Cooled Turbine Rotor Blade

Abstract

A cooled turbine rotor blade for a gas turbine which is traversed axially by flow and is equipped with an attachment area and an airfoil profile is provided. Meandering cooling channels with interposed deflecting regions are provided in the interior of the airfoil profile. In the deflecting regions, it is possible to prevent dead water regions, which are generated in the prior art, by virtue of at least one of the ribs running so as to curve towards the leading edge or towards the trailing edge in the region of the airfoil tip. At the same time, an opening is provided in the curvature of the rib. Through this opening a part of the coolant flows in the deflecting region and can pass over into the adjacent cooling duct.

1 .- 6 . (canceled) 
   
   
       7 . A cooled turbine rotor blade for a stationary axial-flow gas turbine, comprising:
 an airfoil profile formed by a suction-side blade and a pressure-side blade wall;   an airfoil tip;   an attachment area from which the airfoil profile extends as far as the airfoil tip;   a plurality of cooling channels which lie adjacent to one another in an interior of the airfoil profile;   a plurality of ribs;   a terminating wall bounding the plurality of cooling channels at the airfoil tip end; and   an opening arranged in a curvature of one of the plurality of ribs connecting two adjacent cooling channels;   wherein the airfoil profile has a leading edge and a trailing edge,   wherein at least one of the plurality of ribs connects the pressure-side blade wall to the suction-side blade wall and extends from the attachment area to the airfoil tip,   wherein at least one of the plurality of ribs has an essentially constant rib thickness and is curved toward the leading edge or the trailing edge forming a cooling-channel corner area, which has an acute angle in a longitudinal section, in the area of the airfoil tip,   wherein the plurality of cooling channels are at least partially separated from one another by in each case one of the plurality of ribs, and   wherein a part of a coolant flow of one of the plurality of the cooling channels, the cooling channel that is adjacent to a corner area, can flow through the opening into an acute-angled corner area of the adjacent cooling channel.   
   
   
       8 . The cooled turbine rotor blade as claimed in  claim 7 , wherein the rib adjacent to the trailing edge is curved in the area of the airfoil tip. 
   
   
       9 . The cooled turbine rotor blade as claimed in  claim 7 , wherein the opening is arranged such that the terminating wall is impingement-cooled. 
   
   
       10 . The cooled turbine rotor blade as claimed in  claim 7 , wherein an inner face of the terminating wall is equipped with turbulators. 
   
   
       11 . The cooled turbine rotor blade as claimed in  claim 7 , wherein the coolant flows sequentially through the plurality of cooling channels. 
   
   
       12 . The cooled turbine rotor blade as claimed in  claim 7 , wherein the coolant flows in parallel through the plurality of cooling channels. 
   
   
       13 . The cooled turbine rotor blade as claimed in  claim 7 , wherein the cooled turbine rotor blade is cast. 
   
   
       14 . The cooled turbine rotor blade as claimed in  claim 7 , wherein a second rib which is the second one adjacent to the leading edge, curves in the direction of the trailing edge into the terminating wall in the tip area of the cooled turbine rotor blade with an opening provided in a curvature.