Clearance control with ceramic matrix composite rotor assembly for a gas turbine engine

Abstract

A gas turbine engine includes a CMC static structure and a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC static structure.

1 . A gas turbine engine comprising:
 a CMC static structure; and   a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC static structure.   
     
     
         2 . The gas turbine engine as recited in  claim 1 , wherein said CMC static structure is a CMC Outer Air Seal. 
     
     
         3 . The gas turbine engine as recited in  claim 2 , further comprising an abradable material mounted to said CMC Outer Air Seal. 
     
     
         4 . The gas turbine engine as recited in  claim 2 , wherein said CMC Outer Air Seal is mounted to a CMC case. 
     
     
         5 . The gas turbine engine as recited in  claim 2 , wherein said CMC Outer Air Seal is mounted to a metallic alloy case. 
     
     
         6 . The gas turbine engine as recited in  claim 1 , wherein said CMC static structure is a CMC turbine case. 
     
     
         7 . The gas turbine engine as recited in  claim 1 , wherein said CMC static structure is a CMC compressor case. 
     
     
         8 . A gas turbine engine comprising:
 a CMC case; and   a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC case.   
     
     
         9 . The gas turbine engine as recited in  claim 8 , further comprising a CMC Outer Air Seal mounted to said CMC case. 
     
     
         10 . The gas turbine engine as recited in  claim 8 , further comprising at least one knife edge seal which extends from each of said multiple of CMC airfoils, said at least one knife edge seal engaged with said CMC Outer Air Seal. 
     
     
         11 . The gas turbine engine as recited in  claim 8 , further comprising an outer shroud defined about said multiple of CMC airfoils. 
     
     
         12 . The gas turbine engine as recited in  claim 8 , wherein said rotor module is defined about an engine longitude axis. 
     
     
         13 . The gas turbine engine as recited in  claim 8 , wherein said rotor module is a Low Pressure Turbine rotor module. 
     
     
         14 . The gas turbine engine as recited in  claim 8 , wherein said rotor module is a High Pressure Turbine rotor module. 
     
     
         15 . The gas turbine engine as recited in  claim 8 , wherein said rotor module is a compressor rotor module. 
     
     
         16 . A method of tip clearance control for a gas turbine engine comprising:
 matching radial growth of CMC rotational structure with a radial growth of a CMC static structure to provide tip clearance control.   
     
     
         17 . The method as recited in  claim 16 , wherein the CMC rotational structure includes a rotor module with a multiple of CMC airfoils. 
     
     
         18 . The method as recited in  claim 16 , wherein the CMC static structure includes a case structure.