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公开(公告)号：US11951557B2
公开(公告)日：2024-04-09
申请号：US18053408
申请日：2022-11-08
Applicant: General Electric Company
Inventor： Ethan Conrad Schaeffer , James Scott Flanagan , James J. Murray, III , Archie L Swanner, Jr. , Logan Tyler Nelson
CPC classification number: B23K1/0018 , B23K1/008 , B23K1/20 , B23K35/40 , B23P6/002 , G01N21/954 , B33Y80/00
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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公开(公告)号：US10690056B2
公开(公告)日：2020-06-23
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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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：US20170356655A1
公开(公告)日：2017-12-14
申请号：US15181539
申请日：2016-06-14
Applicant: General Electric Company
Inventor： Michael John Hughes , James Scott Flanagan , Jonathan Dwight Berry
Abstract: The present disclosure is directed to a bundled tube type fuel nozzle assembly. The fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band that extends 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 fuel plenum. Each tube of the plurality of tubes includes an inlet defined along an outer surface of the forward plate and an outlet defined downstream from the inlet. The forward plate defines a plurality of fuel inlet slots that is in fluid communication with the fuel plenum. Each fuel inlet slot extends radially outwardly with respect to an axial centerline of the fuel plenum body along the outer surface of the forward plate.
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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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Patent Agency Ranking
公开(公告)号：US20170191668A1
公开(公告)日：2017-07-06
申请号：US14988999
申请日：2016-01-06
Applicant: General Electric Company
Inventor： Michael John Hughes , Jonathan Dwight Berry , James Scott Flanagan
CPC classification number: F23R3/346 , F01D9/023 , F01D9/041 , F02C7/22 , F02C7/222 , F05D2220/32 , F23R3/002 , F23R3/005 , F23R3/06
Abstract: A gas turbine that includes: a combustor coupled to a turbine that together define a working fluid flowpath, the working fluid flowpath extending aftward along a longitudinal axis from a forward end defined by a forward injector in the combustor, through an interface at which the combustor ends and the turbine begins, and then through the turbine to an aftward end; a gap formed at the interface between the combustor and the turbine; and a fuel injector disposed near the gap for injecting a fuel into an airflow that passes through the gap. The gap may include a former leakage pathway occurring at the interface. The former leakage pathway may be expanded so to accommodate a desired level for the airflow passing therethrough.
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27.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：US10408455B2
公开(公告)日：2019-09-10
申请号：US15181539
申请日：2016-06-14
Applicant: General Electric Company
Inventor： Michael John Hughes , James Scott Flanagan , Jonathan Dwight Berry
Abstract: The present disclosure is directed to a bundled tube type fuel nozzle assembly. The fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band that extends 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 fuel plenum. Each tube of the plurality of tubes includes an inlet defined along an outer surface of the forward plate and an outlet defined downstream from the inlet. The forward plate defines a plurality of fuel inlet slots that is in fluid communication with the fuel plenum. Each fuel inlet slot extends radially outwardly with respect to an axial centerline of the fuel plenum body along the outer surface of the forward plate.
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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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