FIELD: application of protective coatings; applicable in manufacture of turbine blades, mainly, of gas turbine engines. SUBSTANCE: the offered method includes successive application of multicomponent aluminum-containing metal and ceramic layers. Metal layer is applied in vacuum followed by vacuum homogenizing annealing. After application of ceramic layer 70-300 mcm thick, the product is subjected to treatment by high-temperature pulsed plasma with subsequent oxidizing roasting at temperature of not less than 1050 C for, at least, 5 h. EFFECT: higher efficiency. 7 dwg
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