Rotor disk assembly for a gas turbine engine

Abstract

A rotor assembly for a gas turbine engine includes a rotor disk. The rotor disk includes a heat barrier feature radially inward of a rotor blade and radially outward of a rotor disk.

1 . A rotor assembly for a gas turbine engine comprising:
 a rotor disk having at least one radially outward blade retention feature;   a rotor blade at least partially received in said blade retention feature; and   a heat barrier radially inward of the blade and radially outward of a rotor disk feature, wherein the heat barrier is a coating applied to a radially outward facing surface of said rotor disk.   
     
     
         2 . The rotor assembly for a gas turbine engine of  claim 1 , wherein the coating is applied to at least one axial facing surface immediately adjacent said radially outward facing surface of said rotor disk. 
     
     
         3 . The rotor assembly of  claim 2 , wherein the coating is applied to each axial facing surface immediately adjacent said radially outward facing surface of said rotor disk. 
     
     
         4 . The rotor assembly of  claim 1 , wherein the coating is an insulative coating. 
     
     
         5 . The rotor assembly of  claim 1 , wherein said coating is applied to each exterior facing surface of said rotor disk. 
     
     
         6 . A gas turbine engine comprising:
 a compressor section;   a combustor section fluidly connected to the compressor section;   a turbine section fluidly connected to the combustor section;   a rotor assembly disposed in one of said compressor section and said turbine section, wherein the rotor assembly includes a rotor disk and a plurality of rotor blades protruding radially outward from an outer periphery of said rotor disk;   each of said rotor blades including at least one internal cooling passage;   a cooling fluid flowpath disposed between a radially inward facing surface of each rotor blade and an outer periphery of the rotor disk, wherein the cooling fluid flowpath is operable to provide a cooling fluid to a corresponding internal cooling passage; and   a heat barrier disposed adjacent said outer periphery of said rotor disk, such that said heat barrier prevents cooling fluid in said cooling fluid flowpath from contacting said outer periphery of said rotor disk.   
     
     
         7 . The gas turbine engine of  claim 6 , wherein each of said heat shields and said rotor blades are distinct components. 
     
     
         8 . The gas turbine engine of  claim 6 , wherein the coating is applied to at least one axial facing surface immediately adjacent said radially outward facing surface of said rotor disk. 
     
     
         9 . The gas turbine engine of  claim 8 , wherein the coating is applied to each axial facing surface immediately adjacent said radially outward facing surface of said rotor disk. 
     
     
         10 . The gas turbine engine of  claim 6 , wherein the coating is an insulative coating. 
     
     
         11 . The gas turbine engine of  claim 6 , wherein said coating is applied to each exterior facing surface of said rotor disk. 
     
     
         12 . A method for protecting a rotor disk comprising:
 defining a cooling flowpath between a radially inward facing surface of a rotor blade and an outer periphery of a rotor disk; and   disposing a heat barrier adjacent said outer periphery of said rotor disk by at least applying a coating to a radially outward facing surface of said rotor disk such that a cooling fluid passing through said cooling flowpath is prevented from contacting said outer periphery of said rotor disk.   
     
     
         13 . The method of  claim 12 , wherein the coating is applied to at least one axial facing surface immediately adjacent said radially outward facing surface of said rotor disk. 
     
     
         14 . The method of  claim 13 , wherein the coating is applied to each axial facing surface immediately adjacent said radially outward facing surface of said rotor disk. 
     
     
         15 . The method of  claim 12 , wherein the coating is an insulative coating. 
     
     
         16 . The method of  claim 12 , wherein said coating is applied to each exterior facing surface of said rotor disk.