Aerodynamic component for a gas turbine engine

Abstract

An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.

What is claimed is: 
     
         1 . An aerodynamic component of a gas turbine engine fittable to a shell having a shell shape, the aerodynamic component comprising:
 a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell, and   deviation of the component shape from the shell shape aiding in an establishment of a final desired shape of the aerodynamic component following the assembly operation.   
     
     
         2 . The aerodynamic component according to  claim 1 , wherein:
 the shell is an inner diameter shell with a substantially uniform radius of curvature,   the shell comprises an exterior surface to which the aerodynamic component is finable, and   the deviation is accomplished by the body being:   cast to have a radius of curvature, which is similar to the substantially uniform radius of curvature of the shell at a central point of the body and which decreases toward opposite edges of the body, and   deformed to have a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         3 . The aerodynamic component according to  claim 1 , wherein:
 the shell is an inner diameter shell with a substantially uniform radius of curvature,   the shell comprises an exterior surface to which the aerodynamic component is finable, and   the deviation is accomplished by the body being:   cast to have a radius of curvature, which is similar to the substantially uniform radius of curvature of the shell at an edge of the body and which decreases toward an opposite edge of the body, and   deformed to have a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         4 . The aerodynamic component according to  claim 1 , wherein:
 the shell is an outer diameter shell with a substantially uniform radius of curvature,   the shell comprises an interior surface to which the aerodynamic component is finable, and   the deviation is accomplished by the body being:   cast to have a radius of curvature, which is similar to the substantially uniform radius of curvature of the combustor shell at a central point of the body and which increases toward opposite edges of the body, and   deformed to have a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         5 . The aerodynamic component according to  claim 1 , wherein:
 the shell is an outer diameter shell with a substantially uniform radius of curvature,   the shell comprises an interior surface to which the aerodynamic component is finable, and   the deviation is accomplished by the body being:   cast to have a radius of curvature, which is similar to the substantially uniform radius of curvature of the combustor shell at an edge of the body and which increases toward an opposite edge of the body, and   deformed to have a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         6 . A combustor section of a gas turbine engine, comprising:
 an inner diameter shell having a shell shape;   an outer diameter shell having a shell shape;   an inner diameter shell panel according to the aerodynamic component of  claim 1  to be fit to an exterior surface of the inner diameter shell; and   an outer diameter shell panel according to the aerodynamic component of  claim 1  to be fit to an interior surface of the outer diameter shell.   
     
     
         7 . A method of manufacturing an aerodynamic component to be fittable to a shell in a gas turbine engine, method comprising:
 forming materials of the aerodynamic component into a body having an initial shape that deviates from a shape of the shell; and   deforming the body to assume a second shape that corresponds to the shape of the shell,   the forming of the materials of the aerodynamic component into the body having the initial shape being executed such that deviation of the initial shape from the shape of the shell aids in an assumption of the second shape by the body.   
     
     
         8 . The method according to  claim 7 , wherein:
 the forming comprises casting the materials of the aerodynamic component into the body having the second shape and cold working the body from the second shape into the initial shape, and   the deforming comprises securing the body having the initial shape in a fixture and coating and/or laser drilling the body from the initial shape into the second shape.   
     
     
         9 . The method according to  claim 8 , wherein the coating comprises electron-beam physical vapor deposition (EBPVD). 
     
     
         10 . The method according to  claim 7 , wherein:
 the forming comprises casting the materials of the aerodynamic component into the body having the second shape and securing the body in a deformed fixture such that the body assumes the initial shape, and   the deforming comprises coating and/or laser drilling the body from the initial shape into the second shape.   
     
     
         11 . The method according to  claim 10 , wherein the coating comprises electron-beam physical vapor deposition (EBPVD). 
     
     
         12 . The method according to  claim 7 , wherein:
 the forming comprises casting the materials of the aerodynamic component into the body having the initial shape, and   the deforming comprises securing the body in a deformed fixture and coating and/or laser drilling the body from the initial shape into the second shape.   
     
     
         13 . The method according to  claim 12 , wherein the coating comprises electron-beam physical vapor deposition (EBPVD). 
     
     
         14 . The method according to  claim 7 , wherein:
 the shell is an inner diameter shell with a substantially uniform radius of curvature,   the shell comprises an exterior surface to which the aerodynamic component is finable,   the forming is executed such that the body has a radius of curvature, which is similar to the substantially uniform radius of curvature of the combustor shell at a central point of the body and which decreases toward opposite edges of the body, and   the deforming is executed such that the body has a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         15 . The method according to  claim 7 , wherein:
 the shell is an inner diameter shell with a substantially uniform radius of curvature,   the shell comprises an exterior surface to which the aerodynamic component is finable,   the forming is executed such that the body has a radius of curvature, which is similar to the substantially uniform radius of curvature of the combustor shell at an edge of the body and which decreases toward an opposite edge of the body, and   the deforming is executed such that the body has a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         16 . The method according to  claim 7 , wherein:
 the shell is an outer diameter shell with a substantially uniform radius of curvature,   the shell comprises an interior surface to which the aerodynamic component is finable,   the forming is executed such that the body has a radius of curvature, which is similar to the substantially uniform radius of curvature of the combustor shell at a central point of the body and which increases toward opposite edges of the body, and   the deforming is executed such that the body has a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         17 . The combustor panel according to  claim 7 , wherein:
 the shell is an outer diameter shell with a substantially uniform radius of curvature,   the shell comprises an interior surface to which the aerodynamic component is finable,   the forming is executed such that the body has a radius of curvature, which is similar to the substantially uniform radius of curvature of the combustor shell at an edge of the body and which increases toward an opposite edge of the body, and   the deforming is executed such that the body has a substantially uniform radius of curvature similar to the substantially uniform radius of curvature of the shell.   
     
     
         18 . A method of aerodynamic component manufacturing, comprising:
 forming the aerodynamic component with an initial shape that deviates from a normal and final desired curvature during an initial manufacturing process; and   deforming the aerodynamic component during a subsequent manufacturing process which results in the aerodynamic component being finable to a shell,   the forming being executed such that the aerodynamic component assumes the normal and final desired curvature upon completion of the deforming during the subsequent manufacturing process.   
     
     
         19 . The method according to  claim 18 , wherein:
 the forming comprises casting and then cold working the aerodynamic component into the initial shape, and   the deforming comprises securing the aerodynamic component having the initial shape in a fixture and coating and/or laser drilling the aerodynamic component such that the aerodynamic component assumes the normal and final desired curvature.   
     
     
         20 . The method according to  claim 18 , wherein:
 the forming comprises casting the aerodynamic component to assume the normal and desired final curvature and securing the aerodynamic component in a deformed fixture such that the aerodynamic component assumes the initial shape, and   the deforming comprises coating and/or laser drilling the aerodynamic component such that the aerodynamic component assumes the normal and desired final curvature.   
     
     
         21 . The method according to  claim 18 , wherein:
 the forming comprises casting the aerodynamic component to have the initial shape, and   the deforming comprises securing the aerodynamic component in a deformed fixture and coating and/or laser drilling the aerodynamic component such that the aerodynamic component assumes the normal and desired final curvature.