Compressor rotor with internal stiffening ring of distinct material

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.