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1. 发明申请

US20130205799A1 Outer Fuel Nozzle Inlet Flow Conditioner Interface to End Cap 审中-公开
标题翻译：外部燃油喷嘴入口流动调节器接口到端盖
公开(公告)号：US20130205799A1
公开(公告)日：2013-08-15
申请号：US13397218
申请日：2012-02-15
申请人： Donald Mark Bailey , Abdul Rafey Khan , Robert Joseph Rohrssen , Mohan Krishna Bobba
发明人： Donald Mark Bailey , Abdul Rafey Khan , Robert Joseph Rohrssen , Mohan Krishna Bobba
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。

2. 发明申请

US20130269350A1 TURBINE COMBUSTOR SYSTEM HAVING AERODYNAMIC FEED CAP 有权
标题翻译：具有气动进给盖的涡轮机系统
公开(公告)号：US20130269350A1
公开(公告)日：2013-10-17
申请号：US13448283
申请日：2012-04-16
申请人： Abdul Rafey Khan , Bradley Donald Crawley , Robert Joseph Rohrssen , Mohan Krishna Bobba
发明人： Abdul Rafey Khan , Bradley Donald Crawley , Robert Joseph Rohrssen , Mohan Krishna Bobba
IPC分类号： F23R3/10 , F23R3/26 , F23R3/28 , F23R3/16
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。

3. 发明授权

US08966907B2 Turbine combustor system having aerodynamic feed cap 有权
标题翻译：具有气动进料盖的涡轮燃烧器系统
公开(公告)号：US08966907B2
公开(公告)日：2015-03-03
申请号：US13448283
申请日：2012-04-16
申请人： Abdul Rafey Khan , Bradley Donald Crawley , Robert Joseph Rohrssen , Mohan Krishna Bobba
发明人： Abdul Rafey Khan , Bradley Donald Crawley , Robert Joseph Rohrssen , Mohan Krishna Bobba
IPC分类号： F02C1/00 , F02G3/00 , F23R3/28 , F23D14/64
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。

4. 发明授权

US08978384B2 Swirler assembly with compressor discharge injection to vane surface 有权
标题翻译：涡轮组件，压缩机排放注入叶片表面
公开(公告)号：US08978384B2
公开(公告)日：2015-03-17
申请号：US13303888
申请日：2011-11-23
申请人： Donald Mark Bailey , Abdul Rafey Khan , Mohan Krishna Bobba
发明人： Donald Mark Bailey , Abdul Rafey Khan , Mohan Krishna Bobba
IPC分类号： F02C1/00 , F02G3/00 , F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23R3/283 , F23R3/286
摘要： A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.
摘要翻译：燃气轮机燃烧器中的旋流器组件包括轮毂，护罩和连接在轮毂和护罩之间的多个叶片。叶片包括空气和燃料撞击叶片和低压侧的高压侧。在从接收压缩机的排出空气中接收多个叶片的每个叶片中设置有空气回路。每个空气回路包括进入叶片的空气进入通道和叶片的低压侧的空气出口通道。

5. 发明申请

US20130125553A1 Swirler Assembly with Compressor Discharge Injection to Vane Surface 有权
标题翻译：涡轮组件，带压缩机排气喷射到叶片表面
公开(公告)号：US20130125553A1
公开(公告)日：2013-05-23
申请号：US13303888
申请日：2011-11-23
申请人： Donald Mark Bailey , Abdul Rafey Khan , Mohan Krishna Bobba
发明人： Donald Mark Bailey , Abdul Rafey Khan , Mohan Krishna Bobba
IPC分类号： F23R3/28
CPC分类号： F23R3/14 , F23R3/283 , F23R3/286
摘要： A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.
摘要翻译：燃气轮机燃烧器中的旋流器组件包括轮毂，护罩和连接在轮毂和护罩之间的多个叶片。叶片包括空气和燃料撞击叶片和低压侧的高压侧。在从接收压缩机的排出空气中接收多个叶片的每个叶片中设置有空气回路。每个空气回路包括进入叶片的空气进入通道和叶片的低压侧的空气出口通道。

