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1. 发明授权

US08745987B2 Late lean injection manifold 有权
标题翻译：延迟注射歧管
公开(公告)号：US08745987B2
公开(公告)日：2014-06-10
申请号：US12914537
申请日：2010-10-28
申请人： Lucas John Stoia , Jonathan Hale Kegley , Crystal McGee McConnaughhay , Bryan Wesley Romig
发明人： Lucas John Stoia , Jonathan Hale Kegley , Crystal McGee McConnaughhay , Bryan Wesley Romig
IPC分类号： F02C7/228
CPC分类号： F02C7/22 , F05D2270/07 , F05D2270/31
摘要： A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube extending from the central nozzle to the first side nozzle such that fuel is communicable between the connector, the central nozzle and the first side nozzle and a second leg. The second leg is formed to define a tube extending from the central nozzle to the second side nozzle such that the fuel is communicable between the central nozzle and the second side nozzle.
摘要翻译：提供了一种后期稀薄注射（LLI）歧管，并且包括中心喷嘴和位于围绕容器限定的周向位置处的第一和第二侧面喷嘴，连接器，连接器连接的第一腿，形成为限定延伸的管从中心喷嘴到第一侧喷嘴，使得燃料可在连接器，中心喷嘴和第一侧喷嘴与第二支管之间连通。第二腿形成为限定从中心喷嘴延伸到第二侧喷嘴的管，使得燃料可在中心喷嘴和第二侧喷嘴之间连通。

2. 发明申请

US20120102958A1 LATE LEAN INJECTION MANIFOLD 有权
标题翻译：最新推荐注意事项
公开(公告)号：US20120102958A1
公开(公告)日：2012-05-03
申请号：US12914537
申请日：2010-10-28
申请人： Lucas John Stoia , Jonathan Hale Kegley , Crystal McGee McConnaughhay , Bryan Wesley Romig
发明人： Lucas John Stoia , Jonathan Hale Kegley , Crystal McGee McConnaughhay , Bryan Wesley Romig
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F05D2270/07 , F05D2270/31
摘要： A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube extending from the central nozzle to the first side nozzle such that fuel is communicable between the connector, the central nozzle and the first side nozzle and a second leg. The second leg is formed to define a tube extending from the central nozzle to the second side nozzle such that the fuel is communicable between the central nozzle and the second side nozzle.
摘要翻译：提供了一种后期稀薄注射（LLI）歧管，并且包括中心喷嘴和位于围绕容器限定的周向位置处的第一和第二侧面喷嘴，连接器，连接器连接的第一腿，形成为限定延伸的管从中心喷嘴到第一侧喷嘴，使得燃料可在连接器，中心喷嘴和第一侧喷嘴与第二支管之间连通。第二腿形成为限定从中心喷嘴延伸到第二侧喷嘴的管，使得燃料可在中心喷嘴和第二侧喷嘴之间连通。

3. 发明申请

US20120036859A1 COMBUSTOR TRANSITION PIECE WITH DILUTION SLEEVES AND RELATED METHOD 审中-公开
公开(公告)号：US20120036859A1
公开(公告)日：2012-02-16
申请号：US12855154
申请日：2010-08-12
申请人： Richard JOHNSON , Crystal McGee McConnaughhay , Bryan Wesley Romig
发明人： Richard JOHNSON , Crystal McGee McConnaughhay , Bryan Wesley Romig
IPC分类号： F02C1/00 , F02C7/12
CPC分类号： F01D9/023 , F02C3/30 , F02C7/141 , F05D2240/127 , F05D2260/2212
摘要： 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.
摘要翻译：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。

4. 发明申请

US20120247108A1 COMBUSTOR PROBE FOR GAS TURBINE 有权
标题翻译：燃气涡轮机COMBUSTOR探头
公开(公告)号：US20120247108A1
公开(公告)日：2012-10-04
申请号：US13075055
申请日：2011-03-29
申请人： Bryan Wesley Romig , Jonathan Hale Kegley , Robert Wade Clifford , Derrick Walter Simons
发明人： Bryan Wesley Romig , Jonathan Hale Kegley , Robert Wade Clifford , Derrick Walter Simons
IPC分类号： F23R3/00 , G01N1/22 , G01M15/00
CPC分类号： G01N1/2252 , F01D21/003 , F05D2270/80 , F23N5/003 , F23N5/18 , F23N2031/18 , F23N2041/20 , F23N2900/05005 , F23R3/00
摘要： Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor.
摘要翻译：本公开的实施例涉及具有燃烧动力学监测探针的涡轮机燃烧器探头，其被配置为监测涡轮机燃烧器内的燃烧动力学。涡轮机燃烧器探头还具有气体采样套筒，该气体采样套筒构造成从涡轮机燃烧器的衬套和流动套筒之间的气流通道收集气体样品。

5. 发明授权

US08997558B2 Combustor probe for gas turbine 有权
标题翻译：燃气轮机用燃烧器探头
公开(公告)号：US08997558B2
公开(公告)日：2015-04-07
申请号：US13075055
申请日：2011-03-29
申请人： Bryan Wesley Romig , Jonathan Hale Kegley , Robert Wade Clifford , Derrick Walter Simons
发明人： Bryan Wesley Romig , Jonathan Hale Kegley , Robert Wade Clifford , Derrick Walter Simons
IPC分类号： G01M15/05 , G01N1/22 , F01D21/00
CPC分类号： G01N1/2252 , F01D21/003 , F05D2270/80 , F23N5/003 , F23N5/18 , F23N2031/18 , F23N2041/20 , F23N2900/05005 , F23R3/00
摘要： Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor.
摘要翻译：本公开的实施例涉及具有燃烧动力学监测探针的涡轮机燃烧器探头，其被配置为监测涡轮机燃烧器内的燃烧动力学。涡轮机燃烧器探头还具有气体采样套筒，该气体采样套筒构造成从涡轮机燃烧器的衬套和流动套筒之间的气流通道收集气体样品。

