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公开(公告)号：US09316155B2
公开(公告)日：2016-04-19
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
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：US09310078B2
公开(公告)日：2016-04-12
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：US20150159873A1
公开(公告)日：2015-06-11
申请号：US14101888
申请日：2013-12-10
Applicant: General Electric Company
Inventor： Patrick Benedict Melton , Richard Martin DiCintio
CPC classification number: F23R3/10 , F01D25/26 , F02C3/14 , F02C7/20 , F04D29/541 , F05D2210/12 , F05D2220/32 , F05D2240/35 , F05D2240/90
Abstract: A compressor discharge casing assembly includes a diffuser disposed proximate an aft region of a compressor section, the diffuser configured to route a compressed airflow to an interior region of the compressor discharge casing assembly. Also included is a strut disposed in the interior region of the compressor discharge casing assembly and located proximate an exit region of the diffuser. Further included is a heat shield disposed proximate an upstream portion of the strut, the heat shield configured to reduce impingement of the compressed airflow on the strut.
Abstract translation: 压缩机排出壳体组件包括邻近压缩机部分的后部区域设置的扩散器，该扩散器构造成将压缩的气流路由到压缩机排出壳体组件的内部区域。 还包括设置在压缩机排出壳体组件的内部区域中并且位于扩散器的出口区域附近的支柱。 还包括设置在支柱的上游部分附近的热屏蔽，该热屏蔽被配置为减少压缩气流在支柱上的冲击。
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公开(公告)号：US20140260318A1
公开(公告)日：2014-09-18
申请号：US13845617
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Christopher Paul Willis , Richard Martin DiCintio , Ronnie Ray Pentecost , Christopher Crookshanks
IPC: F02C7/20
CPC classification number: F02C7/20 , F01D9/023 , F01D11/003 , F23R3/002 , F23R3/46 , F23R3/60 , F23R2900/00012 , F23R2900/00017
Abstract: A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall that extend outward from the first side of the aft frame. A first segment of the upstream wall extends from an inner portion of the aft frame towards an outer portion of the aft frame at a first outward distance from the first side. A second segment of the upstream wall extends from the first segment to the outer portion of the aft frame at a second outward distance from the first side. The second segment of the upstream wall at least partially defines a side seal guide feature to allow for axial insertion of a bottom portion of a side seal into the side seal slot.
Abstract translation: 侧密封槽沿着用于燃气轮机的燃烧衬套的后框架的一侧延伸。 侧密封槽至少部分地限定在从后框架的第一侧向外延伸的下游壁和上游壁之间。 上游壁的第一段从后框架的内部部分朝着离开第一侧的第一向外的距离朝向后部框架的外部部分延伸。 上游壁的第二段从第一侧面以第二向外的距离从后框架的第一部分延伸到外部部分。 上游壁的第二段至少部分地限定侧密封引导件特征，以允许侧密封件的底部部分轴向插入到侧密封槽中。
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25.发明申请ASSEMBLY FOR CONTROLLING CLEARANCE BETWEEN A LINER AND STATIONARY NOZZLE WITHIN A GAS TURBINE 审中-公开用于控制气体涡轮机内衬和静止喷嘴之间的间隙的组件公开(公告)号：US20140260280A1
公开(公告)日：2014-09-18
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
IPC: F23R3/00
CPC classification number: F23R3/002 , F01D9/023 , F01D11/18 , F01D25/24 , F05D2230/642 , F05D2300/50212 , F23R3/005 , F23R3/60 , F23R2900/00012
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.
Abstract translation: 用于控制燃气涡轮机内的衬套和静止喷嘴之间的间隙的组件包括具有设置在衬套的后端的后框架的环形衬套和联接到后架的安装支架。 组件还包括涡轮机，其具有至少部分地限定涡轮机入口的外涡轮机外壳和内涡轮机外壳。 固定喷嘴设置在后框架和入口之间。 固定喷嘴包括顶部平台部分，其具有朝向后部框架延伸的前缘和底部平台部分。 在后框架的后端和顶部平台部分的前缘之间限定间隙。 安装支架联接到外涡轮机外壳，而固定喷嘴与内涡轮机外壳相连。
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Patent Agency Ranking
公开(公告)号：US20210172376A1
公开(公告)日：2021-06-10
申请号：US16708526
申请日：2019-12-10
Applicant: General Electric Company
Inventor： Jason Dean Fuller , Richard Martin DiCintio , William David York
IPC: F02C7/264
Abstract: Turbomachines and methods of operating turbomachines are provided. The turbomachine may include a compressor, a turbine, and a plurality of combustors downstream from the compressor and upstream from the turbine. The turbomachine may also include a plurality of igniters. Methods of operating a turbomachine may include rotating a shaft of the turbomachine at a first speed and rotating the shaft of the turbomachine at a second speed different from the first speed after rotating the shaft of the turbomachine at the first speed. The methods may also include firing at least one igniter of the plurality of igniters repeatedly throughout the period of time at a regular interval and/or when the rotational speed reaches at least one predetermined speed threshold during the period of time.
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公开(公告)号：US10830142B2
公开(公告)日：2020-11-10
申请号：US15289247
申请日：2016-10-10
Applicant: General Electric Company
Abstract: An aft frame for a duct of a combustor includes a rail or radial projection that extends circumferentially around the aft frame and that defines an outer surface of the aft frame. A preformed cover plate having an inner surface is attached to the outer surface of the aft frame. A plurality of micro-cooling channels is formed within at least one of the inner surface of the preformed cover plate and the outer surface of the aft frame. The preformed cover plate extends across the plurality of micro-cooling channels.
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公开(公告)号：US10816208B2
公开(公告)日：2020-10-27
申请号：US15410831
申请日：2017-01-20
Applicant: General Electric Company
Abstract: A fuel injector for a gas turbine combustor includes a fuel conduit fitting and a nozzle having an inlet portion defining a mixing chamber therein. The inlet portion includes a plurality of circumferentially-spaced vanes that define a plurality of inlet flow paths within the mixing chamber. Each vane has at least one port defined therein that is in flow communication with the fuel conduit fitting such that fuel from the fuel conduit fitting is dischargeable into at least one of the inlet flow paths via the at least one port. The resulting fuel/air mixture is delivered into a secondary combustion zone of the gas turbine combustor. A gas turbine including the fuel injector and a method of fabricating the fuel nozzle are also provided.
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29.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：US20180087390A1
公开(公告)日：2018-03-29
申请号：US15275570
申请日：2016-09-26
Applicant: General Electric Company
CPC classification number: F01D9/023 , F02C3/04 , F05D2220/32 , F05D2240/128 , F05D2240/35 , F05D2260/52 , F16J15/0887
Abstract: A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.
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