FIELD: engine building.
SUBSTANCE: present invention relates to the field of protective coatings for heat insulation of parts of aviation or ground gas turbine engines operating under conditions of high temperatures. Proposed part (20) with coating for a gas turbine engine contains substrate (21) and at least one calcium-magnesium aluminosilicates (hereinafter – CMAS) protective layer (22) on substrate (21). Layer (22) contains first phase (220) of calcium-magnesium aluminosilicates (CMAS) protective material capable of forming a phase of an apatite or anorthite type in the presence of calcium-magnesium aluminosilicates (CMAS), and second phase (221) containing particles of at least one silicate of rear earth element REa dispersed in the first phase.
EFFECT: invention allows for extending the service life of the protective anti-CMAS layer formed on the surface of the part of the gas turbine engine.
9 cl, 8 dwg
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