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公开(公告)号：US10228141B2
公开(公告)日：2019-03-12
申请号：US15061434
申请日：2016-03-04
Applicant: General Electric Company
Inventor： David William Cihlar , Christopher Paul Willis , Marissa Ann Singley , Jonathan Glenn Reed
Abstract: An axial fuel staging (AFS) system for a combustor is provided. The AFS system includes a secondary fuel injector, an injector housing surrounding the secondary fuel injector, and a conduit assembly in flow communication with the secondary fuel injector. The conduit assembly includes a first conduit for conveying fuel to the secondary fuel injector, and a second conduit circumscribing the first conduit such that a channel is defined between the first conduit and the second conduit. The first conduit and the second conduit terminate within the injector housing.
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公开(公告)号：US20170254542A1
公开(公告)日：2017-09-07
申请号：US15061434
申请日：2016-03-04
Applicant: General Electric Company
Inventor： David William Cihlar , Christopher Paul Willis , Marissa Ann Singley , Jonathan Glenn Reed
CPC classification number: F23R3/346 , F02C7/228 , F05D2220/32 , F23R3/002 , F23R3/28 , F23R3/283 , F23R3/34 , F23R2900/00005
Abstract: An axial fuel staging (AFS) system for a combustor is provided. The AFS system includes a secondary fuel injector, an injector housing surrounding the secondary fuel injector, and a conduit assembly in flow communication with the secondary fuel injector. The conduit assembly includes a first conduit for conveying fuel to the secondary fuel injector, and a second conduit circumscribing the first conduit such that a channel is defined between the first conduit and the second conduit. The first conduit and the second conduit terminate within the injector housing.
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公开(公告)号：US09528703B2
公开(公告)日：2016-12-27
申请号：US14032225
申请日：2013-09-20
Applicant: General Electric Company
Inventor： Christopher Paul Willis , Patrick Benedict Melton , Lucas John Stoia
CPC classification number: F23R3/286 , B23K1/0018 , F23R3/283 , F23R2900/00017 , F23R2900/00018
Abstract: The present application provides a fuel plenum for a micro-mixer combustor. The fuel plenum may include a first assembly plate with a first assembly plate aperture, a second assembly plate with a second assembly plate aperture, a fuel tube extending through the first assembly plate aperture of the first assembly plate and the second assembly plate aperture of the second assembly plate, and an installation insert positioned between the fuel tube and the first assembly plate aperture.
Abstract translation: 本申请提供了一种用于微型混合器燃烧器的燃料增压室。 燃料增压室可以包括具有第一组件板孔的第一组件板，具有第二组件板孔的第二组件板，延伸穿过第一组件板的第一组件板孔的燃料管和第二组合板孔 第二组装板和位于燃料管和第一组装板孔之间的安装插入件。
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4.发明申请COMBUSTOR SUPPORT ASSEMBLY FOR MOUNTING A COMBUSTION MODULE OF A GAS TURBINE 有权用于安装燃气涡轮机燃烧模块的COMBUSTOR支持组件公开(公告)号：US20140260319A1
公开(公告)日：2014-09-18
申请号：US13845699
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio , Christopher Paul Willis
IPC: F23R3/60
CPC classification number: F23R3/60 , F23R3/005 , F23R3/34 , F23R2900/00017 , F23R2900/00019
Abstract: A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating surface. A combustion module extends through the combustor opening. The combustion module includes a forward end that is circumferentially surrounded by a mounting flange and an aft end that is circumferentially surrounded by an aft frame. The mounting flange extends circumferentially around the combustor opening. The mounting flange is coupled to the outer mating surface of the compressor discharge casing and the aft frame is coupled to the inner mating surface of the outer turbine shell.
Abstract translation: 燃气轮机包括联接到外部涡轮机壳体的压缩机排出壳体。 压缩机排出壳体包括延伸穿过压缩机排出壳体的燃烧器开口和围绕燃烧器开口的外部配合表面。 外涡轮壳体限定内配合表面。 燃烧模块延伸穿过燃烧器开口。 燃烧模块包括由安装凸缘周向地包围的前端和由后框架周向包围的后端。 安装凸缘围绕燃烧器开口周向延伸。 安装凸缘联接到压缩机排出壳体的外配合表面，并且后框架联接到外涡轮机壳体的内配合表面。
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公开(公告)号：US10344978B2
公开(公告)日：2019-07-09
申请号：US15070110
申请日：2016-03-15
Applicant: General Electric Company
Inventor： Andrew Grady Godfrey , Christopher Paul Willis , David William Cihlar , David Philip Porzio
Abstract: The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A bluff body extends radially between the flow sleeve and the liner through the cooling flow annulus. A guide vane is disposed within the cooling flow annulus and extends between the flow sleeve and the liner proximate to the bluff body.
