# US 2013/0156584 A1 · Compressor rotor with internal stiffening ring of distinct material > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2013/0156584 A1 - Document ID: US20130156584A1 - Status: Published application - Kind: A1 - Application number: 13/328,040 - Filed: 2011-12-16 - Published: 2013-06-20 - Earliest claimed: 2011-12-16 - Inventors: Carney R. Anderson; Peter V. Tomeo - Web page: https://patentgrep.com/patent/US20130156584A1 ## CPC - F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) - F05D 2260/37: by a press fit connection - F05D 2260/94: Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 2) 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. ### Claim 4 (depends on 1) The rotor as set forth in claim 1, wherein said stiffening ring is formed of a distinct material from a material forming said hub ### Claim 5 (depends on 4) The rotor as set forth in claim 4, wherein said hub material contains titanium, and said stiffening ring is formed of nickel. ### Claim 6 (depends on 4) The rotor as set forth in claim 4, wherein said hub material contains titanium, and said stiffening ring is formed of aluminum. ### Claim 7 (depends on 1) 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. ### Claim 8 (depends on 7) 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. ### Claim 9 (depends on 1) The rotor as set forth in claim 1, wherein said rotor is a compressor rotor. ### Claim 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. ### Claim 11 (depends on 10) The compressor section as set forth in claim 10, wherein said hub material contains titanium, and said stiffening ring is formed of nickel. ### Claim 12 (depends on 10) The compressor section as set forth in claim 10, wherein said hub material contains titanium, and said stiffening ring is formed of aluminum. ### Claim 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. ### Claim 14 (depends on 13) 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. ### Claim 15 (depends on 13) The engine as set forth in claim 13, wherein said stiffening ring is formed of a distinct material from a material forming said hub ### Claim 16 (depends on 15) The engine as set forth in claim 15, wherein said hub material contains titanium, and said ring is formed of nickel. ### Claim 17 (depends on 15) The engine as set forth in claim 15, wherein said hub material contains titanium, and said stiffening ring is formed of aluminum. ### Claim 18 (depends on 13) 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. ### Claim 19 (depends on 18) 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. ### Claim 20 (depends on 13) The engine as set forth in claim 13, wherein said at least one rotor is in said compressor section.