专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明专利

JP2011141111A Turbo machine nozzle 审中-公开
标题翻译：涡轮喷嘴
公开(公告)号：JP2011141111A
公开(公告)日：2011-07-21
申请号：JP2010285237
申请日：2010-12-22
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： BENJAMIN MARC LIONEL , ROMIG BRYAN WESLEY , SIMONS DERRICK W , STOIA LUCAS JOHN
IPC分类号： F23R3/28 , F02C7/18 , F23R3/14 , F23R3/34
CPC分类号： F23R3/28 , F01D9/023 , F02C7/12 , F02C7/18 , F02C7/22 , F05D2260/14 , F23R3/14
摘要： PROBLEM TO BE SOLVED: To cool a swirler hub of a tip of an injection nozzle assembly mounted in a combustor of a gas turbine. SOLUTION: The injection nozzle assembly 38 includes a swirler member 117 provided with a hub portion 120 having an internal surface 121. The injection nozzle assembly 38 also includes a nozzle section 85, and a nozzle tip member 124 fluidly coupled to the nozzle section 85 and the swirler member 117. The nozzle tip member 124 includes a body having a first end section that extends from the nozzle section 85 to a second end section arranged in the hub portion 120 of the swirler member 117. The nozzle tip member includes an external surface, and a discharge port. At least one of the external surface of the nozzle tip member 124 and the internal surface 121 of the swirler member 117 hub portion 120 is provided with a plurality of grooves. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：冷却安装在燃气轮机的燃烧器中的喷嘴组件的尖端的旋流器毂。注射喷嘴组件38包括设置有具有内表面121的轮毂部分120的旋流器构件117.喷射喷嘴组件38还包括喷嘴部分85和与喷嘴流体连接的喷嘴尖端部件124 部分85和旋流器构件117.喷嘴末端构件124包括具有从喷嘴部分85延伸到设置在旋流器构件117的毂部120中的第二端部的第一端部的主体。喷嘴尖端构件包括外表面和排出口。喷嘴头构件124的外表面和旋流器构件117毂部120的内表面121中的至少一个设置有多个凹槽。版权所有（C）2011，JPO＆INPIT

2. 发明专利

JP2011196681A Combustor with pre-mixing primary fuel-nozzle assembly 审中-公开
标题翻译：燃烧器与预混合燃料喷射装置
公开(公告)号：JP2011196681A
公开(公告)日：2011-10-06
申请号：JP2011082252
申请日：2011-03-16
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： ROMIG BRYAN WESLEY , STOIA LUCAS JOHN , SUBRAMANIAN KARTHIK , SIMONS DERRICK W
IPC分类号： F23R3/28 , F23R3/06 , F23R3/14 , F23R3/30
CPC分类号： F23R3/286 , F23R3/346
摘要： PROBLEM TO BE SOLVED: To provide a two-stage low NOx combustor with a pre-mixing primary fuel-nozzle assembly.SOLUTION: The combustor 200 includes a first combustion chamber 202, a pre-mixing primary fuel-nozzle assembly 210 associated with the first combustion chamber 202, a second combustion chamber 204, and a secondary fuel-nozzle assembly 212 associated with the second combustion chamber 204. The pre-mixing primary fuel-nozzle assembly 210 includes a number of vanes 222 configured to swirl airflow, each vane 222 comprising a number of fuel injection holes 224 configured to inject fuel into the airflow.
摘要翻译：要解决的问题：提供具有预混合的一次燃料喷嘴组件的两级低NOx燃烧器。解决方案：燃烧器200包括第一燃烧室202，与第一燃料喷嘴组件210相关联的预混合主燃料喷嘴组件210 第一燃烧室202，第二燃烧室204和与第二燃烧室204相关联的二次燃料喷嘴组件212.预混合的主燃料喷嘴组件210包括多个叶片222，其构造成涡流，每个叶片 222包括多个燃料喷射孔224，其被配置为将燃料喷射到气流中。

3. 发明专利

JP2013228194A System for supplying fuel to combustor 有权
标题翻译：燃料供应系统
公开(公告)号：JP2013228194A
公开(公告)日：2013-11-07
申请号：JP2013089879
申请日：2013-04-23
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： ROMIG BRYAN WESLEY , STOIA LUCAS JOHN
IPC分类号： F23R3/28 , F23R3/32
CPC分类号： F02C7/22 , F23R3/06 , F23R3/286 , F23R3/346
摘要： PROBLEM TO BE SOLVED: To provide a system for supplying fuel to a combustor.SOLUTION: 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：要解决的问题：提供一种用于向燃烧器供应燃料的系统。解决方案：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流动套管，周向地包围衬垫的至少一部分。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。