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Patent Agency Ranking
公开(公告)号：US20170268783A1
公开(公告)日：2017-09-21
申请号：US15070093
申请日：2016-03-15
Applicant: General Electric Company
Inventor： David William Cihlar , Jonathan Hale Kegley , Christopher Paul Willis , Jonathan Glenn Reed
Abstract: The present disclosure is directed to a system for mounting an axially staged fuel injector assembly. The system includes an annularly shaped liner that at least partially defines a hot gas path of a combustor. The liner defines an injector opening that extends radially through the liner. A flow sleeve circumferentially surrounds at least a portion of the liner and is radially spaced from the liner to form a cooling flow annulus therebetween. An annular injector boss extends radially from the liner through the flow sleeve. The injector boss includes a first end portion that extends circumferentially about the injector opening and a second end portion that is disposed radially outwardly from an outer surface of the flow sleeve. The injector boss is formed to receive a fuel injector. The present disclosure is also directed to a method for mounting an axially staged fuel injector.
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公开(公告)号：US20170268779A1
公开(公告)日：2017-09-21
申请号：US15070110
申请日：2016-03-15
Applicant: General Electric Company
Inventor： Andrew Grady Godfrey , Christopher Paul Willis , David William Cihlar , David Philip Porzio
Abstract: The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A bluff body extends radially between the flow sleeve and the liner through the cooling flow annulus. A guide vane is disposed within the cooling flow annulus and extends between the flow sleeve and the liner proximate to the bluff body.
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公开(公告)号：US20160047317A1
公开(公告)日：2016-02-18
申请号：US14459397
申请日：2014-08-14
Applicant: General Electric Company
Inventor： Christopher Paul Willis , William Michael Poschel , Lucas John Stoia , Patrick Benedict Melton , Vaibhav Nadkarni , Chandrasekhar Pushkaran
IPC: F02C7/22
Abstract: A downstream nozzle for use in a combustor that includes an inner radial wall defining a combustion zone downstream of a primary nozzle and an outer radial wall surrounding the inner radial wall so to form a flow annulus therebetween. The downstream nozzle may include: an injector tube extending between the outer radial wall and the inner radial wall; a first plenum adjacent to the injector tube, and, inboard of the ceiling, a floor disposed between the inner radial wall and the outer radial wall. A feed passage may connect the first plenum to an inlet formed outboard of the outer radial wall and impingement ports may be formed through the floor of the first plenum.
Abstract translation: 一种用于燃烧器的下游喷嘴，其包括限定主喷嘴下游的燃烧区的内部径向壁和围绕内部径向壁的外部径向壁，以在它们之间形成流动环空。 下游喷嘴可以包括：在外径向壁和内径向壁之间延伸的喷射管; 与喷射器管相邻的第一增压室，以及天花板的内侧，设置在内径向壁和外径向壁之间的地板。 进料通道可以将第一增压室连接到外径向壁外部形成的入口，并且冲击口可形成在第一增压室的底板上。
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9.发明授权公开(公告)号：US10436445B2
公开(公告)日：2019-10-08
申请号：US13845565
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Christopher Paul Willis , Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia
Abstract: An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell.
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公开(公告)号：US10203114B2
公开(公告)日：2019-02-12
申请号：US15061395
申请日：2016-03-04
Applicant: General Electric Company
Inventor： David William Cihlar , Jonathan Hale Kegley , Andrew Grady Godfrey , Christopher Paul Willis
Abstract: A sleeve assembly for a combustion system is provided. The sleeve assembly includes a liner defining a combustion chamber having a flow axis and a primary combustion zone. The liner has a forward end and an aft end such that the liner circumscribes the flow axis. The sleeve assembly also includes a shell circumscribing the liner such that a cooling duct is defined between the liner and the shell. The shell includes a unisleeve having a forward end and an aft end. The aft end of the unisleeve is positioned axially upstream of the aft end of the liner, defining a gap between the aft end of the liner and the aft end of the unisleeve. The unisleeve is mounted to the liner at circumferentially spaced locations along an axial plane between the forward end and the aft end of the unisleeve.
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