FIELD: aviation.
SUBSTANCE: present invention relates to the field of protective coatings for thermal insulation of parts of aircraft or ground-based gas turbine engines operating at high temperatures. The proposed coated part for a gas turbine engine contains substrate (21) and at least one layer (24) protecting against calcium and magnesium aluminosilicates (hereinafter – CMAS) located on this substrate (21). Layer (24) contains first phase (240) of material protective against calcium and magnesium aluminosilicates (CMAS) and second phase (241) containing particles of non-wetting material dispersed in the first phase.
EFFECT: invention makes it possible to extend the service life of the part of the gas turbine engine, containing the layer protecting against CMAS.
9 cl, 7 dwg
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