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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：US20140144122A1
公开(公告)日：2014-05-29
申请号：US13688625
申请日：2012-11-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Brandon Taylor Overby , Keith Cletus Belsom , Jonathan Kay Allen , Kyle Eric Benson , Patrick Benedict Melton , Richard Martin DiCintio , Lucas John Stoia , Ronnie Ray Pentecost
IPC: F23R3/48
CPC classification number: F23R3/48
Abstract: A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.
Abstract translation: 相邻燃烧器之间的交火管组件包括适于提供来自第一燃烧器和适于连接以提供来自第二燃烧器的流体连通的第一燃烧器和第二套管的流体连通的第一套筒。 第二套筒至少部分地在第一套筒内部延伸。 偏置在第一和第二袖之间。
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公开(公告)号：US20140116053A1
公开(公告)日：2014-05-01
申请号：US13665182
申请日：2012-10-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Wei Chen , Lucas John Stoia , Richard Martin DiCintio
Abstract: An assembly for use in a fuel injection system within a combustor of a combustion turbine engine is described. The assembly may include: a first port formed through an outer radial wall of the combustor and a second port formed through an inner radial wall. A plenum may be formed about the first port. A tube may be formed that has a first end positioned within the first port and a second end positioned within the second port. At the first end, the tube may be sized smaller than the first port such that two passages are defined therethrough: a first passage defined about an exterior of the tube; and a second passage defined through an interior of the tube.
Abstract translation: 描述了用于燃烧涡轮发动机的燃烧器内的燃料喷射系统中的组件。 组件可以包括：通过燃烧器的外部径向壁形成的第一端口和通过内部径向壁形成的第二端口。 可以围绕第一端口形成增压室。 可以形成具有位于第一端口内的第一端和位于第二端口内的第二端的管。 在第一端，管的尺寸可以小于第一端口，使得两个通道被限定在其中：围绕管的外部限定的第一通道; 以及通过管的内部限定的第二通道。
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公开(公告)号：US10690059B2
公开(公告)日：2020-06-23
申请号：US15275575
申请日：2016-09-26
Applicant: General Electric Company
Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.
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Patent Agency Ranking
公开(公告)号：US20180087457A1
公开(公告)日：2018-03-29
申请号：US15275575
申请日：2016-09-26
Applicant: General Electric Company
Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.
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公开(公告)号：US09650958B2
公开(公告)日：2017-05-16
申请号：US14334219
申请日：2014-07-17
Applicant: General Electric Company
Inventor： Richard Martin DiCintio , Patrick Benedict Melton
Abstract: A combustor cap for a combustor chamber of a combustion system is provided. The combustor cap includes a plate member including: a plurality of openings for accommodating a plurality of fuel nozzles of the combustion system; a cooling passage extending through a plane of the plate member; an entrance opening to the cooling passage; and an exit opening from the cooling passage to a side of the plate member opposite to the combustion chamber.
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18.发明授权Internally cooled transition duct aft frame with serpentine cooling passage and conduit 有权内部冷却过渡管道后部框架与蛇形冷却通道和导管公开(公告)号：US09574498B2
公开(公告)日：2017-02-21
申请号：US14036101
申请日：2013-09-25
Applicant: General Electric Company
Inventor： Elizabeth Angelyn Fadde , Patrick Benedict Melton , David William Cihlar , Richard Martin DiCintio
CPC classification number: F02C7/141 , F01D9/023 , F01D25/12 , F05D2260/2214 , F23R3/002 , F23R3/04 , F23R3/60 , F23R2900/03043 , F23R2900/03044
Abstract: An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion. A serpentine cooling passage is defined within the main body beneath the outer surface. The serpentine cooling passage is in fluid communication with the inlet port and the exhaust port. A conduit may be connected to the exhaust port for routing a compressed working fluid away from aft frame.
Abstract translation: 用于燃气轮机燃烧器的过渡管道的后框架包括主体，其具有外轨，内轨，与相对的第二侧轨周向隔开的第一侧轨，前部，后部和外表面。 入口端口延伸穿过外表面，并且排气口延伸穿过前部。 蛇形冷却通道限定在主体下面的外表面下方。 蛇形冷却通道与入口端口和排气口流体连通。 导管可以连接到排气口，用于使压缩的工作流体远离后框架。
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公开(公告)号：US09353952B2
公开(公告)日：2016-05-31
申请号：US13688625
申请日：2012-11-29
Applicant: General Electric Company
Inventor： Brandon Taylor Overby , Keith Cletus Belsom , Jonathan Kay Allen , Kyle Eric Benson , Patrick Benedict Melton , Richard Martin DiCintio , Lucas John Stoia , Ronnie Ray Pentecost
IPC: F23R3/48
CPC classification number: F23R3/48
Abstract: A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.
Abstract translation: 相邻燃烧器之间的交火管组件包括适于提供来自第一燃烧器和适于连接以提供来自第二燃烧器的流体连通的第一燃烧器和第二套管的流体连通的第一套筒。 第二套筒至少部分地在第一套筒内部延伸。 偏置在第一和第二袖之间。
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20.发明授权公开(公告)号：US09322556B2
公开(公告)日：2016-04-26
申请号：US13845378
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio
Abstract: A flow sleeve assembly for a combustor of a gas turbine includes an annular support sleeve disposed at a forward end of the flow sleeve assembly. The support sleeve includes a forward portion axially separated from an aft portion. An aft frame is disposed at an aft end of the flow sleeve assembly. An annular flow sleeve extends from the aft portion of the support sleeve towards the aft frame. The flow sleeve includes a forward end that is axially separated from an aft end. The forward end of the flow sleeve circumferentially surrounds the aft end of the support sleeve. An annular impingement sleeve extends between the aft end of the flow sleeve and the aft frame. A forward end of the impingement sleeve is connected to the aft end of the flow sleeve, and an aft end of the impingement sleeve is connected to the aft frame.
Abstract translation: 用于燃气涡轮机的燃烧器的流动套筒组件包括设置在流动套筒组件的前端处的环形支撑套筒。 支撑套筒包括从后部轴向分离的前部。 后框架设置在流动套筒组件的后端。 环形流动套筒从支撑套筒的后部向后框架延伸。 流动套筒包括从后端轴向分离的前端。 流动套筒的前端周向地包围支撑套筒的后端。 环形冲击套筒在流动套筒的后端和后框架之间延伸。 冲击套筒的前端连接到流动套筒的后端，并且冲击套筒的后端连接到后架。
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