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公开(公告)号：US08745986B2
公开(公告)日：2014-06-10
申请号：US13545296
申请日：2012-07-10
Applicant: Patrick Benedict Melton , Bryan Wesley Romig , Lucas John Stoia , Thomas Edward Johnson
IPC: F02C3/16
Abstract: A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes.
Abstract translation: 一种用于燃气轮机的燃料供应系统包括燃烧部分，从燃烧部分下游的过渡管道，在过渡管道下游的涡轮部分以及周向布置在涡轮机部分内的静止叶片的第一级。 过渡管道和静止叶片之间的热气体路径，燃料喷射器提供与热气体通道的流体连通。 向燃气轮机供应燃料的方法包括在燃烧室中燃烧第一燃料以产生燃烧气体，使燃烧气体通过过渡管道流动到热气体路径，并使燃烧气体通过热气体路径流动到第一 在涡轮机部分的固定叶片的阶段。 该方法还包括将第二燃料喷射到从过渡管道下游的热气路径和静止叶片的第一级的上游。
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12.发明申请SYSTEMS AND METHODS FOR BULK TEMPERATURE VARIATION REDUCTION OF A GAS TURBINE THROUGH CAN-TO-CAN FUEL TEMPERATURE MODULATION 审中-公开通过CAN-to-CAN燃料温度调节对气体涡轮机进行温度变化的系统和方法公开(公告)号：US20130014514A1
公开(公告)日：2013-01-17
申请号：US13182956
申请日：2011-07-14
Applicant: Bryan Wesley Romig , Willy Steve Ziminsky , Derrick Walter Simons
Inventor： Bryan Wesley Romig , Willy Steve Ziminsky , Derrick Walter Simons
CPC classification number: F23R3/46 , F02C7/224 , F23K5/20 , F23K2301/204 , F23R3/28 , F23R2900/00013
Abstract: A gas turbine includes a plurality of combustion chambers; at least one fuel nozzle for each of the combustion chambers; at least one fuel line for each fuel nozzle in each of the combustion chambers; at least one heat exchanger for each fuel line configured to adjust a temperature of a fuel flow to each fuel nozzle; and a controller configured to control each of the heat exchangers to reduce temperature variations amongst the combustion chambers.
Abstract translation: 燃气轮机包括多个燃烧室; 用于每个燃烧室的至少一个燃料喷嘴; 用于每个燃烧室中的每个燃料喷嘴的至少一个燃料管线; 每个燃料管线的至少一个热交换器被配置为调节到每个燃料喷嘴的燃料流的温度; 以及控制器，被配置为控制每个所述热交换器以减少所述燃烧室之间的温度变化。
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公开(公告)号：US20120036859A1
公开(公告)日：2012-02-16
申请号：US12855154
申请日：2010-08-12
Applicant: Richard JOHNSON , Crystal McGee McConnaughhay , Bryan Wesley Romig
Inventor： Richard JOHNSON , Crystal McGee McConnaughhay , Bryan Wesley Romig
CPC classification number: F01D9/023 , F02C3/30 , F02C7/141 , F05D2240/127 , F05D2260/2212
Abstract: A gas turbine transition piece adapted to carry combustion gases in a hot gas path extending between a gas turbine combustion chamber and a first stage of the gas turbine, includes a hollow duct having a forward end adapted for connection to a combustor liner and an aft end adapted for connection to a first stage nozzle. One or more dilution air holes are located proximate the forward end, the dilution holes each fitted with a hollow sleeve penetrating into the hot gas path within the hollow duct, the hollow sleeves adapted to supply cooling air into the hot gas path.
Abstract translation: 适于在燃气轮机燃烧室和燃气涡轮机的第一级之间延伸的热气体路径中运送燃气的燃气轮机过渡件包括中空管道，其具有适于连接到燃烧器衬套的前端和后端 适于连接到第一级喷嘴。 一个或多个稀释气孔位于靠近前端的位置，每个稀释孔均装有穿过中空管道内的热气路径的中空套管，空心套筒适于将冷却空气供应到热气体通道中。
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公开(公告)号：US09016039B2
公开(公告)日：2015-04-28
申请号：US13439990
申请日：2012-04-05
Applicant: Lucas John Stoia , Patrick Benedict Melton , Bryan Wesley Romig
Inventor： Lucas John Stoia , Patrick Benedict Melton , Bryan Wesley Romig
CPC classification number: F23R3/346 , F23C6/047 , F23C2201/30 , F23R3/14 , F23R3/283 , F23R3/286 , F23R3/34 , F23R3/36 , F23R2900/03341
Abstract: A combustor includes a combustion chamber that defines a longitudinal axis. A primary reaction zone is inside the combustion chamber, and a secondary reaction zone inside the combustion chamber is downstream from the primary reaction zone. A center fuel nozzle extends axially inside the combustion chamber to the secondary reaction zone, and a plurality of fluid injectors circumferentially are arranged inside the center fuel nozzle downstream from the primary reaction zone. Each fluid injector defines an additional longitudinal axis out of the center fuel nozzle that is substantially perpendicular to the longitudinal axis of the combustion chamber.
