Cooled turbine rotor blade

Abstract

A cooled turbine rotor blade for a gas turbine engine includes an airfoil and a profiled root radially inward of the airfoil, a platform between the airfoil and the root, and a cooling air supply channel extending through the platform into an interior of the airfoil and therein up to an outlet opening. An inlet opening of the cooling air supply channel is located at the rear side of the rotor blade, and an inlet part of the cooling air supply channel with the inlet opening is angled into the direction of rotation of the rotor blade and curved into a radially outward direction. Further, a rotor-stator stage for a gas turbine includes a rotor blade as above, and an air cavity radially inwards of sealing features between the rotor stage and a neighboring downstream stator stage to form a source of cooling air for the rotor blade.

1 . A cooled turbine rotor blade for a gas turbine engine, in particular an aircraft turbine engine, comprising an aerofoil portion and a profiled root portion radially inward of the aerofoil portion in installed state, a platform between the aerofoil portion and the root portion, and at least one cooling air supply channel that extends through the platform into the interior of the aerofoil portion and therein up to at least one outlet opening, wherein an inlet opening of the cooling air supply channel is located at the rear side of the rotor blade, and an inlet part of the cooling air supply channel with the inlet opening is angled into the direction of rotation of the rotor blade and curved into a radially outward direction. 
     
     
         2 . The cooled turbine rotor blade as claimed in  claim 1 , wherein the inlet part of the cooling air supply channel provides a serpentine design. 
     
     
         3 . The cooled turbine rotor blade as claimed in  claim 1 , wherein the inlet part of the cooling air supply channel forms at least substantially a S-shape. 
     
     
         4 . The cooled turbine rotor blade as claimed in  claim 1 , wherein the inlet part of the cooling air supply channel comprises a geometry that forms a compressor diffuser. 
     
     
         5 . The cooled turbine rotor blade as claimed in  claim 1 , wherein the inlet opening of the cooling air supply channel is located at the platform at its radially inwards side. 
     
     
         6 . The cooled turbine rotor blade as claimed in  claim 1 , wherein the platform provides at the rear side of the rotor blade a rearward projecting overhang portion, wherein the inlet opening of the cooling air supply channel is located radially inwards of the overhang portion. 
     
     
         7 . The cooled turbine rotor blade as claimed in  claim 1 , wherein at least one outlet opening of the cooling air supply channel is located at a tip of the aerofoil portion. 
     
     
         8 . The cooled turbine rotor blade as claimed in  claim 1 , wherein at least one cooling air supply channel is extending radially straight up in the aerofoil portion. 
     
     
         9 . The cooled turbine rotor blade as claimed in  claim 1 , wherein the cooling air supply channel is configured as a multipass passage system. 
     
     
         10 . A rotor-stator stage for a gas turbine, wherein the rotor stage comprises at least one rotor blade according to  claim 1 , and an air cavity radially inwards of sealing features between the rotor stage and a neighbouring downstream stator stage forms a source for feeding the rotor blade with cooling air.