专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

EP2584177B1 Systems and methods for use in operating turbine engines 有权转让
公开(公告)号：EP2584177B1
公开(公告)日：2019-06-19
申请号：EP12188816.8
申请日：2012-10-17
申请人： General Electric Company
发明人： Hughes, Michael John , Khan, Abdul Rafey , Romig, Bryan Wesley
IPC分类号： F02C9/26 , F02C3/22 , F02C9/40 , F02C9/28

2. 发明公开

EP2672183A3 Combustor assembly having a fuel pre-mixer 有权转让
标题翻译： Brennkammeranordnung mit Brennstoff-Vormischvorrichtung
公开(公告)号：EP2672183A3
公开(公告)日：2017-03-15
申请号：EP13170612.9
申请日：2013-06-05
申请人： General Electric Company
发明人： Bobba, Mohan Krishna , Khan, Abdul Rafey
IPC分类号： F23R3/28 , F23D14/64 , F23R3/14
CPC分类号： F23R3/14 , F23D14/64 , F23D2900/14021 , F23R3/286
摘要： A combustor assembly (14) having a fuel pre-mixer (12) including a duct (28) for mixing an airflow (24) and a fuel therein. Also included is a center body (38) 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 (28). Further included is a planar vane section (40) 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 (42) disposed downstream of the planar vane section (40), wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow (24).
摘要翻译：具有燃料预混合器（12）的燃烧器组件（14），其包括用于混合气流（24）和其中的燃料的管道（28）。还包括在管道内同轴对准的中心体（38），用于从燃料源接收燃料并且构造成将燃料分配到管道（28）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（40），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（40）下游的旋流器叶片部分（42），其中旋流器叶片部分构造成提供燃料的第二次喷射和燃料和气流（24）的混合。

3. 发明公开

EP2672183A2 Combustor assembly having a fuel pre-mixer 有权转让
标题翻译：与燃料预混合燃烧器组件
公开(公告)号：EP2672183A2
公开(公告)日：2013-12-11
申请号：EP13170612.9
申请日：2013-06-05
申请人： General Electric Company
发明人： Bobba, Mohan Krishna , Khan, Abdul Rafey
IPC分类号： F23R3/28 , F23D14/64 , F23R3/14
CPC分类号： F23R3/14 , F23D14/64 , F23D2900/14021 , F23R3/286
摘要： A combustor assembly (14) having a fuel pre-mixer (12) including a duct (28) for mixing an airflow (24) and a fuel therein. Also included is a center body (38) 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 (28). Further included is a planar vane section (40) 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 (42) disposed downstream of the planar vane section (40), wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow (24).

4. 发明公开

EP2629015A2 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量调节器连接到端盖
公开(公告)号：EP2629015A2
公开(公告)日：2013-08-21
申请号：EP13154945.3
申请日：2013-02-12
申请人： General Electric Company
发明人： Bailey, Donald Mark , Khan, Abdul Rafey , Rohrssen, Robert Joseph , Bobba, Mohan Krishna
IPC分类号： F23R3/14 , F23R3/28 , F23R3/16
CPC分类号： F23R3/14 , F23R3/16 , F23R3/286 , F23R2900/00005
摘要： An interface between an inlet flow conditioner (32) and a compressor discharge air passage in a gas turbine includes a cap back plate (30) including a curved exterior surface, and the inlet flow conditioner (IFC) (32) cooperable with the cap back plate. An end of the IFC (32) includes a curved exterior surface that is continued from the curved exterior surface of the cap back plate (30). 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：燃气轮机中的入口流量调节器（32）和压缩机排出空气通道之间的界面包括包括弯曲外表面的帽背板（30），并且入口流量调节器（IFC）（32）与帽后部盘子。 IFC（32）的一端包括从盖背板（30）的弯曲外表面延续的弯曲外表面。接口提供更均匀和更高压力的空气以及更多的空气供应，从而导致更均匀的燃烧。

