# US 8,784,061 B2 · Methods and systems for controlling thermal differential in turbine systems > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,784,061 B2 - Document ID: US8784061B2 - Status: Granted - Kind: B2 - Application number: 13/017,758 - Filed: 2011-01-31 - Published: 2012-08-02 - Granted: 2014-07-22 - Earliest claimed: 2011-01-31 - Assignees: General Electric Company - Applicants: Narendra Are; Roger Clayton Walker; Matthew Ryan Ferslew; Matthew Paul Forcier - Inventors: Narendra Are; Roger Clayton Walker; Matthew Ryan Ferslew; Matthew Paul Forcier - Web page: https://patentgrep.com/patent/US8784061B2 ## CPC - F01D 5/08: Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)} - F05D 2230/90: Coating; Surface treatment - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Method and system are provided for controlling a thermal differential within a turbine rotor for use with a turbine system. A thermal barrier coating is applied to a surface of the turbine rotor. The surface is proximate to a wheel rim of the turbine rotor. ## Claims ### Claim 1 A method for controlling a thermal differential within a compressor of a gas turbine system, said method comprising: selecting one or more surfaces of a plurality of rotors of the compressor, wherein at least one of the surfaces selected is proximate to a wheel rim of a rotor of the plurality of rotors and at least one of within a loading location defined within the rotor and radially inward from the wheel rim; and applying a thermal barrier coating to the one or more surfaces of the plurality of rotors to facilitate reducing a transient heat transfer rate during startup. ### Claim 2 (depends on 1) A method in accordance with claim 1, wherein applying a thermal barrier coating further comprises applying the thermal barrier coating with a thickness of less than approximately 0.04 inches. ### Claim 3 (depends on 1) A method in accordance with claim 1, wherein selecting a surface further comprises selecting a disc, and wherein applying a thermal barrier coating further comprises applying the thermal barrier coating to at least the disc. ### Claim 4 (depends on 1) A method in accordance with claim 1, wherein selecting a surface further comprises selecting a slot defined within a compressor, and wherein applying a thermal barrier coating further comprises applying the thermal barrier coating within at least the slot. ### Claim 5 (depends on 1) A method in accordance with claim 1, wherein selecting a surface further comprises selecting a plurality of discs and an aft section positioned downstream of the plurality of discs, and wherein applying a thermal barrier coating further comprises applying the thermal barrier coating to at least the aft section. ### Claim 6 (depends on 1) A method in accordance with claim 1, wherein selecting a surface further comprises selecting the surface within a portion of a compressor. ### Claim 7 (depends on 1) A method in accordance with claim 1, wherein the surface selected is not directly exposed to a primary hot gas path defined within the turbine system. ### Claim 8 A plurality of rotors for use within a compressor of a gas turbine system, or each rotor of said plurality of rotors comprising: one or more surfaces proximate to a wheel rim of said compressor rotor, wherein said surface is at least one of within a loading location defined within the compressor rotor and radially inward from the wheel rim; and a thermal barrier coating applied to said one or more surfaces to facilitate reducing a transient heat transfer rate during startup. ### Claim 9 (depends on 8) A plurality of rotors in accordance with claim 8, wherein said thermal barrier coating has a thickness of less than approximately 0.04 inches. ### Claim 10 (depends on 8) A plurality of rotors in accordance with claim 8 further comprising a disc, wherein said surface is positioned on said disc. ### Claim 11 (depends on 8) A plurality of rotors in accordance with claim 8 further comprising a circumferential slot defined within said turbine rotor, wherein said surface is positioned within said circumferential slot. ### Claim 12 (depends on 8) A plurality of rotors in accordance with claim 8 further comprising a plurality of discs and an aft section positioned downstream of said plurality of discs, wherein said surface is positioned on said aft section. ### Claim 13 (depends on 8) A plurality of rotors in accordance with claim 8 further comprising a radial slot defined within said turbine rotor, wherein said surface is positioned within said radial slot. ### Claim 14 (depends on 8) A turbine rotor in accordance with claim 8, wherein said surface is not directly exposed to a primary hot gas path defined within the turbine system. ### Claim 15 A gas turbine system comprising a compressor, said compressor comprising: a plurality of rotors, each rotor comprising one or more surfaces, wherein at least one of the surfaces is proximate to a wheel rim of said rotor and is at least one of within a loading location defined within the rotor and radially inward from the wheel rim; and a thermal barrier coating applied to the one or more surfaces of the plurality of rotors to facilitate reducing a transient heat transfer rate during startup. ### Claim 16 (depends on 15) A turbine system in accordance with claim 15, wherein said thermal barrier coating has a thickness of less than approximately 0.04 inches. ### Claim 17 (depends on 15) A turbine system in accordance with claim 15, wherein said turbine rotor further comprises a disc, wherein said surface is positioned on said disc. ### Claim 18 (depends on 15) A turbine system in accordance with claim 15, wherein said turbine rotor further comprises a slot defined within said turbine rotor, wherein said surface is positioned within said slot. ### Claim 19 (depends on 15) A turbine system in accordance with claim 15, wherein said turbine rotor further comprises an aft section positioned downstream of a plurality of discs of said turbine rotor, wherein said surface is positioned on said aft section. ### Claim 20 (depends on 15) A turbine system in accordance with claim 15, wherein the surface is not directly exposed to a primary hot gas path defined within the turbine system.