Aerofoil and a method for construction thereof

Abstract

An aerofoil and a method for construction of the aerofoil are provided. The aerofoil has an outer wall and an inner wall, wherein the walls are separated by a cooling channel, and a coolant fluid is guidable through the cooling channel during the operation of the aerofoil. The inner wall is provided with a protrusion, which is profiled and arranged such that it extends from the inner wall into the cooling channel. The protrusion directs at least a part of the coolant fluid to impinge the coolant fluid on a first region of the outer wall.

1 - 11 . (canceled) 
     
     
         12 . An aerofoil comprising:
 an outer wall and an inner wall, and   a cooling channel located between the outer wall and the inner wall for guiding a coolant fluid during operation of the aerofoil,   wherein the inner wall comprises a protrusion on the inner wall extending from a surface of the inner wall into the cooling channel,   wherein the protrusion on the inner wall is arranged and profiled such that the protrusion on the inner wall directs at least a part of the coolant fluid, when the coolant fluid is flowing through the cooling channel and over the protrusion on the inner wall, for impinging the coolant fluid on to a first region of the outer wall,   wherein the outer wall further comprises a protrusion on the outer wall,   wherein the protrusion on the outer wall extends from a surface of the outer wall into the cooling channel, and   wherein the protrusion on the outer wall is arranged and profiled such that the protrusion on the outer wall directs at least a part of the coolant fluid, when the coolant fluid is flowing through the cooling channel and over the protrusion on the outer wall, for impinging on to a second region of the inner wall.   
     
     
         13 . The aerofoil according to  claim 12 , wherein the protrusion on the inner wall extends both in a direction of flow of the coolant fluid and in a direction towards the outer wall. 
     
     
         14 . The aerofoil according to  claim 12 , wherein in an overall direction of flow of the coolant fluid, the protrusion on the inner wall comprises:
 an ascending portion ascending in a direction towards the outer wall,   a descending portion descending in a direction towards the inner wall, and   a peak located between the ascending portion and the descending portion,   wherein an absolute value of a gradient of the descending portion is greater than an absolute value of a gradient of the ascending portion.   
     
     
         15 . The aerofoil according to  claim 12 , wherein the protrusion on the inner wall is located proximal to a leading edge of the aerofoil compared to a trailing edge of the aerofoil. 
     
     
         16 . The aerofoil according to  claim 15 , wherein the protrusion on the outer wall extends both in the direction of flow of the coolant fluid and in a direction towards the inner wall. 
     
     
         17 . The aerofoil according to  claim 12 , wherein in the overall direction of flow of the coolant fluid, the protrusion on the outer wall comprises:
 an ascending portion ascending in a direction towards the inner wall,   a descending portion descending in a direction towards the outer wall, and   a peak located between the ascending portion and the descending portion,   wherein for the protrusion on the outer wall, an absolute value of a gradient of the descending portion is greater than an absolute value of a gradient of the ascending portion.   
     
     
         18 . The aerofoil according to  claim 17 ,
 wherein the protrusion on the outer wall and the protrusion on the inner wall are located in the overall direction of flow of the coolant fluid such that the part of coolant fluid that is directed towards the first region of the outer wall by the protrusion on the inner wall impinges on the ascending portion of the protrusion on the outer wall.   
     
     
         19 . The aerofoil according to  claim 16 ,
 wherein in the overall direction of flow of the coolant fluid, the peak of the protrusion on the inner wall and the peak of the protrusion on the outer wall are offset to one another.   
     
     
         20 . The aerofoil according to  claim 19 ,
 wherein the protrusion on the outer wall is located proximal to the leading edge of the aerofoil.   
     
     
         21 . A method for construction of an aerofoil, wherein the aerofoil comprises:
 an outer wall and an inner wall, and   a cooling channel located between the outer wall and the inner wall such that the cooling channel separates the outer wall and the inner wall for guiding a coolant fluid during operation of the aerofoil,   wherein the inner wall comprises a protrusion for directing at least a part of the coolant fluid, when the coolant fluid is flowing through the cooling channel, for impinging the coolant fluid on a first region of the outer wall,   wherein the protrusion on the inner wall extends from a surface of the inner wall into the cooling channel,   wherein the outer wall further comprises a protrusion, and   wherein the protrusion on the outer wall extends from a surface of the outer wall into the cooling channel,   the method comprising:
 arranging the outer wall and the inner wall such that the cooling channel separates the outer wall and the inner wall, 
 providing the protrusion on the inner wall such that the protrusion on the inner wall extends from the surface of the inner wall into the cooling channel, and 
 providing the protrusion on the outer wall such that the protrusion on the outer wall extends from the surface of the outer wall into the cooling channel for directing at least a part of the coolant fluid, when the coolant fluid is flowing through the cooling channel and over the protrusion on the outer wall, for impinging on to a second region of the inner wall.