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1. 发明授权

US09518743B2 Method for operating a gas turbine burner with a swirl generator 有权
标题翻译：用涡流发生器操作燃气轮机燃烧器的方法
公开(公告)号：US09518743B2
公开(公告)日：2016-12-13
申请号：US14074292
申请日：2013-11-07
申请人： ALSTOM Technology Ltd
发明人： Adnan Eroglu
IPC分类号： F23R3/34 , F23R3/36 , F23C6/04 , F23D11/10 , F23D11/12 , F23D11/40 , F23D14/58 , F23D14/64 , F23D17/00 , F23R3/12 , F23R3/28
CPC分类号： F23R3/34 , F23C6/047 , F23C2900/07002 , F23C2900/07021 , F23D11/105 , F23D11/12 , F23D11/402 , F23D14/58 , F23D14/64 , F23D17/002 , F23D2900/00015 , F23D2900/11101 , F23R3/12 , F23R3/286 , F23R3/343 , F23R3/346 , F23R3/36 , F23R2900/03341
摘要： Methods are directed to operating a burner of a gas turbine. The burner includes a swirl generator and, downstream of it, a mixing tube. The swirl generator is defined by at least two walls facing one another to define a conical swirl chamber and includes nozzles arranged to inject fuel and apertures arranged to feed an oxidizer into the swirl chamber. The burner includes a lance which extends along a longitudinal axis of the swirl generator and side nozzles for ejecting a fuel within the burner. The side nozzles have their axes inclined with respect to the axis of the lance and can be positioned along the axis of the burner. During operation, an oil fuel or gaseous fuel is injected into to the burner through the lance tip and the lance side nozzles at various percentages depending on an operating mode of the gas turbine.
摘要翻译：方法涉及操作燃气轮机的燃烧器。燃烧器包括涡流发生器，并在其下游设有混合管。漩涡发生器由彼此面对的至少两个壁限定，以限定圆锥形的旋转室，并且包括喷射喷射燃料的喷嘴和布置成将氧化剂进料到涡流室中的孔。燃烧器包括沿着涡流发生器的纵向轴线延伸的喷枪和用于在燃烧器内喷射燃料的侧喷嘴。侧喷嘴具有相对于喷枪的轴线倾斜的轴线，并且可以沿着燃烧器的轴线定位。在操作期间，油燃料或气体燃料根据燃气轮机的操作模式以不同的百分比通过喷枪尖和喷枪侧喷嘴喷射到燃烧器中。

2. 发明授权

US09383098B2 Radial flow fuel nozzle for a combustor of a gas turbine 有权
标题翻译：用于燃气轮机燃烧器的径流燃料喷嘴
公开(公告)号：US09383098B2
公开(公告)日：2016-07-05
申请号：US13664705
申请日：2012-10-31
申请人： General Electric Company
发明人： Gregory Scott Means , Gregory Allen Boardman , Jonathan Dwight Berry
IPC分类号： F23D11/24 , F23R3/28 , F23D14/00 , F23R3/34 , F23R3/46 , F23D11/38
CPC分类号： F23D11/24 , F23D11/38 , F23D14/00 , F23D2900/00015 , F23R3/283 , F23R3/286 , F23R3/343 , F23R3/46 , F23R2900/00012 , F23R2900/03044
摘要： A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.
摘要翻译：用于燃气轮机的燃烧器通常包括具有燃料分配歧管的径流式燃料喷嘴和与燃料分配歧管轴向分离的燃料喷射歧管。燃料喷射歧管通常包括延伸穿过外侧部分的内侧部分，外侧部分和多个周向间隔开的燃料端口。多个管在燃料分配歧管和燃料喷射歧管之间提供轴向间隔。每个管限定在燃料分配歧管和燃料喷射歧管之间的流体连通路径。

3. 发明授权

US09347667B2 Injector for the combustion chamber of a gas turbine having a dual fuel circuit, and combustion chamber provided with at least one such injector 有权
标题翻译：具有双重燃料回路的燃气轮机的燃烧室的喷射器和设置有至少一个这样的喷射器的燃烧室
公开(公告)号：US09347667B2
公开(公告)日：2016-05-24
申请号：US13982608
申请日：2012-01-27
申请人： Bernard Joseph Jean Pierre Carrere , Jean-Luc Dabat
发明人： Bernard Joseph Jean Pierre Carrere , Jean-Luc Dabat
IPC分类号： F23R3/28 , F23D11/10 , F23R3/14 , F23R3/34
CPC分类号： F23R3/28 , F23D11/103 , F23D11/107 , F23D2900/00014 , F23D2900/00015 , F23D2900/00016 , F23R3/14 , F23R3/343
摘要： A starting injector usable in all flight modes without additional cost or weight. The starting injector includes a dual fuel circuit and an air circuit. An injector for a combustion chamber of a gas turbine includes a dual fuel injection circuit including a starting fuel circuit for ignition and then for all the flight modes, and a main fuel circuit for all the flight modes after starting. The circuits include parallel pipes in a common tube having an axis. The pipe of the starting circuit is substantially in communication with a center of a spherical injector body. At the end, the pipe accommodates an injection manifold coupled to a central channel passing through a central wall of a swirler. The pipe of the main circuit is in communication with an annular channel opposite jet channels. An air circuit is guided between two portions shaped as concentric spheres.
摘要翻译：可在所有飞行模式下使用的起动喷油器，无需额外的成本或重量。起动喷射器包括双燃料回路和空气回路。用于燃气轮机的燃烧室的喷射器包括双燃料喷射回路，其包括用于点火的起动燃料回路，然后用于所有飞行模式，以及启动后的所有飞行模式的主燃料回路。电路包括在具有轴线的公共管中的平行管。启动电路的管道基本上与球形喷射器主体的中心连通。最后，管道容纳连接到通过旋流器的中心壁的中心通道的注入歧管。主回路的管道与一个与通道相对的环形通道连通。在形成为同心球的两个部分之间引导空气回路。

