turbine engine component for adaptive cooling

Abstract

A turbine engine component, particularly an aerofoil, including a body is provided. The turbine engine component includes a first surface exposed to a working fluid of high temperatures during operation, a second surface including a depression, the depression is exposed to a cooling fluid during operation and oriented such that, starting from the second surface, the depression deepens in the direction of a back face of the first surface. Furthermore the body includes a body portion between the back face and the first surface. The depression is defined such that a diameter of the depression decreases from the second surface in direction of the back face.

1 .- 10 . (canceled) 
     
     
         11 . A turbine engine component including a body, comprising:
 a first surface exposed to a working fluid having a high temperature during operation;   a second surface including a depression, the depression being exposed to a cooling fluid during operation and oriented such that, starting from the second surface, the depression deepens in a direction of a back face of the first surface; and   a body portion disposed between the back face and the first surface,   wherein a diameter of the depression decreases from the second surface in the direction of the back face.   
     
     
         12 . The turbine engine component according to  claim 11 ,
 wherein the body portion is comprised of a material and/or of a width between the first surface and the back face of the first surface, and   wherein when the body portion is exposed to a specific temperature, erosion and/or corrosion on the first surface side of the body portion a passage through the depression will open.   
     
     
         13 . The turbine engine component according to  claim 12 , wherein a part of the body adjacent to the body portion includes a further material that is less susceptible to erosion and/or corrosion than the body portion. 
     
     
         14 . The turbine engine component according to  claim 13 , wherein the further material is an oxidation resistant coating. 
     
     
         15 . The turbine engine component according to  claim 12 , wherein the open passage provides a cooling fluid producing a cooling to a proximity of the first surface. 
     
     
         16 . The turbine engine component according to  claim 15 , wherein the cooling is film cooling. 
     
     
         17 . The turbine engine component according to  claim 15 , wherein the diameter of the depression decreases from the second surface in the direction of the back face such that, when in use, continuing erosion and/or corrosion on the first surface side of the body portion results in widening the passage to let pass a larger amount of cooling fluid. 
     
     
         18 . The turbine engine component according to  claim 17 , wherein the diameter of the depression decreases from the second surface in direction of the back face such that, when in use, continuing widening of the passage due to erosion and/or corrosion provides an increasing amount of passed cooling fluid such that a temperature of a proximity of the first surface is reduced to a value at which erosion and/or corrosion on the first surface side of the body portion terminates. 
     
     
         19 . The turbine engine component according to  claim 11 , wherein the turbine engine component is an aerofoil. 
     
     
         20 . A gas turbine engine, comprising:
 a turbine engine component, comprising:
 a first surface exposed to a working fluid having a high temperature during operation, 
 a second surface including a depression, the depression being exposed to a cooling fluid during operation and oriented such that, starting from the second surface, the depression deepens in a direction of a back face of the first surface, and 
 a body portion disposed between the back face and the first surface, 
   wherein a diameter of the depression decreases from the second surface in the direction of the back face.   
     
     
         21 . The gas turbine engine according to  claim 20 , wherein the turbine engine component is disposed in a vane aerofoil, and/or a vane platform, and/or a blade aerofoil, and/or a blade platform, and/or a blade shroud, and/or a transition duct between a combustor and a turbine section, and/or a combustor, and/or a static shroud, and/or a heat shield, and/or a diffuser, and/or an exhaust. 
     
     
         22 . The gas turbine engine according to  claim 20 ,
 wherein the body portion is comprised of a material and/or of a width between the first surface and the back face of the first surface, and   wherein when the body portion is exposed to a specific temperature, erosion and/or corrosion on the first surface side of the body portion a passage through the depression will open.   
     
     
         23 . The gas turbine engine according to  claim 22 , wherein a part of the body adjacent to the body portion includes a further material that is less susceptible to erosion and/or corrosion than the body portion. 
     
     
         24 . The gas turbine engine according to  claim 23 , wherein the further material is an oxidation resistant coating. 
     
     
         25 . The gas turbine engine according to  claim 22 , wherein the open passage provides a cooling fluid producing a cooling to a proximity of the first surface. 
     
     
         26 . The gas turbine engine according to  claim 25 , wherein the cooling is film cooling. 
     
     
         27 . The gas turbine engine according to  claim 25 , wherein the diameter of the depression decreases from the second surface in the direction of the back face such that, when in use, continuing erosion and/or corrosion on the first surface side of the body portion results in widening the passage to let pass a larger amount of cooling fluid. 
     
     
         28 . A method for adaptive cooling a turbine engine component, the method comprising:
 providing a cooling fluid to the turbine engine component including a body, the gas turbine component comprising:
 a first surface exposed to a working fluid of a high temperature during operation, 
 a second surface comprising a depression, the depression being exposed to the cooling fluid during operation and oriented such that, starting from the second surface, the depression deepens in a direction of a back face of the first surface, and 
 a body portion disposed between the back face and the first surface; and 
   applying heat to the first surface such that a material of the first surface is eroded and/or corroded on the first surface side of the body portion so that a passage to the depression will open allowing the cooling fluid to pass,   wherein a diameter of the depression decreases from the second surface in direction of the back face.   
     
     
         29 . The method according to  claim 20 , wherein the depression is cast or machined.