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公开(公告)号：EP2578939A3
公开(公告)日：2017-10-25
申请号：EP12186898.8
申请日：2012-10-01
IPC分类号： F23R3/04
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 (40) configured to circumferentially surround at least a portion of the combustor. An inner annular passage (42) extends through the axial fluid injector (40) and provides fluid communication through the axial fluid injector (40) and into a first annular passage (32) that surrounds the combustor. An outer annular passage (44) extends through the axial fluid injector (40) radially outward from the inner annular passage (42) and provides axial flow into the first annular passage (32). A method for supplying flow to a combustor includes flowing a first portion of a working fluid through a first axial flow path (42) and flowing a second portion of the working fluid through a second axial flow path (44).
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公开(公告)号：EP2538027A3
公开(公告)日：2017-12-13
申请号：EP12172492.6
申请日：2012-06-18
CPC分类号： F01D9/023 , F05D2260/2214 , F23R3/002 , F23R3/005 , F23R2900/03045 , Y10T29/49229
摘要： Methods and systems are provided for transferring heat from a transition nozzle (200). The transition nozzle includes a transition portion (204), a nozzle portion (206) integrally formed with the transition portion (204), and at least one surface feature configured to transfer heat away from the transition portion (204) and/or the nozzle portion (206). The transition portion is oriented to channel the combustion gases towards the nozzle portion (206).
摘要翻译： 提供了用于从过渡喷嘴（200）传递热量的方法和系统。 过渡喷嘴包括过渡部分（204），与过渡部分（204）整体形成的喷嘴部分（206）以及构造成将热量从过渡部分（204）和/或喷嘴 部分（206）。 过渡部分被定向成将燃烧气体引向喷嘴部分（206）。
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4.发明公开Combustor with fuel nozzle liner having chevron ribs 审中-公开Brennkammer mitBrennstoffdüsenauskleidungmitFischgrätmuster-Rippen
公开(公告)号：EP2503243A1
公开(公告)日：2012-09-26
申请号：EP12160408.6
申请日：2012-03-20
CPC分类号： F23R3/286 , F23D11/408
摘要： The present application and the resultant patent provide a fuel nozzle (120) for mixing a flow of air and a flow of fuel within a combustor (100). The fuel nozzle (120) may have one or more air passages (180) for the flow of air, one or more fuel pegs (150) for the flow of fuel, and a liner in communication with the air passages (180) and surrounding the fuel pegs (150). The liner includes a number of ribs (230) thereon so as to promote mixing of the flow of air and the flow of fuel therein.
摘要翻译： 本申请和所得专利提供了一种用于混合燃烧器（100）内的空气流和燃料流的燃料喷嘴（120）。 燃料喷嘴（120）可以具有用于空气流动的一个或多个空气通道（180），用于燃料流动的一个或多个燃料栓（150）和与空气通道（180）连通的衬套 燃料栓（150）。 衬套包括多个肋（230），以促进空气流与其中的燃料流的混合。
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公开(公告)号：EP2538028A3
公开(公告)日：2018-03-14
申请号：EP12172554.3
申请日：2012-06-19
IPC分类号： F01D9/02
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 (100) includes a fuel nozzle (210) configured to mix fuel and air and a transition nozzle (200) oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion (204) and a nozzle portion (206) 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： 涡轮机组件（100）包括构造成混合燃料和空气的燃料喷嘴（210）和定向成接收来自燃料喷嘴的燃料和空气混合物的过渡喷嘴（200）。 过渡喷嘴包括过渡部分（204）和与过渡部分一体形成的喷嘴部分（206）。 过渡喷嘴包括多个开口，所述开口定向成引导空气以促进冷却过渡部分和/或喷嘴部分。 过渡部分被定向成朝向喷嘴部分引导燃烧气体。
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公开(公告)号：EP2626635A3
公开(公告)日：2013-09-11
申请号：EP13153606.2
申请日：2013-02-01
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R2900/00015
摘要： Embodiments of the present application include a combustor assembly (25). The combustor assembly may include an annular trapped vortex cavity (116) located adjacent to a downstream end (106) of a bundle of air/fuel premixing injection tubes (102). The annular trapped vortex cavity (116) may include an opening (124) at a radially inner portion of the annular trapped vortex cavity (116) adjacent to the head end (104) of the bundle of premixing tubes (102). The annular trapped vortex cavity (116) may also include one or more air injection holes (126) and one or more fuel sources (128) disposed about the annular trapped vortex cavity (116) such that the one or more air injection holes (126) and the one or more fuel sources (128) are configured to drive a vortex (130) within the annular trapped vortex cavity (116).
