-
公开(公告)号：US08646276B2
公开(公告)日：2014-02-11
申请号：US12616304
申请日：2009-11-11
IPC分类号： F02C1/00
CPC分类号： F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03043 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.
摘要翻译： 用于涡轮发动机的燃烧器组件包括燃烧器衬套和围绕燃烧器衬套的流动套管。 压缩空气流过位于燃烧器衬套的外表面和流动套管的内表面之间的环形空间。 通过流动套筒形成多个冷却孔，以允许压缩空气从流动套筒外部的位置流过冷却孔并进入环形空间。 环形空间的高度可以沿着燃烧器组件的长度而变化。 因此，流动套管可以具有减小的直径部分，这导致环形空间的高度在某些位置比沿着燃烧器组件的长度的其它位置更小。
-
公开(公告)号：US20130086915A1
公开(公告)日：2013-04-11
申请号：US13267994
申请日：2011-10-07
IPC分类号： F02C7/18
CPC分类号： F23R3/002 , F01D9/023 , F05D2240/55 , F23R3/06 , F23R3/46 , F23R2900/00012 , F23R2900/03042 , F23R2900/03044
摘要： A combustion liner assembly is provided and includes a combustion liner and a transition piece. A portion of the transition piece is circumferentially disposed around a portion of the combustion liner. A seal is attached to the transition piece, and the seal is configured to apply a compressive force to an aft end of the combustion liner.
摘要翻译： 提供燃烧衬套组件并且包括燃烧衬套和过渡件。 过渡件的一部分周向地布置在燃烧衬套的一部分周围。 密封件附接到过渡件，并且密封件构造成对燃烧衬套的后端施加压缩力。
-
公开(公告)号：US08359867B2
公开(公告)日：2013-01-29
申请号：US12756329
申请日：2010-04-08
CPC分类号： F23R3/02 , F23R3/44 , F23R2900/03043
摘要： A combustor is provided and includes a liner through which fluid fed from at least two injection points flows from a head end to an interior of a transition piece, a first one of the at least two injection points being axially proximate to a fluid impenetrable coupling between the liner and the transition piece and defining apertures disposed in fluid communication with a first passage leading to the head end, and a second one of the at least two injection points being disposed axially between the apertures and the head end and upstream from the apertures relative to a direction of fluid flow through the first passage, the second one of the at least two injection points being formed of openings disposed in fluid communication with a second passage leading to the head end.
摘要翻译： 提供燃烧器并且包括衬套，通过所述衬套从至少两个注射点供给的流体从头端流动到过渡件的内部，所述至少两个注射点中的第一个轴向靠近液体不可穿透的联接 所述衬套和所述过渡件并且限定出孔设置成与通向所述头端的第一通道流体连通，并且所述至少两个注射点中的第二个注射点轴向地设置在所述孔和所述头部端部之间以及所述孔的相对上游 流体流过第一通道的方向，所述至少两个注射点中的第二个注射点由与通向头端的第二通道流体连通的开口形成。
-
4.发明申请公开(公告)号：US20130000312A1
公开(公告)日：2013-01-03
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。
-
5.发明申请COMBUSTOR ASSEMBLY FOR USE IN A TURBINE ENGINE AND METHODS OF ASSEMBLING SAME 审中-公开用于涡轮发动机的燃烧器组件及其装配方法公开(公告)号：US20120324898A1
公开(公告)日：2012-12-27
申请号：US13164948
申请日：2011-06-21
CPC分类号： F23R3/002 , F01D9/023 , F23R3/425 , F23R2900/03044 , Y10T29/49348
摘要： A combustor assembly for use with a turbine engine that includes a rotor assembly. The combustor assembly includes a casing that includes a plenum and a combustor liner that is spaced a distance from the plenum and that defines a combustion chamber therein. A transition nozzle extends between the combustor liner and the rotor assembly for channeling combustion gases from the combustion chamber to the rotor assembly. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. An annular flowsleeve is coupled radially outward from the transition nozzle such that an annular flow path is defined between the flowsleeve and the transition nozzle. The flowsleeve includes a plurality of openings extending through an outer surface of the flowsleeve for providing flow communication between the plenum and the annular flow path to facilitate impingement cooling of the flowsleeve.
摘要翻译： 一种与包括转子组件的涡轮发动机一起使用的燃烧器组件。 燃烧器组件包括壳体，其包括气室和与集气室隔开一定距离且在其中限定燃烧室的燃烧器衬套。 过渡喷嘴在燃烧器衬套和转子组件之间延伸，用于将燃烧气体从燃烧室引导至转子组件。 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。 环形流动体从过渡喷嘴径向向外耦合，使得在流动流体和过渡喷嘴之间限定环形流动路径。 流动通道包括延伸穿过流动的外表面的多个开口，用于提供气室与环形流路之间的流动连通，以便于流动的冲击冷却。
-
6.发明申请COMBUSTOR ASSEMBLIES FOR USE IN TURBINE ENGINES AND METHODS OF ASSEMBLING SAME 有权用于涡轮发动机的燃烧器组件及其组装方法公开(公告)号：US20120167571A1
公开(公告)日：2012-07-05
申请号：US12983393
申请日：2011-01-03
CPC分类号： F01D9/023 , F02C7/22 , F23R3/002 , F23R3/06 , F23R3/54 , F23R2900/03044 , Y10T29/49348
摘要： A method of assembling a combustor assembly for use in a turbine engine is provided. A combustor liner that defines a combustion chamber therein is provided. The liner includes a forward end and an aft end, wherein the aft end includes at least one channel extending therethrough. The channel is aligned obliquely with respect to a centerline extending through the aft end. A plurality of fuel nozzles are coupled to the forward end such that the fuel nozzles extend through the forward end. An annular sleeve that includes at least one opening extending radially therethrough is coupled to the aft end, wherein the sleeve substantially circumscribes the aft end such that a cavity is defined therebetween and such that a fluid channeled through the at least one opening impinges against a surface of the aft end prior to the fluid being channeled into the combustion chamber.
