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公开(公告)号：US20190383156A1
公开(公告)日：2019-12-19
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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42.发明授权公开(公告)号：US10260358B2
公开(公告)日：2019-04-16
申请号：US14926718
申请日：2015-10-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson , Victor John Morgan
IPC: F01D5/28 , F23R3/00 , C04B35/80 , C23C16/44 , F01D9/02 , F01D11/08 , F01D25/00 , F23R3/42 , B32B18/00 , C04B35/117 , C04B35/185 , C04B35/563 , C04B35/565 , C04B35/573 , C04B35/583 , C04B35/597 , C04B35/638 , F01D5/18 , F01D9/06 , F01D11/24
Abstract: A process of producing a ceramic matrix composite component. The process includes positioning a plurality of ceramic matrix composite plies on top of one another and forming a cavity therein. At least a portion of the cavity includes a terminal diameter sufficiently small to permit infiltration of a densifying material. The plurality of ceramic matrix composite plies are densified to form a densified body. The densifying results in the portion of the cavity including the terminal diameter being filled with densifying material and 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：US20180347378A1
公开(公告)日：2018-12-06
申请号：US15609529
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan , Stephen William Tesh
CPC classification number: F01D5/189 , F01D5/186 , F01D5/187 , F01D5/288 , F02B29/0456 , F05D2260/204 , F05D2260/84 , F05D2300/611
Abstract: A hot gas path component of an industrial machine includes a cooling pathway. The component includes a body including an outer surface; a thermal barrier coating (TBC) over the outer surface, the TBC exposed to a working fluid having a high temperature; and an internal cooling circuit in the body carrying a cooling medium. A cooling pathway is in the body and in fluid communication with the internal cooling circuit. The cooling pathway includes a terminating end in the body and a length extending along and spaced internally from the outer surface by a first spacing. In response to a spall in the TBC occurring at a location over the cooling pathway and the high temperature reaching or exceeding a predetermined temperature of the body, the cooling pathway opens at the location through the first spacing to allow a flow of the cooling medium therethrough.
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公开(公告)号：US20180087390A1
公开(公告)日：2018-03-29
申请号：US15275570
申请日：2016-09-26
Applicant: General Electric Company
CPC classification number: F01D9/023 , F02C3/04 , F05D2220/32 , F05D2240/128 , F05D2240/35 , F05D2260/52 , F16J15/0887
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：US09903218B2
公开(公告)日：2018-02-27
申请号：US14827698
申请日：2015-08-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Victor John Morgan , Frederic Woodrow Roberts
CPC classification number: F01D11/22 , F01D11/14 , F01D11/20 , F01D25/005 , F01D25/04 , F01D25/08 , F05D2220/32 , F05D2240/11 , F05D2260/52 , F05D2260/96 , F05D2300/17 , F05D2300/171 , F05D2300/502 , 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, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.
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Patent Agency Ranking
公开(公告)号：US09784123B2
公开(公告)日：2017-10-10
申请号：US14151859
申请日：2014-01-10
Applicant: General Electric Company
Inventor： Victor John Morgan , Joseph Fagan
CPC classification number: F01D25/12 , F01D5/186 , F01D5/20 , F05D2300/50212
Abstract: 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.
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公开(公告)号：US09784116B2
公开(公告)日：2017-10-10
申请号：US14597772
申请日：2015-01-15
Applicant: General Electric Company
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.
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公开(公告)号：US09771819B2
公开(公告)日：2017-09-26
申请号：US14963735
申请日：2015-12-09
Applicant: General Electric Company
CPC classification number: F01D11/005 , F01D25/005 , F01D25/24 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/14 , F05D2240/55 , F05D2240/57 , F05D2300/502 , F16J15/0825 , F16J15/0887
Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arc segment adjacent to a second arc segment, each arc segment including an end surface and radially facing surfaces extending from opposite ends of the end surface; a slot located between the end surfaces of the first arc segment and the second arc segment; and a first seal disposed in the slot, the first seal contacting the first arc segment at the end surface and extending over the radially facing surfaces of the first arc segment, the first seal including: a shim contacting the first arc segment; a laminate material over the shim and covering the shim; and a conforming material coupling the laminate material to the shim.
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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：US20160237912A1
公开(公告)日：2016-08-18
申请号：US14623570
申请日：2015-02-17
Applicant: General Electric Company
Inventor： Kevin Richard Kirtley , Victor John Morgan
IPC: F02C7/28
CPC classification number: F02C7/28 , F01D11/00 , F01D11/001 , F01D11/005 , F05D2240/11 , F05D2240/55 , F16J15/02
Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a gas turbine segment seal assembly may include a first tapered segment seal with a first tapered portion having a first tapered surface and a first taper angle. The gas turbine segment seal assembly may include a second tapered segment seal with a second tapered portion having a second tapered surface and a second taper angle. The gas turbine segment seal assembly may include a seal pin positioned in between the first tapered segment seal and the second segment seal and adjacent to the first tapered surface and the second tapered surface.
Abstract translation: 本申请和所得专利提供改进的燃气轮机部件密封。 在一个示例性实施例中，燃气涡轮机段密封组件可以包括具有第一锥形部分的第一锥形段密封件，该第一锥形部分具有第一锥形表面和第一锥形角度。 燃气轮机段密封组件可以包括具有第二锥形部分的第二锥形段密封件，第二锥形部分具有第二锥形表面和第二锥形角度。 燃气轮机段密封组件可以包括位于第一锥形段密封件和第二段密封件之间并且紧邻第一锥形表面和第二锥形表面的密封销。
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