Airfoil having cooling circuit

Abstract

An apparatus and method for providing a cooling fluid flow having a wall separating the hot air flow from the cooling fluid flow and having a first surface along which the hot air flows in a hot flow path and a second surface facing the cooling fluid flow, first and second supply circuits for providing the cooling fluid flow, at least one skin cooling circuit with at least one channel formed in the first surface, the at least one channel fluidly coupled with the first supply circuit.

What is claimed is: 
     
         1 . An engine component for a turbine engine, which generates a hot air flow, and provides a cooling fluid flow, the engine component comprising:
 a wall separating the hot air flow from the cooling fluid flow and having a first surface along which the hot air flows in a hot flow path and a second surface facing the cooling fluid flow;   first and second supply circuits for providing the cooling fluid flow;   at least one skin cooling circuit comprising at least one channel formed in the first surface, the at least one channel fluidly coupled with the first supply circuit; and   at least one wall cooling circuit comprising at least one wall cooling passage located within at least a portion of an interior of the wall internally of the at least one channel between the second supply circuit and the at least one channel, the at least one wall cooling passage fluidly coupled with the second supply circuit.   
     
     
         2 . The engine component of  claim 1 , further comprising at least one coating applied to the first surface. 
     
     
         3 . The engine component of  claim 1 , wherein the skin cooling circuit and wall cooling circuit are operated in parallel. 
     
     
         4 . The engine component of  claim 1  further comprising multiple film holes for each of the multiple channels. 
     
     
         5 . The engine component of  claim 1  wherein supply circuits define a first flow direction, the channel defines a second flow direction, and the wall cooling passage defines a third flow direction. 
     
     
         6 . The engine component of  claim 5  wherein at least two of the first, second and third flow directions are the same. 
     
     
         7 . The engine component of  claim 6  wherein second and third flow directions are the same. 
     
     
         8 . The engine component of  claim 5  wherein at least two of the first, second and third flow directions are opposite. 
     
     
         9 . The engine component of  claim 8  wherein second and third flow directions are opposite. 
     
     
         10 . A method of cooling an engine component with at least one skin cooling circuit fluidly separate from at least one wall cooling circuit, the method comprising:
 passing a cooling airflow from a first source through a first internal hole in a first direction to a wall passage in an interior of an outer wall of an airfoil, and then flowing the cooling airflow in a second direction perpendicular to the first direction to a film hole through a coating overlying an outer surface of the airfoil to form the at least one wall cooling circuit; and   passing a cooling airflow from a second source through a second internal hole in the first direction to a channel in an outer surface of the outer wall, and then to another film hole through the coating overlying the outer surface to form the skin cooling circuit;   wherein the wall passage is located internally of the channel between the second source and the channel.   
     
     
         11 . The method of  claim 10 , wherein the passing of the cooling airflow through the skin cooling circuit is in a first direction and the passing of cooling airflow in the at least one wall cooling circuit is in a second direction. 
     
     
         12 . The method of  claim 11 , wherein the first and second directions are the same. 
     
     
         13 . The method of  claim 11 , wherein the first and second directions are different 
     
     
         14 . The method of  claim 13 , wherein the first and second directions are opposite. 
     
     
         15 . A method of cooling an engine component a turbine engine, which generates a hot air flow on an outer surface of the engine component, and provides a cooling fluid flow from an interior of the engine component, the method comprising:
 passing a cooling airflow from a first source located within the interior to a wall passage within an outer wall of the engine component, and then to a film hole in a coating overlying the outer surface to form a wall cooling circuit; and   passing another cooling airflow from a second source located within the interior to a channel in the outer surface, and then to a film hole in a coating overlying the outer surface to form a skin cooling circuit.   
     
     
         16 . The method of  claim 15 , wherein the passing of the cooling air through the skin cooling circuit is in a first direction and the passing of the cooling air in the wall cooling circuit is in a second direction. 
     
     
         17 . The method of  claim 16 , wherein the first and second directions are the same. 
     
     
         18 . The method of  claim 16 , wherein the first and second directions are different. 
     
     
         19 . The method of  claim 18 , wherein the first and second directions are opposite. 
     
     
         20 . The method of  claim 15 , wherein the wall passage is located internally of the channel between the second source and the channel.