METHOD FOR LASER IMPACT PROCESSING OF THIN EDGE OF BLADE MADE OF TITANIUM ALLOY OF GAS TURBINE ENGINE COMPRESSOR Russian patent published in 2025 - IPC B23K26/356 B23K103/14 

FIELD: performing operations; mechanical engineering.

SUBSTANCE: invention relates to hardening of a thin edge of a compressor blade of a gas turbine engine. Prior to laser impact treatment, a protective coating is applied on the blade edge. Blade edge is subjected to laser impact treatment by laser beam with cross-section profile in the form of square with side of 1 mm, with arrangement of laser beam imprints butt-to-joint without overlapping in one layer. Laser impact action is performed in the form of one row of laser impacts in the direction from the end part of the blade aerofoil to its root part. Laser pulse energy is 1 J, laser radiation power density is 10 GW/cm² with pulse duration of 10 ns.

EFFECT: method provides the formation of a homogeneous field of compressive residual stresses at depth of 1 mm in a thin edge of a GTE blade with one processing layer with simultaneous elimination of tensile residual stress zones, which increases fatigue life of the blade and increases its cyclic durability.

3 cl, 10 dwg, 1 tbl, 2 ex