On the application of laser shock peening for retardation of surface fatigue cracks in laser beam‐welded AA6056

Kashaev, Nikolai; Ushmaev, Dmitrii; Ventzke, Volker; Klusemann, Benjamin; Fomin, Fedor

doi:10.1111/ffe.13226

Cited by 20 publications

(10 citation statements)

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“…Therefore, the positive effect of LSP, which was shown is this study, is assumed to remain the same in high cycle fatigue regime. The positive effect of LSP on the retardation of fatigue cracks in the high cycle fatigue regime was also demonstrated in a previous study of Kashaev et al [14].…”

Section: Fatigue Testssupporting

confidence: 79%

“…Lorenzino and Navarro [20] reported that an initial growth of the resonant frequency can be attributed to the effect of cyclic hardening in the material, while a drop in the frequency is associated with a crack growth. Similar observations were also reported in [14]. To monitor the fatigue crack growth, a visual inspection was carried out using an optical microscope on both specimen surfaces.…”

Section: Fatigue Testing Of Specimens and Preparation Of Specimens Wisupporting

confidence: 71%

“…It was observed that LSP mainly affects surface defects rather than internal defects. Another study regarding laser beam welding was performed on AA6056 [14]. The authors studied the effect of LSP on pre-cracked laser beam-welded specimens (crack depth is approximately 1.2 mm), and it was established that LSP allows recovering the fatigue life of specimens with surface fatigue cracks to as-welded condition (without surface fatigue cracks).…”

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confidence: 99%

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The Influence of Laser Shock Peening on Fatigue Properties of AA2024-T3 Alloy with a Fastener Hole

Sikhamov

Fomin

Klusemann

et al. 2020

Metals

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The objective of the present study was to estimate the influence of laser shock peening on the fatigue properties of AA2024-T3 specimens with a fastener hole and to investigate the possibility to heal the initial cracks in such specimens. Fatigue cracks of different lengths were introduced in the specimens with a fastener hole before applying laser shock peening. Deep compressive residual stresses, characterized by the hole drilling method, were generated into the specimens by applying laser shock peening on both sides. Subsequently, the specimens were subjected to fatigue tests. The results show that laser shock peening has a positive effect regarding the fatigue life improvement in the specimens with a fastener hole. In addition, laser shock peening leads to a healing effect on fatigue cracks. The efficiency of this effect depends on the initial crack length. The effect of laser shock peening on the fatigue life periods was determined by using resonant frequency graphs.Metals 2020, 10, 495 2 of 13 and fatigue properties of the aluminum alloy LY12-CZ with various interference values (interference value describes how much a mandrel radius is larger than a hole radius), and it was shown that with increasing interference value from 0% to 6%, the fatigue life increases by a factor of six.Another promising way to improve the behavior of fatigue critical components is laser shock peening (LSP) [7]. LSP is a process in which under the influence of laser pulses, mechanical shock waves arise, propagating under the surface of the material [8]. When the peak pressure of waves exceeds the Hugoniot elastic limit (HEL) of the material, plastic deformation occurs, which leads to compressive residual stresses within the material, i.e., near the surface. The subsurface compressive residual stresses are balanced by the stress field within the material or in zones adjacent to the LSP-treated area. In recent years, various studies have been conducted on the effect of LSP on the fatigue properties of different metallic alloys. Ivetic et al. [9] investigated the effect of the sequence of processes (hole introduction and LSP) on the fatigue properties of AA6082-T6 specimens. The experiments showed that the sequence of processes is important for the improvement of the fatigue life. The beneficial effect of LSP is higher if the hole is introduced after LSP. This is linked to the fact that compressive residual stresses in LSP-treated specimen are compensated by tensile residual stresses [3], and in the case of applying LSP after drilling a hole, the magnitude of tensile stresses would be higher, which would lead to a shorter fatigue life. Achintha et al. [10] evaluated the effect of the size of the LSP-treated area on fatigue properties of AA2024-T3 specimens. Two cases were considered: (i) LSP was performed just around the hole, and (ii) LSP was applied across the entire width of the specimen. The results showed that specimens with a smaller treated area around the hole can withstand more loading cycles than specimens peened along the e...

