FIELD: machine building.
SUBSTANCE: turbine blade of an aircraft gas turbine engine comprises a cooling circuit for its airfoil, in which cavities connected in series are interconnected so that an air stream flows radially outward along the pressure-face wall inside the pressure-face cavities and radially inward along the suction-face wall inside the suction-face cavity separated from the pressure-face cavities by the inner airfoil wall. At least one suction-face cavity comprises at least one reflector protruding from the suction-face wall in the direction of the first inner wall of the airfoil. Reflector has a concavity oriented radially outward and in the direction of the side wall of the suction-face cavity, located on the side of the pressure-face cavity, with which the air outlet section of at least one suction-face cavity is connected.
EFFECT: invention aims to improve cooling by reducing uneven cooling.
10 cl, 8 dwg
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