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公开(公告)号：US11215074B2
公开(公告)日：2022-01-04
申请号：US16504865
申请日：2019-07-08
Applicant: General Electric Company
Inventor： Zachary John Snider , Matthew Troy Hafner , Lyndsay Marie Kibler
Abstract: A flow regulating system for increasing a flow of cooling fluid supplied to a cooling system of a component of a gas turbine system is provided. The flow regulating system includes: a pneumatic circuit embedded within a section of the component, the pneumatic circuit including a set of interconnected pneumatic passages; and a pressure-actuated switch fluidly coupled to the pneumatic circuit. The pressure-actuated switch is activated in response to a formation of a breach in the section of the component and an exposure of at least one of the pneumatic passages of the pneumatic circuit embedded in the section of the component. The activation of the pressure-actuated switch increases the flow of cooling fluid supplied to the cooling system of the component.
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公开(公告)号：US10443437B2
公开(公告)日：2019-10-15
申请号：US15342185
申请日：2016-11-03
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Christopher Donald Porter , David Edward Schick , Lyndsay Marie Kibler
Abstract: A cooled structure of a gas turbine engine has a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and is arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and is arranged along the second side portion. The first and second set of cooling air micro-channels have turning portions positioned adjacent each other and interwoven exhaust ends originating from each opposing side micro-channel. Each interwoven exhaust end extends around the opposing turning portion and is configured to exhaust cooling air from a plurality of exhaust ports positioned generally radially outward from the turning portions.
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公开(公告)号：US11225707B2
公开(公告)日：2022-01-18
申请号：US16539803
申请日：2019-08-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Lyndsay Marie Kibler , Brendon James Leary , David Vincent Bucci
Abstract: A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.
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公开(公告)号：US20180119570A1
公开(公告)日：2018-05-03
申请号：US15342185
申请日：2016-11-03
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Christopher Donald Porter , David Edward Schick , Lyndsay Marie Kibler
CPC classification number: F01D25/12 , F01D5/187 , F01D11/08 , F02C3/04 , F05D2230/22 , F05D2230/50 , F05D2240/11 , F05D2240/128 , F05D2240/30 , F05D2240/81 , F05D2250/71 , F05D2260/204 , F05D2260/2214
Abstract: A cooled structure of a gas turbine engine has a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and is arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and is arranged along the second side portion. The first and second set of cooling air micro-channels have turning portions positioned adjacent each other and interwoven exhaust ends originating from each opposing side micro-channel. Each interwoven exhaust end extends around the opposing turning portion and is configured to exhaust cooling air from a plurality of exhaust ports positioned generally radially outward from the turning portions.
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Patent Agency Ranking
公开(公告)号：US11603764B2
公开(公告)日：2023-03-14
申请号：US17270261
申请日：2018-08-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas Earl Dyson , Joseph I Block , Brendon James Leary , Lyndsay Marie Kibler
IPC: F01D5/18
Abstract: An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the article body portion (36); and at least one internal feature (72) disposed at least partially within the article body portion (36) and at least partially within the pedestal (58A, 60A, 84, 86). At least a portion of the internal feature (72) is hollow.
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公开(公告)号：US20210010423A1
公开(公告)日：2021-01-14
申请号：US16504865
申请日：2019-07-08
Applicant: General Electric Company
Inventor： Zachary John Snider , Matthew Troy Hafner , Lyndsay Marie Kibler
Abstract: A flow regulating system for increasing a flow of cooling fluid supplied to a cooling system of a component of a gas turbine system is provided. The flow regulating system includes: a pneumatic circuit embedded within a section of the component, the pneumatic circuit including a set of interconnected pneumatic passages; and a pressure-actuated switch fluidly coupled to the pneumatic circuit. The pressure-actuated switch is activated in response to a formation of a breach in the section of the component and an exposure of at least one of the pneumatic passages of the pneumatic circuit embedded in the section of the component. The activation of the pressure-actuated switch increases the flow of cooling fluid supplied to the cooling system of the component.
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公开(公告)号：US11434767B2
公开(公告)日：2022-09-06
申请号：US16663941
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Lyndsay Marie Kibler , Brad Wilson VanTassel , Benjamin Paul Lacy , Zachary John Snider , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.
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公开(公告)号：US20210123348A1
公开(公告)日：2021-04-29
申请号：US16663941
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Lyndsay Marie Kibler , Brad Wilson VanTassel , Benjamin Paul Lacy , Zachary John Snider , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
IPC: F01D5/18
Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.
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公开(公告)号：US20210047718A1
公开(公告)日：2021-02-18
申请号：US16539803
申请日：2019-08-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Lyndsay Marie Kibler , Brendon James Leary , David Vincent Bucci
Abstract: A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.
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