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公开(公告)号：US10472973B2
公开(公告)日：2019-11-12
申请号：US15174271
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.
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公开(公告)号：US10150188B1
公开(公告)日：2018-12-11
申请号：US15668993
申请日：2017-08-04
Applicant: GENERAL ELECTRIC COMPANY
IPC: B05D3/02 , B05D5/00 , B22F3/26 , B23P6/04 , C23C6/00 , C04B35/14 , C23C26/02 , C04B35/565 , C04B35/653
Abstract: A method of treating a ceramic matrix composite article, including selecting an article having a ceramic composition formed by a process comprising an initial melt infiltration at an initial temperature with an initial infiltration material, whereby said article has at least one treatable feature. A portion of the ceramic composite is removed from a region abutting the treatable feature to form a treatment region. A treatment material including a reinforcing fiber is positioned in the treatment region and densified by a first melt infiltration with a first infiltration material including silicon. The first melt infiltration is performed at a first temperature lower than the initial infiltration temperature of the initial melt infiltration.
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公开(公告)号：US09945244B2
公开(公告)日：2018-04-17
申请号：US14825636
申请日：2015-08-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Frederic Woodrow Roberts , Victor John Morgan , Matthew Troy Hafner
CPC classification number: F01D11/22 , F05D2240/11 , F05D2260/50 , F05D2300/6033
Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.
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公开(公告)号：US09605553B2
公开(公告)日：2017-03-28
申请号：US13937121
申请日：2013-07-08
Applicant: General Electric Company
Inventor： Matthew Troy Hafner
CPC classification number: F01D11/008 , F01D5/3015 , F05D2230/60 , F05D2240/55 , Y10T29/49245
Abstract: A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage with a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage with a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal assembly extending axially between the first and second turbine stages. The interstage seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first seal. The interstage seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate includes a second seal. The interstage seal assembly also includes a spacer wheel extending from a rotor shaft and configured to engage with the first coverplate and the second coverplate.
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公开(公告)号：US20160208633A1
公开(公告)日：2016-07-21
申请号：US14597772
申请日：2015-01-15
Applicant: General Electric Company
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D25/246 , F05D2230/60 , F05D2230/90 , F05D2240/11 , F05D2300/6033 , F05D2300/611
Abstract: A turbine shroud assembly includes a plurality of arcuate shroud block assemblies annularly arranged to form a shroud segment. The plurality of shroud block assemblies includes a first shroud block assembly having a shroud block and a second shroud block assembly having a shroud block. The first shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the first shroud block. The second shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the second shroud block.
Abstract translation: 涡轮机罩组件包括多个弓形护罩块组件，其环形地设置成形成护罩段。 多个护罩块组件包括具有护罩块的第一护罩块组件和具有护罩块的第二护罩块组件。 第一护罩块组件包括密封接口构件和护罩密封件。 密封接口构件具有与第一护罩块的径向侧表面相邻的侧部。 第二护罩块组件包括密封接口构件和护罩密封件。 密封接口构件具有与第二护罩块的径向侧表面相邻的侧部。
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Patent Agency Ranking
公开(公告)号：US09297271B2
公开(公告)日：2016-03-29
申请号：US13872657
申请日：2013-04-29
Applicant: General Electric Company
Inventor： Matthew Troy Hafner
CPC classification number: F01D17/08 , F01D11/20 , Y10T29/49316
Abstract: A turbine blade monitoring arrangement includes a bucket tip located at a radial outer location of a bucket. Also included is at least one component disposed radially outwardly of the bucket tip. Further included is a hollow portion of the at least one component, wherein the hollow portion extends radially from a first end to a second end through the at least one component. Yet further included is a first sealing component operatively coupled to the at least one component proximate the first end of the hollow portion, wherein the first sealing component comprises a translucent material. Also included is a proximity sensor disposed radially outwardly of the at least one component and aligned with the hollow portion, the proximity sensor configured to generate a first signal through the hollow portion to the bucket tip.
Abstract translation: 涡轮叶片监控装置包括位于铲斗的径向外部位置的铲斗前端。 还包括设置在铲斗前端的径向外侧的至少一个部件。 还包括至少一个部件的中空部分，其中中空部分从第一端径向延伸穿过至少一个部件到第二端。 还包括第一密封部件，其可操作地联接到靠近中空部分的第一端部的至少一个部件，其中第一密封部件包括半透明材料。 还包括接近传感器，其设置在至少一个部件的径向外侧并与中空部分对准，该接近传感器被配置成通过中空部分产生到铲斗前端的第一信号。
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公开(公告)号：US20240026795A1
公开(公告)日：2024-01-25
申请号：US17868911
申请日：2022-07-20
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John M. Matthews , Zachary John Snider
CPC classification number: F01D5/188 , F01D9/041 , F01D9/044 , F05D2230/237 , F05D2240/81 , F05D2260/201 , F05D2260/2214
Abstract: A stator vane includes a platform that defines an opening. The stator vane further includes an airfoil that has a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. At least one of the base or the tip includes a protrusion. The protrusion extends into the opening of the platform such that the platform surrounds the protrusion of the airfoil. The stator vane further includes a braze joint disposed between and fixedly coupling the platform and the protrusion of the airfoil. The stator vane further includes a cooling circuit defined in at least one of the protrusion or the platform to cool the braze joint.
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公开(公告)号：US11466581B1
公开(公告)日：2022-10-11
申请号：US17323354
申请日：2021-05-18
Applicant: General Electric Company
Inventor： Zachary John Snider , Adam John Fredmonski , Matthew Troy Hafner
Abstract: A turbine nozzle assembly system includes a plurality of nozzle sets, where each nozzle set forms an annulus. The nozzles in each set include an inner endwall and an outer endwall that include joint openings to receive the respective endwall mount ends of an airfoil. The airfoils across the plurality of nozzle sets have an inner endwall mount end and an outer endwall mount end that are identical amongst the plurality of nozzle sets. A wing portion of the airfoil has a selected wing shape that is identical within the respective nozzle set but different amongst the plurality of nozzle sets. In this manner, the endwalls can be removed from an airfoil and replaced with an airfoil having a different wing shape that provides a different pairwise throat area. The system allows changing of a pairwise throat area for a nozzle set without replacing the entirety of each nozzle.
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公开(公告)号：US11454133B2
公开(公告)日：2022-09-27
申请号：US16663912
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Brad Wilson VanTassel , 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: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, wherein the plurality of circuits of cooling channels are interwoven together; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling each of the plurality of circuits of cooling channels to at least one supply of cooling fluid, wherein, in each of the plurality of circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes into the 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 of the circuit of cooling channels.
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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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