Effect of Pressure Profile Shape on Residual Stress Distribution during Laser Shock Peening of Titanium Alloy Blade Airfoil Edges

The influence of the pressure pulse profile of a square laser spot with a side size of 3 mm on the distribution of residual compressive stresses on the edge of a compressor blade airfoil made of titanium alloy was studied using mathematical modeling of laser shock peening. The machining was performed by a laser beam without spot overlapping in a single pass on both sides of the blade airfoil edge. The modeling of laser shock peening included two stages. In the first stage, the propagation of elastic-plastic waves was simulated based on the Johnson-Cook constitutive relation, and in the second, a static calculation of the residual stress distribution was performed. The modeling results showed that the inverse pressure pulse profile leads to high surface residual compressive stresses (up to –0.50 relative units), the depth of which does not exceed 0.07 mm. The direct pressure pulse profile ensures a level of residual compressive stresses of –0.21…–0.14 relative units at a depth of up to 0.14 mm. In this case, in the middle of the blade feather edge, a zone with residual tensile stresses reaching 0.06 relative units is formed.

EDN: KMJCVE, https://elibrary/kmjcve

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