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公开(公告)号：US20120324897A1
公开(公告)日：2012-12-27
申请号：US13164908
申请日：2011-06-21
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. The transition nozzle includes a transition portion, a nozzle portion integrally formed with the transition portion, and at least one surface feature configured to transfer heat away from the transition portion and/or the nozzle portion. The transition portion is oriented to channel the combustion gases towards the nozzle portion.
摘要翻译： 提供了用于从转换喷嘴传热的方法和系统。 过渡喷嘴包括过渡部分，与过渡部分一体形成的喷嘴部分，以及被配置为将热量从过渡部分和/或喷嘴部分传递的至少一个表面特征。 过渡部分被定向成将燃烧气体引向喷嘴部分。
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公开(公告)号：US20120297785A1
公开(公告)日：2012-11-29
申请号：US13115058
申请日：2011-05-24
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The structure obstructs an airflow through the air passage. The gas turbine combustor also includes a wake reducer disposed adjacent the structure. The wake reducer directs a flow into a wake region downstream of the structure.
摘要翻译： 一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，在燃烧衬套和流动套筒之间的空气通道，以及燃烧衬套与流体之间的结构 袖。 该结构阻碍通过空气通道的气流。 燃气轮机燃烧器还包括邻近结构布置的尾流减速器。 尾流减速器将流动引导到结构下游的尾流区域。
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公开(公告)号：US20120297783A1
公开(公告)日：2012-11-29
申请号：US13115018
申请日：2011-05-24
申请人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
发明人： Patrick Benedict Melton , Bradley Donald Crawley , David William Cihlar , Robert Joseph Rohrssen , Ronald James Chila
CPC分类号： F23R3/002 , F23R3/045 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.
摘要翻译： 一种系统包括燃气轮机燃烧器，其包括围绕燃烧区域设置的燃烧衬套，围绕燃烧衬套设置的流动套筒，在燃烧衬套和流动套筒之间的空气通道，以及在燃烧衬套和燃烧衬套之间延伸的结构 流动套管 该结构妨碍通过空气通道的气流路径。 燃气轮机燃烧器还包括空气动力尾流减速器，其被配置成重新定向结构周围的气流以减少结构下游的尾流区域。
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公开(公告)号：US08307657B2
公开(公告)日：2012-11-13
申请号：US12401530
申请日：2009-03-10
申请人： Ronald James Chila
发明人： Ronald James Chila
IPC分类号： F02C3/14
CPC分类号： F23R3/06 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A system, in one embodiment, includes a turbine engine. The turbine engine includes a combustor that includes a hollow annular wall having a combustor liner. The turbine engine also includes first flow path in a first direction through the hollow annular wall. The turbine engine further includes a second flow path in a second direction that is opposite the first direction through the hollow annular wall. The second flow path may include one or more film holes configured to supply a cooling film to a downstream end portion of the combustor liner.
摘要翻译： 在一个实施例中，系统包括涡轮发动机。 涡轮发动机包括具有燃烧器衬套的中空环形壁的燃烧器。 涡轮发动机还包括通过中空环形壁的第一方向的第一流动路径。 涡轮发动机还包括在通过中空环形壁与第一方向相反的第二方向上的第二流动路径。 第二流路可以包括一个或多个薄膜孔，其构造成将冷却膜供应到燃烧器衬套的下游端部。
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公开(公告)号：US20110283707A1
公开(公告)日：2011-11-24
申请号：US12784477
申请日：2010-05-20
IPC分类号： F02C3/14
CPC分类号： F23R3/002 , F01D9/023 , F02C7/12 , Y02T50/675
摘要： An air cooling hood offset from an exterior of the transition piece to define an air cooling passage between the air cooling hood and the exterior of the transition piece, wherein the air cooling hood comprises a plurality of air outlets disposed along the exterior of the transition piece, and the plurality of air outlets is configured to expel an airflow from the air cooling passage away from the exterior of the transition piece.
