METHOD OF REPAIRING AIRFOIL OF COOLED WORKING BLADES OF GAS TURBINE ENGINES FROM HEAT-RESISTANT ALLOYS BY LASER POWDER SURFACING Russian patent published in 2024 - IPC B23K26/144 B23K26/342 B22D19/10 B23P6/00 

FIELD: machine building.

SUBSTANCE: invention relates to the technology of repair of cooled working blades of gas turbine engines from heat-resistant alloys by laser powder deposition. Input control and control of main dimensions of blades is performed. Thermal barrier sublayers and ceramic coating are removed, and then thermal treatment of turbine blade is performed. Defects are sampled in the area of the flange and the leading edge of the blade airfoil and the blade is installed and fixed in a vertical position. Blade airfoil flange is restored by laser surfacing of the blade airfoil flange with a laser beam with diameter of 0.8–1.5 mm with simultaneous supply of a gas-powder jet of surfacing material with a flow rate of 2–8 g/min, wherein laser radiation power makes 200–500 W, laser surfacing rate makes 3–10 mm/s, and shielding gas flow rate makes 12 l/min. Then blade is inclined by 90° and the leading edge of the blade airfoil is restored by laser surfacing in a pulsed mode with a laser beam with diameter of 1–2 mm, with simultaneous supply of a gas-powder jet of surfacing material with a flow rate of 5–10 g/min, wherein laser radiation power is 400–800 W, pulse time is 0.15–0.3 s, and protective gas flow is 12 l/min. Thermal and mechanical treatment is performed, thermal barrier and ceramic layers are applied, cooling holes are opened and 3D laser scanning of the turbine blade is performed.

EFFECT: increasing productivity when repairing working blades made of a heat-resistant nickel alloy, as well as the possibility of repairing the leading edge of the turbine blade airfoil without the possibility of cracks forming in it.

3 cl