METHOD OF REPAIRING SURFACE DEFECTS OF GAS TURBINE BLADE BODY Russian patent published in 2011 - IPC B23P6/00 B23K1/05 

FIELD: process engineering.

SUBSTANCE: invention may be used for repair of parts made from high-alloy refractory steels and alloys in aircraft engineering, ship building and power engineering. Turbine blade body is, first, conditioned for powder to be applied thereon by microplasma evaporation, said powder containing 70% of nickel-based filler and 30% of high-temperature solder. High-temperature soldering is carried out. Blade body section, a transverse strip covering section to be repaired, is heated by scanning electron beam to solder solidus temperature all over blade thickness. Then, repaired section is heated to temperature 100°C-120°C higher than solder solidus temperature and said temperature is maintained in pulsed mode for 1 minute. Note here that intermittent heating is performed for 5-7 s and temperature is reduced to 1000°C and maintained for 10-15 s.

EFFECT: complete recovery of parts shape, higher efficiency of repair and longer life of recovered parts.

2 cl, 1 dwg