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公开(公告)号：US11428413B2
公开(公告)日：2022-08-30
申请号：US15464406
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , James Scott Flanagan
Abstract: The present disclosure is directed to a fuel injection module for a segmented annular combustion system. The fuel injection module includes a housing body, a fuel nozzle portion, and at least one fuel injection lance. The fuel nozzle portion is fluidly coupled to a fuel nozzle plenum within the housing body, and the at least one fuel injection lance is fluidly coupled to an injector fuel plenum within the housing body. In some cases, the fuel nozzle portion is a bundled tube fuel nozzle having one or more subsets of tubes. The fuel injection lances are positioned along a radial side of the housing body or circumferentially between two subsets of tubes. Liquid fuel cartridges extend through the fuel nozzle portion, the fuel injection lances, or both.
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公开(公告)号：US10920605B2
公开(公告)日：2021-02-16
申请号：US15849703
申请日：2017-12-21
Applicant: General Electric Company
Inventor： Travis Edwin Lipstein , Taylor Janae Million , Glen William Brooksby , Sandra Beverly Kolvick , James Scott Flanagan , Thomas Alan Mogle, II
Abstract: A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.
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公开(公告)号：US10830442B2
公开(公告)日：2020-11-10
申请号：US15464400
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , James Scott Flanagan
Abstract: A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.
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14.发明申请公开(公告)号：US20190195084A1
公开(公告)日：2019-06-27
申请号：US15849703
申请日：2017-12-21
Applicant: General Electric Company
Inventor： Travis Edwin Lipstein , Taylor Janae Million , Glen William Brooksby , Sandra Beverly Kolvick , James Scott Flanagan , Thomas Alan Mogle, II
CPC classification number: F01D21/003 , F05D2260/30 , F05D2270/305 , F05D2270/54 , F05D2270/804 , F05D2270/807 , F05D2270/821 , G01B11/14 , G01B11/27
Abstract: A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.
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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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Patent Agency Ranking
公开(公告)号：US20180087776A1
公开(公告)日：2018-03-29
申请号：US15273846
申请日：2016-09-23
Applicant: General Electric Company
Inventor： James Scott Flanagan , Jerome David Brown , Donald Timothy Lemon
CPC classification number: F01D25/00 , F02C7/00 , F02C7/20 , F02C7/22 , F02C7/222 , F05D2230/642 , F05D2240/35 , F05D2260/30 , F05D2300/50212 , F23R3/283 , F23R3/346 , F23R2900/00005
Abstract: The present disclosure is directed to a mounting assembly for a fluid conduit. The mounting assembly includes a casing, a first fluid conduit segment, and a second fluid conduit segment. A fitting is spaced apart from the casing. The fitting couples the first fluid conduit segment and the second fluid conduit segment. A bracket includes a casing mounting portion coupled to the casing, a first fitting mounting portion spaced apart from the casing mounting portion and coupled to the fitting, and a thickness. The thickness of the bracket permits the fitting to move relative to the casing.
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公开(公告)号：US20170276369A1
公开(公告)日：2017-09-28
申请号：US15464394
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , James Scott Flanagan , Joseph Vincent Citeno , Kevin Weston McMahan
Abstract: A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustion system is part of a gas turbine.
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18.发明申请SYSTEMS AND METHODS FOR A FUEL PRESSURE OSCILLATION DEVICE FOR REDUCTION OF COHERENCE 有权用于降低相关性的燃油压力振荡装置的系统和方法公开(公告)号：US20150377138A1
公开(公告)日：2015-12-31
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：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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