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1. 发明申请

US20120304652A1 INJECTOR APPARATUS 审中-公开
标题翻译：注射器装置
公开(公告)号：US20120304652A1
公开(公告)日：2012-12-06
申请号：US13149044
申请日：2011-05-31
申请人： Bradley Donald Crawley , David William Cihlar , Patrick Benedict Melton , Frederick Millard Setzer, JR.
发明人： Bradley Donald Crawley , David William Cihlar , Patrick Benedict Melton , Frederick Millard Setzer, JR.
IPC分类号： F02C7/22
CPC分类号： F01D9/023 , F23R3/06 , F23R3/286 , F23R3/346
摘要： An injector apparatus is provided and includes an annular inlet in which a first fluid traveling in a first direction is mixable with a second fluid to form a mixture, an annular outlet disposed downstream from the inlet from which the mixture is injectable into a main flow in a third direction and an annular intermediate section fluidly interposed between the inlet and the outlet and along which the mixture is re-directable from the inlet to the outlet.
摘要翻译：提供了一种注射器装置，其包括环形入口，其中在第一方向上行进的第一流体可与第二流体混合以形成混合物，设置在入口下游的环形出口，混合物从该入口可注入主流体第三方向和流体介于入口和出口之间的环形中间部分，并且混合物可从该入口和出口重新定向。

2. 发明授权

US08826667B2 System and method for flow control in gas turbine engine 有权
标题翻译：燃气轮机发动机流量控制系统及方法
公开(公告)号：US08826667B2
公开(公告)日：2014-09-09
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
IPC分类号： F02C1/00 , F02G3/00
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。

3. 发明申请

US20120297783A1 SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE 有权
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：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
IPC分类号： F23R3/02 , F23R3/28 , F23R3/26
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。

4. 发明申请

US20130111909A1 Combustion System Having A Venturi For Reducing Wakes In An Airflow 有权
标题翻译：具有文丘里燃烧系统以减少气流中的气味
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。

5. 发明授权

US08397514B2 System and method for flow control in gas turbine engine 有权
标题翻译：燃气轮机发动机流量控制系统及方法
公开(公告)号：US08397514B2
公开(公告)日：2013-03-19
申请号：US13115063
申请日：2011-05-24
申请人： Bradley Donald Crawley , David William Cihlar , Abdul Rafey Khan
发明人： Bradley Donald Crawley , David William Cihlar , Abdul Rafey Khan
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。

6. 发明授权

US09267687B2 Combustion system having a venturi for reducing wakes in an airflow 有权
标题翻译：燃烧系统具有文丘里管，用于减少气流中的醒来
公开(公告)号：US09267687B2
公开(公告)日：2016-02-23
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： F23R3/54 , F23R3/00
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。

7. 发明申请

US20120297786A1 SYSTEM AND METHOD FOR FLOW CONTROL IN GAS TURBINE ENGINE 有权
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：US20120297786A1
公开(公告)日：2012-11-29
申请号：US13115063
申请日：2011-05-24
申请人： Bradley Donald Crawley , David William Cihlar , Abdul Rafey Khan
发明人： Bradley Donald Crawley , David William Cihlar , Abdul Rafey Khan
IPC分类号： F23R3/42 , F23R3/28 , F23R3/26
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。

8. 发明授权

US07134287B2 Turbine combustor endcover assembly 有权
标题翻译：涡轮燃烧器内盖组件
公开(公告)号：US07134287B2
公开(公告)日：2006-11-14
申请号：US10615776
申请日：2003-07-10
申请人： Keith Cletus Belsom , Larry Lou Thomas , Donald Timothy Lemon , Bradley Donald Crawley , Matthew Eugene Roberts , David Kevin Spikings
发明人： Keith Cletus Belsom , Larry Lou Thomas , Donald Timothy Lemon , Bradley Donald Crawley , Matthew Eugene Roberts , David Kevin Spikings
IPC分类号： F02C7/20
CPC分类号： F23R3/60
摘要： The endcover assembly for a combustor includes an endcover having an aperture, an insert disposed in the stepped bore opening through an internal face of the endcover, a fuel cartridge extending through the insert and aperture and a seal cover on the external face of the endcover. Seal cover/endcover annular seals are disposed in registering axial cavities to seal against fluid leakage externally of the endcover assembly. Generally C-shaped and W-shaped seals are disposed in the cavities between the stepped shoulders of the insert and aperture to seal against leakage through the internal face of the endcover. The seals maintain sealing engagement during assembly and thermal distortion during turbine usage.
摘要翻译：用于燃烧器的封盖组件包括具有开口的端盖，通过端盖的内表面设置在阶梯式孔开口中的插入件，延伸穿过插入件和孔的燃料盒以及在封盖的外表面上的密封盖。密封盖/端盖环形密封件设置成对准轴向空腔以密封外罩组件的流体泄漏。通常，C形和W形密封件设置在插入件的阶梯状肩部和孔之间的空腔中，以防止通过内罩的内表面泄漏。涡轮机使用期间，密封件在组装和热变形期间保持密封接合。

9. 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。

10. 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。

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