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公开(公告)号：EP2626635B1
公开(公告)日：2016-06-01
申请号：EP13153606.2
申请日：2013-02-01
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R2900/00015
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公开(公告)号：EP2626635A2
公开(公告)日：2013-08-14
申请号：EP13153606.2
申请日：2013-02-01
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23R2900/00015
摘要： Embodiments of the present application include a combustor assembly (25). The combustor assembly may include an annular trapped vortex cavity (116) located adjacent to a downstream end (106) of a bundle of air/fuel premixing injection tubes (102). The annular trapped vortex cavity (116) may include an opening (124) at a radially inner portion of the annular trapped vortex cavity (116) adjacent to the head end (104) of the bundle of premixing tubes (102). The annular trapped vortex cavity (116) may also include one or more air injection holes (126) and one or more fuel sources (128) disposed about the annular trapped vortex cavity (116) such that the one or more air injection holes (126) and the one or more fuel sources (128) are configured to drive a vortex (130) within the annular trapped vortex cavity (116).
摘要翻译： 本申请的实施例包括燃烧器组件（25）。 燃烧器组件可包括邻近空气/燃料预混合注射管束（102）的下游端（106）定位的环形收集涡流腔（116）。 环形驻涡流腔116可以包括在环形驻涡流腔116的与预混管束102的头端104相邻的径向内部处的开口124。 环形驻涡腔（116）还可包括围绕环形驻涡腔（116）设置的一个或多个空气喷射孔（126）和一个或多个燃料源（128），使得一个或多个空气喷射孔 ）以及一个或多个燃料源（128）被配置为驱动环形驻涡流腔（116）内的涡流（130）。
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公开(公告)号：EP2578939A2
公开(公告)日：2013-04-10
申请号：EP12186898.8
申请日：2012-10-01
IPC分类号： F23R3/04
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 (40) configured to circumferentially surround at least a portion of the combustor. An inner annular passage (42) extends through the axial fluid injector (40) and provides fluid communication through the axial fluid injector (40) and into a first annular passage (32) that surrounds the combustor. An outer annular passage (44) extends through the axial fluid injector (40) radially outward from the inner annular passage (42) and provides axial flow into the first annular passage (32). A method for supplying flow to a combustor includes flowing a first portion of a working fluid through a first axial flow path (42) and flowing a second portion of the working fluid through a second axial flow path (44).
摘要翻译： 用于供应流过燃烧器的装置包括轴向流体喷射器（40），所述轴向流体喷射器（40）构造成沿周向围绕燃烧器的至少一部分。 内部环形通道（42）延伸穿过轴向流体喷射器（40）并且提供通过轴向流体喷射器（40）的流体连通并进入围绕燃烧器的第一环形通道（32）。 外部环形通道（44）从内部环形通道（42）径向向外延伸穿过轴向流体喷射器（40）并且提供轴向流入第一环形通道（32）。 用于向燃烧器供应流的方法包括使工作流体的第一部分流过第一轴向流动路径（42）并使工作流体的第二部分流过第二轴向流动路径（44）。
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10.发明公开Methods and systems for cooling a transition nozzle 审中-公开Verfahren und Systeme zumKühleneinesÜbergangskanals
公开(公告)号：EP2538028A2
公开(公告)日：2012-12-26
申请号：EP12172554.3
申请日：2012-06-19
IPC分类号： F01D9/02
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 (100) includes a fuel nozzle (210) configured to mix fuel and air and a transition nozzle (200) oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion (204) and a nozzle portion (206) 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（100）包括构造成混合燃料和空气的燃料喷嘴（210）和定向成从燃料喷嘴接收燃料和空气混合物的过渡喷嘴（200）。 过渡喷嘴包括与过渡部分整体形成的过渡部分（204）和喷嘴部分（206）。 过渡喷嘴包括多个开口，其定向成引导空气以便于冷却过渡部分和/或喷嘴部分。 过渡部分被定向成将燃烧气体引向喷嘴部分。
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