Turbine Blade

Abstract

A turbine blade, having a plurality of auxiliary cooling channels which branch off from a main cooling channel, formed within a blade body, is provided. The plurality of auxiliary cooling channels open into outlet openings in the leading edge region of the blade body. A heat shield element is attached to the blade body in the leading edge region at a predefined spacing, wherein the heat shield element has a number of outlet channels which are arranged behind one another in the longitudinal direction and extend from the main cooling channel to the outer wall face of the heat shield element.

1 .- 7 . (canceled) 
   
   
       8 . A turbine blade, comprising:
 a blade body, provided with a first outside surface which is an outside surface of the blade body, in a leading edge region of the blade body;   a heat shield element, which is arranged on the first outside surface at a distance from the blade body; and   a plurality of secondary cooling passages, which branch off from a main cooling passage formed inside the blade body,   wherein the plurality of secondary cooling passages open into a plurality of discharge openings in the leading edge region, and   wherein the heat shield element has a plurality of discharge passages which extend from the main cooling passage to a second outside surface, the second outside surface is an outside surface of the heat shield element.   
   
   
       9 . The turbine blade as claimed in  claim 8 , wherein the turbine blade is used in a gas turbine. 
   
   
       10 . The turbine blade as claimed in  claim 8 , wherein the heat shield element has a shape that is adapted to a profile of the turbine blade in the leading edge region. 
   
   
       11 . The turbine blade as claimed in  claim 10 , wherein the heat shield element is produced from a first material which is more resistant to temperature than a second material of the blade body. 
   
   
       12 . The turbine blade as claimed in  claim 8 , wherein the heat shield element is arranged at the distance of no more than 3 mm from the blade body. 
   
   
       13 . The turbine blade as claimed in  claim 8  wherein the heat shield element is curved whereby a constant distance between an inside surface of the heat shield element and the first outside surface is maintained. 
   
   
       14 . The turbine blade as claimed in  claim 8 , wherein the plurality of secondary cooling passages are arranged essentially perpendicularly to an inside wall surface of the heat shield element. 
   
   
       15 . The turbine blade as claimed in  claim 14 , wherein the plurality of secondary cooling passages, are uniformly distributed behind the heat shield element. 
   
   
       16 . The turbine blade as claimed in  claim 8 , wherein a plurality of edge regions of the heat shield element are connected to the blade body. 
   
   
       17 . The turbine blade as claimed in  claim 8 , wherein the plurality of discharge passages are arranged one behind the other. 
   
   
       18 . A thermal turbomachine, comprising:
 a plurality of turbine blades, each turbine blade comprising:
 a blade body, provided with a first outside surface which is an outside surface of the blade body, in a leading edge region of the blade body, 
 a heat shield element, which is arranged in the first outside surface at a distance from the blade body, and 
 a plurality of secondary cooling passages, which branch off from a main cooling passage formed inside the blade body; 
   wherein the plurality of secondary cooling passages open into a plurality of discharge openings in the leading edge region, and   wherein the heat shield element has a plurality of discharge passages which extend from the main cooling passage to a second outside surface, an outside surface of the heat shield element.   
   
   
       19 . A thermal turbomachine as claimed in  claim 18 , wherein the turbomachine is a gas turbine. 
   
   
       20 . The thermal turbomachine as claimed in  claim 18 , wherein the heat shield element has a shape that is adapted to a profile of the turbine blade in the leading edge region. 
   
   
       21 . The thermal turbomachine as claimed in  claim 20 , wherein the heat shield element is produced from a first material which is more resistant to temperature than a second material of the blade body. 
   
   
       22 . The thermal turbomachine as claimed in  claim 18 , wherein the heat shield element is arranged at the distance of no more than 3 mm from the blade body. 
   
   
       23 . The turbine blade as claimed in  claim 18  wherein the heat shield element is curved whereby a constant distance between an inside surface of the heat shield element and the first outside surface is maintained. 
   
   
       24 . The thermal turbomachine as claimed in  claim 18 , wherein the plurality of secondary cooling passages are arranged essentially perpendicularly to an inside wall surface of the heat shield element. 
   
   
       25 . The thermal turbomachine as claimed in  claim 24 , wherein the plurality of secondary cooling passages, are uniformly distributed behind the heat shield element. 
   
   
       26 . The thermal turbomachine as claimed in  claim 18 , wherein a plurality of edge regions of the heat shield element are connected to the blade body. 
   
   
       27 . The thermal turbomachine as claimed in  claim 18 , wherein the plurality of discharge passages are arranged one behind the other.