METHOD FOR APPLICATION OF HEAT-RESISTANT COATING ON TURBINE BLADES OF HIGH-LOAD ENGINE Russian patent published in 2019 - IPC C23C28/00 C23C14/06 C23C14/24 

FIELD: technological processes.

SUBSTANCE: invention relates to a method of applying heat-resistant coating on turbine blades operating at high temperatures in high-load engines. Multilayer coating is applied. Alloy of the first layer of the heat-resistant coating is an alloy containing Ni-Co-Cr-Al-Y-Ta-W-Hf. Second layer consists of powder mixture containing Cr-Al, third layer – ceramics ZrO₂-Y₂O₄. Additionally, a barrier layer of Ni-Co-Cr-Al-Y-based alloy is applied on ceramic layer by electron-beam evaporation and condensation in vacuum with subsequent diffusion annealing. First layer of heat-resistant coating is applied by vacuum-plasma method, which together with powder mixture after application of second layer of coating is subjected to thermo-vacuum treatment until diffusion saturation with chromium and aluminum of coating surface of first layer.

EFFECT: use of the method increases coating resistance by delamination by 47 %, and heat resistance by the number of cycles (heating-cooling) by 37 %, and consequently, increases service life of the blade in a high-pressure gas turbine engine.

1 cl, 3 dwg