PROTECTION METHOD OF GAS TURBINE BLADES Russian patent published in 2010 - IPC C23C14/28 

FIELD: machine building.

SUBSTANCE: protection method of gas turbine blades by application of combined heat resistant coating, mainly to surface of gas turbine blade fin made from heat-resistant alloy is proposed. Method involves vacuum deposition of inner coating layer on the basis of nickel, which contains at least cobalt, chrome, aluminium and yttrium, deposition of outer coating layer from alloy on the basis of aluminium, which contains nickel, silica, and boron, and vacuum annealing of blade with coating. Blade fin surface is also treated with flow of glass spherical particles under compressed air pressure of 0.4-0.6 MPa, at least twice- after deposition of inner coating layer and after vacuum annealing is completed. Thickness of inner coating layer is 10-30 mcm. Size of glass spherical particles is 20-250 mcm. After final treatment with flow of glass spherical particles the blade with coating is subject to final vacuum annealing. Vacuum annealing is carried out at temperature of 950-1100°C during 2-4 h.

EFFECT: corrosion resistance of combined coating increases and GTU blade surface life increases.

5 cl, 1 tbl, 4 ex