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公开(公告)号：US09617859B2
公开(公告)日：2017-04-11
申请号：US13645729
申请日：2012-10-05
Applicant: General Electric Company
Inventor： Victor John Morgan , Stephen Gerard Pope , Jacob Kittleson , Lawrence Matthew Levy
CPC classification number: F01D5/18 , F01D5/186 , F01D5/187 , F05D2230/10 , F05D2230/50 , F05D2300/611
Abstract: The present application provides a turbine component for use in a hot gas path of a gas turbine. The turbine component may include an outer surface, an internal cooling circuit, a number of cooling pathways in communication with the internal cooling circuit and extending through the outer surface, and a number of adaptive cooling pathways in communication with the internal cooling circuit and extending through the outer surface. The adaptive cooling pathways may include a high temperature compound therein.
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22.发明申请SHIM SEAL ASSEMBLIES AND ASSEMBLY METHODS FOR STATIONARY COMPONENTS OF ROTARY MACHINES 审中-公开旋转机械静态组件的SHIM密封组件和组装方法公开(公告)号：US20160215643A1
公开(公告)日：2016-07-28
申请号：US15089706
申请日：2016-04-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
CPC classification number: F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2250/12 , F05D2250/75 , F16J15/0812 , F16J15/0893 , F16J15/128
Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes a shim seal including multiple seal plates forming a box shaped shim seal. The box shaped seal includes a plurality of cuts at two opposing sides or corners for allowing high pressure fluid to occupy the cavity of the box-shaped shim seal. The seal may be inserted within one or more slots between adjacent stator components of the rotary machine.
Abstract translation: 提供了一种用于旋转机器的密封组件。 密封组件包括垫片密封件，该密封件包括形成盒形垫片密封件的多个密封板。 箱形密封件包括在两个相对的侧面或拐角处的多个切口，用于允许高压流体占据箱形垫片密封件的空腔。 密封件可以插入在旋转机器的相邻定子部件之间的一个或多个槽内。
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公开(公告)号：US20140348642A1
公开(公告)日：2014-11-27
申请号：US13875370
申请日：2013-05-02
Applicant: General Electric Company
Inventor： David Wayne Weber , Victor John Morgan , Neelesh Nandkumar Sarawate
CPC classification number: F01D11/005 , F05D2240/11 , F05D2240/59 , F05D2250/75
Abstract: A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer.
Abstract translation: 公开了一种包括用于减少燃气涡轮机中的间隙间隙（例如，成角度间隙，“L'形间隙等”）泄漏的结合层压体界面密封件的装置。 在一个实施例中，一种用于燃气涡轮机的密封装置包括：第一凸缘，其被成形为设置在第一弓形部件的第一槽内和第二弧形部件的第一相邻狭槽内; 连接到所述第一凸缘的第一表面的连接层，所述第一表面被配置为面对所述燃气轮机的工作流体流; 以及第二凸缘，其被成形为设置在所述第一弓形部件的第二狭槽内以及所述第二弓形部件的第二相邻狭槽中，所述第二凸缘包括连接到所述连结层的第二表面。
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公开(公告)号：US20140091531A1
公开(公告)日：2014-04-03
申请号：US13633891
申请日：2012-10-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Victor John Morgan , David Wayne Weber
CPC classification number: F01D11/005 , F01D25/12 , F05D2240/55 , F05D2260/20 , F16J15/027 , F16J15/0812 , F16J15/0825
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：US20210324754A1
公开(公告)日：2021-10-21
申请号：US17358691
申请日：2021-06-25
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Klara Sezer , Deepak Trivedi
Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.
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Patent Agency Ranking
公开(公告)号：US10830069B2
公开(公告)日：2020-11-10
申请号：US15275570
申请日：2016-09-26
Applicant: General Electric Company
Abstract: A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.
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公开(公告)号：US10794197B2
公开(公告)日：2020-10-06
申请号：US15623842
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joshua Lee Margolies , Victor John Morgan , Matthew Troy Hafner
Abstract: A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate including a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.
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28.发明授权公开(公告)号：US10465533B2
公开(公告)日：2019-11-05
申请号：US14878084
申请日：2015-10-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Victor John Morgan , Jacob John Kittleson , Andres Jose Garcia-Crespo , Benjamin Paul Lacy
IPC: F01D5/28 , C23C16/44 , F01D9/02 , F01D25/00 , B32B18/00 , C04B35/573 , C04B35/626 , C04B35/80
Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.
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公开(公告)号：US10436048B2
公开(公告)日：2019-10-08
申请号：US15236083
申请日：2016-08-12
Applicant: General Electric Company
Inventor： Brian Gene Brzek , Victor John Morgan , James Fredric Wiedenhoefer
IPC: F01D9/06
Abstract: An airfoil for turbomachines includes a first plurality of projections coupled to a suction sidewall adjacent a trailing edge and extending from the suction sidewall towards a pressure sidewall. A second plurality of projections is coupled to the pressure sidewall adjacent the trailing edge and extending from the pressure sidewall towards the suction sidewall. The airfoil includes a divider coupled to the first and second pluralities of projections and extending within a space between the first and second pluralities of projections. A first cooling channel is defined adjacent the suction sidewall and a second cooling channel is defined adjacent the pressure sidewall. The first and second cooling channels are configured to receive a coolant stream. The first plurality of projections is configured to meter the coolant stream through the first cooling channel and the second plurality of projections is configured to meter the coolant stream through the second cooling channel.
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公开(公告)号：US20190203606A1
公开(公告)日：2019-07-04
申请号：US15862520
申请日：2018-01-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Neelesh Nandkumar Sarawate , Christopher Edward Wolfe , Victor John Morgan , Jason Ray Gregg
CPC classification number: F01D11/005 , F01D9/041 , F05D2220/32 , F05D2230/60 , F05D2240/55
Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.
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