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公开(公告)号：US20160208700A1
公开(公告)日：2016-07-21
申请号：US15012173
申请日：2016-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Paul Minnear , Ronald Scott Bunker , Narendra Digamber Joshi , Andrei Tristan Evulet
CPC classification number: F02C7/16 , C04B41/0072 , C04B41/009 , C04B41/80 , F01D15/10 , F01D25/12 , F02C7/12 , F05D2260/232 , Y02T50/672 , Y02T50/676 , C04B35/56 , C04B35/565 , C04B35/806 , C04B41/4529
Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
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公开(公告)号：US09708977B2
公开(公告)日：2017-07-18
申请号：US14067844
申请日：2013-10-30
Applicant: General Electric Company
Inventor： John Farrior Woodall , Andrei Tristan Evulet , Samuel David Draper
Abstract: A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas to generate the combustion products, at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, and an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path.
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Patent Agency Ranking
公开(公告)号：US20140366550A1
公开(公告)日：2014-12-18
申请号：US13920244
申请日：2013-06-18
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Andrei Tristan Evulet
IPC: F02C3/04
CPC classification number: F02C7/141 , F02C3/10 , F23R3/18 , F23R3/26 , F23R2900/03341
Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and combusting the compressed air stream to generate a post combustion gas. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting the first turbine is split into a first stream, a second stream and a third stream in a splitting zone including one or more aerodynamically shaped flow diverters. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.
Abstract translation: 用于操作燃气涡轮发动机的燃气涡轮发动机和方法包括压缩压缩机中的空气流并燃烧压缩空气流以产生后燃烧气体。 后燃烧气体在第一涡轮机中膨胀。 离开第一涡轮机的膨胀的燃烧气体被分裂成包括一个或多个空气动力学形状的分流器的分流区中的第一流，第二流和第三流。 膨胀燃烧气体的第一流在再热燃烧器中燃烧。 使用扩展燃烧气体的第二流冷却再热燃烧器的外衬和火焰稳定器。 再加热燃烧器的内衬层使用膨胀燃烧气体的第三流冷却，并且膨胀的燃烧气体的第二流的一部分通过一个或多个火焰稳定器。
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4.发明申请公开(公告)号：US20140182299A1
公开(公告)日：2014-07-03
申请号：US14067844
申请日：2013-10-30
Applicant: General Electric Company
Inventor： John Farrior Woodall , Andrei Tristan Evulet , Samuel David Draper
IPC: F02C6/00
Abstract: A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas to generate the combustion products, at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, and an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path.
Abstract translation: 一种系统包括具有通过多个涡轮级的排气流动路径的涡轮机，其中所述多个涡轮级由流过所述排气流路的燃烧产物驱动，至少一个设置在所述涡轮机上游的主燃烧器，其中至少 一个主燃烧器被配置为燃烧燃料与第一氧化剂和废气以产生燃烧产物，至少一个再热燃烧器设置在涡轮机的涡轮级之间或涡轮级之间，其中至少一个再热燃烧器被配置为重新加热 通过添加第二氧化剂与燃烧产物中的未燃烧燃料反应的燃烧产物，以及排气压缩机，其中，排气压缩机构造成沿着排气口将废气从涡轮机压缩并路由至至少一个主燃烧器 再循环路径。
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公开(公告)号：US10161310B2
公开(公告)日：2018-12-25
申请号：US15012173
申请日：2016-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Paul Minnear , Ronald Scott Bunker , Narendra Digamber Joshi , Andrei Tristan Evulet
Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
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公开(公告)号：US09366184B2
公开(公告)日：2016-06-14
申请号：US13920244
申请日：2013-06-18
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Andrei Tristan Evulet
CPC classification number: F02C7/141 , F02C3/10 , F23R3/18 , F23R3/26 , F23R2900/03341
Abstract: A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and combusting the compressed air stream to generate a post combustion gas. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting the first turbine is split into a first stream, a second stream and a third stream in a splitting zone including one or more aerodynamically shaped flow diverters. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.
Abstract translation: 用于操作燃气涡轮发动机的燃气涡轮发动机和方法包括压缩压缩机中的空气流并燃烧压缩空气流以产生后燃烧气体。 后燃烧气体在第一涡轮机中膨胀。 离开第一涡轮机的膨胀的燃烧气体被分裂成包括一个或多个空气动力学形状的分流器的分流区中的第一流，第二流和第三流。 膨胀燃烧气体的第一流在再热燃烧器中燃烧。 使用扩展燃烧气体的第二流冷却再热燃烧器的外衬和火焰稳定器。 再加热燃烧器的内衬层使用膨胀燃烧气体的第三流冷却，并且膨胀的燃烧气体的第二流的一部分通过一个或多个火焰稳定器。
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公开(公告)号：US20160090912A1
公开(公告)日：2016-03-31
申请号：US14958971
申请日：2015-12-04
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Ross Hartley Kenyon , Andrei Tristan Evulet
CPC classification number: F02C7/052 , B01D45/04 , B64D33/02 , B64D2033/0246 , F05D2220/329 , F05D2260/607 , Y02T50/671 , Y02T50/675
Abstract: An inlet particle separator system coupled to an engine having an engine exhaust is presented. The inlet particle separator system includes an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air. The inlet particle separator system further includes a scavenge subsystem in flow communication with the axial flow separator for receiving the first flow of substantially contaminated air. Furthermore, the inlet particle separator system includes a fluidic device including a first inlet and an exhaust, where the fluidic device is configured to accelerate the first flow of substantially contaminated air through the scavenge subsystem and emit the first flow of substantially contaminated air via the exhaust of the fluidic device, wherein the exhaust of the fluidic device is different from an exhaust of the engine.
Abstract translation: 提出了一种与具有发动机排气的发动机连接的入口颗粒分离器系统。 入口颗粒分离器系统包括用于将空气从发动机入口分离成基本上被污染的空气的第一流和基本上清洁的空气的第二流的轴流分离器。 入口颗粒分离器系统还包括与轴流分离器流体连通的清除子系统，用于接收基本被污染的空气的第一流。 此外，入口颗粒分离器系统包括包括第一入口和排气的流体装置，其中流体装置构造成加速基本上被污染的空气的第一流通过扫气子系统，并且经由排气物排出基本上污染的空气的第一流 的流体装置，其中流体装置的排气与发动机的排气不同。
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