4. 发明专利

JP2012093080A Late lean injection manifold 有权
标题翻译：最新推荐注意事项
公开(公告)号：JP2012093080A
公开(公告)日：2012-05-17
申请号：JP2011231208
申请日：2011-10-21
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： STOIA LUCAS JOHN , KEGLEY JONATHAN HALE , MCCONNAUGHHAY CRYSTAL MCGEE , ROMIG BRYAN WESLEY
IPC分类号： F23R3/28 , F02C7/228 , F23R3/32
CPC分类号： F02C7/22 , F05D2270/07 , F05D2270/31
摘要： PROBLEM TO BE SOLVED: To provide a late lean injection manifold.SOLUTION: The late lean injection (LLI) manifold 70 is provided and includes a central nozzle 80 and first and second side nozzles 81 and 82 positioned at circumferential locations defined around a vessel, a connector 50, a first leg 71, to which the connector 50 is connected, formed to define a tube extending from the central nozzle 80 to the first side nozzle 81 such that fuel is communicable between the connector 50, the central nozzle 80 and the first side nozzle 81 and a second leg 72. The second leg 72 is formed to define a tube extending from the central nozzle 80 to the second side nozzle 82 such that the fuel is communicable between the central nozzle 80 and the second side nozzle 82.
摘要翻译：要解决的问题：提供后期的稀注射歧管。解决方案：提供后期稀薄注射（LLI）歧管70，并且包括中心喷嘴80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81和82，连接器50，第一腿部71，至连接器50连接的连接器50形成为限定从中心喷嘴80延伸到第一侧喷嘴81的管，使得燃料可在连接器50，中心喷嘴80和第一侧喷嘴81与第二支腿72之间连通。第二腿72形成为限定从中心喷嘴80延伸到第二侧喷嘴82的管，使得燃料可在中心喷嘴80和第二侧喷嘴82之间连通。（C）2012年， JPO＆INPIT

5. 发明专利

JP2011237168A Turbomachine injection nozzle assembly 审中-公开
标题翻译：涡轮喷射喷嘴组件
公开(公告)号：JP2011237168A
公开(公告)日：2011-11-24
申请号：JP2011095573
申请日：2011-04-22
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： JOHNSON RICHARD WILLIAM , ROMIG BRYAN WESLEY
IPC分类号： F23R3/14 , F23R3/18
CPC分类号： F23R3/14 , F23R3/286
摘要： PROBLEM TO BE SOLVED: To provide a combustor swirler capable of uniformizing the velocity distribution of the downstream of the swirler and lowering NOx emission.SOLUTION: A turbomachine includes a compressor, a turbine, a combustor operatively coupled to the compressor and the turbine, and an injection nozzle assembly 38 mounted in the combustor. The injection nozzle assembly 38 includes a swirler member 74 for conditioning a fluid flow passing through the injection nozzle assembly 38. The swirler member 74 includes a hub portion 84, a plurality of vanes 86 that extend from the hub portion 84, and at least one flow conditioning band 94, 95. The at least one flow conditioning band 94, 95 extends around the hub portion 84 and between the plurality of vanes 86 to provide a localized flow impediment within the injection nozzle assembly 38.
摘要翻译：要解决的问题：提供能够使旋流器下游的速度分布均匀化并降低NOx排放的燃烧器旋流器。解决方案：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38。注射喷嘴组件38包括用于调节通过喷嘴组件38的流体流的旋流器构件74.旋流器构件74包括毂部分84，从轮毂部分84延伸的多个叶片86和至少一个流动调节带94,95。至少一个流动调节带94,95围绕毂部分84延伸并且在多个叶片86之间延伸，以在喷嘴组件38内提供局部流动障碍。版权所有（C））2012，JPO＆INPIT

