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公开(公告)号：US20170268778A1
公开(公告)日：2017-09-21
申请号：US15070047
申请日：2016-03-15
Applicant: General Electric Company
Inventor： Lucas John Stoia , Ronnie Ray Pentecost , Jonathan Hale Kegley
Abstract: The present disclosure is directed to a combustor including an annularly shaped liner that at least partially defines a hot gas path of the combustor and a flow sleeve that circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A plurality of fuel injector assemblies circumferentially spaced about the flow sleeve and each fuel injector assembly extends radially through the flow sleeve, the cooling flow annulus and the liner. A first portion of the flow sleeve defined between a first pair of circumferentially adjacent fuel injector assemblies of the plurality of fuel injector assemblies bulges radially outwardly with respect to an outer surface of the liner so as to enlarge a flow volume of the cooling flow annulus.
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公开(公告)号：US09709279B2
公开(公告)日：2017-07-18
申请号：US14192687
申请日：2014-02-27
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Lucas John Stoia , William Francis Carnell, Jr.
CPC classification number: F23R3/42 , F23R3/04 , F23R3/16 , F23R3/26 , F23R3/46 , F23R2900/00014 , Y02T50/675
Abstract: A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed in the first oxidant flow path. The second combustor includes a second oxidant flow path and a second perforated structure comprising a second plurality of oxidant ports. The second perforated structure is disposed in the second oxidant flow path and the first perforated structure has at least one difference relative to the second perforated structure.
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公开(公告)号：US09528703B2
公开(公告)日：2016-12-27
申请号：US14032225
申请日：2013-09-20
Applicant: General Electric Company
Inventor： Christopher Paul Willis , Patrick Benedict Melton , Lucas John Stoia
CPC classification number: F23R3/286 , B23K1/0018 , F23R3/283 , F23R2900/00017 , F23R2900/00018
Abstract: The present application provides a fuel plenum for a micro-mixer combustor. The fuel plenum may include a first assembly plate with a first assembly plate aperture, a second assembly plate with a second assembly plate aperture, a fuel tube extending through the first assembly plate aperture of the first assembly plate and the second assembly plate aperture of the second assembly plate, and an installation insert positioned between the fuel tube and the first assembly plate aperture.
Abstract translation: 本申请提供了一种用于微型混合器燃烧器的燃料增压室。 燃料增压室可以包括具有第一组件板孔的第一组件板，具有第二组件板孔的第二组件板，延伸穿过第一组件板的第一组件板孔的燃料管和第二组合板孔 第二组装板和位于燃料管和第一组装板孔之间的安装插入件。
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公开(公告)号：US09291350B2
公开(公告)日：2016-03-22
申请号：US13845407
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio
Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber disposed downstream from the fuel nozzle, an inner flow sleeve that circumferentially surrounds the combustion chamber and a plurality of injectors circumferentially arranged around the inner flow sleeve. The plurality of injectors provide for fluid communication through the inner flow sleeve and into the combustion chamber downstream from the fuel nozzle. The system further includes an outer air shield that defines an injection air plenum that surrounds the plurality of injectors. An inlet passage extends through the outer air shield to define a flow path into the injection air plenum. An outer sleeve is slidingly engaged with the outer air shield. The outer sleeve has a first position that restricts flow through the inlet passage and a second position that increases flow through the inlet passage.
Abstract translation: 用于向燃烧器供应工作流体的系统包括燃料喷嘴，设置在燃料喷嘴下游的燃烧室，周向围绕燃烧室的内部流动套筒和围绕内部流动套筒周向布置的多个喷射器。 多个喷射器提供通过内部流动套筒的流体连通并进入燃料喷嘴下游的燃烧室。 该系统还包括限定围绕多个喷射器的喷射空气室的外部空气屏蔽。 入口通道延伸穿过外部空气屏蔽件以限定进入注入空气室的流动路径。 外套筒与外部空气屏蔽滑动接合。 外套筒具有限制通过入口通道的流动的第一位置和增加通过入口通道的流动的第二位置。
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公开(公告)号：US09267436B2
公开(公告)日：2016-02-23
申请号：US13845422
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Lucas John Stoia , Patrick Benedict Melton , Stanley Kevin Widener , William Michael Poschel
Abstract: A fuel distribution manifold for a combustor of a gas turbine includes an annular flange having an outer surface that extends circumferentially around the flange. A primary fuel plenum extends circumferentially within the flange. A first orifice and a second orifice extend radially through the outer surface of the flange to provide for fluid communication into the primary fuel plenum. The first orifice includes an inlet that is adjacent to the outer surface. The second orifice includes an inlet that is adjacent to the outer surface. A fuel distribution cap extends partially across the outer surface of the flange. The fuel distribution cap includes an inlet port. A fuel distribution plenum is at least partially defined within the fuel distribution cap. The fuel distribution plenum is in fluid communication with the inlet port and with the first orifice inlet and the second orifice inlet.
