Residual Stress Field of a Single Edge Notch Specimen after Laser Shock Peening and Shot Peening Treatment

2018 ◽  
Vol 7 (4) ◽  
pp. 20170133
Author(s):  
Stefano Coratella ◽  
T. J. Spradlin ◽  
Kristina Langer ◽  
Michael A. Gharghouri ◽  
U. C. Heckenberger ◽  
...  
Keyword(s):  
Residual Stress ◽  
Stress Field ◽  
Shot Peening ◽  
Laser Shock Peening ◽  
Laser Shock ◽  
Single Edge ◽  
Residual Stress Field ◽  
Single Edge Notch ◽  
Edge Notch ◽  
Shock Peening

Numerical Simulation of Laser Shock Peening on Residual Stress Field of 7075-T6 Aluminum Alloy Welding

2014 ◽  
Vol 34 (4) ◽  
pp. 0414003
Author(s):  
罗密 Luo Mi ◽  
罗开玉 Luo Kaiyu ◽  
王庆伟 Wang Qingwei ◽  
鲁金忠 Lu Jinzhong
Keyword(s):  
Numerical Simulation ◽  
Residual Stress ◽  
Aluminum Alloy ◽  
Stress Field ◽  
Laser Shock Peening ◽  
Laser Shock ◽  
Residual Stress Field ◽  
Shock Peening

An Analytical Model to Predict Residual Stress Field Induced by Laser Shock Peening

2009 ◽  
Vol 131 (3) ◽  
Author(s):  
Yongxiang Hu ◽  
Zhenqiang Yao ◽  
Jun Hu
Keyword(s):  
Residual Stress ◽  
Stress Field ◽  
Analytical Model ◽  
Laser Shock Peening ◽  
Treatment Technique ◽  
Laser Shock ◽  
Residual Stress Field ◽  
Proposed Model ◽  
Shock Peening ◽  
The Impact

Laser shock peening (LSP) is an innovative surface treatment technique similar to shot peening. An analytical model to predict the residual stress field can obtain the impact effect much quickly, and will be invaluable in enabling a close-loop process control in production, saving time and cost of processing. A complete analytical model of LSP with some reasonable simplification is proposed to predict residual stresses in depth by a sequential application of a confined plasma development model and a residual stress model. The spatial distribution of the shock pressure and the high strain rate effect are considered in the model. Good agreements have been shown with several experimental measured results for various laser conditions and target materials, thus proving the validity of the proposed model.

INVESTIGATION OF RESIDUAL STRESS FIELD IN THE CURVED SURFACE OF ROUND ROD SUBJECTED TO MULTIPLE LASER SHOCK PEENING

2021 ◽  
pp. 2150029
Author(s):  
XINGQUAN ZHANG ◽  
WENWU NIU ◽  
YUANDE YIN ◽  
JINXIU FANG ◽  
SYED SOHAIL AHMAD SHAH ◽  
...  
Keyword(s):  
Residual Stress ◽  
Finite Element Analysis ◽  
Stress Field ◽  
Compressive Residual Stress ◽  
Laser Shock Peening ◽  
Curved Surface ◽  
Laser Shock ◽  
Residual Stress Field ◽  
Element Analysis ◽  
Shock Peening

Laser shock peening (LSP) was employed to squeeze compressive residual stress (CRS) into the curved surface of the round rod with diameter of 16[Formula: see text]mm. The residual stress field was induced by nine laser shots irradiating at different locations along the specified path. The developing process of the residual stress field was investigated with finite element analysis, and the corresponding experiments were also carried out to validate the calculated results. Results demonstrate that multiple LSP with 50% overlapping rate can result in residual stress field with the maximum CRS varying from 155.2[Formula: see text]MPa to 198.8[Formula: see text]MPa along the direction of the rod axis. The peened surface appears wavy in shape and the maximum depth of plastic deformation in the curved surface is 13.41[Formula: see text][Formula: see text]m. The value of surface roughness increases from 3.87[Formula: see text][Formula: see text]m to 4.65[Formula: see text][Formula: see text]m.

scholarly journals Residual stress in geometric features subjected to laser shock peening

