Component for a turbine engine with a film hole

Abstract

An apparatus and method relating to a film hole of a predetermined inner dimension in a component of a turbine engine that generates a hot combustion gas flow, and provides a cooling fluid flow, where a wall separates the hot combustion gas flow from the cooling fluid flow and defines a hot surface along which the hot combustion gas flows in a hot flow path and a cooled surface facing the cooling fluid flow including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.

What is claimed is: 
     
         1 . A method of making a film hole of a predetermined inner dimension in a component of a turbine engine that generates a hot combustion gas flow, and provides a cooling fluid flow, where a wall separates the hot combustion gas flow from the cooling fluid flow and defines a hot surface along which the hot combustion gas flows in a hot flow path and a cooled surface facing the cooling fluid flow, the method comprising:
 forming a hole passage defining a centerline in the component with the hole passage having a layup portion facing away from the hot surface and defining at least a portion of an asymmetrical area with respect to the centerline to form a first asymmetry;   applying a coating to the component such that the coating fills in the layup portion leaving the hole with a substantially symmetrical area around the centerline and having less asymmetry than the first asymmetry.   
     
     
         2 . The method of  claim 1 , wherein the layup portion is provided on a portion of the hole. 
     
     
         3 . The method of  claim 1 , wherein the dimension symmetrical around the centerline is circular. 
     
     
         4 . The method of  claim 3 , wherein the layup portion comprises a crescent portion adjacent the circle. 
     
     
         5 . The method of  claim 3 , wherein the layup portion comprises a circle having a larger diameter than the dimension symmetrical around the centerline. 
     
     
         6 . The method of  claim 1 , wherein the hole comprises a conical section and the layup portion extends along the conical section. 
     
     
         7 . The method of  claim 6 , wherein the hole comprises a metering section upstream of the conical section. 
     
     
         8 . The method of  claim 7 , wherein the metering section comprises a circular cross section. 
     
     
         9 . The method of  claim 1 , wherein the coating comprises a substrate, bond coat, and one or more ceramic-based topcoats. 
     
     
         10 . The method of  claim 1 , wherein the film hole is made by machining via electro-discharge machining, 3-D printing, machining via a laser, or by casting in. 
     
     
         11 . The method of  claim 1 , wherein the asymmetrical area is at least one of a diameter, major axis or minor axis. 
     
     
         12 . The method of  claim 1 , wherein the hole has at least one of a circular or non-circular cross section. 
     
     
         13 . An engine component for a turbine engine, which generates a hot combustion gas flow, and provides a cooling fluid flow, comprising:
 a wall separating the hot combustion gas flow from the cooling fluid flow and having a hot surface along which the hot combustion gas flows in a hot flow path and a cooled surface facing the cooling fluid flow;   at least one film hole comprising a passage extending between an inlet at the cooled surface and an outlet at the heated surface and defining a centerline;   a layup portion defining a portion of an asymmetrical area with respect to the centerline to form a first asymmetry and facing away from the heated surface; and   a coating filling the layup portion to define a portion of the passage.   
     
     
         14 . The engine component of  claim 13 , further comprising a laydown portion opposite the layup portion and defining at least a portion of the passage. 
     
     
         15 . The engine component of  claim 13 , wherein a predetermined inner dimension when viewed from the outlet defines a substantially symmetrical area having less asymmetry than the first asymmetry about the centerline. 
     
     
         16 . The engine component of  claim 15 , wherein the predetermined inner dimension portion is a circle. 
     
     
         18 . The engine component of  claim 13 , wherein the layup portion is a crescent. 
     
     
         17 . The engine component of  claim 15 , wherein the layup portion comprises a circle having a larger diameter than the predetermined inner dimension. 
     
     
         19 . The engine component of  claim 13 , wherein the film hole comprises a conical section and the layup portion extends along the conical section. 
     
     
         20 . The engine component of  claim 19 , wherein the film hole comprises a metering section upstream of the conical section.