Compressor rotor with internal stiffening ring of distinct material

Abstract

A compressor rotor has a hub at a radially outer location, and a leg extending from an inner ring at a radially inner location to the hub. The hub has an inner bore at a location spaced from the leg. A stiffening ring is force fit into the inner bore of the hub.

What is claimed is: 
     
         1 . A rotor comprising:
 a hub at a radially outer location, and a leg extending from an inner ring at a radially inner location to said hub, said hub having an inner bore at a location spaced from said leg; and   a stiffening ring force fit into said inner bore of said hub.   
     
     
         2 . The rotor as set forth in  claim 1 , wherein said leg extends from said inner ring to said hub in a direction having an axial component and a radial component, such that its axial component extends along a direction that will be downstream when the compressor rotor is mounted in a gas turbine engine, and said stiffening ring positioned in said inner bore at a location that will be upstream of a location where said leg connects into said hub when the rotor is mounted in a gas turbine engine. 
     
     
         3 . The rotor as set forth in  claim 2 , wherein an axial location of said stiffening ring is such that a plane defined perpendicularly to a central axis of said rotor, and passing through said stiffening ring, also passes through a portion of said leg. 
     
     
         4 . The rotor as set forth in  claim 1 , wherein said stiffening ring is formed of a distinct material from a material forming said hub 
     
     
         5 . The rotor as set forth in  claim 4 , wherein said hub material contains titanium, and said stiffening ring is formed of nickel. 
     
     
         6 . The rotor as set forth in  claim 4 , wherein said hub material contains titanium, and said stiffening ring is formed of aluminum. 
     
     
         7 . The rotor as set forth in  claim 1 , wherein said inner bore has a surface which receives said stiffening ring, and a ledge extending radially inwardly of a portion of said inner bore to provide a stop for said stiffening ring. 
     
     
         8 . The rotor as set forth in  claim 7 , wherein said ledge has a radially innermost extent, and said stiffening ring extending radially inwardly of said radially innermost extent of said ledge. 
     
     
         9 . The rotor as set forth in  claim 1 , wherein said rotor is a compressor rotor. 
     
     
         10 . A compressor section for a gas turbine section comprising:
 at least one rotor, said rotor receiving a plurality of blades;   a hub at a radially outer location, and a leg extending from an inner ring at a radially inner location to said hub, said hub having an inner bore at a location spaced from said leg, said leg extends from said inner ring in a direction having an axial component and a radial component, such that its axial component extends along a direction that will be downstream when the compressor rotor is mounted in a gas turbine engine, and said stiffening ring positioned in said inner bore at a location that will be upstream of a location where said leg connects into said hub when the rotor is mounted in a gas turbine engine, an axial location of said stiffening ring is such that a plane defined perpendicularly to the central axis of said rotor, and passing through said stiffening ring, also passes through a portion of said leg; and   a stiffening ring force fit into said inner bore of said hub, said stiffening ring being formed of a distinct material from a material forming said hub, said inner bore has a surface which receives said stiffening ring, and a ledge extending radially inwardly of said portion of said inner bore to provide a stop for said stiffening ring, said ledge has a radially innermost portion, and said stiffening ring extending radially inwardly of said radially innermost portion of said ledge.   
     
     
         11 . The compressor section as set forth in  claim 10 , wherein said hub material contains titanium, and said stiffening ring is formed of nickel. 
     
     
         12 . The compressor section as set forth in  claim 10 , wherein said hub material contains titanium, and said stiffening ring is formed of aluminum. 
     
     
         13 . A gas turbine engine compressing:
 a compressor section, a combustor section and a turbine section, said turbine section driving a shaft to in turn drive said compressor section, said compressor section and said turbine section including at least one rotor; and   said rotor of at least one of said compressor and turbine sections including a hub at a radially outer location, and a leg extending to an inner ring at a radially inner location, said hub having an inner bore at a location spaced from said leg, a stiffening ring force fit into said inner bore of said hub.   
     
     
         14 . The engine as set forth in  claim 13 , wherein said leg extends from said inner ring to said hub in a direction having an axial component and a radial component, such that its axial component extends along a direction that will be downstream when the compressor rotor is mounted in a gas turbine engine, and said stiffening ring positioned in said inner bore at a location that will be upstream of a location where said leg connects into said hub when the rotor is mounted in a gas turbine engine. 
     
     
         15 . The engine as set forth in  claim 13 , wherein said stiffening ring is formed of a distinct material from a material forming said hub 
     
     
         16 . The engine as set forth in  claim 15 , wherein said hub material contains titanium, and said ring is formed of nickel. 
     
     
         17 . The engine as set forth in  claim 15 , wherein said hub material contains titanium, and said stiffening ring is formed of aluminum. 
     
     
         18 . The engine as set forth in  claim 13 , wherein said inner bore has a surface which receives said stiffening ring, and a ledge extending radially inwardly of said portion of said inner bore to provide a stop for said stiffening ring. 
     
     
         19 . The engine as set forth in  claim 18 , wherein said ledge has a radially innermost portion, and said stiffening ring extending radially inwardly of said radially innermost portion of said ledge. 
     
     
         20 . The engine as set forth in  claim 13 , wherein said at least one rotor is in said compressor section.