# US 8,540,482 B2 · Rotor assembly for gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,540,482 B2 - Document ID: US8540482B2 - Status: Granted - Kind: B2 - Application number: 12/794,918 - Filed: 2010-06-07 - Published: 2011-12-08 - Granted: 2013-09-24 - Earliest claimed: 2010-06-07 - Assignees: United Technologies Corporation - Applicants: Eric W. Malmborg; Matthew E. Bintz - Inventors: Eric W. Malmborg; Matthew E. Bintz - Web page: https://patentgrep.com/patent/US8540482B2 ## 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}) - F01D 5/025: {Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00)} - F01D 5/06: Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections {(F01D5/022, F01D5/023 take precedence)} - F01D 5/14: Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) - F01D 5/30: Fixing blades to rotors; Blade roots {; Blade spacers} - F01D 5/3038: {the slot having inwardly directed abutment faces on both sides} - F01D 5/3069: {between two discs or rings} - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) ## Abstract A rotor assembly for a gas turbine engine includes a rotor airfoil and a first rotor disk. The rotor airfoil extends along a radial axis. The first rotor disk includes an outer rim, a bore and a web extending between the outer rim and the bore. The first rotor disk is axially offset from the radial axis of the rotor airfoil. ## Claims ### Claim 1 A rotor assembly for a gas turbine engine, comprising: a bladed ring defining a radial axis and having a plurality of separate components that are spaced apart from one another; a rotor airfoil that extends from each of said plurality of separate components along said radial axis; a first rotor disk radially supporting said rotor airfoil and having an outer rim, a bore and a web extending between said outer rim and said bore, wherein said first rotor disk is axially offset from said radial axis of said rotor airfoil; and a second rotor disk radially supporting another rotor airfoil and having an outer rim, a bore and a web extending between said outer rim and said bore, wherein said second rotor disk is axially in-line with a radial axis of said another rotor airfoil. ### Claim 2 (depends on 1) The assembly as recited in claim 1, wherein said rotor airfoil is integrally formed with said bladed ring. ### Claim 3 (depends on 1) The assembly as recited in claim 1, wherein said bladed ring is a full hoop bladed ring. ### Claim 4 (depends on 1) The assembly as recited in claim 1, wherein said bladed ring is segmented. ### Claim 5 (depends on 1) The assembly as recited in claim 1, wherein said rotor airfoil and said bladed ring are a single, continuous structure with no mechanical attachments. ### Claim 6 (depends on 1) The assembly as recited in claim 1, comprising a third rotor disk, wherein said bladed ring is radially trapped between said first rotor disk and said third rotor disk. ### Claim 7 (depends on 6) The assembly as recited in claim 6, comprising a spacer that extends between said first rotor disk and said third rotor disk. ### Claim 8 (depends on 7) The assembly as recited in claim 7, wherein said spacer is positioned radially inwardly from said rotor airfoil. ### Claim 9 (depends on 1) The assembly as recited in claim 1, wherein said first rotor disk is axially offset in an upstream direction from said radial axis of said rotor airfoil. ### Claim 10 (depends on 1) The assembly as recited in claim 1, wherein said first rotor disk is axially offset in a downstream direction from said radial axis of said rotor airfoil. ### Claim 11 (depends on 1) The assembly as recited in claim 1, wherein an axially outermost portion of said web is fully axially offset from an axially outermost portion of said rotor airfoil in a direction away from said rotor airfoil. ### Claim 12 A gas turbine engine, comprising: a section including alternating rows of rotating rotor airfoils and static stator vanes; wherein said section includes a first rotor assembly having a first rotor disk and a second rotor assembly having a second rotor disk, and each of said first rotor disk and said second rotor disk radially supporting a plurality of said rotor airfoils, wherein said first rotor disk is axially offset from a first radial axis of said plurality of rotor airfoils of said first rotor disk and said second rotor disk is axially in-line with a second radial axis of said plurality of rotor airfoils of said second rotor disk. ### Claim 13 (depends on 12) The gas turbine engine as recited in claim 12, wherein said section is a compressor section and includes a plurality of rotor assemblies, and said rotor assemblies are connected with a tie shaft. ### Claim 14 (depends on 12) The gas turbine engine as recited in claim 12, wherein said first rotor disk is fully axially offset from said plurality of said rotor airfoils. ### Claim 15 (depends on 12) The gas turbine engine as recited in claim 12, wherein each of said first rotor disk and said second rotor disk includes an outer rim, a bore and a web that extends between said outer rim and said bore, wherein said outer rim, said bore and said web are radially inward from one of said static stator vanes. ### Claim 16 A method for providing a rotor assembly for a gas turbine engine, comprising the steps of: positioning a first rotor assembly such that a first rotor disk of the first rotor assembly is axially offset from a first radial axis of a first rotor airfoil of the first rotor assembly; and positioning a second rotor assembly such that a second rotor disk of the second rotor assembly is axially in-line with a second radial axis of a second rotor airfoil of the second rotor assembly, wherein the first rotor disk radially supports the first rotor airfoil and the second rotor disk radially supports the second rotor airfoil. ### Claim 17 (depends on 16) The method as recited in claim 16, wherein the first rotor disk is axially offset in an upstream direction relative to the first radial axis of the first rotor airfoil. ### Claim 18 (depends on 16) The method as recited in claim 16, wherein the first rotor disk is axially offset in a downstream direction relative to the first radial axis of the first rotor blade. ### Claim 19 (depends on 16) The method as recited in claim 16, wherein said first rotor disk includes an outer rim, a bore and a web extending between said outer rim and said bore, and including the step of: positioning each of the outer rim, the bore and the web at a position that is fully axially offset from the first radial axis of the first rotor airfoil.