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公开(公告)号：US11524350B1
公开(公告)日：2022-12-13
申请号：US17492760
申请日：2021-10-04
Applicant: General Electric Company
Inventor： Ethan Conrad Schaeffer , James Scott Flanagan , James J. Murray, III , Archie L Swanner, Jr. , Logan Tyler Nelson
Abstract: A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.
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2.发明授权Systems and methods for a fuel pressure oscillation device for reduction of coherence 有权用于降低相干性的燃料压力振荡装置的系统和方法公开(公告)号：US09551283B2
公开(公告)日：2017-01-24
申请号：US14316616
申请日：2014-06-26
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , James Scott Flanagan , Lewis Berkley Davis, Jr.
CPC classification number: F02C7/22 , F05D2260/964 , F23R2900/00013
Abstract: A system with a gas turbine engine is provided. The gas turbine engine includes a first combustor comprising a first fuel nozzle, a second combustor comprising a second fuel nozzle, and a first fuel pressure oscillation system. The first fuel pressure oscillation system includes a first rotary device coupled to a first fuel circuit. The first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle. The first rotary device is configured to generate a first fuel pressure oscillation through the first fuel nozzle. The gas turbine engine also includes a second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit. The second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and the second rotary device is configured to generate a second fuel pressure oscillation through the second fuel nozzle.
Abstract translation: 提供具有燃气涡轮发动机的系统。 燃气涡轮发动机包括第一燃烧器，其包括第一燃料喷嘴，包括第二燃料喷嘴的第二燃烧器和第一燃料压力振荡系统。 第一燃料压力振荡系统包括耦合到第一燃料电路的第一旋转装置。 第一燃料回路沿着通向第一燃料喷嘴的第一燃料通道设置。 第一旋转装置构造成通过第一燃料喷嘴产生第一燃料压力振荡。 燃气涡轮发动机还包括具有联接到第二燃料回路的第二旋转装置的第二燃料压力振荡系统。 第二燃料回路沿着通向第二燃料喷嘴的第二燃料通路设置，第二旋转装置构造成通过第二燃料喷嘴产生第二燃料压力振荡。
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公开(公告)号：US09322555B2
公开(公告)日：2016-04-26
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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公开(公告)号：US09080447B2
公开(公告)日：2015-07-14
申请号：US13848204
申请日：2013-03-21
Applicant: General Electric Company
Inventor： Kevin Weston McMahan , Jeffrey Scott LeBegue , Jaime Javier Maldonado , Daniel Jackson Dillard , James Scott Flanagan
CPC classification number: F01D9/023 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F23R3/002 , F23R3/425 , F23R2900/03043 , F23R2900/03044
Abstract: Turbine systems are provided. In one embodiment, a turbine system includes a transition duct comprising an inlet, an outlet, and a duct passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The duct passage includes an upstream portion extending from the inlet and a downstream portion extending from the outlet. The turbine system further includes a rib extending from an outer surface of the duct passage, the rib dividing the upstream portion and the downstream portion.
Abstract translation: 提供涡轮机系统。 在一个实施例中，涡轮机系统包括过渡管道，其包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切向轴线的管道通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 管道通道包括从入口延伸的上游部分和从出口延伸的下游部分。 涡轮机系统还包括从管道通道的外表面延伸的肋，肋分隔上游部分和下游部分。
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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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Patent Agency Ranking
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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7.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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8.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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10.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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