Low-plastic burnishing impact on the surface layer parameters of samples of the gas turbine engine compressor blades made of titanium alloy

Hydro-shot peening is most often used to increase strength and durability of the gas turbine engine blade airfoils, creates a favorable diagram of compressive residual stresses on the airfoil surface and makes it possible to increase the endurance limit up to 19%. However, the compressive residual stresses depth with this peening method is not more than 0.2 mm, which is not enough to ensure the required fatigue strength level of the blades in case of damage to the nick-type edges due to foreign objects attacking to the depth of 1 mm. To increase the blade resistance against foreign objects, the paper proposes a promising peening method, i.e. the low-plasticity burnishing. To evaluate efficiency of each method, an object was selected, it was a titanium blade of the gas turbine engine compressor first stage. The blade airfoil edge section with the width of 5 mm was subjected to the low-plasticity burnishing. It was established that the blade airfoil surface after such peening satisfied requirements of the design documentation in roughness. The compressive residual stresses depth in the low-plasticity burnishing exceeding 0.3 mm turned out to be lower than in the hydro-shot peening. The blade microstructure was not changing after peening, and their surface micro-relief in the peening zone consisted of many depressions in the form of parallel tracks 0.1 mm wide. The blade trailing edge turned out to be highly deformed with waviness and thinning, which could be explained by incorrect selection of the peening mode.
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