Abstract translation: 用于燃气涡轮机的燃烧器的燃料分配歧管包括具有围绕凸缘周向延伸的外表面的环形凸缘。 主燃料增压室在凸缘内周向延伸。 第一孔口和第二孔口径向延伸穿过凸缘的外表面以提供流体连通到主燃料增压室中。 第一孔包括邻近外表面的入口。 第二孔包括与外表面相邻的入口。 燃料分配帽部分地延伸穿过凸缘的外表面。 燃料分配盖包括入口端口。 燃料分配室至少部分地限定在燃料分配盖内。 燃料分配气室与入口端口和第一孔口入口和第二孔口入口流体连通。
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Patent Agency Ranking
公开(公告)号：US20160047316A1
公开(公告)日：2016-02-18
申请号：US14459392
申请日：2014-08-14
Applicant: General Electric Company
Inventor： Patrick Benedict Melton , Vaibhav Nadkarni , Hasan Karim , Lucas John Stoia
Abstract: A gas turbine engine having a combustor that includes: an inner radial wall defining axially stacked first and second interior chambers, wherein the first interior chamber extends axially from an end cover to a fuel nozzle, and the second interior chamber extends axially from the fuel nozzle to an inlet of the turbine; and an outer radial wall formed about the inner radial wall so to form a flow annulus therebetween. The flow annulus may include a flow conditioning section that has: conditioning passages defined therethrough for directing a flow from inlets formed at an upstream end to outlets formed at a downstream end of the flow conditioning section; and structure rigidly attaching the inner radial wall to the outer radial wall.
Abstract translation: 一种具有燃烧器的燃气涡轮发动机，其包括：限定轴向堆叠的第一和第二内部室的内部径向壁，其中所述第一内部腔室从端盖轴向延伸到燃料喷嘴，并且所述第二内部腔室从所述燃料喷嘴 到涡轮机的入口; 以及围绕内部径向壁形成的外部径向壁，以在它们之间形成流动环空。 流动环空可以包括流动调节部分，其具有通过限定的调节通道，用于将形成在上游端的入口的流动引导到形成在流量调节部分的下游端的出口; 并且结构将内部径向壁刚性地附接到外部径向壁。
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公开(公告)号：US20150159877A1
公开(公告)日：2015-06-11
申请号：US14099515
申请日：2013-12-06
Applicant: General Electric Company
Inventor： Lucas John Stoia , Patrick Benedict Melton , Ronnie Ray Pentecost , William Francis Carnell, JR.
Abstract: A manifold mixing system for combustor of a gas turbine engine includes a fuel supply, a fuel injector coupled with the fuel supply, and a manifold mixer cooperable with the fuel injector and including mixing air inlets. The fuel injector is displaceable relative to the manifold mixer while being positioned to deliver fuel from the fuel supply to the manifold mixer. The manifold mixer is shaped to mix the fuel from the fuel supply with air input via the mixing air inlets for injection into the combustor.
Abstract translation: 用于燃气涡轮发动机的燃烧器的歧管混合系统包括燃料供应器，与燃料供应器耦合的燃料喷射器以及与燃料喷射器配合并包括混合空气入口的歧管混合器。 燃料喷射器相对于歧管混合器可位移，同时被定位成将燃料从燃料供应输送到歧管混合器。 歧管混合器成形为将来自燃料供应的燃料与通过混合空气入口的空气输入混合以便注入燃烧器。
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88.发明申请COMBUSTOR SUPPORT ASSEMBLY FOR MOUNTING A COMBUSTION MODULE OF A GAS TURBINE 有权用于安装燃气涡轮机燃烧模块的COMBUSTOR支持组件公开(公告)号：US20140260319A1
公开(公告)日：2014-09-18
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
IPC: F23R3/60
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：US20140260275A1
公开(公告)日：2014-09-18
申请号：US13845378
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio
IPC: F23R3/20
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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90.发明申请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：US20140260264A1
公开(公告)日：2014-09-18
申请号：US13845397
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Lucas John Stoia , Patrick Benedict Melton , Richard Martin DiCintio
IPC: F02C7/22
CPC classification number: F02C7/22 , F01D9/02 , F02C6/08 , F02C9/52 , F23R3/045 , F23R3/26 , F23R3/346
Abstract: 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.
Abstract translation: 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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