Abstract translation: 燃烧器包括限定纵向轴线的燃烧室。 主反应区在燃烧室内，燃烧室内的二次反应区位于主反应区的下游。 中心燃料喷嘴在燃烧室内轴向延伸到二次反应区，并且多个流体喷射器周向布置在主反应区下游的中心燃料喷嘴的内部。 每个流体注入器限定基本上垂直于燃烧室的纵向轴线的中心燃料喷嘴外的附加纵向轴线。
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公开(公告)号：US20140013723A1
公开(公告)日：2014-01-16
申请号：US13545296
申请日：2012-07-10
Applicant: Patrick Benedict Melton , Bryan Wesley Romig , Lucas John Stoia , Thomas Edward Johnson
IPC: F02C3/30
Abstract: A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes.
Abstract translation: 一种用于燃气轮机的燃料供应系统包括燃烧部分，从燃烧部分下游的过渡管道，在过渡管道下游的涡轮部分以及周向布置在涡轮机部分内的静止叶片的第一级。 过渡管道和静止叶片之间的热气体路径，燃料喷射器提供与热气体通道的流体连通。 向燃气轮机供应燃料的方法包括在燃烧室中燃烧第一燃料以产生燃烧气体，使燃烧气体通过过渡管道流动到热气体路径，并使燃烧气体通过热气体路径流动到第一 在涡轮机部分的固定叶片的阶段。 该方法还包括将第二燃料喷射到从过渡管道下游的热气路径和静止叶片的第一级的上游。
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Patent Agency Ranking
公开(公告)号：US20130283801A1
公开(公告)日：2013-10-31
申请号：US13457726
申请日：2012-04-27
Applicant: Bryan Wesley Romig , Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Gregory Allen Boardman
Inventor： Bryan Wesley Romig , Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Gregory Allen Boardman
IPC: F23R3/34
Abstract: A system for supplying fuel to a combustor includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber. A plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber. A liquid fuel plenum provides fluid communication to the plurality of passages. A baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum.
Abstract translation: 用于向燃烧器供应燃料的系统包括提供与燃烧室的流体连通的燃烧室和燃料喷嘴。 围绕燃烧室周向布置的多个通道提供流体连通到燃烧室中。 液体燃料增压室提供与多个通道的流体连通。 挡板周向地围绕多个通道内的液体燃料增压室的至少一部分，并在液体燃料增压室周围形成多个叶片。
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公开(公告)号：US20130219899A1
公开(公告)日：2013-08-29
申请号：US13405550
申请日：2012-02-27
Applicant: Jong Ho Uhm , Derrick Walter Simons , Gregory Allen Boardman , Bryan Wesley Romig , Kara Edwards , Michael John Hughes
Inventor： Jong Ho Uhm , Derrick Walter Simons , Gregory Allen Boardman , Bryan Wesley Romig , Kara Edwards , Michael John Hughes
IPC: F23R3/28
CPC classification number: F23R3/286 , F23C7/004 , F23C2900/07001 , F23D14/08 , F23R3/14 , F23R3/343 , F23R2900/03343
Abstract: A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits.
