Effect of Young’s modulus on fatigue crack growth

Borges, M.F.; Antunes, F.V.; Prates, Pedro A.; Branco, R.; Vojtek, Tomáš

doi:10.1016/j.ijfatigue.2019.105375

Cited by 16 publications

(10 citation statements)

References 22 publications

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“…As mentioned, nano-particles could increase mechanical properties of aluminum alloys. [14][15][16][17][18] Since these properties could affect fatigue properties; 19,20 therefore, as the second group of the literature review, the following paragraph is about the fatigue behavior of aluminum matrix composites. Raju et al 14 studied the effect of the nano-Al 2 O 3 -reinforcement on the fatigue lifetime of aluminum matrix nano-composites.…”

Section: Introductionmentioning

confidence: 99%

Fabrication of heat-treated nano-clay-composite for improving high-cycle fatigue properties of AlSiCu aluminum alloy under stress-controlled fully-reversed bending loads

Sharifi

Azadi

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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In the present article, a heat-treated nano-clay-composite was fabricated by stir-casting to improve high-cycle bending fatigue properties of AlSiCu aluminum alloys, which have been widely used in engine cylinder-heads. For such an objective, after ball milling of nano-clay-particles with micro-copper-particles, these coated particles were added to the aluminum melt and cylindrical specimens were stir-casted. Then, fully-reversed stress-controlled fatigue testing was performed on standard samples. In addition, the fracture surface was examined by the field-emission scanning electron microscopy to find failure mechanisms. Obtained results showed that reinforcements, including nano-clay-particles and the heat treatment increased the fatigue lifetime, at least 9%. Such an improvement in the fatigue lifetime was 125% under low values of the stress level. Due to have a proper distribution of nano-particles in the aluminum matrix, the scatter-band for the fatigue lifetime was narrower in the heat-treated nano-composite. The endurance fatigue limit was also improved 30% at 106 cycles, for the heat-treated nano-composite, comparing to the base material. The brittle fracture was observed due to have cleavage and quasi-cleavage marks on the fracture surface for both materials. Micro-cracks were initiated and propagated from Si and intermetallics phases.

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Section: Introductionmentioning

confidence: 99%

Fabrication of heat-treated nano-clay-composite for improving high-cycle fatigue properties of AlSiCu aluminum alloy under stress-controlled fully-reversed bending loads

Sharifi

Azadi

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…In previous works, 39,40 the authors used an approach based on plastic CTOD measured at the first node behind the crack tip, assuming that this is representative of crack tip plastic deformation. However, a fixed number of load cycles was applied between crack increments (usually 2 or 5), which is unrealistic and may affect da/dN.…”

Section: Numerical Modelmentioning

confidence: 99%

“…The values of the identified constants show minor sensitivities regarding the specimen orientation, as highlighted in Table 3. In a previous study, 39 a sensitivity analysis was developed to quantify the relative importance of the different elastic–plastic properties on the FCG rate. It was found that Y 0 had a higher effect, followed by

X_{Sat}

and

C_{X}

.…”

Section: Numerical Modelmentioning

confidence: 99%

Effect of L‐T and S‐T orientations on fatigue crack growth in an aluminum 7050‐T7451 plate

Borges

Antunes

Jesús

et al. 2023

Fatigue Fract Eng Mat Struct

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This study is focused on the anisotropic fatigue crack growth (FCG) behavior of an aluminum AA7050‐T7451 plate. L‐T and S‐T orientations were studied in M(T) samples with W = 50 mm, in mode I loading, with R‐ratio of +0.05. A numerical approach was used, assuming that crack tip plastic strain is the crack driving force. A purely kinematic elastic–plastic model was calibrated using experimental data from low cycle fatigue tests of smooth specimens in L and S orientations. The predicted FCG rates agree well with experimental trends in the Paris' regime, suggesting that cyclic plastic deformation is the main damage mechanism. The numerical model was used to estimate the stress ratio effect for both orientations, which was found to be linked with crack closure variations. However, the closure free predicted trends for both microstructural orientations at R = 0.05 are not overlapped, suggesting an effect of microstructure not linked to crack closure.

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“…The C(T) specimen was fatigue pre-cracked to emulate the natural crack characteristics. The effect of loading and material properties (mainly yield stress) strongly influences fatigue crack growth [35]. The pre-cracking load details are shown in Table 2.…”

Section: Fracture Toughness Test Analysismentioning

confidence: 99%

Effect of Strain Rate and Temperature on Tensile and Fracture Performance of AA2050-T84 Alloy

et al. 2022

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AA2050-T84 alloy is widely used in primary structures of modern transport aircraft. AA2050-T84 is established as a low-density aluminum alloy with improved Young’s modulus, less anisotropy, and temperature-dependent mechanical properties. During flights, loading rate and temperature variation in aircraft engine subsequent parts are commonly observed. The present work focuses on the effect of loading rate and temperature on tensile and fracture properties of the 50 mm thick (2-inch) AA2050-T84 alloy plate. Quasi-static strain rates of 0.01, 0.1, and 1 s−1 at −20 °C, 24 °C and 200 °C are considered. Tensile test results revealed the sensitivity of mechanical properties towards strain rate variations for considered temperatures. The key tensile properties, yield, and ultimate tensile stresses were positive strain rate dependent. However, Young’s modulus and elongation showed negative strain rate dependency. Experimental fracture toughness tests exhibited the lower Plane Strain Fracture Toughness (KIC) at −20 °C compared to 24 °C. Elastic numerical fracture analysis revealed that the crack driving and constraint parameters are positive strain rate dependent and maximum at −20 °C, if plotted and analyzed over the stress ratio. The current results concerning strain rates and temperatures will help in understanding the performance-related issues of AA2050-T84 alloy reported in aircraft applications.

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Effect of Young’s modulus on fatigue crack growth

Cited by 16 publications

References 22 publications

Fabrication of heat-treated nano-clay-composite for improving high-cycle fatigue properties of AlSiCu aluminum alloy under stress-controlled fully-reversed bending loads

Fabrication of heat-treated nano-clay-composite for improving high-cycle fatigue properties of AlSiCu aluminum alloy under stress-controlled fully-reversed bending loads

Effect of L‐T and S‐T orientations on fatigue crack growth in an aluminum 7050‐T7451 plate

Effect of Strain Rate and Temperature on Tensile and Fracture Performance of AA2050-T84 Alloy

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