Laser shock peening treatment to control and moderate fatigue crack growth in aircraft structure based on residual stress engineering approach

Laser Shock Peening (LSP) is a surface enhancement treatment which induces a significant layer of beneficial compressive residual stresses of up to several mm underneath the surface of metal components in order to improve the detrimental effects of the crack growth behavior rate in it. The aim of this thesis is to predict the crack growth behavior in metallic specimens with one or more stripes which define the compressive residual stress area induced by the Laser Shock Peening treatment. The process was applied as crack retardation stripes perpendicular to the crack propagation direction with the object of slowing down the crack when approaching the peened stripes. The finite element method has been applied to simulate the redistribution of stresses in a cracked model when it is subjected to a tension load and to a compressive residual stress field, and to evaluate the Stress Intensity Factor (SIF) in this condition. Finally, the Afgrow software is used to predict the crack growth behavior of the component following the Laser Shock Peening treatment and to detect the improvement in the fatigue life comparing it to the baseline specimen. An educational internship at the “Research & Technologies Germany – Hamburg” department of AIRBUS helped to achieve knowledge and experience to write this thesis. The main tasks of the thesis are the following: •To up to date Literature Survey related to “Laser Shock Peening in Metallic Structures” •To validate the FE model developed against experimental measurements at coupon level •To develop design of crack growth slowdown in Centered Cracked Tension specimens based on residual stress engineering approach using laser peened strip transversal to the crack path •To evaluate the Stress Intensity Factor values for Centered Cracked Tension specimens after the Laser Shock Peening treatment via Finite Element Analysis •To predict the crack growth behavior in Centered Cracked Tension specimens using as input the SIF values evaluated with the FE simulations •To validate the results by means of experimental tests

Debonding and crack propagation in cracked steel beams strengthened with CFRP and subjected to cyclic loads.

The reinforcement methods used to restore or increase the bearing capacity of metal structures are based on the application of steel plates to be bolted or welded to the original structure, which can cause problems to the integrity of the original structure. These difficulties can be overcome with the introduction of fiber-reinforced composite materials. FRPs are characterized by high strength to weight ratio, and they are very resistant to corrosion. In this dissertation a cracked steel I-beam reinforced with Carbon Fiber-Reinforced Polymer will be studied by performing a numerical evaluation of the structure with the commercial Finite Element Method software ABAQUS. The crack propagation will be computed using XFEM, while the debonding of the reinforcement layer will be found by considering a cohesive contact interface between the beam and the CFRP plate. The results will show the efficiency of the strengthening method in increasing the load carrying capacity of the cracked beam, and in reducing the crack opening of the initial notch.