniform precipitation of strengthening phases in grains, as well as narrowed precipitation-free zones (PFZ). Compared with the artificially aged alloy, the yield strength and hardness of the creep aged alloy increased, but the fatigue resistance decreased. In the low stress intensity factor region (∆K ≤ 7 MPa·m 1/2 ), the fatigue crack propagation (FCP) rate was mainly affected by the characteristics of precipitates, and the fatigue resistance noticeably decreased with the increased creep time. In a 4 h creep aged alloy, the microstructure was dominated by Cu-Mg clusters and Guinier-Preston (GP) zones, while S" phases began to precipitate in the matrix, showing better fatigue resistance. After aging for 24 h, the needle-shaped S' phases were largely precipitated and coarsened, which changed the mode of dislocation slip, reduced the reversibility of slip, and accelerated the accumulation of fatigue damage. In stable and rapid crack propagation regions, the influence of precipitates on the FCP rate was negligible.in the creep aged alloy and increase its density and uniformity, leading to a shortened time for peak aging and improved strength.The current research on creep aged alloys focuses mainly on conventional mechanical properties and less on the fatigue properties. Influenced by frequent takeoff, landing, and airflow, creep aging-formed fuselage skin, wings, and other components are the most vulnerable to fatigue failure [15]. The fatigue crack propagation (FCP) resistance of aerospace structural components is an extremely important indicator. Yin [16] and Shou [17] et al. discussed the influence of grain size on the crack growth rate of 2524 aluminum alloy. Yin suggested that within the range of low stress intensity factor ∆K, the crack closure effect of the coarse grain samples was greater than that of the fine grain samples, and the grain refinement degraded the fatigue resistance. Shou demonstrated that when the grain size was between 50 and 100 µm, the crack growth rate was relatively low, and the crack growth path became more zigzagged. Srivatsan et al. [18] studied the effect of test temperature on the high-cycle fatigue and fracture properties of AA2524, indicating that the fatigue life decreased with the increasing test temperature. Baptista et al. [19] introduced an enhanced two-parameter exponential equation model to describe the subcritical FCP behavior of 2524-T3 aluminum alloy, which performed better than other test models. However, the aforementioned studies focused on the materials without thoroughly examining the impact of the creep age forming process.Liu studied the fatigue behavior of creep aged AA2524 at 180 • C and suggested that the crack growth resistance of the alloy was reduced after treatment [20]. On the contrary, the research of Wenke...

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Effect of grain size on fatigue-crack growth in 2524 aluminium alloy

Cited by 106 publications

References 30 publications

Effects of heating rate during solid-solution treatment on microstructure and fatigue properties of AA2524 T3 Al–Cu–Mg sheet

Effects of heating rate during solid-solution treatment on microstructure and fatigue properties of AA2524 T3 Al–Cu–Mg sheet

Investigation of fatigue and fracture behaviour of sensitized marine grade aluminium alloy AA 5754

Precipitate Evolution and Fatigue Crack Growth in Creep and Artificially Aged Aluminum Alloy

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