Effect of grain size on the fatigue crack growth behavior of 2524-T3 aluminum alloy

Shou, Wenbin; Yi, Danqing; Liu, H. Q.; Tang, Chaojun; Shen, Fanghua; Wang, B.

doi:10.1016/j.acme.2016.01.004

Cited by 56 publications

(33 citation statements)

References 28 publications

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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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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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“…In some cases [ 50 ], plastic strains caused the formation of dissipative structures in the materials, especially under dynamic loading. In some papers—for example, [ 51 ]—the cyclic crack resistance increased not only at the crack nucleation stage but also at crack propagation one. The authors attributed this fact to a change in the shapes and purity of the grain boundaries.…”

Section: Resultsmentioning

confidence: 99%

Increasing Fatigue Life of 09Mn2Si Steel by Helical Rolling: Theoretical–Experimental Study on Governing Role of Grain Boundaries

et al. 2020

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The structure and mechanical properties of the 09Mn2Si high-strength low-alloyed steel after the five-stage helical rolling (HR) were studied. It was revealed that the fine-grained structure had been formed in the surface layer ≈ 1 mm deep as a result of severe plastic strains. In the lower layers, the “lamellar” structure had been formed, which consisted of thin elongated ferrite grains oriented in the HR direction. It was shown that the five-stage HR resulted in the increase in the steel fatigue life by more than 3.5 times under cyclic tension. The highest values of the number of cycles before failure were obtained for the samples cut from the bar core. It was demonstrated that the degree of the elastic energy dissipation in the steel samples under loading directly depended on the area of the grain boundaries as well as on the grain shapes. The fine-grained structure possessed the maximum value of the average torsional energy among all the studied samples, which caused the local material structure transformation and the decrease in the elastic energy level. This improved the crack resistance under the cyclic mechanical loading. The effect of the accumulation of the rotational strain modes at the grain boundaries was discovered, which caused the local structure transformation at the boundary zones. In the fine-grained structure, the formation of grain conglomerates was observed, which increased the values of the specific modulus of the moment of force. This could be mutually compensated due to the small sizes of grains. At the same time, the coarse-grained structures were characterized by the presence of the small number of grains with a high level of the moments of forces at their boundaries. They could result in trans-crystalline cracking.

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“…Yan and Fan [22] have also reported that the direction of microcrack propagation can be influenced by grain boundary. The effect of grain size on the fatigue crack growth in 2524-T3 alloy was examined by Shou et al [23]. They observed that alloys with grain sizes in the range of 50 -100 µm to exhibit higher fatigue crack growth rates.…”

Section: Introductionmentioning

confidence: 99%

Fatigue Responses of Three AA 2000 Series Aluminum Alloys

Owolabi¹,

Thom²,

Ajide³

et al. 2019

MSCE

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In this paper, smooth specimens of three aluminum alloys: AA 2219-T8, AA 2519-T8 and AA 2624-T351, were subjected to the same level of uniaxial (tension/compression) fatigue loading to compare their fatigue responses. Fractographic investigations of the failed specimens after fatigue loading was also conducted using a scanning electron microscope. The fatigue test results showed considerable differences in the fatigue lives of the three investigated alloys with AA 2219-T8 having the shortest fatigue life and AA 2624-T351 the longest fatigue life. The fractographic analysis showed that coalescence of micropores, microvoids, particles cleavage and microcracks are the predominant features in the fracture surface of AA 2219-T8. The fracture surface features of AA 2519-T8 revealed higher resistance to fatigue cracks nucleation and growth when compared to AA 2219-T8. The features depicted mainly partly ductile and partly brittle fracture. The AA 2624-T351 fracture surface features revealed noteworthy ductile failure mechanism. The results suggest a strong correlation between the surface fractographic features and the fatigue lives of the alloys. It is also observed that in addition to the yield strengths and ultimate tensile strengths, the total strain energy densities (SED) may provide a reasonable indication of the relative fatigue performance of the three alloys. AA 2219-T8 had the lowest SED and the lowest fatigue life, while AA 2624-T351 had the highest SED and the highest fatigue life. Thus, AA 2624-T351 would be the most suitable materials for components subjected to fatigue loading.

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Effect of grain size on the fatigue crack growth behavior of 2524-T3 aluminum alloy

Cited by 56 publications

References 28 publications

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

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

Increasing Fatigue Life of 09Mn2Si Steel by Helical Rolling: Theoretical–Experimental Study on Governing Role of Grain Boundaries

Fatigue Responses of Three AA 2000 Series Aluminum Alloys

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