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公开(公告)号：US09360221B2
公开(公告)日：2016-06-07
申请号：US14081062
申请日：2013-11-15
Applicant: General Electric Company
Inventor： Jesse Blair Butler , David Leach , Kevin Weston McMahan , Mark Allan Hadley , Geoffrey David Myers
CPC classification number: F23R3/286 , F23C2900/07001 , F23D2900/14004 , F23D2900/14701 , F23R3/14
Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.
Abstract translation: 燃气轮机包括压缩机和至少一个在压缩机下游的燃烧器。 所述燃烧器包括燃烧器，所述燃烧器具有沿所述燃烧器的至少一部分轴向延伸的内罩，所述外护罩与所述内护罩径向分离并且沿着所述燃烧器的至少一部分轴向延伸;以及多个定子叶片， 内护罩和外护罩。 定子叶片具有靠近内护罩的内端和靠近外护罩的外端。 燃烧器还包括在定子叶片的内端或外端之一处的涡流尖端。 涡流尖端在内端和内护罩或外端和外护罩之间提供间隙，并且涡流尖端包括多个燃料口。 燃气轮机还包括从燃烧器下游的涡轮机。
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公开(公告)号：US09291103B2
公开(公告)日：2016-03-22
申请号：US13705443
申请日：2012-12-05
Applicant: General Electric Company
Inventor： Keith Cletus Belsom , Kevin Weston McMahan , Larry Lou Thomas
Abstract: A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.
Abstract translation: 用于燃气轮机的燃料喷嘴通常包括具有与下游端轴向分离的上游端的主体。 主体至少部分地限定了延伸穿过上游端并且至少部分地穿过主体的燃料供应通道。 燃料分配歧管设置在主体的下游端。 燃料分配歧管包括延伸穿过燃料分配歧管的多个轴向延伸的通道。 多个燃料喷射口限定了燃料供给通道和多个轴向延伸通道中的每一个之间的流动路径。
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13.发明申请COMBUSTION ARRANGEMENT AND METHOD OF REDUCING PRESSURE FLUCTUATIONS OF A COMBUSTION ARRANGEMENT 审中-公开燃烧装置和降低燃烧装置压力波动的方法公开(公告)号：US20140245746A1
公开(公告)日：2014-09-04
申请号：US13784052
申请日：2013-03-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Shiva Kumar Srinivasan , James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan
CPC classification number: F23R3/42 , F01D9/023 , F02C7/18 , F05D2260/96 , F05D2260/962 , F05D2260/964 , F23R3/46 , F23R2900/00014
Abstract: A combustion arrangement includes a combustion section. Also included is an air discharge section downstream of the combustion section. Further included is a transition region disposed between the combustion section and the air discharge section. Yet further included is a transition piece defining the combustion section and the transition region, wherein the transition piece is configured to carry a combusted gas flow from the combustion section to the air discharge section. Also included is a damping device operatively coupled to the transition piece proximate the air discharge section.
Abstract translation: 燃烧装置包括燃烧部。 还包括在燃烧部下游的排气部。 还包括设置在燃烧部和排气部之间的过渡区域。 还包括限定燃烧部分和过渡区域的过渡件，其中过渡件构造成将燃烧气体流从燃烧部分运送到排气部分。 还包括一个阻尼装置，其可操作地联接到靠近空气排放部分的过渡件。
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公开(公告)号：US20140150434A1
公开(公告)日：2014-06-05
申请号：US13705443
申请日：2012-12-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Keith Cletus Belsom , Kevin Weston McMahan , Larry Lou Thomas
IPC: F02C7/22
Abstract: A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.
Abstract translation: 用于燃气轮机的燃料喷嘴通常包括具有与下游端轴向分离的上游端的主体。 主体至少部分地限定了延伸穿过上游端并且至少部分地穿过主体的燃料供应通道。 燃料分配歧管设置在主体的下游端。 燃料分配歧管包括延伸穿过燃料分配歧管的多个轴向延伸的通道。 多个燃料喷射口限定了燃料供给通道和多个轴向延伸通道中的每一个之间的流动路径。
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公开(公告)号：US20140123650A1
公开(公告)日：2014-05-08
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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Patent Agency Ranking
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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公开(公告)号：US10260424B2
公开(公告)日：2019-04-16
申请号：US15079116
申请日：2016-03-24
Applicant: General Electric Company
Inventor： James Scott Flanagan , Kevin Weston McMahan , Jeffrey Scott LeBegue
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：US10260360B2
公开(公告)日：2019-04-16
申请号：US15079101
申请日：2016-03-24
Applicant: General Electric Company
Inventor： James Scott Flanagan , Kevin Weston McMahan , Jeffrey Scott LeBegue
Abstract: A turbomachine includes a plurality of transition ducts and a support ring assembly. The outlet of a transition duct includes an inner flange and an outer flange. The turbomachine includes bore holes defined in the inner flange and outer flange, mating bore holes defined in the support ring assembly, and mechanical fasteners connecting the inner flange and the outer flange to the support ring assembly. A first one of the bore holes or mating bore holes has a first maximum radial gap and a first maximum tangential gap relative to an associated mechanical fastener. A second one of the bore holes or mating bore holes has a second maximum radial gap and a second maximum tangential gap relative to an associated mechanical fastener. The second maximum radial gap is greater than the first maximum radial gap or the second maximum tangential gap is greater than the first maximum tangential gap.
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公开(公告)号：US20180245792A1
公开(公告)日：2018-08-30
申请号：US15441421
申请日：2017-02-24
Applicant: General Electric Company
Inventor： Kevin Weston McMahan , Jonathan Dwight Berry , Michael John Hughes
CPC classification number: F23R3/346 , F02C7/22 , F05D2220/32 , F05D2240/35 , F23R3/06
Abstract: An axially staged combustion system includes a primary fuel nozzle, a primary combustion zone defined downstream from the primary fuel nozzle, a conical duct disposed downstream from the primary combustion zone and an integrated exit piece disposed downstream from the conical duct. The conical duct and the integrated exit piece at least partially form a hot gas path of the duct section. A plurality of fuel injectors is oriented radially inwardly with respect to an axial centerline of the duct section and is disposed downstream from the primary combustion zone. Each fuel injector of the plurality of fuel injectors provides for injection of a secondary fuel-air mixture into the hot gas path. The plurality of fuel injectors is distributed along at least one of the conical duct and the integrated exit piece.
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公开(公告)号：US20170276368A1
公开(公告)日：2017-09-28
申请号：US15079091
申请日：2016-03-24
Applicant: General Electric Company
Inventor： Jeffrey Scott LeBegue , Kevin Weston McMahan , James Scott Flanagan
CPC classification number: F23R3/346 , F23R3/425 , F23R3/46 , F23R2900/03041 , F23R2900/03044
Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each of the plurality of transition ducts 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 of the plurality of transition ducts is offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine 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. The turbomachine includes a late injection assembly providing fluid communication for an injection fluid to flow into the interior downstream of the inlet of at least one transition duct of the plurality of transition ducts.
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