METHOD OF TURBINE BLADE REPAIR Russian patent published in 2003 - IPC

FIELD: mechanical engineering; applicable in repair of nozzle vanes and blades of aircraft, ship and power gas-turbine engines. SUBSTANCE: method includes removal from blade surface of damaged sections by formation of cylindrical hole whose axis is located from edge of blade for distance amounting up to 0.35-0.45 hole diameter. Damaged sections of blade are built-in by diffusion soldering with insert made of blade material. Cylindrical hole is built-in simultaneously with thermovacuum treatment of blade. Insert may be made with diameter of 10-20 mm. Building-in of cylindrical hole with insert may be made with clearance across diameter of not in excess of 0.12 mm. In repair of hollow blades, material removal corresponding to internal cavity of blade in point of hole may be made on insert. Offered method is applicable in repair of blades made of nickel-base alloys. EFFECT: increased service life of blades by a factor of 1.5-2, reduced consumption of material in repairs. 6 cl, 1 dwg, 2 tbl, 1 ex