Turbine blade for a gas turbine

Abstract

A turbine blade for a gas turbine is provided. The quantity of coolant flowing off the rear edge thereof is set relatively simply and exactly directly upon casting the turbine blade, without reworking the cast turbine blade with respect to the setting of coolant consumption being necessary. Raised areas are situated on the inner surfaces of the intake side wall or pressure side wall, between which a throttle element is present, by means of which the quantity of coolant flowing out is set. This arrangement allows a core tool to be produced simply, by means of which the casting cores required for casting the turbine blade are produced having the desired precision in great quantities.

1 - 6 . (canceled) 
     
     
         7 . A turbine blade for a gas turbine, comprising:
 a main blade part, around which a hot gas flows and which comprises a suction-side wall and a pressure-side wall which extend in the direction of flow of the hot gas from a common leading edge to a trailing edge,   wherein an opening for blowing out a coolant which cools the main blade part beforehand is arranged on the trailing edge, which opening is fluidically connected to a cavity arranged in the main blade part by means of a channel,   wherein the channel is also delimited by an inwardly facing face of the suction-side wall and by an inwardly facing face of the pressure-side wall and a throttling element is provided for setting the quantity of coolant emerging from the opening,   wherein the throttling element comprises two elevations, upstream in relation to the throughflow direction of the channel, of the opening, which are arranged offset in relation to one another, as seen in the throughflow direction of the cooling channel, and between which there is arranged the minimum throughflow cross section of the channel, and   wherein the two throttling elements are each arranged each on one of the two inwardly facing faces.   
     
     
         8 . The turbine blade as claimed in  claim 7 , wherein a first elevation which is arranged on the inwardly facing face of the pressure-side wall is arranged downstream of a second elevation which is arranged on the inwardly facing face of the suction-side wall. 
     
     
         9 . The turbine blade as claimed in  claim 7 , wherein a plurality of openings are arranged on the trailing edge and the cooling channel collectively connects a plurality of openings to the cavity. 
     
     
         10 . The turbine blade as claimed in  claim 7 , wherein the elevations are in the form of fins. 
     
     
         11 . The turbine blade as claimed in  claim 7 , wherein the cooling channel converges and the two elevations are situated on the inwardly facing faces with a continuous and edge-free profile. 
     
     
         12 . The turbine blade as claimed in  claim 9 , wherein the plurality of openings are provided on the pressure wall side.