Effect of creep aging forming on the fatigue crack growth of an AA2524 alloy

Liu, Chi; Liu, Yilun; Li, Songbai; Ma, Liyong; Zhao, Xian; Wang, Qing

doi:10.1016/j.msea.2018.04.044

Cited by 8 publications

(7 citation statements)

References 24 publications

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“…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 Li [21] showed that the fatigue life of AA2524 was improved after creep aging.…”

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confidence: 99%

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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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confidence: 99%

“…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 Li [21] showed that the fatigue life of AA2524 was improved after creep aging.…”

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confidence: 99%

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

Liu

et al. 2018

Metals

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“…Such components are used in aviation structures. In response to this problem, a new procedure was proposed by Textron Aero structures 23 with the ability to produce specimens of complex shapes and suitable strength. This process was referred to as creep age forming (CAF) and is basically related to the release and/or creep with the artificial aging of a metal alloy.…”

Section: Introductionmentioning

confidence: 99%

“…Liu et al. 23 investigated the microstructure, fatigue cracking growth and mechanical properties of aluminum alloy 2524 after CAF. Their experimental results show that by increasing the aging time, fatigue performance of the metal alloy reduces and crack propagates in low stress intensity facture.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation, statistical modeling and multi-objective optimization of creep age forming of fiber metal laminates

Safari

Salamat‐talab

Abdollahzade

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part L:

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The experimental assessment of the creep age forming performance of fiber metal laminates was considered in this study. To this end, different fiber metal laminates with the stacking sequence of [Al/02/Al] were manufactured using aluminum alloy 6061 sheets as skins along with E-glass fiber-reinforced polypropylene and E-glass fiber-reinforced polyamide 6 as two different cores. Next, a comprehensive investigation was conducted on the impacts of two main parameters in the creep forming process, i.e. the effect of time and temperature on the spring-back properties of deformed fiber metal laminates. Initially, using the design of experiments and based on the response surface methodology, an imposed spring-back of the creep age formed fiber metal laminates was modeled and the governing linear regression equations were derived and verified. Then, to find the best combination yielding the minimum spring-back, the process inputs (time and temperature) were optimized. The results proved that with an increase in either time or temperature, the spring-backs of the two types of creep age formed fiber metal laminates decreased due to the decrease in elastic strains and the increase of creep strains. Also, to achieve a creep age formed fiber metal laminate with minimum spring-back according to multi-objective optimization in both fiber metal laminates, the most proper values of time and temperature should be taken as 6 h and approximately 160°C, respectively.

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“…With the rapid development of modern industry, the high requirements of aerospace equipment tend to accelerate the invention and the application of new manufacturing technologies. Creep age forming technology is one of those advanced aluminum alloy forming technologies, which synchronizes forming and artificial aging [3]. Compared with traditional forming methods such as drawing, rolling and bending, and shot peening, the creep age forming technology has a range of advantages such as lesser material waste than milling, lower residual stress and better surface quality.…”

Section: Introductionmentioning

confidence: 99%

Effects of Prebending Radii on Microstructure and Fatigue Performance of Al-Zn-Mg-Cu Aluminum Alloy after Creep Age Forming

Yang

Miao

Zhang

et al. 2019

Metals

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A series of creep age forming experiments were carried out on 7075 aluminum alloy with different prebending radii at 443 K for 10 h. The hardness, tensile properties and high cycle fatigue performance of the alloy after creep age forming were obtained. In addition, the microstructure and fatigue fracture of the alloy were observed by transmission electron microscopy (TEM) and scanning electron microscope (SEM). The results show that with the increase of the prebending radius, the hardness, strength and elongation of the alloy increased; meanwhile, the conditional fatigue limit increased, the size of precipitated phase decreased and the quantity increased, while the width of precipitate free zone decreased.

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Effect of creep aging forming on the fatigue crack growth of an AA2524 alloy

Cited by 8 publications

References 24 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

Experimental investigation, statistical modeling and multi-objective optimization of creep age forming of fiber metal laminates

Effects of Prebending Radii on Microstructure and Fatigue Performance of Al-Zn-Mg-Cu Aluminum Alloy after Creep Age Forming

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