LSPwC influence on the surface layer parameters of the titanium alloy GTE compressor blades

Hydro-shot peening is most often used to increase strength and durability of the gas turbine engine (GTE) blade airfoils and creates a favorable diagram of the residual compressive stresses on its surface. However, their depth is no more than 0.2 mm, which is not sufficient to ensure the required level of the blade fatigue strength with the edges damaged by foreign objects entering to a depth of 1.0 mm. To increase the blades’ durability, the paper considers the laser shock peening without coating (LSPwC). Using an example of the titanium blade of the GTE compressor first stage, it studies the influence of this peening method on the blade airfoil geometric characteristics and surface layer. The blade airfoil edge section with the width of 5 mm was subjected to LSPwC. It was established that the blade airfoil surface after hardening was not meeting requirements of the design documentation in roughness. It became necessary to introduce the finishing surface treatment to remove the melted layer with a depth of 2 to 6 microns. Melting areas were located mainly in the center of the laser shock spots. Surface melting was accompanied by multiple cracking. No microstructural alterations were found under the melted layer. Depth of the compressive residual stresses was not exceeding 0.3 mm, which was superior to the hydro-shot peening. Peening the blade airfoil edge led to its deformation, which was increasing from the tail to the blade tip. The most significant deformation was observed at the blade’s trailing edge and peripheral zone. In this regard, it is required to continue developing the peening modes to meet the design documentation requirements.
EDN: JEEASU, https://elibrary/jeeasu

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