6. 发明专利

JP2014102068A Turbomachine with trapped vortex feature 审中-公开
标题翻译：涡轮发动机带有VORTEX特征
公开(公告)号：JP2014102068A
公开(公告)日：2014-06-05
申请号：JP2013238394
申请日：2013-11-19
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： STOIA LUCAS JOHN , ROMIG BRYAN WESLEY
IPC分类号： F23R3/42
CPC分类号： F23R3/28 , F23R3/20 , F23R3/286 , F23R3/346 , F23R2900/00015 , F23R2900/03041
摘要： PROBLEM TO BE SOLVED: To allow secondary combustion with reduced pollutant emissions without removing any heat from a head end of a combustor.SOLUTION: A turbomachine with a trapped vortex feature 41 comprises a unibody liner 20 formed to define a flow path for combustion products, the unibody liner including first and second portions 401, 402 defining first radial planes, a third portion 403 defining a second radial plane, a fourth portion 404 extending substantially radially between proximal ends of the first and third portions, and a fifth portion 405 extending substantially radially between proximal ends of the second and third portions. The turbomachine also includes a fuel injector 50 configured to deliver a fuel or a fuel/air mixture gas to a space partially bound by the third, fourth and fifth portions.
摘要翻译：要解决的问题：允许具有减少的污染物排放的二次燃烧而不从燃烧器的头端去除任何热量。解决方案：具有被捕获的涡流特征41的涡轮机包括形成为限定燃烧产物的流动路径的单体衬套20，一体式衬套包括限定第一径向平面的第一和第二部分401,402，限定第二径向平面的第三部分403，在第一和第三部分的近端之间基本上径向延伸的第四部分404以及基本上延伸的第五部分405 径向地在第二和第三部分的近端之间。涡轮机还包括燃料喷射器50，该燃料喷射器50构造成将燃料或燃料/空气混合气体输送到由第三，第四和第五部分部分地界定的空间。

7. 发明专利

JP2014088874A Combustor cap assembly 有权
标题翻译： COMBUSTOR CAP ASSEMBLY
公开(公告)号：JP2014088874A
公开(公告)日：2014-05-15
申请号：JP2013219723
申请日：2013-10-23
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： MELTON PATRICK BENEDICT , ROMIG BRYAN WESLEY , STOIA LUCAS JOHN
IPC分类号： F02C7/18 , F23R3/14 , F23R3/28 , F23R3/30
CPC分类号： F23R3/286 , F23D11/36 , F23D14/78 , F23D2214/00 , F23R3/14 , F23R3/28 , F23R3/283 , F23R2900/03043 , F23R2900/03044
摘要： PROBLEM TO BE SOLVED: To provide a combustor which cools a cap assembly and improves pre-mixing of a compressed working fluid with a fuel for combustion.SOLUTION: A combustor generally includes a shroud that defines at least one inlet passage extending circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port and at least one outlet port, and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve extends through the fuel nozzle passage. The tube, the sleeve, and the first plate at least partially define an outlet passage. A first fluid flow path generally extends from the inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.
摘要翻译：要解决的问题：提供一种冷却盖组件并改善压缩工作流体与用于燃烧的燃料的预混合的燃烧器。解决方案：燃烧器通常包括护罩，其限定在燃烧器内周向延伸的至少一个入口通道。第一板在入口通道下游的护罩的径向内部延伸。第一板限定至少一个入口端口和至少一个出口端口，并且至少部分限定至少一个燃料喷嘴通道。护罩至少部分地围绕围绕燃料喷嘴通道延伸的套筒。至少部分地被套筒包围的管延伸穿过燃料喷嘴通道。管，套管和第一板至少部分地限定出口通道。第一流体流动路径通常从入口通道延伸到入口端口，并且第二流体流动路径大体上从出口延伸到出口通道。

8. 发明专利

JP2013217637A Combustor and method for supplying fuel to combustor 有权
标题翻译：燃料和燃料供应方法
公开(公告)号：JP2013217637A
公开(公告)日：2013-10-24
申请号：JP2013077311
申请日：2013-04-03
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： STOIA LUCAS JOHN , MELTON PATRICK BENEDICT , ROMIG BRYAN WESLEY
IPC分类号： F23R3/34 , F02C7/22 , F23C6/04 , F23R3/10 , F23R3/28 , F23R3/32
CPC分类号： F23R3/346 , F23C6/047 , F23C2201/30 , F23R3/14 , F23R3/286 , F23R3/34 , F23R3/36 , F23R2900/03341
摘要： PROBLEM TO BE SOLVED: To provide a combustor and a method for supplying fuel to the combustor.SOLUTION: 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. A plurality of fluid injectors are circumferentially 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：要解决的问题：提供一种燃烧器和用于向燃烧器供应燃料的方法。解决方案：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部轴向延伸到第二反应区。多个流体喷射器周向地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。

