COOLED BLADE OF TURBOMACHINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering; gas-turbine engines. SUBSTANCE: proposed cooled blade of turbomachine of gas-turbine engine contains hollow airfoil portion with convex and concave outer surfaces mated through inlet and outlet edges. Concave surface of airfoil portion and zones of inlet edge and outlet edge from side of concave surface are provided with heat protection coating. Length of coating zone on inlet edge of airfoil portion from side of convex surface of aircraft portion along its length does not exceed 0.12 of chord length. Heat protection coating in zone of inlet edge from side of convex surface of airfoil portion and in zone of outlet edge is made with thickness gradually decreasing towards outer surface of airfoil portion. EFFECT: improved reliability and service life of turbomachine cooled blades owing to reduction of temperature gradient between convex and concave surfaces of airfoil portion. 3 cl, 2 dwg