FIELD: machine building.
SUBSTANCE: method of application of multilayer thermal-protective coating on gas-turbine engine details includes application of the main metal heat-resistant underlayer and application by a plasma spraying method of additional metal heat-resistant underlayer and top ceramic thermal-protective layer. The main metal heat-resistant underlayer is applied using the method of high-speed gas-flame spaying of the layer with the thickness 20-150 mcm of MCrAlY system alloy, where M=Ni, Co, Fe. The additional metal heat-resistant underlayer is applied using MCrAlY system alloy, where M=Ni, Co, Fe, with the thickness 10-50 mcm. The top ceramic thermal-protective layer is applied using the material based on zirconium oxide which is partially stabilised 6-8 wt % with yttrium oxide with the thickness 120-750 microns.
EFFECT: protection against high temperature effects, erosion and corrosion by formation of durable thermal-protective coatings.
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