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公开(公告)号：US20170276363A1
公开(公告)日：2017-09-28
申请号：US15464443
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Kevin Weston McMahan
IPC: F23R3/28
Abstract: A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. An aft end portion of the fuel injection panel defines a turbine nozzle. One or more hook plates attached to the outer surfaces of the liner segments are used to mount the integrated combustor nozzle to an inner mounting ring or an outer mounting ring. A mounting strut or mounting tenon(s) attached to the liner segments may also be employed.
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公开(公告)号：US20170276071A1
公开(公告)日：2017-09-28
申请号：US15079116
申请日：2016-03-24
Applicant: General Electric Company
Inventor： James Scott Flanagan , Kevin Weston McMahan , Jeffrey Scott LeBegue
CPC classification number: F02C7/222 , F01D5/02 , F01D9/023 , F05D2220/32 , F05D2270/08 , F23R3/346 , F23R3/46
Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each transition duct includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. Each transition duct further includes an upstream portion and a downstream portion. The turbomachine further includes a late injection assembly disposed between the upstream portion and the downstream portion of a transition duct and which provides fluid communication for an injection fluid to flow into the interior downstream of the inlet of the transition duct. The late injection assembly includes a late injection ring.
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公开(公告)号：US20170276001A1
公开(公告)日：2017-09-28
申请号：US15079083
申请日：2016-03-24
Applicant: General Electric Company
Inventor： Kevin Weston McMahan , Jeffrey Scott LeBegue , James Scott Flanagan
CPC classification number: F01D9/023 , F01D11/003 , F01D11/005 , F01D25/265 , F01D25/28 , F05D2220/32 , F05D2240/55 , F05D2260/30 , F05D2260/31
Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array and including a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly.
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公开(公告)号：US09649690B2
公开(公告)日：2017-05-16
申请号：US14189734
申请日：2014-02-25
Applicant: General Electric Company
Inventor： Kevin Weston McMahan , Geoffrey David Myers
IPC: B22F7/02 , B22F3/105 , B23K15/00 , B32B15/01 , F01D5/28 , F01D25/00 , F01D5/14 , F01D9/02 , F01D9/04 , F04D29/02 , F04D29/32 , F23K5/00 , F23R3/00 , B23K26/32 , B23K26/342 , B32B7/02 , F23M5/00 , B22F5/00 , B22F7/06 , B33Y10/00 , B33Y80/00 , B23K101/00 , B23K103/08 , B29C67/00 , B23K103/14 , B23K103/04 , B23K103/18
CPC classification number: F23R3/286 , B22F3/1055 , B22F5/009 , B22F5/04 , B22F7/008 , B22F7/02 , B22F7/06 , B22F2207/17 , B22F2301/15 , B22F2301/205 , B22F2301/35 , B22F2998/10 , B23K15/0086 , B23K15/0093 , B23K26/0006 , B23K26/32 , B23K26/342 , B23K2101/001 , B23K2103/05 , B23K2103/08 , B23K2103/14 , B23K2103/166 , B23K2103/24 , B23K2103/26 , B28B1/001 , B29C64/153 , B32B7/02 , B32B15/01 , B32B2264/105 , B32B2307/102 , B32B2307/304 , B32B2603/00 , B32B2605/18 , B33Y10/00 , B33Y80/00 , F01D5/147 , F01D5/28 , F01D9/023 , F01D9/041 , F01D25/005 , F04D29/023 , F04D29/324 , F05D2230/22 , F05D2230/31 , F05D2300/10 , F05D2300/6111 , F23K5/00 , F23M5/00 , F23M2900/05004 , F23R3/00 , F23R3/002 , F23R2900/00018 , Y02P10/295 , Y10T428/12028
Abstract: A system includes a layered structure. The layered structure includes first and second coalesced layers and an intermediate layer disposed between the first and second coalesced layers. The first and second coalesced layers have a higher degree of coalescence than the intermediate layer.
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公开(公告)号：US09546601B2
公开(公告)日：2017-01-17
申请号：US13681453
申请日：2012-11-20
Applicant: General Electric Company
Inventor： Won-Wook Kim , Kevin Weston McMahan , Shiva Kumar Srinivasan
CPC classification number: F02C7/24 , F23C5/08 , F23R3/46 , F23R2900/00014
Abstract: The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation.
Abstract translation: 本申请提供了一种用于燃气涡轮发动机中的相干减少的时钟燃烧室阵列。 时钟式燃烧室阵列可以包括定位在圆周阵列中的多个燃烧器罐。 燃烧器罐的第一组可以具有第一取向，并且第二组燃烧器罐可具有第二取向。
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Patent Agency Ranking
公开(公告)号：US09360220B2
公开(公告)日：2016-06-07
申请号：US13669479
申请日：2012-11-06
Applicant: General Electric Company
Inventor： Wei Chen , Kevin Weston McMahan , Gregory Allen Boardman , Jerome David Brown
CPC classification number: F23R3/286 , F23D11/40 , F23D11/402 , F23D14/02 , F23D14/08 , F23D14/10 , F23D14/105 , F23D14/62 , F23D2900/14021
Abstract: The present application provides a micro-mixer combustion nozzle for mixing a flow of fuel and a flow of air in a gas turbine engine. The micro-mixer combustion nozzle may include a fuel plate with a number of fuel plate apertures and a fuel plate passage in communication with the flow of fuel and an air plate with a number of air plate apertures and an air plate passage in communication with the flow of air. The fuel plate passage and the air plate passage may align to mix in part the flow of fuel and the flow of air.
Abstract translation: 本申请提供了一种用于混合燃气流和燃气涡轮发动机中的空气流的微混合器燃烧喷嘴。 微型混合器燃烧喷嘴可以包括具有多个燃料板孔的燃料板和与燃料流连通的燃料板通道和具有多个气板孔的空气板和与该空气板通道连通的空气板通道 空气流动 燃料板通道和空气板通道可以对齐以部分地混合燃料流和空气流。
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公开(公告)号：US20140000263A1
公开(公告)日：2014-01-02
申请号：US14015322
申请日：2013-08-30
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Kevin Weston McMahan , Carl Robert Barker
IPC: F23R3/10
Abstract: A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.
Abstract translation: 一种包括燃料喷嘴的系统。 燃料喷嘴包括安装基座和沿着下游方向从安装基座直接延伸的入口流动调节器。 此外，入口流动调节器结构地支撑燃料喷嘴，而没有直接从入口流动调节器内的安装基座延伸的中心支撑构件。
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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：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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公开(公告)号：US11137143B2
公开(公告)日：2021-10-05
申请号：US15595760
申请日：2017-05-15
Applicant: General Electric Company
Inventor： Kevin Weston McMahan , Geoffrey David Myers
IPC: B22F5/04 , B22F10/20 , B33Y10/00 , F23R3/28 , B23K15/00 , F01D5/14 , F01D9/02 , F01D9/04 , F04D29/02 , F04D29/32 , F23K5/00 , F23R3/00 , B23K26/32 , B23K26/342 , B32B7/02 , F23M5/00 , B22F5/00 , B22F7/06 , B33Y80/00 , B32B15/01 , F01D5/28 , F01D25/00 , B22F7/02 , B22F7/00 , B23K26/00 , B28B1/00 , B23K101/00 , B23K103/04 , B23K103/08 , B23K103/14 , B23K103/24 , B23K103/18 , B23K103/16 , B29C64/153
Abstract: A system includes a layered structure. The layered structure includes first and second coalesced layers and an intermediate layer disposed between the first and second coalesced layers. The first and second coalesced layers have a higher degree of coalescence than the intermediate layer.
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