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1.发明授权Systems and methods for suppressing combustion driven pressure fluctuations with a premix combustor having multiple premix times 有权用具有多个预混时间的预混合燃烧器抑制燃烧驱动的压力波动的系统和方法公开(公告)号：US09212823B2
公开(公告)日：2015-12-15
申请号：US13604952
申请日：2012-09-06
申请人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
发明人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R2900/00014 , F23R2900/03043 , F23R2900/03045
摘要： A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.
摘要翻译： 具有燃烧室的燃烧器设置有外部流动套筒和围绕燃烧室的燃烧室衬套。 多个流动通道设置在燃烧器衬套上，并且多个喷嘴设置在流动通道上的预定位置处。 选择喷嘴的位置以为通过喷嘴喷射的燃料提供不同的混合时间。
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公开(公告)号：US09182122B2
公开(公告)日：2015-11-10
申请号：US13253537
申请日：2011-10-05
CPC分类号： F23R3/04 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/08 , F23R2900/03044 , F23R2900/03045
摘要： A device for supplying flow across a combustor includes an axial fluid injector configured to circumferentially surround at least a portion of the combustor. An inner annular passage extends through the axial fluid injector and provides fluid communication through the axial fluid injector and into a first annular passage that surrounds the combustor. An outer annular passage extends through the axial fluid injector radially outward from the inner annular passage and provides axial flow into the first annular passage. A method for supplying flow to a combustor includes flowing a first portion of a working fluid through a first axial flow path and flowing a second portion of the working fluid through a second axial flow path.
摘要翻译： 用于供应流过燃烧器的流的装置包括被配置为周向地围绕燃烧器的至少一部分的轴向流体喷射器。 内环形通道延伸穿过轴向流体注射器并且提供通过轴向流体注入器的流体连通并且包围围绕燃烧器的第一环形通道。 外部环形通道从内部环形通道径向向外延伸穿过轴向流体喷射器，并提供轴向流入第一环形通道。 用于向燃烧器供应流量的方法包括将工作流体的第一部分流过第一轴向流动路径并使工作流体的第二部分流过第二轴向流动路径。
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公开(公告)号：US08904802B2
公开(公告)日：2014-12-09
申请号：US13173951
申请日：2011-06-30
申请人： Sridhar Venkat Kodukulla , Ronald James Chila , Sarah Lori Crothers , Shreekrishna Jayakumar Rao , Shivakumar Srinivasan
发明人： Sridhar Venkat Kodukulla , Ronald James Chila , Sarah Lori Crothers , Shreekrishna Jayakumar Rao , Shivakumar Srinivasan
CPC分类号： F23R3/005 , F23M20/005 , F23R3/06 , F23R3/16 , F23R2900/03044 , F23R2900/03045
摘要： A turbomachine combustor assembly includes a combustor body, and a combustor liner arranged within the combustor body and defining a combustion chamber. The combustor liner includes a venturi portion arranged within the combustion chamber. A fluid passage is defined between the combustor body and the combustor liner, and at least one turbulator is arranged in the fluid passage. The at least one turbulator is configured and disposed to create vortices in the fluid passage. A vortex modification system is arranged at the fluid passage and is configured and disposed to disrupt the vortices in the fluid passage.
摘要翻译： 涡轮机燃烧器组件包括燃烧器主体和布置在燃烧器主体内并限定燃烧室的燃烧器衬套。 燃烧器衬套包括布置在燃烧室内的文氏管部分。 流体通道限定在燃烧器主体和燃烧器衬套之间，并且至少一个湍流器布置在流体通道中。 至少一个湍流器被配置和设置成在流体通道中产生涡流。 涡流改质系统布置在流体通道处，并被配置和设置成破坏流体通道中的涡流。
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4.发明授权公开(公告)号：US08887508B2
公开(公告)日：2014-11-18
申请号：US13048394
申请日：2011-03-15
申请人： Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Matthew Paul Berkebile , Wei Chen , John Drake Vanselow
发明人： Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Matthew Paul Berkebile , Wei Chen , John Drake Vanselow
CPC分类号： F01D9/023 , F05D2260/201 , F23R2900/03044 , Y10T29/49229
摘要： An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, a method for designing an impingement sleeve is disclosed. The method includes determining a desired operational value for a transition piece, inputting a combustor characteristic into a processor, and utilizing the combustor characteristic in the processor to determine a cooling hole pattern for the impingement sleeve, the cooling hole pattern comprising a plurality of cooling holes, at least a portion of the plurality of cooling holes being generally longitudinally asymmetric, the cooling hole pattern providing the desired operational value.
摘要翻译： 公开了一种冲击套筒和用于设计和形成冲击套筒的方法。 在一个实施例中，公开了一种用于设计冲击套筒的方法。 该方法包括确定过渡件的期望操作值，将燃烧器特性输入到处理器中，以及利用处理器中的燃烧器特性来确定冲击套筒的冷却孔图案，冷却孔图案包括多个冷却孔 所述多个冷却孔的至少一部分大致纵向不对称，所述冷却孔图案提供期望的操作值。
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5.发明申请Systems and Methods For Suppressing Combustion Driven Pressure Fluctuations With a Premix Combustor Having Multiple Premix Times 有权用具有多个预混时间的预混合燃烧器抑制燃烧驱动的压力波动的系统和方法公开(公告)号：US20140060063A1
公开(公告)日：2014-03-06
申请号：US13604952
申请日：2012-09-06
申请人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
发明人： Gregory Allen Boardman , Ronald James Chila , Mark Allan Hadley , Johnie Franklin McConnaughhay , Sarah Lori Crothers
CPC分类号： F23R3/286 , F23R2900/00014 , F23R2900/03043 , F23R2900/03045
摘要： A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.