摘要翻译： 空气冷却罩从过渡件的外部偏移以限定空气冷却罩和过渡件的外部之间的空气冷却通道，其中空气冷却罩包括沿着过渡件的外部设置的多个空气出口 并且多个空气出口构造成从空气冷却通道排出远离过渡件外部的气流。
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公开(公告)号：US20110247339A1
公开(公告)日：2011-10-13
申请号：US12756329
申请日：2010-04-08
IPC分类号： F23R3/42
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。
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公开(公告)号：US20100257863A1
公开(公告)日：2010-10-14
申请号：US12422536
申请日：2009-04-13
IPC分类号： F23R3/00
CPC分类号： F23R3/06 , F23R3/005 , F23R2900/03041
摘要： An industrial turbine engine comprises a combustion section, an air discharge section downstream of the combustion section, a transition region between the combustion and air discharge section, a combustion transition piece and a sleeve. The transition piece defines an interior space for combusted gas flow. The sleeve surrounds the combustor transition piece so as to form a flow annulus between the sleeve and the transition piece. The sleeve includes a first set of apertures for directing cooling air from compressor discharge air into the flow annulus. The transition piece includes an outer surface bounding the flow annulus and an inner surface bounding the interior surface, and includes a second set of apertures for directing cooling air in the flow annulus to the interior space. Each of the second set of apertures extends from an entry portion on the outer surface to an exit portion on the inner surface.
摘要翻译： 工业涡轮发动机包括燃烧部分，燃烧部分下游的排气部分，燃烧和排气部分之间的过渡区域，燃烧过渡件和套筒。 过渡件限定了用于燃烧气体流动的内部空间。 套管围绕燃烧器过渡件，以在套筒和过渡件之间形成流动环。 套筒包括第一组孔，用于将冷却空气从压缩机排放空气引导到流动环空中。 过渡件包括限定流动环空的外表面和限定内表面的内表面，并且包括用于将流动环空中的冷却空气引导到内部空间的第二组孔。 第二组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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公开(公告)号：US20100011770A1
公开(公告)日：2010-01-21
申请号：US12176510
申请日：2008-07-21
IPC分类号： F02C1/00
摘要： A premixer for a gas turbine combustor includes a swirler including a plurality of turning vanes that impart swirl velocity to airflow through the premixer, and at least one fuel injection site enabling fuel to mix with the airflow in the premixer. The fuel injection site terminates in a cratered hole. The cratered hole increases mixing efficiency and increases flashback/flameholding resistance.
摘要翻译： 用于燃气轮机燃烧器的预混合器包括旋流器，其包括多个转动叶片，所述转动叶片赋予通过预混合器的气流涡旋速度，以及至少一个燃料喷射位置，使燃料与预混合器中的气流混合。 燃料喷射场地终止于一个装有打包的孔。 起吊孔提高了混合效率，增加了回火/阻焰性。
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公开(公告)号：US20090212504A1
公开(公告)日：2009-08-27
申请号：US12098860
申请日：2008-04-07
IPC分类号： F16J15/22
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28 , F05D2240/57 , F16J15/0887 , F16J15/104
摘要： A turbine includes a static member, a moveable member fluidly connected to the static member, and a flexible seal. The flexible seal includes a spring component having a base section mounted to one of the static member and the moveable member of the turbine and a plurality of biasing members. Each of the plurality of biasing members includes a first portion extending from the base section and a cantilevered portion. The flexible seal further includes a seal component provided on the cantilevered portion of each of the plurality of biasing members. The seal component is biased into contact with the other of the static member and the moveable member.
摘要翻译： 涡轮机包括静止部件，流体连接到静止部件的可移动部件和柔性密封件。 柔性密封件包括弹簧部件，其具有安装到涡轮机的静止部件和可移动部件之一的基部以及多个偏置部件。 多个偏置构件中的每一个包括从基部延伸的第一部分和悬臂部分。 柔性密封件还包括设置在多个偏置构件中的每一个的悬臂部分上的密封部件。 密封部件被偏置成与静止部件和可移动部件中的另一个接触。
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70.发明申请Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine 审中-公开具有径向分段流动通道的燃气轮机预混合器和用于在燃气轮机中混合空气和气体的方法公开(公告)号：US20090056336A1
公开(公告)日：2009-03-05
申请号：US11892891
申请日：2007-08-28
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23C2900/07001 , F23D2900/14004 , F23R3/14
摘要： A burner for use in a combustion system of an industrial gas turbine. The burner includes a fuel/air premixer including a splitter vane defining a first, radially inner passage and a second, radially outer passage, the first and second passages each having air flow turning vane portions which impart swirl to the combustion air passing through the premixer. The vane portions in each passage are commonly configured to impart a same swirl direction in each passage. A plurality of splitter vanes may be provided to define three or more annular passages in the premixer.
摘要翻译： 一种用于工业燃气轮机燃烧系统的燃烧器。 燃烧器包括燃料/空气预混合器，其包括限定第一径向内部通道的分流叶片和第二径向外部通道，所述第一和第二通道各自具有气流转动叶片部分，其向通过预混合器的燃烧空气施加漩涡 。 每个通道中的叶片部分通常构造成在每个通道中赋予相同的旋转方向。 可以设置多个分流叶片以在预混合器中限定三个或更多个环形通道。
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