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公开(公告)号：US08281596B1
公开(公告)日：2012-10-09
申请号：US13108164
申请日：2011-05-16
申请人： Robert Joseph Rohrssen , Erich Daniel Charters , Abdul Rafey Khan , Patrick Benedict Melton , John Drake Vanselow
发明人： Robert Joseph Rohrssen , Erich Daniel Charters , Abdul Rafey Khan , Patrick Benedict Melton , John Drake Vanselow
CPC分类号： F23R3/06 , F23D2900/14004 , F23R3/002 , F23R3/286 , F23R2900/00014 , F23R2900/03042
摘要： A combustor assembly for a turbomachine includes combustor housing and a flow sleeve arranged between the combustor housing and a combustor liner. The flow sleeve defines a first annular fluid passage, and a second annular fluid passage. A quaternary cap is mounted to the combustor housing. The quaternary cap includes a first fluid plenum fluidly connected to the first annular fluid passage, a second fluid plenum fluidly connected to the second annular fluid passage, and a plurality of vanes fluidly connected to each of the first and second fluid plenums. Each of the plurality of vanes includes a body portion having a first fluid channel coupled to the first fluid plenum, and a second fluid channel coupled to the second fluid plenum. The first fluid channel extends completely through the body portion and the second fluid channel extends partially into the body portion.
摘要翻译： 用于涡轮机的燃烧器组件包括燃烧器壳体和布置在燃烧器壳体和燃烧器衬套之间的流动套筒。 流动套管限定第一环形流体通道和第二环形流体通道。 四角帽安装在燃烧器壳体上。 四级盖包括流体连接到第一环形流体通道的第一流体增压室，与第二环形流体通道流体连接的第二流体室，以及与第一和第二流体通道中的每一个流体连接的多个叶片。 多个叶片中的每一个包括主体部分，其具有联接到第一流体增压室的第一流体通道和联接到第二流体增压室的第二流体通道。 第一流体通道完全延伸穿过主体部分，并且第二流体通道部分地延伸到主体部分中。
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公开(公告)号：US20120297784A1
公开(公告)日：2012-11-29
申请号：US13115051
申请日：2011-05-24
IPC分类号： F23R3/16
CPC分类号： F23R3/002 , F23R3/48 , 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 an airflow guide vane disposed in the air passage. The airflow guide vane includes an upstream vane portion and a downstream vane portion. The upstream vane portion is oriented at an angle from an axial axis of the gas turbine combustor. The downstream vane portion is aligned with the axial axis. The airflow guide vane is configured to remove a circumferential swirl of an airflow upstream of the airflow guide vane to straighten the airflow downstream of the airflow guide vane along the axial axis.
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，燃烧衬套和流动套筒之间的空气通道以及设置在空气通道中的气流引导叶片 。 气流引导叶片包括上游叶片部分和下游叶片部分。 上游叶片部分与燃气轮机燃烧器的轴线成一角度定向。 下游叶片部分与轴向对准。 气流引导叶片被构造成去除气流引导叶片上游的气流的周向漩涡，以沿着轴向平衡气流引导叶片下游的气流。
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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：US08919127B2
公开(公告)日：2014-12-30
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：US20130205799A1
公开(公告)日：2013-08-15
申请号：US13397218
申请日：2012-02-15
IPC分类号： F02C6/04
CPC分类号： F23R3/14 , F23R3/16 , F23R3/286 , F23R2900/00005
摘要： An interface between an inlet flow conditioner and a compressor discharge air passage in a gas turbine includes a cap back plate including a curved exterior surface, and an inlet flow conditioner (IFC) cooperable with the cap back plate. An end of the IFC includes a curved exterior surface that is continued from the curved exterior surface of the cap back plate. The interface provides for more uniform and higher pressure air as well as more air supply, resulting in more uniform combustion.
摘要翻译： 燃气涡轮机中的入口流动调节器和压缩机排出空气通道之间的界面包括具有弯曲外表面的盖背板和与盖背板配合的入口流动调节器（IFC）。 IFC的端部包括从盖背板的弯曲外表面延续的弯曲外表面。 该界面提供更均匀和更高压力的空气以及更多的空气供应，导致更均匀的燃烧。
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公开(公告)号：US20130269350A1
公开(公告)日：2013-10-17
申请号：US13448283
申请日：2012-04-16
CPC分类号： F23R3/286 , F23D14/64 , F23D2209/10 , F23D2900/14021 , F23D2900/14701
摘要： Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.