5. 发明公开

EP2369237A2 Multiple zone pilot for low emission combustion system 审中-公开
标题翻译： Mehrzonen-Pilotfürein Verbrennungssystem mit geringer Emission
公开(公告)号：EP2369237A2
公开(公告)日：2011-09-28
申请号：EP11158382.9
申请日：2011-03-16
申请人： General Electric Company
发明人： Khan, Abdul Rafey , Johnson, Thomas Edward
IPC分类号： F23R3/34
CPC分类号： F23R3/343 , F23C2900/07001 , F23R3/346
摘要： A method of operating a combustor includes delivering a primary fuel flow through a plurality of primary fuel nozzles toward a primary combustion zone and combusting the primary fuel flow in the primary combustion zone. A secondary fuel flow is delivered through a secondary fuel nozzle toward a secondary combustion zone and combusted therein. The secondary fuel is located such that the plurality of primary fuel nozzles are arrayed around the secondary fuel nozzle. An outer swirler is located between the plurality of primary fuel nozzles and the secondary fuel nozzle and includes a plurality of outer swirler channels extending therethrough. A flow of swirler fuel is delivered through the plurality of outer swirler channels into the combustor substantially between the primary combustion zone and the secondary combustion zone to stabilize combustion in the primary combustion zone and/or the secondary combustion zone.
摘要翻译：操作燃烧器的方法包括将主要燃料流通过多个主要燃料喷嘴朝向初级燃烧区输送并燃烧主燃烧区中的主要燃料流。二次燃料流通过二次燃料喷嘴向二次燃烧区输送并在其中燃烧。第二燃料定位成使得多个主燃料喷嘴围绕次燃料喷嘴排列。外旋流器位于多个主燃料喷嘴和次燃料喷嘴之间，并且包括从其延伸穿过的多个外旋流器通道。旋流器燃料的流动通过多个外部旋流器通道输送到主燃烧区和次燃烧区之间的燃烧器中，以稳定主燃烧区和/或二次燃烧区中的燃烧。

6. 发明授权

EP2525151B1 Combustor assembly for a turbomachine 有权转让
公开(公告)号：EP2525151B1
公开(公告)日：2019-01-16
申请号：EP12167945.0
申请日：2012-05-14
申请人： General Electric Company
发明人： Rohrssen, Robert Joseph , Charters, Erich Daniel , Khan, Abdul Rafey , Melton, Patrick Benedict , Vanselow, John Drake
IPC分类号： F23R3/06 , F23R3/28 , F23R3/00

7. 发明授权

EP2527739B1 System and method for flow control in gas turbine engine 有权转让
公开(公告)号：EP2527739B1
公开(公告)日：2018-07-11
申请号：EP12168558.0
申请日：2012-05-18
申请人： General Electric Company
发明人： Melton, Patrick Bendict , Chila, Ronald James , Khan, Abdul Rafey , Antoniono, Carolyn Ashley
IPC分类号： F23R3/02 , F23R3/28
CPC分类号： F23R3/02 , F23R3/286
摘要： A system includes a gas turbine combustor (16), which includes a combustion liner (42) disposed about a combustion region, a flow sleeve (44) disposed about the combustion liner (42), an air passage (46) between the combustion liner (42) and the flow sleeve (44), and a structure (66) between the combustion liner (42) and the flow sleeve (44). The structure (66) obstructs an airflow (64) through the air passage (46). The gas turbine combustor (16) also includes a wake reducer (71) disposed adjacent the structure (66). The wake reducer (71) directs a flow (78) into a wake region (67) downstream of the structure (66).

8. 发明公开

EP2653783A3 Turbine combustor system having aerodynamic feed cap 有权转让
标题翻译：涡轮燃烧器系统具有空气动力学的进料盖
公开(公告)号：EP2653783A3
公开(公告)日：2018-03-28
申请号：EP13163005.5
申请日：2013-04-09
申请人： General Electric Company
发明人： Khan, Abdul Rafey , Bobba, Mohan Krishna , Crawley, Bradley Donald , Rohrssen, Robert Joseph
IPC分类号： 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 (52) of a turbine combustor (14). Embodiments include a system having a turbine combustor (14). The turbine combustor includes a fuel nozzle (20) having an inner shell (130) and an outer shell (92), and a feed cap (50) disposed about the fuel nozzle (20) and having an outer wall (90) and a back plate (88). The back plate (88) joins respective upstream ends of the outer shell (92) of the fuel nozzle (20) and the outer wall (90) of the feed cap (50). The turbine combustor (14) is configured to flow a first pressurized air via an air path (72) extending along the outer wall (90) of the feed cap (50), the back plate (88) of the feed cap (50), and into the fuel nozzle (20).
摘要翻译：当前的实施例旨在减少涡轮机燃烧室（14）的头端（52）中的低流量或无流动情况。实施例包括具有涡轮燃烧器（14）的系统。涡轮燃烧器包括具有内壳（130）和外壳（92）的燃料喷嘴（20）以及设置在燃料喷嘴（20）周围并具有外壁（90）和进气盖背板（88）。后板（88）连接燃料喷嘴（20）的外壳（92）和进料盖（50）的外壁（90）的相应上游端。涡轮燃烧器（14）构造成经由沿着供给盖（50）的外壁（90），供给盖（50）的背板（88）延伸的空气路径（72）流动第一加压空气，并进入燃料喷嘴（20）。