Abstract translation: 用于燃气涡轮发动机的燃烧器具有承载至少一个燃料/空气喷嘴的头端部分。 每个燃料/空气喷嘴包括预混合引燃喷嘴，其具有预混合导管，其配置有同心轴线，其将燃料/空气混合物从预混合的先导喷嘴轴向引导。 预混合引导喷嘴可以包括从预混物径向向外设置的环形通道，并且包括从预混合导管径向向外引导空气的空气射流。
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公开(公告)号：US20130098053A1
公开(公告)日：2013-04-25
申请号：US13277352
申请日：2011-10-20
Applicant: Michael John Hughes , Bryan Wesley Romig , Abdul Rafey Khan
Inventor： Michael John Hughes , Bryan Wesley Romig , Abdul Rafey Khan
IPC: F02C9/26
Abstract: A control system for use with a turbine engine that is configured to operate at a rated power output is provided. The control system includes a computing device that includes a processor that is programmed to calculate an amount of fluid to be supplied for combustion in the turbine engine. The processor is also programmed to designate at least one nozzle of a plurality of nozzles to receive the fluid. Moreover, the control system includes at least one control valve coupled to the computing device. The control valve is configured to receive at least one control parameter from the computing device for use in modulating the amount of the fluid to be channeled to the nozzle such that the rated power output is generated while emission levels are maintained below a predefined emissions threshold level.
Abstract translation: 提供了一种与被配置为以额定功率输出操作的涡轮发动机一起使用的控制系统。 控制系统包括计算装置，该计算装置包括处理器，该处理器被编程为计算用于在涡轮发动机中燃烧供应的流体的量。 处理器还被编程为指定多个喷嘴的至少一个喷嘴以接收流体。 此外，控制系统包括耦合到计算设备的至少一个控制阀。 所述控制阀配置成从所述计算装置接收至少一个控制参数，以用于调制要引导到所述喷嘴的流体的量，使得在排放水平保持低于预定排放阈值水平时产生所述额定功率输出 。
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公开(公告)号：US20110225973A1
公开(公告)日：2011-09-22
申请号：US12726704
申请日：2010-03-18
Applicant: Bryan Wesley Romig , Derrick Walter Simons , Lucas John Stoia , Karthik Subramanian
Inventor： Bryan Wesley Romig , Derrick Walter Simons , Lucas John Stoia , Karthik Subramanian
Abstract: A combustor includes a first combustion chamber, a pre-mixing primary fuel-nozzle assembly associated with the first combustion chamber, a second combustion chamber, and a secondary fuel-nozzle assembly associated with the second combustion chamber. The pre-mixing primary fuel-nozzle assembly includes a number of vanes configured to swirl airflow, each vane comprising a number of fuel injection holes configured to inject fuel into the airflow.
Abstract translation: 燃烧器包括第一燃烧室，与第一燃烧室相关联的预混合初级燃料喷嘴组件，第二燃烧室和与第二燃烧室相关联的二次燃料喷嘴组件。 预混合的主燃料喷嘴组件包括多个叶片，其构造成涡流，每个叶片包括多个燃料喷射孔，其被配置为将燃料喷射到气流中。
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公开(公告)号：US20110162377A1
公开(公告)日：2011-07-07
申请号：US12683102
申请日：2010-01-06
Applicant: Marc Lionel Benjamin , Bryan Wesley Romig , Derrick Walter Simons , Lucas John Stoia
Inventor： Marc Lionel Benjamin , Bryan Wesley Romig , Derrick Walter Simons , Lucas John Stoia
IPC: F02C7/22
CPC classification number: F23R3/28 , F01D9/023 , F02C7/12 , F02C7/18 , F02C7/22 , F05D2260/14 , F23R3/14
Abstract: A turbomachine includes a compressor, a turbine, a combustor operatively coupled to the compressor and the turbine, and an injection nozzle assembly mounted in the combustor. The injection nozzle assembly includes a swirler member provided with a hub portion having an internal surface. The injection nozzle assembly also includes a nozzle section, and a nozzle tip member fluidly coupled to the nozzle section and the swirler member. The nozzle tip member includes a body having a first end section that extends from the nozzle section to a second end section arranged in the hub portion of the swirler member. The nozzle tip member includes an external surface, and a discharge port. At least one of the external surface of the nozzle tip member and the internal surface of the swirler member hub portion is provided with a plurality of grooves.
Abstract translation: 涡轮机包括压缩机，涡轮机，可操作地联接到压缩机和涡轮机的燃烧器，以及安装在燃烧器中的喷嘴组件。 注射喷嘴组件包括设置有具有内表面的毂部的旋流器构件。 注射喷嘴组件还包括喷嘴部分和流体地联接到喷嘴部分和旋流器部件的喷嘴尖端部件。 喷嘴头构件包括具有第一端部的本体，该第一端部从喷嘴部延伸到设置在旋流器构件的毂部中的第二端部。 喷嘴头构件包括外表面和排出口。 喷嘴头部件的外表面和旋流器部件毂部的内表面中的至少一个设置有多个槽。
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