FIELD: application of protective coatings to turbine cooled blades and nozzle vanes of stationary and transportation gas-turbine engines. SUBSTANCE: method includes hydraulic pulse pumping-through of cavities and perforation holes and subsequent application of diffusion coatings. Prior to hydraulic pulse pumping-through, preliminary annealing is effected at temperature of 1000-1050 C for 2-3 h in vacuum or protective atmosphere. EFFECT: increased service life of turbine blades and vanes due to application of uniform protective coating of preset thickness to surfaces of perforation holes and cavities. 1 tbl
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