FIELD: mechanical engineering; turbines.
SUBSTANCE: proposed turbine blade of gas-turbine engine has hollow airfoil portion, lock and multilayer heat-insulating coating of airfoil portion consists of metal underlayer with air channels and with applied porous ceramic layer. Upper metal layer is applied to ceramic layer from outside. Air channels are made in form of coaxial holes part of which passes through wall of blade airfoil portion, metal underlayer and ceramic layer, and part, through ceramic and upper metal layers forming pneumatic coupling between inner space of blade and its surface through porous ceramic layer. Ceramic layer is formed by ceramic columnar fibers. Each metal layer applied to blade airfoil portion is arranged so that layer with lower linear expansion coefficient is located in zone of action of higher temperature, and layer with larger linear expansion coefficient is located in zone of action lower temperature.
EFFECT: increased service life of blade.
4 cl, 3 dwg
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