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Section: Fatigue Testssupporting

confidence: 79%

Section: Fatigue Testing Of Specimens and Preparation Of Specimens Wisupporting

confidence: 71%

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confidence: 99%

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The Influence of Laser Shock Peening on Fatigue Properties of AA2024-T3 Alloy with a Fastener Hole

Sikhamov

Fomin

Klusemann

et al. 2020

Metals

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“…Note that similar observations of how weld defects affect the fatigue behaviour have also been reported for FS aluminium weldments, where the crack either initiates at surface irregularities like weld undercuts and flash ridges or at root defects. 10,[37][38][39][40] In that sense, there is no significant difference between a HYB weld and a FS weld. Figure 8 shows a comparison of the calculated S-N curves for the BM and the two sets of welded specimens, EZ and EZ red .…”

Section: Fracture Analysismentioning

confidence: 94%

Fatigue properties of AA6060‐T6 butt welds made by hybrid metal extrusion & bonding

Sandnes

Grong

Welo

et al. 2020

Fatigue Fract Eng Mat Struct

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The present investigation is concerned with high‐cycle axial fatigue testing of a 2‐mm AA6060‐T6 hybrid metal extrusion & bonding (HYB) butt weld produced in the solid state using AA6082 filler metal addition. The results complement the three‐point bend testing and the tensile testing done in two previous studies. In this study, optical microscope and scanning electron microscope examinations have been carried out to reveal the joint macro/microstructure and document possible surface and root defects deemed to affect fatigue life. In the as‐welded condition, the HYB weld suffers from surface irregularities at the weld face and ‘kissing’ bond formation in the root region. Despite of this, the subsequent testing shows that the fatigue properties exceed those reported for comparable AA6082‐T6 gas metal arc butt welds and matching those reported for corresponding high‐strength laser beam and friction stir weldments.

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“…However, they found that LSP could not inhibit the initiation of cracks at scribe roots. Similarly, Kashaev et al 18 employed LSP to restore the fatigue life of laser beam‐welded AA6056‐T6 butt joints with a pre‐existing crack to the level of specimens tested in as‐welded condition. Sikhamov et al 19 exhibited healing of initial cracks in AA2024‐T3 alloy with a fastener hole due to LSP, which improved fatigue life by increasing the crack growth period.…”

Section: Introductionmentioning

confidence: 99%

Fatigue performance of laser shock peened Ti6Al4V and Al6061‐T6 alloys

Maharjan¹,

Chan²,

Ramesh³

et al. 2020

Fatigue Fract Eng Mat Struct

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Propagation of fatigue crack in laser shock peened metallic component is retarded by introduction of deep compressive residual stresses during the process. Apart from large compressive residual stress build‐up near the surface, surface topography is also significantly altered during laser shock peening. However, a systematic evaluation of the individual effects of residual stresses and surface topography as well as their interaction effects on fatigue crack initiation and growth is still lacking. This study investigates the effect of laser shock peening on near‐surface properties of Ti6Al4V and Al6061‐T6 alloys and how these changes dictate their overall fatigue performance. Microstructure, surface topography, hardness and residual stress state of the alloys are investigated before and after peening, and four‐point bending fatigue tests are performed to obtain Wöhler curves (S‐N curves) for each case. The results show that both surface residual stresses and surface topography influence the fatigue life of a component. Compressive residual stresses were induced to a depth beyond 1 mm for both alloys. Fatigue life of Ti6Al4V alloy increased by at least 1.28 times after laser shock peening due to the introduction of deep compressive residual stresses with minimal change in surface topography. By contrast, the improvement is nominal for Al6061‐T6 alloy due to the surface roughening effect introduced by laser peening, which results in early crack initiation and negates the beneficial effect of compressive residual stresses.

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On the application of laser shock peening for retardation of surface fatigue cracks in laser beam‐welded AA6056

Cited by 20 publications

References 50 publications

The Influence of Laser Shock Peening on Fatigue Properties of AA2024-T3 Alloy with a Fastener Hole

The Influence of Laser Shock Peening on Fatigue Properties of AA2024-T3 Alloy with a Fastener Hole

Fatigue properties of AA6060‐T6 butt welds made by hybrid metal extrusion & bonding

Fatigue performance of laser shock peened Ti6Al4V and Al6061‐T6 alloys

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