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1. 发明公开

EP2622278A1 GAS TURBINE ASSEMBLY AND METHOD THEREFOR 有权转让
标题翻译：燃气轮机及其方法
公开(公告)号：EP2622278A1
公开(公告)日：2013-08-07
申请号：EP11790777.4
申请日：2011-11-30
申请人： Siemens Aktiengesellschaft , Siemens Energy, Inc.
发明人： BÖTTCHER, Andreas , FOX, Timothy A. , GARAN, Daniel W. , GRIEB, Thomas , KLEINFELD, Jens , KRIEGER, Tobias , RAMIER, Stephen A. , RITLAND, David M , ZURHORST, Marcus
IPC分类号： F23R3/28 , F02C7/20
CPC分类号： F02C7/20 , F05D2260/94 , F05D2260/941 , F23R3/283 , F23R3/286 , F23R2900/00005 , F23R2900/00012 , Y10T29/49229
摘要： An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.

2. 发明授权

EP3250856B1 FUEL INJECTOR INCLUDING A LOBED MIXER AND VANES FOR INJECTING ALTERNATE FUELS IN A GAS TURBINE 有权
公开(公告)号：EP3250856B1
公开(公告)日：2020-10-07
申请号：EP15706962.6
申请日：2015-01-29
申请人： Siemens Energy, Inc.
发明人： LASTER, Walter Ray , FOX, Timothy A. , BARTLEY, Robert H.
IPC分类号： F23R3/14 , F23R3/28 , F23R3/36 , F23D14/24

3. 发明公开

EP2577170A2 SELF-REGULATING FUEL STAGING PORT FOR TURBINE COMBUSTOR 审中-公开
标题翻译： SELBSTREGULIERENDER KRAFTSTOFFVERSORGUNGSPORTFÜREINE TURBINENBRENNKAMMER
公开(公告)号：EP2577170A2
公开(公告)日：2013-04-10
申请号：EP11719738.4
申请日：2011-05-04
申请人： Siemens Energy, Inc.
发明人： VAN NIEUWENHUIZEN, William F. , FOX, Timothy A. , WILLIAMS, Steven
IPC分类号： F23R3/28 , F23R3/34
CPC分类号： F23R3/286 , F23R3/346
摘要： A port (60) for axially staging fuel and air into a combustion gas flow path 28 of a turbine combustor (10A). A port enclosure (63) forms an air path through a combustor wall (30). Fuel injectors (64) in the enclosure provide convergent fuel streams (72) that oppose each other, thus converting velocity pressure to static pressure. This forms a flow stagnation zone (74) that acts as a valve on airflow (40, 41 ) through the port, in which the air outflow (41) is inversely proportion to the fuel flow (25). The fuel flow rate is controlled (65) in proportion to engine load. At high loads, more fuel and less air flow through the port, making more air available to the premixing assemblies (36).
摘要翻译：用于将燃料和空气轴向分级到涡轮机燃烧器（10A）的燃烧气体流路28中的端口（60）。端口外壳（63）形成通过燃烧器壁（30）的空气通路。外壳中的燃料喷射器（64）提供相互对置的会聚燃料流（72），从而将速度压力转换成静压。这形成一个流动停滞区（74），其作用在通过该端口的气流（40,41）上的阀，其中空气流出（41）与燃料流（25）成反比。与发动机负荷成比例地控制燃油流量（65）。在高负载下，更多的燃料和更少的空气流过该端口，使得预混合组件（36）能够获得更多的空气。

4. 发明授权

EP3186558B1 FILM COOLING HOLE ARRANGEMENT FOR ACOUSTIC RESONATORS IN GAS TURBINE ENGINES 有权
公开(公告)号：EP3186558B1
公开(公告)日：2020-06-24
申请号：EP14761520.7
申请日：2014-08-26
申请人： Siemens Energy, Inc.
发明人： SCHILP, Reinhard , FOX, Timothy A.
IPC分类号： F23R3/00 , F23R3/06

