Turbine blade for a gas turbine

Abstract

There is described a turbine blade, with a platform and with an aerodynamically profiled blade leaf which extends transversely thereto and which comprises a suction-side blade leaf wall and a pressure-side blade leaf wall which extend from an inflow-side leading edge to an outflow-side trailing edge, with respect to a hot gas flowable along the platform or the blade leaf walls during operation, the platform and/or one of the two blade leaf walls having at least two adjacent regions. To prolong the service life of the turbine blade by equalizing the thermal stresses arising there during operation, the two regions have different heat transfer coefficients on the hot-gas side.

1 .- 8 . (canceled) 
   
   
       9 . A turbine blade, comprising:
 a platform;   an aerodynamically profiled blade leaf extending transversely to the platform;   a suction-side blade leaf wall extending from an inflow-side leading edge to an outflow-side trailing edge;   a pressure-side blade leaf wall extending from the inflow-side leading edge to the outflow-side trailing edge;   at least two regions at the turbine blade which are adjacent in a flow direction of hot gas; and   a turbulence element to equalize thermal stresses in the adjacent regions during operation of the turbine blade, wherein the adjacent regions are of different heat transfer coefficients on the hot gas side based upon the turbulence element.   
   
   
       10 . The turbine blade as claimed in  claim 9 , wherein the turbulence element is arranged in one of the regions on the hot-gas side at an edge of the platform. 
   
   
       11 . The turbine blade as claimed in  claim 9 , wherein an inflow and an outflow are based upon a hot gas flowing along the platform or the blade leaf walls during operation. 
   
   
       12 . The turbine blade as claimed in  claim 9 , wherein the region of the platform adjacent to the suction-side blade leaf wall has at least one turbulence element. 
   
   
       13 . The turbine blade as claimed in  claim 12 , wherein the turbulence elements are in a middle region of the platform between the leading edge and the trailing edge. 
   
   
       14 . The turbine blade as claimed in  claim 9 , wherein the turbulence element is a turbulator. 
   
   
       15 . The turbine blade as claimed in  claim 9 , wherein the turbulence element is a dimple. 
   
   
       16 . The turbine blade as claimed in  claim 9 , wherein the turbulence element is a rib. 
   
   
       17 . The turbine blade as claimed in  claim 9 , wherein the turbulence element is a pin. 
   
   
       18 . The turbine blade as claimed in  claim 9 , wherein a plurality of turbulence elements are arranged one behind the other in a flow direction of a hot gas. 
   
   
       19 . The turbine blade as claimed in  claim 9 , wherein the turbine blade is free of a heat insulation layer. 
   
   
       20 . A cast turbine blade, comprising:
 a cooled platform;   an aerodynamically profiled cooled blade leaf extending transversely to the platform;   a suction-side blade leaf wall extending from an inflow-side leading edge to an outflow-side trailing edge;   a pressure-side blade leaf wall extending from the inflow-side leading edge to the outflow-side trailing edge;   at least two regions of the turbine blade which are adjacent in a flow direction of hot gas during operation of the turbine blade, wherein the platform comprises the regions; and   a turbulence element to equalize thermal stresses in the adjacent regions during operation, wherein the adjacent regions are of different heat transfer coefficients on the hot gas side based upon the turbulence element.   
   
   
       21 . The turbine blade as claimed in  claim 20 , wherein a plurality of turbulence elements are arranged one behind the other in a flow direction of a hot gas. 
   
   
       22 . The turbine blade as claimed in  claim 21 , wherein the turbulence element is a dimple or a pin. 
   
   
       23 . A gas turbine, comprising:
 a plurality of turbine blades, wherein the blades have:
 a platform with a wavy surface, 
 an aerodynamically profiled blade leaf extending transversely to the platform, 
 a suction-side blade leaf wall, and 
 a pressure-side blade leaf wall. 
   
   
   
       24 . The gas turbine as claimed in  claim 23 , wherein a wave front of the wave surface is oriented transversely to a flow direction of a hot gas during operation. 
   
   
       25 . The gas turbine as claimed in  claim 23 , wherein wave troughs and wave crests are arranged in regions or close to regions of thermal stresses to influence the heat transfer coefficient.