Retardation of fatigue crack growth in aircraft aluminium alloys via laser heating – Experimental proof of concept

Schnubel, D.; Horstmann, Μ.; Ventzke, Volker; Riekehr, Stefan; Staron, Peter; Fischer, Torben; Huber, N.

doi:10.1016/j.msea.2012.02.094

Cited by 28 publications

(25 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the following sections, a stepwise validation of the numerical simulation results is conducted on the basis of experimental data [1]. Where needed, the lateral extension of the heating zone (HZ), the heat-affected zone (HAZ) and the areas with base material properties (BM) estimated on basis of the measured micro hardness (see [1] and Fig.…”

Section: Resultsmentioning

confidence: 99%

“…Where needed, the lateral extension of the heating zone (HZ), the heat-affected zone (HAZ) and the areas with base material properties (BM) estimated on basis of the measured micro hardness (see [1] and Fig. 8) are indicated in the figures.…”

Section: Resultsmentioning

confidence: 99%

“…As was demonstrated in an experimental study on the laser heating of AA2198-T8 specimens [1], residual stresses induced in metallic structures can have a significant impact on fatigue crack growth. Considering the growing interest in advanced manufacturing technologies for the production of metallic integral airframe structures, such as laser beam welding or friction stir welding [2,3], this issue gained special attention [4][5][6] because residual stresses are an unavoidable side effect of these technologies [7,8].…”

Section: Introductionmentioning

confidence: 83%

“…Walker Equation σ yy [MPa] x,a y Figure 1: Steps in the extended approach with temperature field T (x, y, z, t), residual stress field σ(x, y, z, t), displacement field u(x, y, z, t), cooling time t cool , crack length a, applied load F appl , total stress intensity factor K tot (a, F appl ), total stress intensity factor range ∆K tot (a), total stress intensity ratio R tot (a) and fatigue crack growth rate da/dN . : Sketch of the specimen/model dimensions and coordinate system definitions as used also in the experimental study [1]. All measures are given in millimetres.…”

Section: Mechanical Fe Analysismentioning

confidence: 99%

“…Figure 2 shows the specimen geometry and coordinate system, which are identical to those used in [1], where the results of the experimental investigation on laser heating of AA2198-T8 C(T)100 specimens were presented in detail.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Retardation of fatigue crack growth in aircraft aluminium alloys via laser heating – Numerical prediction of fatigue crack growth

Schnubel

Huber

2012

Computational Materials Science

Self Cite

View full text Add to dashboard Cite

The presented study discusses a quantitative numerical approach for predicting the fatigue crack growth in AA2198-T8 C(T)100 specimens containing one line of laser heating. By heating the with a defocused laser residual stresses are introduced and the fatigue crack growth is retarded. The developed methodology, which investigates coupling of the structural process simulation, the extraction of the total stress intensity K tot and the prediction of the resulting fatigue crack growth rates by an empirical crack growth law is stepwise validated on the basis of experimental results. The prediction is found to be highly accurate. Special attention needs to be given to the quality of the process simulation results because the prediction of fatigue crack growth is highly sensitive to the results obtained in this simulation step.

show abstract

Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 83%

Section: Mechanical Fe Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Retardation of fatigue crack growth in aircraft aluminium alloys via laser heating – Numerical prediction of fatigue crack growth

Schnubel

Huber

2012

Computational Materials Science

Self Cite

View full text Add to dashboard Cite

show abstract

Effects of shot peening and artificial surface defects on fatigue properties of 50CrV4 steel

Saklakoğlu

Bolouri

İrizalp

et al. 2021

Int J Adv Manuf Technol

View full text Add to dashboard Cite

Shot peening processes are commonly used for improving the fatigue properties of steels. Shot peening introduces a compressive residual stress field in the near surface of steel, which can reduce or stop the growth of fatigue cracks and improve fatigue properties. This study experimentally investigated the effect of shot peening on the fatigue properties of 50CrV4 steel alloys with different artificial surface defects. Drilling tools were used to introduce different artificial defects with root radii of 0.585 mm and 0.895 mm on the surface of unpeened samples. The shot peening was applied to the drilled and undrilled samples. Scanning electron microscopy (SEM) observations, micro-hardness and X-ray diffraction residual stress measurements were conducted to analyse the characteristics of the shot-peened and unpeened samples. The results show that the shot peening leads to the transformation of the retained austenite to martensite in the near-surface microstructure. The hardness rates of the surface and near surface both increase by 8% after the shot peening. The peened samples exhibit compressive residual stresses with a high degree of isotropy in the near surface. The fatigue properties of samples were experimentally evaluated by conducting 3-point bending tests. The results indicate that the shot peening improves the fatigue life of drilled and undrilled samples. For the defects with the root radius of 0.895 mm, the shot peening leads to a 500% improvement in the fatigue life compared to unpeened samples regardless of defect depth. For the defects with the root radius of 0.585 mm, the improvement in fatigue life is 40% for the defect depth of 0.2 mm compared to unpeened samples. The improvement increases to 60% and 200% by increasing the defect depths to 0.4 mm and 0.6 mm. The fatigue properties are linked to the changes in the features of defects mainly caused by the deformation hardening and compressive residual stress after shot peening.

show abstract

Effects of Laser Shock Processing on Fatigue Crack Growth in Ti-17 Titanium Alloy

Huang

Zhu

Guo

et al. 2017

J. of Materi Eng and Perform

View full text Add to dashboard Cite

The effects of laser shock processing (LSP) on the fatigue crack properties of Ti-17 titanium alloy are investigated. Surfaces on either side of a fatigue slot are subjected to LSP. The residual stress of the irradiated surface is measured by x-ray diffraction measurement and fatigue crack growth testing of the treated and untreated specimens. The fatigue fracture morphology and microstructure are examined by scanning electron microscopy and transmission electron microscopy. Proliferation and tangles of dislocations occur in the Ti-17, and the density of dislocation increases after the LSP treatment. The fine spacing of the fatigue striations indicates that LSP produces residual compressive stress on the irradiated surfaces which can delay micro-crack formation and expansion. Consequently, the fatigue propagation life of the specimen increases considerably after LSP.

show abstract

Retardation of fatigue crack growth in aircraft aluminium alloys via laser heating – Experimental proof of concept

Cited by 28 publications

References 20 publications

Retardation of fatigue crack growth in aircraft aluminium alloys via laser heating – Numerical prediction of fatigue crack growth

Retardation of fatigue crack growth in aircraft aluminium alloys via laser heating – Numerical prediction of fatigue crack growth

Effects of shot peening and artificial surface defects on fatigue properties of 50CrV4 steel

Effects of Laser Shock Processing on Fatigue Crack Growth in Ti-17 Titanium Alloy

Contact Info

Product

Resources

About