6. 发明申请

US20130327046A1 COMBUSTOR ASSEMBLY HAVING A FUEL PRE-MIXER 有权
标题翻译：具有燃料预混器的燃烧器组件
公开(公告)号：US20130327046A1
公开(公告)日：2013-12-12
申请号：US13490061
申请日：2012-06-06
申请人： Mohan Krishna Bobba , Abdul Rafey Khan
发明人： Mohan Krishna Bobba , Abdul Rafey Khan
IPC分类号： F23R3/14 , F02C7/22
CPC分类号： F23R3/14 , F23D14/64 , F23D2900/14021 , F23R3/286
摘要： A combustor assembly having a fuel pre-mixer including a duct for mixing an airflow and a fuel therein. Also included is a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct. Further included is a planar vane section in communication with the airflow and the fuel to provide a first injection of fuel and a flow conditioning effect on the airflow. Yet further included is a swirler vane section disposed downstream of the planar vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow.
摘要翻译：一种燃烧器组件，其具有燃料预混合器，该燃料预混合器包括用于混合气流的管道和其中的燃料。还包括在管道内同轴对准的中心体，用于从燃料源接收燃料并且构造成将燃料分配到管道内的至少一个轴向位置。进一步包括与气流和燃料连通的平面叶片部分，以提供燃料的第一次喷射和对气流的流动调节作用。还包括设置在平面叶片部分下游的旋流器叶片部分，其中旋流叶片部分构造成提供燃料的第二次喷射和燃料与气流的混合。

7. 发明授权

US09395084B2 Fuel pre-mixer with planar and swirler vanes 有权
标题翻译：具有平面和旋流器叶片的燃料预混合器
公开(公告)号：US09395084B2
公开(公告)日：2016-07-19
申请号：US13490061
申请日：2012-06-06
申请人： Mohan Krishna Bobba , Abdul Rafey Khan
发明人： Mohan Krishna Bobba , Abdul Rafey Khan
IPC分类号： F23D14/64 , F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23D14/64 , F23D2900/14021 , F23R3/286
摘要： A combustor assembly having a fuel pre-mixer including a duct for mixing an airflow and a fuel therein. Also included is a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct. Further included is a planar vane section in communication with the airflow and the fuel to provide a first injection of fuel and a flow conditioning effect on the airflow. Yet further included is a swirler vane section disposed downstream of the planar vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow.
摘要翻译：一种燃烧器组件，其具有燃料预混合器，该燃料预混合器包括用于混合气流的管道和其中的燃料。还包括在管道内同轴对准的中心体，用于从燃料源接收燃料并且构造成将燃料分配到管道内的至少一个轴向位置。进一步包括与气流和燃料连通的平面叶片部分，以提供燃料的第一次喷射和对气流的流动调节作用。还包括设置在平面叶片部分下游的旋流器叶片部分，其中旋流叶片部分构造成提供燃料的第二次喷射和燃料与气流的混合。

8. 发明申请

US20120297784A1 SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机流量控制系统与方法
公开(公告)号：US20120297784A1
公开(公告)日：2012-11-29
申请号：US13115051
申请日：2011-05-24
申请人： Patrick Benedict Melton , David William Cihlar , Robert Joseph Rohrssen , Abdul Rafey Khan
发明人： Patrick Benedict Melton , David William Cihlar , Robert Joseph Rohrssen , Abdul Rafey Khan
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。

9. 发明授权

US08281596B1 Combustor assembly for a turbomachine 有权
标题翻译：用于涡轮机的燃烧器组件
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
IPC分类号： F23R3/14 , F02C3/14
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。

10. 发明授权

US08850821B2 System for fuel injection in a fuel nozzle 有权
标题翻译：燃料喷嘴燃料喷射系统
公开(公告)号：US08850821B2
公开(公告)日：2014-10-07
申请号：US13269510
申请日：2011-10-07
申请人： Abdul Rafey Khan , Bradley Donald Crawley , Donald Mark Bailey , Ajay Pratap Singh
发明人： Abdul Rafey Khan , Bradley Donald Crawley , Donald Mark Bailey , Ajay Pratap Singh
IPC分类号： F02C1/00 , F23R3/28 , F23R3/36 , F23R3/14
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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