FIELD: mechanical engineering and metallurgy. SUBSTANCE: method, applicable in aviation and power gas turbine engineering for protection of turbine blades against high-temperature oxidation and corrosion, involves vacuum arc- mediated deposition of metal (titanium, chromium, niobium, tantalum, tungsten, vanadium, or hafnium) carbide layer 1 to 6 mcm thick followed by successive deposition of refractory nickel-based -alloy layer and external aluminum alloy layer. Finally, coated blades are subjected to vacuum annealing. EFFECT: increased capacity of coating within a wide temperature range (between 850 and 1250 C).
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