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公开(公告)号：US20170254537A1
公开(公告)日：2017-09-07
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
CPC classification number: F23R3/002 , F02C3/04 , F23R3/60 , F23R2900/00012 , F23R2900/00018 , F23R2900/03043
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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公开(公告)号：US09360217B2
公开(公告)日：2016-06-07
申请号：US13845485
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia , Christopher Paul Willis , Ronnie Ray Pentecost
CPC classification number: F23R3/20 , F02C7/22 , F23R3/005 , F23R3/34 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/03043 , F23R2900/03045
Abstract: A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.
Abstract translation: 用于燃气轮机的燃烧器的燃烧模块包括设置在燃烧模块的上游端的环形燃料分配歧管。 燃料分配歧管包括具有内表面的环形支撑套筒。 燃烧模块还包括燃料喷射组件，该燃料喷射组件具有环形燃烧衬套，所述环形燃烧衬套从燃料分配歧管的下游延伸并终止在后部框架处;以及环形流动套筒，其环绕燃烧衬套。 流动套筒从燃料分配歧管的下游延伸并终止于后部框架。 流动套筒在支撑套筒和后架之间连续延伸。 流动套筒的前部部分同心地定位在支撑套筒内，其中前部部分与支撑套筒的内表面滑动接合。
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公开(公告)号：US20160076578A1
公开(公告)日：2016-03-17
申请号：US14485296
申请日：2014-09-12
Applicant: General Electric Company
IPC: F16B39/08
Abstract: A nut anti-rotation cap includes an end wall having an inner surface configured to be operatively coupled to an end of a threaded mechanical fastener. Also included is at least one sidewall extending from the end wall, wherein the at least one sidewall is a solid wall configured to be secured to a nut engaged with the threaded mechanical fastener and to enclose an exposed portion of the threaded mechanical fastener.
Abstract translation: 螺母防旋转盖包括端壁，所述端壁具有构造成可操作地联接到螺纹机械紧固件的端部的内表面。 还包括从端壁延伸的至少一个侧壁，其中至少一个侧壁是实心壁，其构造成固定到与螺纹机械紧固件接合的螺母并且包围螺纹机械紧固件的暴露部分。
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14.发明授权Combustor support assembly for mounting a combustion module of a gas turbine 有权用于安装燃气轮机的燃烧模块的燃烧器支撑组件公开(公告)号：US09400114B2
公开(公告)日：2016-07-26
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
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：US20160047313A1
公开(公告)日：2016-02-18
申请号：US14460470
申请日：2014-08-15
Applicant: General Electric Company
CPC classification number: F16B43/00 , F01D9/023 , F01D25/28 , F05D2230/64 , F05D2240/91 , F05D2250/312 , F05D2260/36 , F16B37/122 , Y02T50/675
Abstract: A bushing includes a body extending from a first end to a second end through an intermediate portion. The body includes a passage having a first centerline extending from the first end to the second end. A first alignment member is formed on a first section of the intermediate portion at the first end. The first alignment member includes an outer surface having a plurality of splines configured to be received by a first component to be joined. A second alignment member is formed on a second section of the intermediate portion. The second alignment member includes a second centerline that is off-set relative to the first centerline and is configured to be received by a second component to be joined with the first component.
Abstract translation: 衬套包括从第一端延伸到第二端穿过中间部分的主体。 主体包括具有从第一端延伸到第二端的第一中心线的通道。 第一对准部件在第一端部的中间部分的第一部分上形成。 第一对准构件包括具有多个花键的外表面，该多个花键构造成被待接合的第一构件接收。 第二对准构件形成在中间部分的第二部分上。 第二对准构件包括相对于第一中心线偏移的第二中心线，并且构造成由第二部件接收以与第一部件接合。
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Patent Agency Ranking
公开(公告)号：US20140352316A1
公开(公告)日：2014-12-04
申请号：US13908050
申请日：2013-06-03
Applicant: General Electric Company
Inventor： Elizabeth Angelyn Fadde , Lucas John Stoia , Christopher Paul Willis
IPC: F23R3/00
CPC classification number: F23R3/002 , F02C7/264 , F02C7/266 , F23R3/60 , F23R2900/00012
Abstract: The present application provides a combustor with a radial penetration. The combustor may include a combustion chamber, a liner surrounding the combustion chamber, a flow sleeve surrounding the liner, a penetration tube extending through the liner and the flow sleeve with the radial penetration positioned within the penetration tube, a flange extending from the penetration tube about the flow sleeve, and a ferrule positioned about the flange and the radial penetration so as to limit leakage about the radial penetration.