9. 发明公开

EP2244014A3 Radial lean direct injection burner 审中-公开
标题翻译：径向倾斜直喷式燃烧器
公开(公告)号：EP2244014A3
公开(公告)日：2017-11-15
申请号：EP10153189.5
申请日：2010-02-10
申请人： General Electric Company
发明人： Khan, Abdul Rafey , Kraemer, Gilbert Otto , Stevenson, Christian Xavier
IPC分类号： F23D14/24
CPC分类号： F23D14/24 , F23C2900/9901
摘要： A burner (2) for use in a gas turbine engine includes a burner tube having an inlet end (6) and an outlet end (8); a plurality of air passages (12) extending axially in the burner tube configured to convey air flows from the inlet end to the outlet end; a plurality of fuel passages (14) extending axially along the burner tube and spaced around the plurality of air passages configured to convey fuel from the inlet end to the outlet end; and a radial air swirler (22) provided at the outlet end configured to direct the air flows radially toward the outlet end and impart swirl to the air flows. The radial air swirler includes a plurality of vanes (28) to direct and swirl the air flows and an end plate (36). The end plate includes a plurality of fuel injection passages (16) to inject the fuel radially into the swirling air flows. A method of mixing air and fuel in a burner of a gas turbine includes introducing an air flow into the air passages at the inlet end; introducing a fuel into fuel passages; swirling the air flow at the outlet end; and radially injecting the fuel into the swirling air flow.
摘要翻译：用于燃气涡轮发动机的燃烧器（2）包括具有入口端（6）和出口端（8）的燃烧器管; 在所述燃烧器管中轴向延伸的多个空气通道（12），所述空气通道构造成将空气流从所述入口端输送到所述出口端; 多个燃料通道（14），所述多个燃料通道（14）沿所述燃烧器管轴向延伸并且围绕所述多个空气通道间隔开，所述多个空气通道构造成将燃料从所述入口端输送到所述出口端; 以及设置在出口端处的径向空气旋流器（22），该径向空气旋流器（22）构造成将气流朝向出口端径向引导并且向气流施加涡流。径向空气旋流器包括多个引导和旋转气流的叶片（28）和端板（36）。端板包括多个燃料喷射通道（16），以将燃料径向地喷射到旋流气流中。一种在燃气轮机的燃烧器中混合空气和燃料的方法包括：将空气流引入入口端处的空气通道; 将燃料引入燃料通道; 在出口端旋转气流; 并将燃料径向喷射到旋流气流中。

10. 发明公开

EP2369237A3 Multiple zone pilot for low emission combustion system 审中-公开
标题翻译：多区域的导频用于低排放燃烧系统
公开(公告)号：EP2369237A3
公开(公告)日：2014-11-19
申请号：EP11158382.9
申请日：2011-03-16
申请人： General Electric Company
发明人： Khan, Abdul Rafey , Johnson, Thomas Edward
IPC分类号： F23R3/34
CPC分类号： F23R3/343 , F23C2900/07001 , F23R3/346
摘要： A method of operating a combustor includes delivering a primary fuel flow through a plurality of primary fuel nozzles toward a primary combustion zone and combusting the primary fuel flow in the primary combustion zone. A secondary fuel flow is delivered through a secondary fuel nozzle toward a secondary combustion zone and combusted therein. The secondary fuel is located such that the plurality of primary fuel nozzles are arrayed around the secondary fuel nozzle. An outer swirler is located between the plurality of primary fuel nozzles and the secondary fuel nozzle and includes a plurality of outer swirler channels extending therethrough. A flow of swirler fuel is delivered through the plurality of outer swirler channels into the combustor substantially between the primary combustion zone and the secondary combustion zone to stabilize combustion in the primary combustion zone and/or the secondary combustion zone.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式