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11.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
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F01D9/023 , F01D11/18 , F01D25/24 , F05D2230/642 , F05D2300/50212 , F23R3/005 , F23R3/60 , F23R2900/00012
摘要： 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.
摘要翻译： 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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公开(公告)号：US20180187894A1
公开(公告)日：2018-07-05
申请号：US15728009
申请日：2017-10-09
发明人： Jun Cai , Andrew Grady Godfrey , Richard Martin DiCintio , Seth Reynolds Hoffman , Ronnie Ray Pentecost , Jayaprakash Natarajan , Wei Zhao
摘要： A fuel injector is provided for the radial introduction of a fuel/air mixture to a combustor. The fuel injector includes a frame having interior sides defining an opening for passage of a first fluid; at least one fuel injection body; and a conduit fitting. The at least one fuel injection body is coupled to the frame and positioned within the opening, thereby defining flow paths for the first fluid. The at least one fuel injection body defines a fuel plenum, and a set of fuel injection holes are defined through an outer surface of the at least one fuel injection body. The conduit fitting is coupled to the frame and conveys fuel from a fuel supply line to the fuel plenum. Fuel and the first fluid mix in the flow paths and are delivered through the outlet to the combustor.
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公开(公告)号：US20180058331A1
公开(公告)日：2018-03-01
申请号：US15254037
申请日：2016-09-01
摘要： A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.
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公开(公告)号：US09494321B2
公开(公告)日：2016-11-15
申请号：US14102006
申请日：2013-12-10
CPC分类号： F23R3/08 , F23R3/06 , F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00018 , F23R2900/03043
摘要： A wake reducing structure includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is a wake generating component boss operatively coupled to the combustor liner and disposed within a combustor liner aperture. Also included is a cooling channel extending through the wake generating component boss, the cooling channel having an air inlet on an upstream region of the wake generating component boss and an air outlet on a downstream region of the wake generating component boss, the cooling channel configured to supply air to the wake region.
摘要翻译： 尾流减少结构包括具有内表面和外表面的燃烧器衬套，内表面限定了燃烧室。 还包括沿着燃烧器衬套的外表面设置的气流路径。 进一步包括设置在气流路径中并且靠近燃烧器衬套的尾流产生部件，其中，尾流产生部件产生位于尾流产生部件下游的尾流区域。 另外还包括一个尾灯产生部件凸台，可操作地联接到燃烧器衬套并设置在燃烧器衬套孔内。 还包括延伸穿过尾流产生部件凸台的冷却通道，冷却通道在尾流产生部件凸台的上游区域上具有空气入口，在尾流发生部件凸起的下游区域具有空气出口，冷却通道配置 向尾流区供应空气。
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公开(公告)号：US20160218489A1
公开(公告)日：2016-07-28
申请号：US15088426
申请日：2016-04-01
IPC分类号： H01T21/02 , B23K26/342
CPC分类号： H01T21/02 , B23K26/342 , F02C7/18 , F02C7/266
摘要： An igniter tip for a combustion system is provided. The igniter tip may include a central electrode; an insulator sleeve about the central electrode; and an outer electrode about the insulator sleeve, the outer electrode including a tubular wall having a cooling passage extending within the tubular wall, the cooling passage including an entrance opening and an exit opening to an exterior of the outer electrode. A combustion system may include the igniter tip.
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16.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
CPC分类号： F23R3/60 , F23R3/005 , F23R3/34 , F23R2900/00017 , F23R2900/00019
摘要： 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.
摘要翻译： 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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17.发明授权System for controlling a flow rate of a compressed working fluid to a combustor fuel injector 有权用于控制压缩工作流体到燃烧器燃料喷射器的流量的系统公开(公告)号：US09376961B2
公开(公告)日：2016-06-28
申请号：US13845397
申请日：2013-03-18
摘要： A system for controlling air flow rate of a compressed working fluid to a fuel injector of a combustor includes an outer casing that defines a high pressure plenum around a portion of the combustor, an extraction port in fluid communication with the high pressure plenum and an inlet port. The combustor includes a plurality of fuel injectors arranged around a combustion liner, an inner flow sleeve, an outer air shield that surrounds the plurality of fuel injectors and the inner flow sleeve. The outer air shield defines an injection an air plenum between the outer air shield and the inner flow sleeve and an inlet to the injection air plenum. An external fluid circuit provides fluid communication between the extraction port and the inlet port. A baffle extends between the outer casing and the outer air shield to provide flow separation between the inlet and the high pressure plenum.
