International Journal of Fatigue

Detected weld defect collected as part of weld quality programme of two newbuilding cruise ships. The defects are detected by non-destructive testing. The data includes material thickness, hull area, NDT method used, type of defect and defect lengths. The joint are all butt joints.

This study investigated the effects of the ‘as-built’ condition on the fatigue properties of an AlSi10Mg aluminium alloy manufactured by Selective Laser Melting (SLM) in different orientations. The results showed a moderate correlation between defects/surface features at the fracture origin and the roughness measurements. On the other hand, a fatigue strength analysis based on the size of features at fracture origin and residual stress just below the surface proved to be successful. Although considering the synergistic effect of different variables increased the scatter in fatigue life data points, a fatigue strength model including short crack effect and residual stresses made it possible to estimate the EIFS close to the real critical features. This dataset contains the full details of experimental data for the paper: "Fatigue strength assessment of “as built” AlSi10Mg manufactured by SLM with different build orientations" by: S. Beretta , M. Gargourimotlagh , S. Foletti , A. du Plessis , M. Riccio International Journal of Fatigue 139 (2020) 105737 https://doi.org/10.1016/j.ijfatigue.2020.105737

All data

Experimental Test results

The data includes all necessary information for repeating the calculations, such as the specimen diameters, force amplitudes, β angles and experimental fatigue lives N_exp, are included. The registered force amplitude histories for all specimens subjected to variable-amplitude loading are stored.

The file contains the entire set of experimental data obtained in the work: Characterisation and analysis of transverse crack-induced delamination in cross-ply composite laminates under fatigue loadings. The meaning of the symbols is reported in the same paper. Abstract of the work: The delamination growth represents one of the main phenomena involved in the fatigue damage evolution in composite laminates. With the aim of characterising qualitatively and quantitatively this mechanism and its interaction with the other damage modes occurring during the fatigue life, an experimental campaign was carried out on glass/epoxy infused laminates. Two lay-ups were adopted, namely [02/904]s and [0/902]s. The damage evolution was characterised at the macro and micro-scales. The adopted macro-scale damage indicators were the laminate stiffness drop, the crack density and the delamination ratio, of which the evolution along with the fatigue cycles is shown. Damage evolution and final failure were seen to be sensitive to scale effect. Micro-scale edge observations were useful to understand the interaction between transverse cracks, delamination and fibre failure, all these mechanisms concurring in the laminate final failure.

1. Strain distribution along steel tude when subjected to a monotonic load for a bolting specimen. 2. AE data for bolting systems when subjected to cyclic loading. 3. MTS captured data for a bolts in regards to load-time relationship when subjected to cyclic loading.

The fatigue properties of gas metal arc welded and friction stir welded assemblies made of aluminum alloy 6061-T6 structural extrusions were examined. The mechanical performances of welded joints were obtained using uniaxial tensile and force-controlled constant amplitude axial fatigue tests. Microstructural and fractographic analyses were conducted to document the influence of the process on microstructure evolution, fatigue crack initiation sites, and propagation mechanisms leading to the final rupture of the assemblies. Microhardness measurements and digital image correlation techniques paired with interrupted tensile tests were also used to investigate the complex heterogeneous local mechanical behavior and to highlight the fact that the crack initiation mechanism was driven by the microstructural state of the joint as well as by the structural-contact-fretting occurring at the notch root. The corresponding fatigue strengths at 2 million and 10 million cycles were evaluated respectively at 10% and 20% higher for friction stir welded assemblies versus gas metal arc welded assemblies. Fractographic analyses revealed that the fatigue cracks were initiated from microstructural features (pores for the GMAW configuration and banded structure on the crown side for the FSW configuration), or from large sub-surface grains in a shallow region below the structural-contact-fretting occurring at the notch root.

This paper investigates the strain controlled fatigue and cyclic deformation behaviour of a wire + arc additive manufactured Ti-6Al-4V alloy in the as-built condition. Higher local heat input used to build the material exhibited a coarser parent columnar β grain structure along with a coarser transformation microstructure compared to other additive manufactured Ti-6Al-4V. Test specimens were manufactured in horizontal and vertical orientations with respect to the deposited layers. Property isotropy was observed at lower applied strain values. When the strain amplitude was above 0.6%, the vertical samples, where the loading axis was in parallel with the parent columnar β grains, showed marginally higher fatigue strength owing to larger plastic deformation. Moreover, higher cyclic softening ratio by a factor of two was measured in the vertical samples when the strain amplitude was above 0.6%. No porosity defects were found in the material. Cracks were initiated from α lath due to cyclic slip localisation.

This paper investigates the strain controlled fatigue and cyclic deformation behaviour of a wire + arc additive manufactured Ti-6Al-4V alloy in the as-built condition. Higher local heat input used to build the material exhibited a coarser parent columnar β grain structure along with a coarser transformation microstructure compared to other additive manufactured Ti-6Al-4V. Test specimens were manufactured in horizontal and vertical orientations with respect to the deposited layers. Property isotropy was observed at lower applied strain values. When the strain amplitude was above 0.6%, the vertical samples, where the loading axis was in parallel with the parent columnar β grains, showed marginally higher fatigue strength owing to larger plastic deformation. Moreover, higher cyclic softening ratio by a factor of two was measured in the vertical samples when the strain amplitude was above 0.6%. No porosity defects were found in the material. Cracks were initiated from α lath due to cyclic slip localisation.