Turbine blades and methods of forming modified turbine blades and turbine rotors

Abstract

Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.

What is claimed is: 
     
         1 . A turbine blade for use in an engine, the turbine blade comprising:
 a platform including a surface configured to define a portion of a flowpath, the surface including an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine; and   an airfoil extending from the platform.   
     
     
         2 . The turbine blade of  claim 1 , wherein the operation of the engine includes a predetermined maximum speed and a predetermined maximum temperature. 
     
     
         3 . The turbine blade of  claim 1 , wherein:
 the airfoil has an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the convex suction side wall, the concave pressure side wall, and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon.   
     
     
         4 . The turbine blade of  claim 1 , wherein the initial contour is a depression. 
     
     
         5 . The turbine blade of  claim 4 , wherein the depression is located adjacent to the concave pressure side wall. 
     
     
         6 . The turbine blade of  claim 4 , wherein the depression is located adjacent to the convex suction side wall.