Abstract
AbstractThis study deals with fatigue crack growth prediction for thin sheet AA2024 specimens with residual stresses introduced through laser shock peening and laser heating treatments. Different weight functions are used to calculate the stress intensity factor due to the presence of residual stresses. A superposition principle is used by calculating the total stress intensity factor considering the applied loads and residual stresses. The fatigue crack growth is predicted using the Paris' law based on the effective stress intensity factor range, in that the effect of residual stresses is considered by changing the total stress intensity factor ratio. It is concluded, that weight functions are a powerful tool to predict fatigue crack growth in AA2024 containing residual stress fields, as long as the gradient in the loading direction, as induced by laser shock peening and laser heating, is moderate.
Highlights
As fatigue is the predominant failure mode in an aircraft,[1,2] different local engineering techniques have been developed to improve the fatigue life of safetycritical components and structures.[3]
The residual stress maps for the laser shock peening (LSP)-treated specimen with 5Â layers are shown in Figure 4A,B as twodimensional plots, where depicted stresses correspond to the values averaged through the thickness
The application of the prediction methodology for the fatigue crack growth (FCG) in a residual stress field was investigated with the help of experimental data from specimens that were treated with laser heating (LH) and LSP in different geometrical configurations
Summary
As fatigue is the predominant failure mode in an aircraft,[1,2] different local engineering techniques have been developed to improve the fatigue life of safetycritical components and structures.[3]. The experimental results regarding the residual stress fields induced and related FCG behaviors of the specimens with different geometries of LH treatments as well as of the LSP-treated specimens were used from previous studies of the authors.[8,11]
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