Influence of laser shock peening parameters on the distribution of residual stresses in the edge of a titanium alloy compressor blade

The paper studies influence of the laser shock peening strategy on the residual compressive stress distribution in the titanium alloy compressor blade airfoil edge. Laser shock peening is performed by a laser beam without spot overlap in a single pass on both sides of the edge. The paper considers sequential and simultaneous laser shock peening at different radiation power densities and laser spot overlap coefficients. Simulation includes two stages: simulating the elastic-plastic wave propagation based on the Johnson-Cook constitutive relation and static computation of the residual stress distribution. The paper proposes an algorithm for developing recommendations for assigning the technological parameters in the laser shock peening of a titanium alloy blade. It shows that simultaneous two-sided laser shock peening of a blade provides a more uniform distribution of the residual compressive stresses over the blade edge cross-section in a single pass. The laser spot size changes the area of the high residual compressive stresses, which should be avoided since they are a potential source of the crack initiation. Increasing the laser pulse energy causes induction of the residual tensile stresses in the blade airfoil edge radius with a spot side size of 2 mm. The paper determines a permissible range of the radiation power density for providing the residual compressive stresses in the blade airfoil edge.
EDN: UNCSOO, https://elibrary/uncsoo

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