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公开(公告)号：US10260752B2
公开(公告)日：2019-04-16
申请号：US15079091
申请日：2016-03-24
Applicant: General Electric Company
Inventor： Jeffrey Scott LeBegue , Kevin Weston McMahan , James Scott Flanagan
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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公开(公告)号：US20140283520A1
公开(公告)日：2014-09-25
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
IPC: F01D9/02
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：US08707673B1
公开(公告)日：2014-04-29
申请号：US13734156
申请日：2013-01-04
Applicant: General Electric Company
Inventor： James Scott Flanagan , Kevin Weston McMahan , Jeffrey Scott LeBegue , Ronnie Ray Pentecost
IPC: F02C3/00
CPC classification number: F01D9/023 , F05D2230/642 , F05D2250/43 , F05D2250/713
Abstract: Turbine systems are provided. 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 and a downstream portion. The upstream portion extends from the inlet between an inlet end and an aft end. The downstream portion extends from the outlet between an outlet end and a head end. The turbine system further includes a joint coupling the aft end of the upstream portion and the head end of the downstream portion together. The joint is configured to allow movement of the upstream portion and the downstream portion relative to each other about or along at least one axis.
Abstract translation: 提供涡轮机系统。 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。 管道通道包括上游部分和下游部分。 上游部分在入口端和后端之间从入口延伸。 下游部分在出口端和头端之间从出口延伸。 涡轮机系统还包括将上游部分的后端和下游部分的头端连接在一起的接头。 所述接头构造成允许所述上游部分和所述下游部分围绕或沿着至少一个轴线相对于彼此移动。
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公开(公告)号：US10934893B2
公开(公告)日：2021-03-02
申请号：US15779317
申请日：2015-12-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandra Beverly Kolvick , Jeffrey Scott LeBegue , Ansley Michelle Heard , Jesse Ellis Barton , Paul Robert Fernandez , Adrian Adam Klejc
Abstract: A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.
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公开(公告)号：US20180106163A1
公开(公告)日：2018-04-19
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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Patent Agency Ranking
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：US10145251B2
公开(公告)日：2018-12-04
申请号：US15079110
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. An outlet of each of the plurality of transition ducts is offset from an inlet along the longitudinal axis and the tangential axis. Each of the plurality of transition ducts further includes an upstream portion and a downstream portion, the upstream portion extending between the inlet and an aft end, the downstream portion extending between a head end and the outlet. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path. The turbomachine further includes a plurality of support assemblies directly connecting the upstream portion of at least one transition duct of the plurality of transition ducts to the support ring assembly. Each of the plurality of support assemblies includes a rod extending between the upstream portion and the support ring assembly.
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公开(公告)号：US20170343216A1
公开(公告)日：2017-11-30
申请号：US15166493
申请日：2016-05-27
Applicant: General Electric Company
CPC classification number: F23R3/286 , F02C7/222 , F05D2220/32 , F05D2240/35 , F05D2260/96 , F23R2900/00014
Abstract: A fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band extending between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the forward wall, the fuel plenum and the aft wall and each tube defines a premix flow passage through and downstream from the fuel plenum body. Each tube is rigidly connected to the aft plate. A damping plate is disposed downstream from the aft plate. At least one tube of the plurality of tubes extends through a corresponding tube opening defined by the damping plate. The damping plate includes a plurality of spring members fixedly connected to the damping plate. At least one spring member of the plurality of spring members is engaged with an outer wall of the at least one tube.
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公开(公告)号：US20170276003A1
公开(公告)日：2017-09-28
申请号：US15079110
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 , F01D9/02 , F01D25/28 , F05D2220/32 , F05D2260/30 , F23R3/60
Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. An outlet of each of the plurality of transition ducts is offset from an inlet along the longitudinal axis and the tangential axis. Each of the plurality of transition ducts further includes an upstream portion and a downstream portion, the upstream portion extending between the inlet and an aft end, the downstream portion extending between a head end and the outlet. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path. The turbomachine further includes a plurality of support assemblies directly connecting the upstream portion of at least one transition duct of the plurality of transition ducts to the support ring assembly. Each of the plurality of support assemblies includes a rod extending between the upstream portion and the support ring assembly.
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