摘要翻译： 提供一种组装用于涡轮发动机的燃烧器组件的方法。 提供了一种在其中限定燃烧室的燃烧器衬套。 衬套包括前端和后端，其中后端包括延伸穿过其中的至少一个通道。 通道相对于延伸穿过后端的中心线倾斜地对准。 多个燃料喷嘴联接到前端，使得燃料喷嘴延伸穿过前端。 包括至少一个径向延伸穿过其中的开口的环形套筒联接到后端，其中套筒基本上围绕后端，使得在其间限定空腔，使得通过至少一个开口引导的流体撞击表面 在流体被引导进入燃烧室之前的后端。
-
7.发明申请Hybrid Prefilming Airblast, Prevaporizing, Lean-Premixing Dual-Fuel Nozzle for a Gas Turbine Combustor 有权用于燃气轮机燃烧器的混合预吹风机，预蒸发，预混合双燃料喷嘴公开(公告)号：US20110289933A1
公开(公告)日：2011-12-01
申请号：US12787990
申请日：2010-05-26
CPC分类号： F23R3/36 , F23D2900/11101 , F23D2900/14004 , F23R3/14 , F23R3/286
摘要： A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject liquid fuel radially outward from the hub. An annular air passage includes a swirler that imparts swirl to air flowing in the annular air passage, and a splitter ring is disposed in the annular air passage and surrounds the plurality of liquid fuel jets. The nozzle allows liquid fuels to be injected into a swirling annular airstream and then atomized, dispersed and vaporized inside a lean premixing dual fuel nozzle for a gas turbine combustor.
摘要翻译： 用于燃气轮机燃烧器的双燃料喷嘴包括限定燃料入口的轮毂和设置在轮毂的下游端的多个液体燃料喷嘴。 燃料喷嘴被定向成从轮毂径向向外喷射液体燃料。 环形空气通道包括向在环形空气通道中流动的空气产生漩涡的旋流器，并且分离环设置在环形空气通道中并围绕多个液体燃料喷嘴。 喷嘴允许将液体燃料注入旋转的环形空气流中，然后在用于燃气轮机燃烧器的贫预混合双燃料喷嘴内雾化，分散和蒸发。
-
公开(公告)号：US20100223930A1
公开(公告)日：2010-09-09
申请号：US12399536
申请日：2009-03-06
申请人： Ronald James Chila
发明人： Ronald James Chila
摘要： A turbomachine includes a compressor, a combustor including a first end operatively connected to the compressor and a second end, a transition piece mounted to the second end of the combustor, and at least one injection device mounted to one of the combustor and the transition piece. The at least one injection device includes a first end portion that extends to a second end portion through an intermediate portion. The intermediate portion includes a flow conditioning mechanism. Combustion air from the compressor enters the first end portion passes through the flow conditioning mechanism and into the one of the combustion liner and transition piece. The flow conditioning mechanism creates an air flow disturbance in the combustion air to promote mixing of combustion gases.
摘要翻译： 涡轮机包括压缩机，燃烧器，其包括可操作地连接到压缩机的第一端和第二端，安装到燃烧器的第二端的过渡件，以及安装到燃烧器和过渡件之一的至少一个注射装置 。 所述至少一个注射装置包括通过中间部分延伸到第二端部的第一端部。 中间部分包括流动调节机构。 来自压缩机的燃烧空气进入第一端部，通过流量调节机构并进入燃烧衬套和过渡件中的一个。 流动调节机构在燃烧空气中产生气流扰动以促进燃烧气体的混合。
-
公开(公告)号：US20100005804A1
公开(公告)日：2010-01-14
申请号：US12171386
申请日：2008-07-11
IPC分类号： F02C1/00
CPC分类号： F23R3/16 , F01D9/023 , F23R3/002 , F23R2900/00014 , F23R2900/03044
摘要： A combustor includes at least one combustor liner defining a combustion chamber capable of directing combustion products toward a turbine. At least one combustor sleeve is located outside of the combustion chamber and is capable of reducing a magnitude of acoustic waves in the combustion chamber. The at least one combustor liner and the at least one combustor sleeve define at least one flow channel therebetween. Further, a combustor includes at least one combustor liner defining a combustion chamber capable of directing combustion products toward turbomachinery. At least one combustor sleeve disposed outside of the combustion chamber and is capable of controlling distribution of fluid flow in the combustor to modify a uniformity of the fluid flow to the combustion chamber.
摘要翻译： 燃烧器包括限定燃烧室的至少一个燃烧器衬套，其能够将燃烧产物引向涡轮。 至少一个燃烧器套筒位于燃烧室的外部，并且能够减小燃烧室中的声波的大小。 所述至少一个燃烧器衬套和所述至少一个燃烧器套筒在其间限定至少一个流动通道。 此外，燃烧器包括限定能够将燃烧产物引导到涡轮机械的燃烧室的至少一个燃烧器衬套。 至少一个燃烧器套筒设置在燃烧室的外部，并且能够控制燃烧器中的流体流动的分布，以改变流向燃烧室的流体的均匀性。
-
10.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。
-
-
-
-
-
-
-
-
-
搜索结果
71 条记录 (耗时 0.022 秒)