5. 发明公开

EP3126739A1 GAS TURBINE ENGINE HAVING A DUAL OUTLET FUEL-PREMIX-NOZZLE FOR A SECONDARY COMBUSTOR STAGE 审中-公开
标题翻译：与KRAFTSTOFFVORMISCHUNGSDÜSE燃气涡轮发动机采用双出二次燃烧阶段
公开(公告)号：EP3126739A1
公开(公告)日：2017-02-08
申请号：EP15717707.2
申请日：2015-03-26
申请人： Siemens Energy, Inc.
发明人： LASTER, Walter R. , MARTIN, Scott M. , PORTILLO BILBAO, Juan Enrique , HARDES, Jacob William , FOX, Timothy A.
IPC分类号： F23R3/06 , F23R3/16 , F23R3/28 , F23R3/34
CPC分类号： F23R3/346 , F23R3/06 , F23R3/16 , F23R3/286
摘要： A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone upstream of the secondary fuel stage to ignite working gas. The secondary fuel stage includes a nozzle (18) with dual outlets (20, 22) oriented with a circumferential component to inject an air-fuel mixture into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas such that a peak temperature of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle.
摘要翻译：燃气涡轮发动机的燃烧器的二次燃料级（14）。该燃烧器具有一个主燃烧区（43）的辅助燃料级的上游，以点燃工作气体的二次燃料级包括喷嘴（18）与周向分量定向双输出口（20，22）在空气 - 燃料混合物喷射（24）到燃烧器。喷嘴是有效的与工作气体夹带的空气燃料混合物（44）检测所做的工作气体的峰值温度（46），在二次燃料阶段的下游的位置处小于工作的峰值温度（50）如果空气 - 燃料混合物被喷射到燃烧器具有单个出口的喷嘴（118）的气体。

6. 发明公开

EP3250856A1 FUEL INJECTOR INCLUDING A LOBED MIXER AND VANES FOR INJECTING ALTERNATE FUELS IN A GAS TURBINE 有权
标题翻译：燃料喷射器，包括用于在燃气轮机中喷射替代燃料的凸轮式混合器和蒸汽
公开(公告)号：EP3250856A1
公开(公告)日：2017-12-06
申请号：EP15706962.6
申请日：2015-01-29
申请人： Siemens Energy, Inc.
发明人： LASTER, Walter Ray , FOX, Timothy A. , BARTLEY, Robert H.
IPC分类号： F23R3/14 , F23R3/28 , F23R3/36 , F23D14/24
摘要： A fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches into passages (24) (e.g., axial passages) to inject a first fuel without jet in cross-flow injection. This may be effective to reduce flashback in fuels having a relatively high flame speed. A mixer (30) with lobes (32) for injection of a second fuel may be arranged at the downstream end of a fuel delivery tube (12). A fuel-routing structure (38) may be configured to route the second fuel within a respective lobe so that fuel injection of the second fuel takes place radially outwardly relative to a central region of the mixer. This may be conducive to an improved (e.g., a relatively more uniform) mixing of air and fuel.

7. 发明授权

EP2318765B1 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 失效
标题翻译：燃烧设备的燃气涡轮发动机
公开(公告)号：EP2318765B1
公开(公告)日：2013-07-17
申请号：EP09788707.9
申请日：2009-02-17
申请人： Siemens Energy, Inc.
发明人： FOX, Timothy A. , WIEBE, David J. , RITLAND, David M. , GLESSNER, John Carl
IPC分类号： F23R3/16 , F23R3/28 , F23R3/34
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005

8. 发明公开

EP2318765A2 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 失效
标题翻译：燃烧设备的燃气涡轮发动机
公开(公告)号：EP2318765A2
公开(公告)日：2011-05-11
申请号：EP09788707.9
申请日：2009-02-17
申请人： Siemens Energy, Inc.
发明人： FOX, Timothy A. , WIEBE, David J. , RITLAND, David M. , GLESSNER, John Carl
IPC分类号： F23R3/16 , F23R3/28 , F23R3/34
CPC分类号： F23R3/16 , F23R3/283 , F23R3/346 , F23R2900/00005
摘要： A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element

