# US 10,309,251 B2 · Interlocking rotor assembly with thermal shield > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,251 B2 - Document ID: US10309251B2 - Status: Granted - Kind: B2 - Application number: 14/770,832 - Filed: 2014-03-10 - Published: 2016-01-07 - Granted: 2019-06-04 - Earliest claimed: 2013-03-15 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Jonathan Perry Sandoval; Julian Partyka - Web page: https://patentgrep.com/patent/US10309251B2 ## CPC - F01D 25/08: Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) - 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 5/066: {Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps} - F01D 5/3015: {with side plates} - F05D 2260/33: with a bayonet coupling - F05D 2260/36: by a form fit connection, e.g. by interlocking - 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 rotor assembly includes a first rotor, a second rotor mounted on the first rotor and co-rotatable there with, and a thermal shield interlocked with the second rotor for co-rotation there with. ## Claims ### Claim 1 A rotor assembly comprising: a first rotor; a second rotor mounted on the first rotor and co-rotatable there with; and a thermal shield interlocked with the second rotor for co-rotation there with, wherein the first rotor has a first outer diameter and the second rotor has a second outer diameter that is smaller than the first outer diameter, and the second rotor includes at least one radially-extending tab and the thermal shield includes at least one radially-extending tab circumferentially interlocked with the at least one radially-extending tab of the second rotor. ### Claim 2 (depends on 1) The rotor assembly as recited in claim 1, wherein the at least one radially-extending tab of the second rotor includes a step. ### Claim 3 (depends on 1) The rotor assembly as recited in claim 1, wherein the second rotor includes a plurality of radially-extending circumferentially-spaced tabs and the thermal shield includes a plurality of radially-extending circumferentially-spaced tabs circumferentially interlocked with the plurality of radially-extending circumferentially-spaced tabs of the second rotor. ### Claim 4 (depends on 3) The rotor assembly as recited in claim 3, wherein the first rotor includes a plurality of radially-extending circumferentially-spaced tabs and the plurality of radially-extending circumferentially-spaced tabs of the second rotor are circumferentially interlocked with the plurality of radially-extending circumferentially-spaced tabs of the first rotor. ### Claim 5 (depends on 4) The rotor assembly as recited in claim 4, wherein the plurality of radially-extending circumferentially-spaced tabs of the thermal shield are circumferentially aligned with the plurality of radially-extending circumferentially-spaced tabs of the first rotor. ### Claim 6 (depends on 4) The rotor assembly as recited in claim 4, wherein the plurality of radially-extending circumferentially-spaced tabs of the thermal shield are axially trapped between the second rotor and the plurality of radially-extending circumferentially-spaced tabs of the first rotor. ### Claim 7 (depends on 1) The rotor assembly as recited in claim 1, wherein the second rotor includes an axially-facing pocket, and a portion of the thermal shield is seated in the axially-facing pocket. ### Claim 8 (depends on 1) The rotor assembly as recited in claim 1, wherein the thermal shield is a continuous ring. ### Claim 9 A gas turbine engine comprising: a first rotor; a second rotor mounted on the first rotor and co-rotatable there with; and a thermal shield interlocked with the second rotor for co-rotation there with, wherein the first rotor has a first outer diameter and the second rotor has a second outer diameter that is smaller than the first outer diameter, and the second rotor includes at least one radially-extending tab and the thermal shield includes at least one radially-extending tab circumferentially interlocked with the at least one radially-extending tab of the second rotor. ### Claim 10 A method of assembling a rotor assembly, the method comprising: interlocking a thermal shield with a second rotor for co-rotation there with, the second rotor being mounted on a first rotor and co-rotatable there with, wherein the first rotor has a first outer diameter and the second rotor has a second outer diameter that is smaller than the first outer diameter, and the second rotor includes at least one radially-extending tab and the thermal shield includes at least one radially-extending tab circumferentially interlocked with the at least one radially-extending tab of the second rotor. ### Claim 11 (depends on 10) The method as recited in claim 10, wherein the interlocking includes mounting the thermal shield on the second rotor and rotating the thermal shield to circumferentially misalign the at least one radially-extending tab on the thermal shield with the at least one radially-extending tab on the second rotor. ### Claim 12 (depends on 11) The method as recited in claim 11, wherein the at least one radially-extending tab on the thermal shield is axially offset with respect to the at least one radially-extending tab on the second rotor. ### Claim 13 (depends on 12) The method as recited in claim 12, wherein the interlocking includes moving the second rotor relative to the thermal shield to axially align, and circumferentially interlock, the at least one radially-extending tab on the thermal shield with the at least one radially-extending tab on the second rotor.