Reinforcement and cooling structure of a turbine blade

Abstract

The invention relates to a blade ( 13, 14 ) for a turbine ( 10 ) which has at least one channel ( 22 ) that can be impinged with a coolant fluid. Several turbulators ( 23 ) which improve the heat exchange between the wall ( 19, 20 ) and the coolant fluid are provided on at least one wall ( 19, 20 ) of the channel ( 22 ). In addition, the turbulators ( 23 ) reinforce the wall ( 19; 20 ) and converge. As a result of said reinforcement, the thickness (d) of the wall ( 19, 20 ) in the area between the turbulators ( 23 ) can be reduced.

1 . A blade/vane, in particular a turbine blade/vane ( 13 ;  14 ), having at least one duct ( 22 ), which is bounded by walls ( 19 ,  20 ,  21 ) and to which a cooling fluid can be admitted, a plurality of turbulators ( 23 ) being provided on at least one wall ( 19 ;  20 ) to improve the heat exchange between the wall ( 19 ;  20 ) and the cooling fluid, characterized in that the turbulators ( 23 ) merge into one another and are used to reinforce the wall ( 19 ;  20 ).  
     
     
         2 . The blade/vane as claimed in  claim 1 , characterized in that the turbulators ( 23 ) have a straight configuration.  
     
     
         3 . The blade/vane as claimed in  claim 2 , characterized in that all the turbulators ( 23   a,    23   b ) include the same angle (α, β) with a longitudinal center line ( 25 ) of the blade/vane ( 13 ;  14 ).  
     
     
         4 . The blade/vane as claimed in  claim 2  or  3 , characterized in that the turbulators ( 23   a,    23   b ) include a right angle ( 26 ).  
     
     
         5 . The blade/vane as claimed in  claim 2 , characterized in that a first group of turbulators ( 23   a ) includes a first angle (α) with a longitudinal center line ( 25 ) of the blade/vane ( 13 ;  14 ) and a second group of turbulators ( 23   b ) includes a second angle (β) with the longitudinal center line ( 25 ) of the blade/vane ( 13 ;  14 ).  
     
     
         6 . The blade/vane as claimed in one of  claims 2  to  5 , characterized in that the turbulators ( 23 ) are arranged in such a way that they form recesses located adjacent to one another and above one another in the form of polygons, in particular squares, rhombuses or hexagons.  
     
     
         7 . The blade/vane as claimed in one of  claims 1  to  6 , characterized in that the wall thickness (d) of the wall ( 19 ;  20 ) is reduced, at least in the region between the turbulators ( 23 ).  
     
     
         8 . The blade/vane as claimed in one of  claims 1  to  7 , characterized in that the blade/vane ( 13 ;  14 ) has a plurality of sections ( 28 ,  29 ,  30 ) provided with different arrangements of turbulators ( 23 ).  
     
     
         9 . The blade/vane as claimed in  claim 8 , characterized in that the sections ( 28 ,  29 ,  30 ) are at a distance from one another.  
     
     
         10 . The blade/vane as claimed in  claim 8 , characterized in that the sections ( 28 ,  29 ,  30 ) merge into one another.  
     
     
         11 . The blade/vane as claimed in one of  claims 1  to  10 , characterized in that the blade is configured as a guide vane ( 13 ) or as a rotor blade ( 14 ) of a turbomachine ( 10 ).