9. 发明公开

EP3186559A1 COOLING SYSTEM FOR FUEL NOZZLES WITHIN COMBUSTOR IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机燃烧室内燃料喷嘴的冷却系统
公开(公告)号：EP3186559A1
公开(公告)日：2017-07-05
申请号：EP14766275.3
申请日：2014-08-26
申请人： Siemens Energy, Inc.
发明人： LASTER, Walter Ray , MARTIN, Scott M. , PORTILLO BILBAO, Juan Enrique , HARDES, Jacob William , FOX, Timothy A.
IPC分类号： F23R3/28 , F23R3/34 , F23R3/04
CPC分类号： F23R3/283 , F02C3/30 , F23R3/045 , F23R3/34
摘要： A cooling system (10) for a fuel system in a turbine engine (14) that is usable to cool a fuel nozzle (16) is disclosed. The cooling system (10) may include one or more cooling system housings (18) positioned around the fuel nozzle (16), such that the cooling system housing (18) forms a cooling chamber (20) defined at least partially by an inner surface (22) of the cooling system housing (18) and an outer surface (24) of the fuel nozzle (16). The fuel nozzle (16) may extend into a combustor chamber (26) formed at least in part by a combustor housing (32). The fuel nozzle (16) may include one or more fuel exhaust orifices (28) with an opening (30) in an outer surface (24) of the fuel nozzle (16) and configured to exhaust fluids unrestricted by the housing (18) forming the cooling system cooling chamber (20). The cooling system (10) may provide cooling fluids to cool the fuel nozzle (16) within the cooling system cooling chamber (20) regardless of whether the fuel nozzle (16) is in use.
摘要翻译：公开了一种用于涡轮发动机（14）中的燃料系统的冷却系统（10），其可用于冷却燃料喷嘴（16）。冷却系统（10）可以包括围绕燃料喷嘴（16）定位的一个或多个冷却系统壳体（18），使得冷却系统壳体（18）形成冷却室（20），该冷却室至少部分地由内表面（18）的外表面（22）和燃料喷嘴（16）的外表面（24）之间。燃料喷嘴（16）可以延伸到至少部分地由燃烧器壳体（32）形成的燃烧室（26）中。燃料喷嘴（16）可以包括在燃料喷嘴（16）的外表面（24）中具有开口（30）的一个或多个燃料排出孔（28），并且该燃料排出孔构造成排出不受壳体（18）形成限制的流体冷却系统冷却室（20）。无论燃料喷嘴（16）是否在使用中，冷却系统（10）都可以提供冷却流体以冷却冷却系统冷却室（20）内的燃料喷嘴（16）。

10. 发明公开

EP3186558A1 FILM COOLING HOLE ARRANGEMENT FOR ACOUSTIC RESONATORS IN GAS TURBINE ENGINES 有权
标题翻译：气体涡轮发动机声子共振器的薄膜冷却孔布置
公开(公告)号：EP3186558A1
公开(公告)日：2017-07-05
申请号：EP14761520.7
申请日：2014-08-26
申请人： Siemens Energy, Inc.
发明人： SCHILP, Reinhard , FOX, Timothy A.
IPC分类号： F23R3/00 , F23R3/06
摘要： The present disclosure provides a gas turbine combustor liner (34) comprising an outer surface (38) and an inner surface (36), a plurality of film cooling holes (44) through a thickness of the gas turbine combustor liner (34), and a plurality of resonator boxes (32) affixed to the outer surface (38) of the gas turbine combustor liner (34). The film cooling holes (44) extend circumferentially around the gas turbine combustor liner (34) and comprise a first set of holes (56) having a first axial row spacing X and a second set of holes (58) having a second axial row spacing X′. The second set of holes (58) is formed in the gas turbine combustor liner (34) in a downstream direction relative to the first set of holes (56). The second axial row spacing X′ is greater than the first axial row spacing X.
摘要翻译：本公开提供了一种燃气轮机燃烧器衬套（34），其包括外表面（38）和内表面（36），贯穿燃气轮机燃烧器衬套（34）厚度的多个膜冷却孔（44），以及多个谐振器盒（32），所述谐振器盒固定到燃气轮机燃烧器衬套（34）的外表面（38）上。膜冷却孔（44）围绕燃气轮机燃烧器衬套（34）周向延伸并且包括具有第一轴向行距X的第一组孔（56）和具有第二轴向行距的第二组孔（58） X'。第二组孔（58）在相对于第一组孔（56）的下游方向上形成在燃气轮机燃烧器衬套（34）中。第二轴向行间距X'大于第一轴向行间距X.

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