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1. 发明授权

US08966903B2 Combustor resonator with non-uniform resonator passages 有权
标题翻译：具有不均匀谐振器通道的燃烧器谐振器
公开(公告)号：US08966903B2
公开(公告)日：2015-03-03
申请号：US13212105
申请日：2011-08-17
申请人： Mohan Krishna Bobba , Kwanwoo Kim , Patrick Benedict Melton , Carolyn Ashley Antoniono
发明人： Mohan Krishna Bobba , Kwanwoo Kim , Patrick Benedict Melton , Carolyn Ashley Antoniono
IPC分类号： F02C7/24 , F23R3/00
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014
摘要： Certain embodiments of the present disclosure include a combustor resonator having a non-uniform annulus between a combustor assembly and a resonator shell. The combustor resonator may further include resonator necks or passages having non-uniform lengths and geometries.
摘要翻译：本公开的某些实施例包括在燃烧器组件和谐振器壳体之间具有不均匀环空的燃烧器谐振器。燃烧器谐振器还可以包括具有不均匀长度和几何形状的谐振器颈部或通道。

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

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。

4. 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。

5. 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。

6. 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。

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。

9. 发明申请

US20130042619A1 COMBUSTOR RESONATOR 有权
标题翻译： COMBUSTOR谐振器
公开(公告)号：US20130042619A1
公开(公告)日：2013-02-21
申请号：US13212105
申请日：2011-08-17
申请人： Mohan Krishna Bobba , Kwanwoo Kim , Patrick Benedict Melton , Carolyn Ashley Antoniono
发明人： Mohan Krishna Bobba , Kwanwoo Kim , Patrick Benedict Melton , Carolyn Ashley Antoniono
IPC分类号： F23R3/16
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014
摘要： Certain embodiments of the present disclosure include a combustor resonator having a non-uniform annulus between a combustor assembly and a resonator shell. The combustor resonator may further include resonator necks or passages having non-uniform lengths and geometries.
摘要翻译：本公开的某些实施例包括在燃烧器组件和谐振器壳体之间具有不均匀环空的燃烧器谐振器。燃烧器谐振器还可以包括具有不均匀长度和几何形状的谐振器颈部或通道。

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