6. 发明申请

US20130283807A1 SYSTEM AND METHOD FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR 有权
标题翻译：向工作人员提供工作流体的系统和方法
公开(公告)号：US20130283807A1
公开(公告)日：2013-10-31
申请号：US13455480
申请日：2012-04-25
申请人： Lucas John Stoia , Bryan Wesley Romig , Thomas Edward Johnson , Christian Xavier Stevenson
发明人： Lucas John Stoia , Bryan Wesley Romig , Thomas Edward Johnson , Christian Xavier Stevenson
IPC分类号： F23R3/28
CPC分类号： F23R3/346 , F23R3/34 , F23R2900/03341
摘要： A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. Injectors circumferentially arranged around the flow sleeve provide fluid communication through the flow sleeve and into the combustion chamber. A valve upstream from the injectors has a first position that permits working fluid flow to the injectors and a second position that prevents working fluid flow to the injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through injectors circumferentially arranged around the combustion chamber, and operating a valve upstream from the injectors to control the working fluid flow through the injectors.
摘要翻译：用于向燃烧器供应工作流体的系统包括燃料喷嘴，燃料喷嘴下游的燃烧室和周向围绕燃烧室的流动套筒。周向布置在流动套筒周围的注射器提供通过流动套筒并进入燃烧室的流体连通。喷射器上游的阀具有允许工作流体流向喷射器的第一位置和防止工作流体流向喷射器的第二位置。用于将工作流体供应到燃烧室的方法包括使工作流体流过燃烧室，使工作流体的一部分通过周向布置在燃烧室周围的喷射器转向，并且在喷射器上游操作阀以控制工作流体流动通过注射器。

7. 发明授权

US09284888B2 System for supplying fuel to late-lean fuel injectors of a combustor 有权
标题翻译：用于向燃烧器的后期稀燃燃料喷射器供应燃料的系统
公开(公告)号：US09284888B2
公开(公告)日：2016-03-15
申请号：US13455429
申请日：2012-04-25
申请人： Bryan Wesley Romig , Lucas John Stoia
发明人： Bryan Wesley Romig , Lucas John Stoia
IPC分类号： F02C7/22 , F23R3/34 , F23R3/06 , F23R3/28
CPC分类号： F02C7/22 , F23R3/06 , F23R3/286 , F23R3/346
摘要： A system for supplying fuel to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for a working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube includes a tube wall. A plurality of fuel ports through the tube wall provide fluid communication for fuel to flow through the tube wall and into the tube, and the fuel ports are non-circular.
摘要翻译：用于向燃烧器供应燃料的系统包括燃烧室，周向围绕燃烧室的至少一部分的衬套和周向围绕衬套的至少一部分的流动套筒。管提供用于工作流体的流体连通以流过流动套管和衬套并进入燃烧室，并且管包括管壁。通过管壁的多个燃料端口提供流体连通，用于燃料流过管壁并进入管中，并且燃料端口是非圆形的。

8. 发明授权

US08745986B2 System and method of supplying fuel to a gas turbine 有权
标题翻译：向燃气轮机供应燃料的系统和方法
公开(公告)号：US08745986B2
公开(公告)日：2014-06-10
申请号：US13545296
申请日：2012-07-10
申请人： Patrick Benedict Melton , Bryan Wesley Romig , Lucas John Stoia , Thomas Edward Johnson
发明人： Patrick Benedict Melton , Bryan Wesley Romig , Lucas John Stoia , Thomas Edward Johnson
IPC分类号： F02C3/16
CPC分类号： F02C7/22 , F01D9/023
摘要： 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.
摘要翻译：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。

9. 发明申请

US20130263571A1 COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR 有权
标题翻译：用于向燃烧器供应燃料的燃烧器和方法
公开(公告)号：US20130263571A1
公开(公告)日：2013-10-10
申请号：US13439990
申请日：2012-04-05
申请人： Lucas John Stoia , Patrick Benedict Melton , Bryan Wesley Romig
发明人： Lucas John Stoia , Patrick Benedict Melton , Bryan Wesley Romig
IPC分类号： F02C3/22 , F02C3/24 , F02C7/22
CPC分类号： F23R3/346 , F23C6/047 , F23C2201/30 , F23R3/14 , F23R3/283 , F23R3/286 , F23R3/34 , F23R3/36 , F23R2900/03341
摘要： 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.
摘要翻译：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。

10. 发明授权

US09016039B2 Combustor and method for supplying fuel to a combustor 有权
标题翻译：用于向燃烧器供应燃料的燃烧器和方法
公开(公告)号：US09016039B2
公开(公告)日：2015-04-28
申请号：US13439990
申请日：2012-04-05
申请人： Lucas John Stoia , Patrick Benedict Melton , Bryan Wesley Romig
发明人： Lucas John Stoia , Patrick Benedict Melton , Bryan Wesley Romig
IPC分类号： F23R3/34 , F23R3/28 , F23R3/14 , F23C6/04 , F23R3/36
CPC分类号： F23R3/346 , F23C6/047 , F23C2201/30 , F23R3/14 , F23R3/283 , F23R3/286 , F23R3/34 , F23R3/36 , F23R2900/03341
摘要： 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.
摘要翻译：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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