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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
摘要： 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：US20180087457A1
公开(公告)日：2018-03-29
申请号：US15275575
申请日：2016-09-26
摘要： 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
摘要： 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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4.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
发明人： Elizabeth Angelyn Fadde , Patrick Benedict Melton , David William Cihlar , Richard Martin DiCintio
CPC分类号： F02C7/141 , F01D9/023 , F01D25/12 , F05D2260/2214 , F23R3/002 , F23R3/04 , F23R3/60 , F23R2900/03043 , F23R2900/03044
摘要： 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.
摘要翻译： 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
发明人： 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分类号： F23R3/48
CPC分类号： F23R3/48
摘要： 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.
摘要翻译： 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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6.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
摘要： 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.
摘要翻译： 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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公开(公告)号：US09316155B2
公开(公告)日：2016-04-19
申请号：US13845365
申请日：2013-03-18
摘要： 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.
摘要翻译： 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
摘要： 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.
摘要翻译： 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
CPC分类号： F23R3/10 , F01D25/26 , F02C3/14 , F02C7/20 , F04D29/541 , F05D2210/12 , F05D2220/32 , F05D2240/35 , F05D2240/90
摘要： 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.
摘要翻译： 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
发明人： Christopher Paul Willis , Richard Martin DiCintio , Ronnie Ray Pentecost , Christopher Crookshanks
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F01D9/023 , F01D11/003 , F23R3/002 , F23R3/46 , F23R3/60 , F23R2900/00012 , F23R2900/00017
摘要： 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.
摘要翻译： 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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