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公开(公告)号：US20150198062A1
公开(公告)日：2015-07-16
申请号：US14151859
申请日：2014-01-10
Applicant: General Electric Company
Inventor： Victor John Morgan , Joseph Fagan
IPC: F01D25/12
CPC classification number: F01D25/12 , F01D5/186 , F01D5/20 , F05D2300/50212
Abstract: The present application thus provides a turbine component for use in a hot gas path of a gas turbine engine. The turbine component may include an outer surface, an internal cooling circuit, an adaptive cooling pathway in communication with the internal cooling circuit and extending through the outer surface, and a cooling plug having two or more materials positioned within the adaptive cooling pathway.
Abstract translation: 因此，本申请提供了一种在燃气涡轮发动机的热气路径中使用的涡轮机部件。 涡轮机部件可以包括外表面，内部冷却回路，与内部冷却回路连通并延伸穿过外表面的自适应冷却通道，以及具有位于自适应冷却通路内的两个或多个材料的冷却塞。
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公开(公告)号：US20150098808A1
公开(公告)日：2015-04-09
申请号：US14049020
申请日：2013-10-08
Applicant: General Electric Company
Inventor： Victor John Morgan , Gregory Thomas Foster , Neelesh Nandkumar Sarawate , David Wayne Weber
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D9/041 , F01D11/003 , F05D2230/60 , F05D2260/38 , Y10T29/4932
Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
Abstract translation: 提供了一种在燃气轮机内的部件之间进行密封的方法和系统。 限定在第一部件中的第一凹部接收密封构件。 限定在与第一部件相邻的第二部件中的第二凹部也接收密封部件。 第一和第二凹槽位于通过燃气涡轮机限定的热气路径附近，并限定围绕涡轮机轴线的圆周路径。 密封构件包括沿基本上平行于涡轮机轴线的方向延伸的密封面。 密封构件还包括多个密封层，其中至少一个密封层包括用于促进第一密封构件弯曲的至少一个应力释放区域。
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公开(公告)号：US11773739B2
公开(公告)日：2023-10-03
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
CPC classification number: F01D11/005 , F16J15/0887 , F23R3/46 , F05D2240/35 , F05D2240/55 , F23R2900/00012
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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公开(公告)号：US11352886B2
公开(公告)日：2022-06-07
申请号：US16754302
申请日：2017-10-13
Applicant: General Electric Company
Inventor： James Albert Tallman , Andrew Philip Shapiro , Gary Michael Itzel , Curtis Alan Johnson , Victor John Morgan , Jacob John Kittleson , Bradley Thomas Richards
Abstract: A component includes an outer wall that includes an exterior surface, and at least one plenum defined interiorly to the outer wall and configured to receive a cooling fluid therein. The component also includes a coating system disposed on the exterior surface. The coating system has a thickness. The component further includes a plurality of adaptive cooling openings defined in the outer wall. Each of the adaptive cooling openings extends from a first end inflow communication with the at least one plenum, outward through the exterior surface and to a second end covered underneath at least a portion of the thickness of the coating system.
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公开(公告)号：US11231175B2
公开(公告)日：2022-01-25
申请号：US16012412
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Sezer , Neelesh Nandkumar Sarawate , Deepak Trivedi
Abstract: An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.
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Patent Agency Ranking
公开(公告)号：US11047248B2
公开(公告)日：2021-06-29
申请号：US16012380
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim 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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公开(公告)号：US20180347442A1
公开(公告)日：2018-12-06
申请号：US15609550
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Victor John Morgan
CPC classification number: F01D5/186 , F01D5/187 , F01D5/288 , F05D2260/202 , F05D2270/46
Abstract: A hot gas path component of an industrial machine includes a cooling pathway with a lattice structure therein. The component and lattice structure are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; a thermal barrier coating over the outer surface; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. A lattice structure is in the cooling pathway at the outer surface. The lattice structure is configured to support the thermal barrier coating over the cooling pathway and in response to a spall in the thermal barrier coating occurring over the cooling pathway, allow a cooling medium from the internal cooling circuit to pass therethrough.
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公开(公告)号：US20180347371A1
公开(公告)日：2018-12-06
申请号：US15609576
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Victor John Morgan
CPC classification number: F01D9/065 , B22F5/04 , F01D9/023 , F02K1/822 , F05D2230/31 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F05D2270/3032 , F23R3/002 , F23R3/06 , F23R2900/00018
Abstract: A hot gas path component of an industrial machine includes an adaptive cover for a cooling pathway. The component and adaptive cover are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. The adaptive cover is positioned in the cooling pathway at the outer surface. The adaptive cover may include a heat transfer enhancing surface at the outer surface causing the adaptive cover to absorb heat faster than the outer surface.
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公开(公告)号：US20180320536A1
公开(公告)日：2018-11-08
申请号：US15585326
申请日：2017-05-03
Applicant: General Electric Company
Inventor： John Franklin Ryman , Victor John Morgan , Mary Virginia Holloway
IPC: F01D9/04
CPC classification number: F01D9/041 , F05D2220/32 , F05D2240/12 , F05D2250/74
Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US10012091B2
公开(公告)日：2018-07-03
申请号：US14818695
申请日：2015-08-05
Applicant: General Electric Company
Inventor： Victor John Morgan , George Andrew Gergely , Frederic Woodrow Roberts, Jr. , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , B23P15/02 , F01D9/065 , F05D2240/81 , F05D2250/314 , F05D2250/75 , F05D2260/2212 , F05D2260/2214
Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.
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