摘要翻译： 用于控制压缩工作流体对燃烧器的燃料喷射器的空气流量的系统包括：外壳，其围绕燃烧器的一部分限定高压增压室;与高压气室流体连通的抽出口和入口 港口。 燃烧器包括围绕燃烧衬套布置的多个燃料喷射器，内部流动套筒，围绕多个燃料喷射器和内部流动套筒的外部空气屏蔽件。 外部空气屏蔽件限定了在外部空气屏蔽和内部流动套筒之间的注入空气增压室和注入空气增压室的入口。 外部流体回路在提取口和入口之间提供流体连通。 挡板在外壳和外部空气屏蔽之间延伸，以提供入口和高压集气室之间的流动分离。
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公开(公告)号：US20160003150A1
公开(公告)日：2016-01-07
申请号：US14323144
申请日：2014-07-03
CPC分类号： H01T21/02 , B23K26/342 , F02C7/18 , F02C7/266
摘要： An igniter tip for a combustion system is provided. The igniter tip may include a central electrode; an insulator sleeve about the central electrode; and an outer electrode about the insulator sleeve, the outer electrode including a tubular wall having a cooling passage extending within the tubular wall, the cooling passage including an entrance opening and an exit opening to an exterior of the outer electrode. A combustion system may include the igniter tip.
摘要翻译： 提供了用于燃烧系统的点火器尖端。 点火头可包括中心电极; 围绕中心电极的绝缘体套管; 以及围绕所述绝缘体套筒的外部电极，所述外部电极包括具有在所述管状壁内延伸的冷却通道的管状壁，所述冷却通道包括入口和外部电极外部的出口。 燃烧系统可以包括点火器尖端。
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19.发明申请SYSTEM FOR COOLING A FUEL INJECTOR EXTENDING INTO A COMBUSTION GAS FLOW FIELD AND METHOD FOR MANUFACTURE 有权用于冷却燃料喷射器的系统扩展到燃烧气体流场和制造方法公开(公告)号：US20150285501A1
公开(公告)日：2015-10-08
申请号：US14247509
申请日：2014-04-08
CPC分类号： F23R3/283 , B22F1/0011 , B22F3/1055 , B22F5/10 , B22F5/106 , B33Y10/00 , B33Y80/00 , C22C1/0433 , F23R3/14 , F23R3/34 , F23R3/346 , Y02P10/295
摘要： A system for cooling a fuel injector extending into a combustion gas flow field includes a liner that defines a combustion gas flow path within a combustor and a fuel injector that extends through the liner. The fuel injector includes a main body having an annular first portion that extends outward from the liner and a second portion that extends from the first portion inward into the combustion gas flow path. The main body defines a cooling channel that is fully circumscribed within the main body and that extends between the first portion and the second portion. A cooling air inlet is defined within the annular first portion and is in fluid communication with the cooling channel. A cooling air outlet is in fluid communication with the cooling channel and is defined within the second portion downstream from the cooling air inlet.
摘要翻译： 用于冷却延伸到燃烧气体流场中的燃料喷射器的系统包括限定燃烧器内的燃烧气体流动路径和延伸穿过衬套的燃料喷射器的衬套。 燃料喷射器包括主体，其具有从衬套向外延伸的环形第一部分和从第一部分向内延伸到燃烧气体流动路径的第二部分。 主体限定了在主体内完全外接并在第一部分和第二部分之间延伸的冷却通道。 冷却空气入口限定在环形第一部分内并与冷却通道流体连通。 冷却空气出口与冷却通道流体连通并限定在冷却空气入口下游的第二部分内。
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公开(公告)号：US20150198332A1
公开(公告)日：2015-07-16
申请号：US14157021
申请日：2014-01-16
IPC分类号： F23R3/20
摘要： A combustion system is provided and includes an annular body defining a combustion zone and a fuel nozzle. The fuel nozzle includes a tubular element having a hollow interior and is disposable such that the hollow interior fluidly communicates with the combustion zone. The tubular element includes wall portions defining a channel disposable for fluid communication with at least one of the hollow interior and the combustion zone. The defined channel is pressurizable with coolant at a pressure exceeding that of the combustion zone.
摘要翻译： 提供燃烧系统并且包括限定燃烧区和燃料喷嘴的环形体。 燃料喷嘴包括具有中空内部并且是一次性的管状元件，使得中空内部与燃烧区流体连通。 管状元件包括限定通道的壁部分，该通道一次性用于与中空内部和燃烧区域中的至少一个流体连通。 限定的通道在压力超过燃烧区域的压力下可与冷却剂一起加压。
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