FORMATION METHOD OF THERMAL PROTECTIVE COATING ON PARTS OF GAS TURBINES FROM NICKEL AND COBALT ALLOYS Russian patent published in 2013 - IPC C23C14/16 F01D5/28 

FIELD: machine building.

SUBSTANCE: formation method of a thermal protective coating on parts of gas turbines from nickel or cobalt alloys involves application of a thermal resistant underlayer and formation on the underlayer of a ceramic layer from zirconium dioxide stabilised with yttrium oxide. Thermal resistant layer with thickness of 10 to 30 mcm is applied by ion-plasma method; then, a layer with thickness of 30 to 500 mcm from alloy of zirconium with yttrium with yttrium content of 5…9 wt % is applied. Then, the applied zirconium layer with yttrium is subject to micro-arc oxidation throughout the thickness, and thermal resistant layer to the thickness of 1 to 3 mcm. Thermal resistant underlayer is formed from the alloy containing the following, wt %: Cr - 18% to 34%; Al - 3% to 16%; Y - 0.2% to 0.7%; Ni is the rest, or Cr - 18% to 34%, Al - 3% to 16%, Y - 0.2% to 0.7%, Co - 16% to 30%, Ni is the rest, and their combinations. Micro-arc oxidation is performed in the environment of 3-5% of water solution of ammonium phosphate when positive potential of 300 to 1100 V is being supplied to the coated part.

EFFECT: obtaining thermal protective coating having high operating characteristics and increased adhesion strength.

20 cl, 1 dwg, 2 tbl