9. 发明专利

JP2013217376A System and method for detecting fuel leaks in gas turbine engine 有权
标题翻译：用于检测燃气涡轮发动机燃油泄漏的系统和方法
公开(公告)号：JP2013217376A
公开(公告)日：2013-10-24
申请号：JP2013080880
申请日：2013-04-09
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： ROMIG BRYAN WESLEY , SIMONS DERRICK , DEAN DOUGLAS
IPC分类号： F02C7/00 , F02C7/22 , F02C9/00
CPC分类号： F02C7/232 , F01D21/14 , F02C7/22 , F02C9/28 , F02D2041/225 , F05D2260/80
摘要： PROBLEM TO BE SOLVED: To provide systems and methods for detecting fuel leaks in gas turbine engines.SOLUTION: Embodiments of this invention can provide systems and methods for detecting fuel leaks in gas turbine engines. According to one embodiment, there is disclosed a method for detecting a fuel leak in a gas turbine engine. The method may include adjusting a control valve to correspond with a desired fuel flow. The method may also include determining an actual fuel flow based at least in part on an upstream pressure in a fuel manifold and one or more gas turbine engine parameters. The method may also include comparing the desired fuel flow with the actual fuel flow. Moreover, the method may include determining a difference between the desired fuel flow and the actual fuel flow, wherein the difference indicates a fuel leak.
摘要翻译：要解决的问题：提供用于检测燃气涡轮发动机中的燃料泄漏的系统和方法。解决方案：本发明的实施例可以提供用于检测燃气涡轮发动机中的燃料泄漏的系统和方法。根据一个实施例，公开了一种用于检测燃气涡轮发动机中的燃料泄漏的方法。该方法可以包括调节控制阀以对应于期望的燃料流。该方法还可以包括至少部分地基于燃料歧管中的上游压力和一个或多个燃气涡轮发动机参数来确定实际燃料流。该方法还可以包括将所需燃料流与实际燃料流进行比较。此外，该方法可以包括确定期望燃料流量与实际燃料流量之间的差异，其中差值表示燃料泄漏。

10. 发明专利

JP2013148090A Combustor blowout recovery method and system 有权
标题翻译： COMBUSTOR BLOWOUT恢复方法和系统
公开(公告)号：JP2013148090A
公开(公告)日：2013-08-01
申请号：JP2013005867
申请日：2013-01-17
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： ROMIG BRYAN WESLEY , SIMONS DERRICK W , NARRA VENKAT
IPC分类号： F02C9/28 , F02C7/00 , F02C7/228 , F02C9/00 , F02C9/50 , F23R3/00 , F23R3/48
CPC分类号： F02C7/262 , F02C9/26 , F23R3/48 , Y02E20/344
摘要： PROBLEM TO BE SOLVED: To provide a method for controlling gas turbine operation in response to lean blowout of a combustion can.SOLUTION: A gas turbine includes a pair of combustion cans. A method includes sensing that a first combustion can is extinguished during a full load operation of the gas turbine, adjusting a fuel ratio between the fuel nozzles in each can, delivering a richer fuel mixture to the fuel nozzles nearest to the cross-fire tubes, generating a cross-fire from the second combustion can to the first combustion can, detecting a recovery of the turbine load, and adjusting the fuel ratio to the normal balanced fuel distribution between the fuel nozzles in each can.
摘要翻译：要解决的问题：提供一种响应于燃烧罐的精馏而控制燃气轮机操作的方法。解决方案：一种燃气轮机包括一对燃烧罐。一种方法包括检测在燃气轮机的全负载操作期间第一燃烧罐被熄灭，调节每个罐中的燃料喷嘴之间的燃料比，将更丰富的燃料混合物输送到最靠近交叉火管的燃料喷嘴，产生从第二燃烧罐到第一燃烧罐的交叉火焰，检测涡轮机负载的恢复，以及将燃料比调整到每个罐中的燃料喷嘴之间的正常平衡燃料分配。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式