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公开(公告)号：US09624784B2
公开(公告)日：2017-04-18
申请号：US13937109
申请日：2013-07-08
Applicant: General Electric Company
Inventor： Matthew Troy Hafner
CPC classification number: F01D11/001 , F01D5/3015 , F01D11/003 , F01D11/005 , F01D11/006 , F01D11/008 , Y10T29/49245
Abstract: A system includes a multi-stage turbine that includes a first turbine stage having a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel. The turbine also includes a second turbine stage having a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel. The turbine also includes a seal assembly extending axially between the first and second turbine stages. The seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first air director. The seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate comprises a second air director. The seal assembly also includes an interstage seal. The first coverplate, the second coverplate, or both are configured to support the interstage seal.
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公开(公告)号：US20160319685A1
公开(公告)日：2016-11-03
申请号：US14697765
申请日：2015-04-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Victor John Morgan , Jacob John Kittleson , Neelesh N. Sarawate
CPC classification number: F01D11/005 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/55 , F05D2260/20 , F16J15/064
Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.
Abstract translation: 本申请提供了在面向高压冷却空气流的部件发动机和燃气涡轮机中的热气体路径之间使用的密封件。 密封件可以包括第一垫片，具有空气出口孔的第二垫片，位于第一垫片和第二垫片之间的一个或多个中间层，以及延伸穿过用于高压冷却空气流的中间层的一个或多个冷却路径 通过空气出口孔流入热气路径。
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公开(公告)号：US20150010393A1
公开(公告)日：2015-01-08
申请号：US13937109
申请日：2013-07-08
Applicant: General Electric Company
Inventor： Matthew Troy Hafner
IPC: F01D11/00
CPC classification number: F01D11/001 , F01D5/3015 , F01D11/003 , F01D11/005 , F01D11/006 , F01D11/008 , Y10T29/49245
Abstract: A system includes a multi-stage turbine that includes a first turbine stage having a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel. The turbine also includes a second turbine stage having a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel. The turbine also includes a seal assembly extending axially between the first and second turbine stages. The seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first air director. The seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate comprises a second air director. The seal assembly also includes an interstage seal. The first coverplate, the second coverplate, or both are configured to support the interstage seal.
Abstract translation: 一种系统包括多级涡轮机，该多级涡轮机包括具有第一轮的第一涡轮级，该第一轮具有围绕第一车轮周向间隔开的多个第一叶片段。 涡轮机还包括具有第二轮的第二涡轮级，该第二轮具有围绕第二轮围绕圆周间隔开的多个第二叶片段。 涡轮机还包括在第一和第二涡轮级之间轴向延伸的密封组件。 密封组件包括联接到第一涡轮级的第一盖板。 第一盖板包括第一空气导向器。 密封组件还包括联接到第二涡轮级的第二盖板。 第二盖板包括第二空气导向器。 密封组件还包括级间密封。 第一盖板，第二盖板或两者被构造成支撑级间密封。
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公开(公告)号：US11724969B2
公开(公告)日：2023-08-15
申请号：US16220822
申请日：2018-12-14
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Jason Robert Parolini , Rajendra Kumar Bordia , Quan Li
CPC classification number: C04B41/4584 , C04B41/4543 , C04B41/4545 , C04B41/5031 , C04B41/5035 , C04B41/5045 , F01D5/282 , F05D2240/11 , F05D2300/603 , F05D2300/6033 , F05D2300/611
Abstract: A ceramic matrix composite (CMC) component includes at least one seal surface, the at least one seal surface disposed adjacent an interfacing surface for providing a seal therebetween; and a coating disposed on the seal surface. The coating includes an aluminum oxide and/or a silicon dioxide.
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公开(公告)号：US20230142974A1
公开(公告)日：2023-05-11
申请号：US18149858
申请日：2023-01-04
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Christopher Donald Porter , Zachary John Snider , Jeffrey Clarence Jones
CPC classification number: B22F10/00 , B22F3/1007 , B22F3/24 , B33Y80/00 , B22F10/28 , B05B12/26 , B33Y10/00
Abstract: An additively manufactured (AM) object may include a body including an opening in an exterior surface thereof, the opening having a shape and a first area at the exterior surface of the body. A mask may be positioned over the opening. The mask has the shape of the opening and a second area that is larger than the first area so as to overhang the exterior surface of the body about the opening. A plurality of support ligaments couple to the mask and the exterior surface of the body at a location adjacent to the opening to support a portion of the mask. A coating can be applied to the object, and the mask removed. The final AM object includes a plurality of ligament elements extending from the exterior surface of the body and through the coating adjacent the opening, each ligament element at least partially surrounded by the coating.
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Patent Agency Ranking
公开(公告)号：US20220220858A1
公开(公告)日：2022-07-14
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
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: 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：US20220205363A1
公开(公告)日：2022-06-30
申请号：US16663873
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Brad Wilson VanTassel , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
IPC: F01D5/18
Abstract: A coolant delivery system for a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, each independent circuit of cooling channels including a plurality of headers and a plurality of feed tubes fluidly coupling the plurality of headers to a supply of cooling fluid; and an impingement plate connected to the exterior wall of the component by the plurality of feed tubes of the independent circuits of cooling channels, wherein, in each of the plurality of independent circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes and the plurality of headers 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：US11319816B2
公开(公告)日：2022-05-03
申请号：US16787819
申请日：2020-02-11
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. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
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公开(公告)号：US20220118514A1
公开(公告)日：2022-04-21
申请号：US17073565
申请日：2020-10-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Christopher Donald Porter , Zachary John Snider , Jeffrey Clarence Jones
IPC: B22F3/105 , B22F3/10 , B22F3/24 , B23K26/066
Abstract: An additively manufactured (AM) object may include a body including an opening in an exterior surface thereof, the opening having a shape and a first area at the exterior surface of the body. A mask may be positioned over the opening. The mask has the shape of the opening and a second area that is larger than the first area so as to overhang the exterior surface of the body about the opening. A plurality of support ligaments couple to the mask and the exterior surface of the body at a location adjacent to the opening to support a portion of the mask. A coating can be applied to the object, and the mask removed. The final AM object includes a plurality of ligament elements extending from the exterior surface of the body and through the coating adjacent the opening, each ligament element at least partially surrounded by the coating.
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公开(公告)号：US11174738B1
公开(公告)日：2021-11-16
申请号：US16868165
申请日：2020-05-06
Applicant: General Electric Company
Inventor： Zachary John Snider , Matthew Troy Hafner , Jeffrey Clarence Jones
Abstract: Aspects of the embodiments set forth a sacrificial plug system including a component having a surface and at least one cooling hole in the surface; a sacrificial plug integrally formed with the component and integrally formed in the at least one cooling hole, where the sacrificial plug includes a top portion; a cover portion; and a bottom portion, the bottom portion integrally formed, engaged to, and connected to at least one cooling hole. The sacrificial plug system also includes at least one connective member integrally formed with the bottom portion of the sacrificial plug and integral with an inner wall of each respective at least one cooling hole; each at least one connective member being severable from the respective inner wall when a force is applied to the top portion, thus permitting the sacrificial plug to be removed from the at least one respective cooling hole.
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