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11.发明申请公开(公告)号：US20140338342A1
公开(公告)日：2014-11-20
申请号：US13734165
申请日：2013-01-04
Applicant: General Electric Company
Inventor： Kaitlin Marie Graham , James Scott Flanagan , Jeffrey Scott LeBegue
CPC classification number: F23R3/28 , F02C7/22 , F23D2207/00 , F23R3/34
Abstract: A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged.
Abstract translation: 燃气轮机的燃烧器的燃料喷射器包括环形主体。 流体回路至少部分地延伸穿过主体。 轴向延伸的内体在主体内延伸。 内体至少部分地限定内部腔室，其至少部分地延伸通过内部主体。 内室与流体回路流体连通。 当流体回路充电时，可伸缩点火器从内室线性地向外延伸。
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公开(公告)号：US10227883B2
公开(公告)日：2019-03-12
申请号：US15079083
申请日：2016-03-24
Applicant: General Electric Company
Inventor： Kevin Weston McMahan , Jeffrey Scott LeBegue , James Scott Flanagan
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：US20170276002A1
公开(公告)日：2017-09-28
申请号：US15079101
申请日：2016-03-24
Applicant: General Electric Company
Inventor： James Scott Flanagan , Kevin Weston McMahan , Jeffrey Scott LeBegue
CPC classification number: F01D9/023 , F01D25/28 , F05D2220/32 , F05D2260/30
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：US20170268780A1
公开(公告)日：2017-09-21
申请号：US15070000
申请日：2016-03-15
Applicant: General Electric Company
Inventor： Timothy James Purcell , Jeffrey Scott LeBegue , Lucas John Stoia
Abstract: A bundled tube fuel nozzle includes a forward plate, an intermediate plate, an aft plate and an outer sleeve. The forward plate, the intermediate plate and the outer sleeve define a fuel plenum therebetween. An aft plate axially is spaced from the intermediate plate and the intermediate plate, the aft plate and the outer sleeve define a cooling air plenum. A plurality of tubes extends through the forward plate, the fuel plenum, the intermediate plate, the cooling air plenum and the aft plate. Each tube of the plurality of tubes extends through a respective tube opening defined by the aft plate. A radial gap is defined between an outer surface of each tube and an inner surface of the respective tube opening. The plurality of tubes comprises at least one tube that is radially loaded against the inner surface of the respective tube opening.
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15.发明授权公开(公告)号：US09371997B2
公开(公告)日：2016-06-21
申请号：US13932301
申请日：2013-07-01
Applicant: General Electric Company
Inventor： Jeffrey Scott LeBegue , Patrick Benedict Melton , James Harold Westmoreland, III , James Scott Flanagan
IPC: F23R3/28
CPC classification number: F23R3/28 , F23R3/283 , F23R3/286 , F23R2900/00017
Abstract: A combustor includes an end cover having an outer side and an inner side, an outer barrel having a forward end that is adjacent to the inner side of the end cover and an aft end that is axially spaced from the forward end. An inner barrel is at least partially disposed concentrically within the outer barrel and is fixedly connected to the outer barrel. A fluid conduit extends downstream from the end cover. A first bundled tube fuel injector segment is disposed concentrically within the inner barrel. The bundled tube fuel injector segment includes a fuel plenum that is in fluid communication with the fluid conduit and a plurality of parallel tubes that extend axially through the fuel plenum. The bundled tube fuel injector segment is fixedly connected to the inner barrel.
Abstract translation: 燃烧器包括具有外侧和内侧的端盖，外筒具有邻近端盖的内侧的前端和与前端轴向间隔开的后端。 内筒至少部分地同心地设置在外筒内并且固定地连接到外筒。 流体导管从端盖的下游延伸。 第一束管燃料喷射器段同心地设置在内筒内。 捆束管燃料喷射器部分包括与流体导管流体连通的燃料增压室和沿轴向延伸通过燃料增压室的多个平行的管。 捆扎管燃料喷射器部分固定地连接到内筒。
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Patent Agency Ranking
16.发明授权Fuel injector having an ignitor for igniting a combustor of a gas turbine 有权具有用于点燃燃气轮机的燃烧器的点火器的燃料喷射器公开(公告)号：US09021781B2
公开(公告)日：2015-05-05
申请号：US13734165
申请日：2013-01-04
Applicant: General Electric Company
Inventor： Kaitlin Marie Graham , James Scott Flanagan , Jeffrey Scott LeBegue
CPC classification number: F23R3/28 , F02C7/22 , F23D2207/00 , F23R3/34
Abstract: A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged.
Abstract translation: 燃气轮机的燃烧器的燃料喷射器包括环形主体。 流体回路至少部分地延伸穿过主体。 轴向延伸的内体在主体内延伸。 内体至少部分地限定内部腔室，其至少部分地延伸通过内部主体。 内室与流体回路流体连通。 当流体回路充电时，可伸缩点火器从内室线性地向外延伸。
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公开(公告)号：US20150000284A1
公开(公告)日：2015-01-01
申请号：US13932317
申请日：2013-07-01
Applicant: General Electric Company
Inventor： Jeffrey Scott LeBegue , Patrick Benedict Melton , James Harold Westmoreland, III , James Scott Flanagan
CPC classification number: F23R3/10 , F23D14/62 , F23R3/283 , F23R3/286 , F23R2900/00005 , F23R2900/00012
Abstract: A cap assembly for a bundled tube fuel injector includes an impingement plate and an aft plate that is disposed downstream from the impingement plate. The aft plate includes a forward side that is axially separated from an aft side. A tube passage extends through the impingement plate and the aft plate. A tube sleeve extends through the impingement plate within the tube passage towards the aft plate. The tube sleeve includes a flange at a forward end and an aft end that is axially separated from the forward end. A retention plate is positioned upstream from the impingement plate. A spring is disposed between the retention plate and the flange. The spring provides a force so as to maintain contact between at least a portion of the aft end of the tube sleeve and the forward side of the aft plate.
Abstract translation: 用于捆束管燃料喷射器的盖组件包括设置在冲击板下游的冲击板和后板。 后板包括从后侧轴向分离的前侧。 管道延伸穿过冲击板和后板。 管套管穿过管通道内的冲击板向后板延伸。 管套包括在前端的凸缘和与前端轴向分离的后端。 保持板位于冲击板的上游。 弹簧设置在保持板和凸缘之间。 弹簧提供力以保持管套管的后端的至少一部分与后板的前侧之间的接触。
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18.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：US10584610B2
公开(公告)日：2020-03-10
申请号：US15292452
申请日：2016-10-13
Applicant: General Electric Company
Inventor： Seth Reynolds Hoffman , Lucas John Stoia , Sven Georg Bethke , Richard Martin DiCintio , Jeffrey Scott LeBegue , Jayaprakash Natarajan
Abstract: A combustion liner assembly includes a combustion liner having an upstream end portion and a downstream end portion and a resonator disposed proximate to the upstream end portion of the combustion liner. The resonator includes a plurality of circumferentially spaced inlet apertures disposed along a radially outer surface of the resonator, an air chamber defined within the resonator and a plurality of outlet apertures disposed along a radially inner surface of the resonator. The plurality of inlet apertures provide for fluid flow into the air chamber and the plurality of outlet apertures provide for fluid flow out of the air chamber and into a radial flow passage defined within the combustor.
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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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