2014 ◽  
Vol 229 (11) ◽  
pp. 1923-1938 ◽  
Author(s):  
M Achintha ◽  
D Nowell
Keyword(s):  
Residual Stress ◽  
Stress Field ◽  
Structural Integrity ◽  
Laser Shock Peening ◽  
Geometric Features ◽  
Laser Shock ◽  
Computationally Efficient ◽  
Residual Stress Field ◽  
Subsequent Performance ◽  
Shock Peening

This article reports selected findings from a collaborative research study into the fundamental understanding of laser shock peening (LSP), when applied to key airframe and aero-engine alloys. The analyses developed include explicit simulations of the peening process together with a simpler eigenstrain approach, which may be used to provide an approximation to the residual stress field in a number of geometries. These are chosen to represent parts of structural components under conditions relevant to service applications. The article shows that the eigenstrain approach can provide good approximations to the stress field in most circumstances and may provide a computationally efficient tool for exploring different peening strategies. Both explicit and eigenstrain results demonstrate that the interaction between the LSP process and geometric features is important for understanding the subsequent performance of components. Particularly relevant for engineering applications is that not all instances of LSP application may provide an improvement in structural integrity.

scholarly journals Strengthening effect of laser shock peening on 7075-T6 aviation aluminum alloy

2020 ◽  
Vol 12 (8) ◽  
pp. 168781402095217
Author(s):  
Junhao Zhang ◽  
Xiuquan Cheng ◽  
Qinxiang Xia ◽  
Chang Yan
Keyword(s):  
Residual Stress ◽  
Aluminum Alloy ◽  
Shot Peening ◽  
Strain Distribution ◽  
Equivalent Strain ◽  
Laser Shock Peening ◽  
Strengthening Effect ◽  
Laser Shock ◽  
Shock Peening ◽  
Overlap Ratio

The strengthening effect and uniformity of residual stress and strain of 7075-T6 aviation aluminum after laser shock peening were investigated. The finite element simulation model of laser shot peening on 7075-T6 aviation aluminum alloy was established and verified. On this basis and combined with experiment, the microstructure, residual stress distribution and equivalent strain distribution of 7075-T6 aviation aluminum alloy after laser shock peening were studied. An index U for evaluating the strain uniformity in the peened area was proposed based on the statistical processing of the equivalent strain distribution in the peened area. The results show that the average grain size on the peened surface of the specimen was refined to 20–30 μm after LSP, and a residual compressive stress layer with thickness of about 0.5 mm was induced on the surface. Grain refinement and residual compressive stress can promote the strength and fatigue properties of 7075-T6 aviation aluminum alloy. The minimum value of U is obtained in the 6 × 6 spot array (the corresponding overlap ratio is 58%), which suggest that the most uniform deformation peened area can be obtained by using 58% overlap ratio in the laser shot peening process, which can avoid stress concentration and improve fatigue life.

Fatigue Life Recovery via Laser Shock Peening in Mechanically Damaged Aluminium Sheet; Experiments and Prediction Models

2014 ◽  
Vol 891-892 ◽  
pp. 980-985 ◽  
Author(s):  
Niall Smyth ◽  
Philip E. Irving
Keyword(s):  
Residual Stress ◽  
Fatigue Life ◽  
Prediction Models ◽  
Load Cycle ◽  
Laser Shock Peening ◽  
Stress Fields ◽  
Hole Drilling ◽  
Laser Shock ◽  
Aluminium Sheet ◽  
Shock Peening

This paper reports the effectiveness of residual stress fields induced by laser shock peening (LSP) to recover pristine fatigue life. Scratches 50 and 150 μm deep with 5 μm root radii were introduced into samples of 2024-T351 aluminium sheet 2 mm thick using a diamond tipped tool. LSP was applied along the scratch in a band 5 mm wide. Residual stress fields induced were measured using incremental hole drilling. Compressive residual stress at the surface was-78 MPa increasing to-204 MPa at a depth of 220 μm. Fatigue tests were performed on peened, unpeened, pristine and scribed samples. Scratches reduced fatigue lives by factors up to 22 and LSP restored 74% of pristine life. Unpeened samples fractured at the scratches however peened samples did not fracture at the scratches but instead on the untreated rear face of the samples. Crack initiation still occurred at the root of the scribes on or close to the first load cycle in both peened and unpeened samples. In peened samples the crack at the root of the scribe did not progress to failure, suggesting that residual stress did not affect initiation behaviour but instead FCGR. A residual stress model is presented to predict crack behaviour in peened samples.

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