摘要翻译： 具有燃烧室的燃烧器设置有外部流动套筒和围绕燃烧室的燃烧室衬套。 多个流动通道设置在燃烧器衬套上，并且多个喷嘴设置在流动通道上的预定位置处。 选择喷嘴的位置以为通过喷嘴喷射的燃料提供不同的混合时间。
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公开(公告)号：US20120328421A1
公开(公告)日：2012-12-27
申请号：US13164887
申请日：2011-06-21
CPC分类号： F01D9/023 , F05D2260/20 , F23R3/002 , F23R3/06 , F23R3/346 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y10T29/4932 , Y10T29/49323
摘要： A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.
摘要翻译： 涡轮组件包括构造成混合燃料和空气的燃料喷嘴和定向成从燃料喷嘴接收燃料和空气混合物的过渡喷嘴。 过渡喷嘴包括过渡部分和与过渡部分一体形成的喷嘴部分。 过渡喷嘴包括定向成引导空气以便于冷却过渡部分和/或喷嘴部分的多个开口。 过渡部分被定向成将燃烧气体引向喷嘴部分。
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7.发明申请IMPINGEMENT SLEEVE AND METHODS FOR DESIGNING AND FORMING IMPINGEMENT SLEEVE 有权IMPINGEMENT SLEEVE AND METHODS FOR DESIGN AND FORMING IMPINGEMENT SLEEVE公开(公告)号：US20120304659A1
公开(公告)日：2012-12-06
申请号：US13589375
申请日：2012-08-20
申请人： Matthew Paul Berkebile , Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Wei Chen , John Drake Vanselow
发明人： Matthew Paul Berkebile , Jerome David Brown , Ronald James Chila , Patrick Benedict Melton , Russell DeForest , David William Cihlar , Wei Chen , John Drake Vanselow
CPC分类号： F01D9/023 , F05D2260/201 , F23R3/06 , F23R2900/03044
摘要： An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric.
摘要翻译： 公开了一种冲击套筒和用于设计和形成冲击套筒的方法。 在一个实施例中，冲击套筒包括构造成至少部分地围绕燃烧器的过渡件的主体。 所述冲击套筒还包括限定在所述主体中的多个冷却孔，所述多个冷却孔具有冷却孔图案，所述冷却孔图案被配置为为所述过渡件提供期望的操作值。 多个冷却孔中的至少一个具有至少部分地在所述多个冷却孔中的至少一个冷却孔的入口和出口之间延伸的倒角。 多个冷却孔的至少一部分大体上是纵向不对称的。
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公开(公告)号：US20120052451A1
公开(公告)日：2012-03-01
申请号：US12872743
申请日：2010-08-31
CPC分类号： F23R3/286 , F23C2900/07002 , F23R3/14 , F23R3/26
摘要： According to one aspect of the disclosure, an apparatus for injecting fuel is provided, where the apparatus includes a cone structure that includes a passage to form a swirl of an air-fuel mixture in a combustion chamber. The apparatus also includes at least one adjustable vane positioned in the passage configured to control the swirl of the air-fuel mixture and control a flame stability.
摘要翻译： 根据本公开的一个方面，提供了一种用于喷射燃料的装置，其中所述装置包括锥形结构，所述锥形结构包括在燃烧室中形成空气 - 燃料混合物的涡流的通道。 该设备还包括位于通道中的至少一个可调叶片，其构造成控制空气 - 燃料混合物的涡流并控制火焰稳定性。
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公开(公告)号：US20110113783A1
公开(公告)日：2011-05-19
申请号：US12618636
申请日：2009-11-13
申请人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
发明人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
摘要： In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.
摘要翻译： 在一个实施例中，系统包括燃料喷嘴，其包括燃料喷射器，燃料喷射器包括燃料口和预混合管。 预混合管包括围绕中心通道设置的壁，多个空气端口延伸穿过壁进入中心通道，以及催化区域。 催化区域包括沿着中心通道设置在壁内的催化剂，构造成增加燃料和空气的反应。
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公开(公告)号：US20100218502A1
公开(公告)日：2010-09-02
申请号：US12395739
申请日：2009-03-02
IPC分类号： F23R3/42
CPC分类号： F23R3/06 , F23R3/002 , F23R3/005 , F23R3/46 , F23R2900/03041
摘要： A combustor for an industrial turbine includes a single transition piece transitioning directly from a combustor head-end to a turbine inlet. The transition piece includes an inner surface and an outer surface. The inner surface bounds an interior space for combusted gas flow from the combustor head-end to the turbine inlet. The outer surface at least partially defines an area for compressor discharge air flow. The transition piece includes a plurality of apertures configured to allow compressor discharge air flow into the interior space. Each of the plurality of apertures extends from an entry portion on the outer surface to an exit portion on the inner surface.
摘要翻译： 用于工业涡轮机的燃烧器包括直接从燃烧器头端转换到涡轮机入口的单个过渡件。 过渡件包括内表面和外表面。 内表面限定用于从燃烧器头端到涡轮机入口的燃烧气体流的内部空间。 外表面至少部分地限定用于压缩机排出气流的区域。 过渡件包括多个孔，其构造成允许压缩机排出空气流入内部空间。 多个孔中的每一个从外表面上的入口部分延伸到内表面上的出口部分。
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