METHOD FOR REPAIR OF GAS TURBINE BLADES MADE OF NICKEL AND COBALT ALLOYS

FIELD: technological processes, metal working. ^ SUBSTANCE: invention is related to the field of machine building and may be used in repair of gas turbine hot path components: segments of nozzle set, nozzle and rotor blades of aviation, naval and power gas turbine engines. In order to produce areas of fusing and fused material with minimum defect by improvement of weldability, and also to increase blade performance characteristics, method includes thermal treatment with heating up to curing temperature, curing at this temperature, cooling, restoration of damaged sections of blade by means of metal fusing or welding, at that heating is done in vacuum up to temperature of 200-950C, and curing at this temperature is done in vacuum for at least 2 hours until degassing is over and dislocation structure of metal is restored. After welding mechanical processing is carried out, then microbeads are applied for strengthening, then ion implantation is carried out, as well as post-implantation treatment. Ions used for implantation are ions of Cr, Y, Yb, C, B, Zr or their combination. After implantation protective coating is applied using MeCrAlY, where Me - Ni, Co, NiCo, or Ni-Pt-Al, by ion-plasma method or electron-ray evaporation in vacuum. Layer of ceramic material with thickness of 20-300 mcm is applied on layer of coating; ceramic layer material is ZrO2-Y2O3, at that ZrO2-Y2O3 may be used in ratio of Y2O3 - 5...9 wt %, ZrO2 - the rest. ^ EFFECT: development of efficient method for repair of gas turbine hot path components. ^ 20 cl, 1 ex, 3 tbl