摘要翻译： 本发明的实施例旨在减少涡轮机燃烧器的头端中的低流量或不流动情况。 实施例包括具有涡轮机燃烧器的系统。 涡轮机燃烧器包括具有内壳和外壳的燃料喷嘴和设置在燃料喷嘴周围并且具有外壁和后板的进料盖。 背板连接燃料喷嘴的外壳的各个上游端和进料盖的外壁。 涡轮机燃烧器构造成使第一加压空气经由沿进料盖的外壁，进料盖的后板延伸并进入燃料喷嘴的空气路径。
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公开(公告)号：US08966907B2
公开(公告)日：2015-03-03
申请号：US13448283
申请日：2012-04-16
CPC分类号： F23R3/286 , F23D14/64 , F23D2209/10 , F23D2900/14021 , F23D2900/14701
摘要： Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.
摘要翻译： 本发明的实施例旨在减少涡轮机燃烧器的头端中的低流量或不流动情况。 实施例包括具有涡轮机燃烧器的系统。 涡轮机燃烧器包括具有内壳和外壳的燃料喷嘴和设置在燃料喷嘴周围并且具有外壁和后板的进料盖。 背板连接燃料喷嘴的外壳的各个上游端和进料盖的外壁。 涡轮机燃烧器构造成使第一加压空气经由沿进料盖的外壁，进料盖的后板延伸并进入燃料喷嘴的空气路径。
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公开(公告)号：US08850821B2
公开(公告)日：2014-10-07
申请号：US13269510
申请日：2011-10-07
CPC分类号： F23R3/286 , F23C2900/07001 , F23D2900/14021 , F23R3/14 , F23R3/36 , F23R2900/00013
摘要： A system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets.
摘要翻译： 系统包括燃料喷嘴。 燃料喷嘴包括轮毂，围绕毂设置的护罩，轮毂和护罩之间的气流路径，设置在轮毂上的多个第一燃料出口以及设置在多个第一燃料出口下游的气流通道中的多个涡流叶片。
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公开(公告)号：US20130111909A1
公开(公告)日：2013-05-09
申请号：US13289537
申请日：2011-11-04
申请人： Abdul Rafey Khan , David William Cihlar , Ajay Pratap Singh , Bradley Donald Crawley , Jason Thurman Stewart
发明人： Abdul Rafey Khan , David William Cihlar , Ajay Pratap Singh , Bradley Donald Crawley , Jason Thurman Stewart
IPC分类号： F23R3/42
CPC分类号： F23R3/002 , F23R3/54 , F23R2900/03044
摘要： A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow.
摘要翻译： 提供了具有衬套，流动套筒，阻流元件和文氏管的燃烧系统。 衬套围绕燃烧区域设置。 流动套管围绕衬套设置。 衬套和流动套管配合以产生具有位于衬套和流动套筒之间的气流的空气通道。 流动阻塞元件设置在空气通道内，并且通常阻碍空气通道中的气流在气流中产生醒来。 文丘里管设置在阻流元件的下游，并且通常限制和扩散空气通道中的气流以减少气流中的醒来。
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公开(公告)号：US08397514B2
公开(公告)日：2013-03-19
申请号：US13115063
申请日：2011-05-24
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23R3/005 , F23R3/02 , F23R3/48 , F23R3/60 , 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, a fuel injector disposed downstream of the combustion liner and the flow sleeve, a liner mount extending between the combustion liner and the flow sleeve, and a crossfire tube extending between the combustion liner and the flow sleeve. The fuel injector, the liner mount, and the crossfire tube are aligned with one another in a flow enhancing arrangement along a common axis in an axial direction relative to an axis of the gas turbine combustor. The flow enhancing arrangement reduces an air flow disturbance caused by the fuel injector, the liner mount, and the crossfire tube.
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，设置在燃烧衬套下游的燃料喷射器， 流动套管，在燃烧衬套和流动套筒之间延伸的衬垫安装件，以及在燃烧衬套和流动套筒之间延伸的交叉火焰管。 燃料喷射器，衬套安装件和交叉火管彼此沿着沿着相对于燃气轮机燃烧器的轴线的轴向方向上的共同轴线的流动增强装置彼此对准。 流动增强装置减少了由燃料喷射器，衬套安装件和交火管引起的气流干扰。
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