Abstract translation: 本申请提供了具有径向穿透的燃烧器。 燃烧器可以包括燃烧室，围绕燃烧室的衬套，围绕衬套的流动套筒，穿过衬套延伸的穿透管和流体套筒，其中径向穿透位于穿透管内，从穿透管延伸的凸缘 围绕流动套筒和围绕凸缘定位的套圈和径向穿透以限制径向穿透的泄漏。
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公开(公告)号：US20140260277A1
公开(公告)日：2014-09-18
申请号：US13845485
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia , Christopher Paul Willis , Ronnie Ray Pentecost
IPC: F23R3/20
CPC classification number: F23R3/20 , F02C7/22 , F23R3/005 , F23R3/34 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/03043 , F23R2900/03045
Abstract: A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.
Abstract translation: 用于燃气轮机的燃烧器的燃烧模块包括设置在燃烧模块的上游端的环形燃料分配歧管。 燃料分配歧管包括具有内表面的环形支撑套筒。 燃烧模块还包括燃料喷射组件，该燃料喷射组件具有环形燃烧衬套，所述环形燃烧衬套从燃料分配歧管的下游延伸并终止在后部框架处;以及环形流动套筒，其环绕燃烧衬套。 流动套筒从燃料分配歧管的下游延伸并终止于后部框架。 流动套筒在支撑套筒和后架之间连续延伸。 流动套筒的前部部分同心地定位在支撑套筒内，其中前部部分与支撑套筒的内表面滑动接合。
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公开(公告)号：US20140260272A1
公开(公告)日：2014-09-18
申请号：US13845365
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia , Christopher Paul Willis
IPC: F02C7/22
Abstract: A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold.
Abstract translation: 用于向燃气涡轮机的燃烧器提供燃料的系统包括至少部分地限定燃料增压室的环形燃料分配歧管。 燃料分配歧管包括从后端轴向分离的前端，沿着前端径向向外且周向延伸的凸缘以及从凸缘的下游延伸的环形支撑环。 LLI组件从燃料分配歧管的下游延伸。 LLI组件包括至少部分地限定燃烧器内的主燃烧区域和二次燃烧区域的单体衬套。 LLI注射器基本上径向地延伸通过单体衬套并且提供通过单体衬套到二次燃烧区域的流体连通。 与燃料增压室流体连通的流体导管在LLI喷射器和燃料分配歧管之间延伸。
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公开(公告)号：US09989254B2
公开(公告)日：2018-06-05
申请号：US13908050
申请日：2013-06-03
Applicant: General Electric Company
Inventor： Elizabeth Angelyn Fadde , Lucas John Stoia , Christopher Paul Willis
CPC classification number: F23R3/002 , F02C7/264 , F02C7/266 , F23R3/60 , F23R2900/00012
Abstract: The present application provides a combustor with a radial penetration. The combustor may include a combustion chamber, a liner surrounding the combustion chamber, a flow sleeve surrounding the liner, a penetration tube extending through the liner and the flow sleeve with the radial penetration positioned within the penetration tube, a flange extending from the penetration tube about the flow sleeve, and a ferrule positioned about the flange and the radial penetration so as to limit leakage about the radial penetration.
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公开(公告)号：US20170268776A1
公开(公告)日：2017-09-21
申请号：US15070074
申请日：2016-03-15
Applicant: General Electric Company
Inventor： Christopher Paul Willis , David William Cihlar , Jonathan Hale Kegley , Andrew Grady Godfrey , David Philip Porzio
CPC classification number: F23R3/002 , F02C3/04 , F23R3/06 , F23R3/46 , F23R2900/00005
Abstract: The present disclosure is directed a combustor. The combustor includes an annularly shaped liner having a downstream end that is rigidly connected to an aft frame. 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. A plurality of fuel injector assemblies is circumferentially spaced about the flow sleeve. Each fuel injector assembly extends radially through the flow sleeve and the liner. Each fuel injector assembly is rigidly connected to the flow sleeve and to the liner. An aft portion of the flow sleeve terminates axially short of the aft frame to form an axial gap between the aft end and the aft frame to allow for unrestrained axial expansion and contraction of the aft end.
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