4. 发明授权

US09046039B2 Staged pilots in pure airblast injectors for gas turbine engines 有权
标题翻译：燃气涡轮发动机纯空气喷射器中的分期驾驶员
公开(公告)号：US09046039B2
公开(公告)日：2015-06-02
申请号：US13292258
申请日：2011-11-09
申请人： Brandon Phillip Williams , Viraphand Cholvibul , David H. Bretz
发明人： Brandon Phillip Williams , Viraphand Cholvibul , David H. Bretz
IPC分类号： F23R3/14 , F23R3/28 , F23R3/34 , F02C9/34 , F02C7/22 , F02C7/228 , F23D11/10
CPC分类号： F02C7/222 , F02C7/22 , F02C7/228 , F02C9/34 , F23D11/107 , F23D2900/00015 , F23D2900/11101 , F23R3/14 , F23R3/286 , F23R3/343 , Y02T50/675
摘要： An injector includes a main nozzle body defining a central axis and having a main fuel circuit. A pilot nozzle body is mounted inboard of the main nozzle body. The pilot nozzle body includes a pilot air circuit on the central axis with fuel circuitry radially outboard of the pilot air circuit for delivering fuel to a fuel outlet in a downstream portion of the pilot nozzle body. The fuel circuitry includes a primary pilot fuel circuit configured and adapted to deliver fuel to the fuel outlet and a secondary pilot fuel circuit configured and adapted to deliver fuel to the same fuel outlet.
摘要翻译：喷射器包括限定中心轴线并具有主燃料回路的主喷嘴体。主喷嘴体安装在主喷嘴体的内侧。引导喷嘴主体包括在中心轴线上的先导空气回路，其中燃料回路沿先导空气回路径向排出，用于将燃料输送到先导喷嘴体的下游部分中的燃料出口。燃料电路包括构造并适于将燃料输送到燃料出口的主要先导燃料回路和构造并适于将燃料输送到相同燃料出口的次级引燃燃料回路。

5. 发明申请

US20150052899A1 AIRBLAST FUEL INJECTOR 有权
标题翻译： AIRBLAST燃油喷射器
公开(公告)号：US20150052899A1
公开(公告)日：2015-02-26
申请号：US14456353
申请日：2014-08-11
申请人： ROLLS-ROYCE PLC
发明人： Ian James TOON
IPC分类号： F23R3/14 , F23R3/34
CPC分类号： F23R3/286 , F23D11/105 , F23D2900/00015 , F23D2900/11101 , F23R3/14 , F23R3/28 , F23R3/343
摘要： An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile. Relative to the overall axial direction of flow through the injector the shroud inner surface profile has a convergent section followed by a divergent section, the transition of which forming a first inwardly directed annular nose. The injector further has an annular wall having an outer surface profile, and having an inner surface profile. Relative to the overall axial direction of flow through the injector the wall outer surface profile has a convergent section followed by an outwardly turning section which faces across the shroud air passage to the first nose.
摘要翻译：用于燃气涡轮发动机燃料喷雾喷嘴的喷气燃料喷射器从径向内到外依次具有内部空气旋流器通道，环形燃料通道，环形外部空气旋流器通道和环形外壳空气旋流器的同轴布置通道。喷射器还具有具有内表面轮廓的环形护罩。相对于通过喷射器的整个轴向流动方向，护罩内表面轮廓具有会聚部分，随后是发散部分，其转变形成第一向内指向的环形鼻部。喷射器还具有具有外表面轮廓并具有内表面轮廓的环形壁。相对于通过注射器的整个轴向方向，壁外表面轮廓具有会聚部分，随后是向外转动部分，其面向穿过护罩空气通道到达第一鼻部。

6. 发明授权

US08820087B2 Method and system for controlling fuel to a dual stage nozzle 有权
标题翻译：用于将燃料控制到双级喷嘴的方法和系统
公开(公告)号：US08820087B2
公开(公告)日：2014-09-02
申请号：US12205963
申请日：2008-09-08
申请人： William R. Ryan
发明人： William R. Ryan
IPC分类号： F02C7/22 , F02C9/26 , F23R3/34 , F23N1/00 , F23D11/38
CPC分类号： F23R3/343 , F23D11/38 , F23D2900/00015 , F23N1/002 , F23N2027/26 , F23N2035/14 , F23N2035/28
摘要： A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles.
摘要翻译：一种用于控制向燃气轮机的燃烧器中的双级喷嘴输送燃料的方法和系统。液体燃料从单级燃料供给通过多个初级燃料供给管路输送到包括多个主喷嘴的第一喷嘴台。识别燃气轮机的预定操作条件，并响应于所识别的操作条件产生信号。信号影响位于从每个主燃料供应管线延伸到辅助燃料供应管线上的阀的致动，以将燃料供应到相应的次级喷嘴。

7. 发明申请

US20140116054A1 RADIAL FLOW FUEL NOZZLE FOR A COMBUSTOR OF A GAS TURBINE 有权
标题翻译：用于燃气轮机燃烧器的径流式燃料喷嘴
公开(公告)号：US20140116054A1
公开(公告)日：2014-05-01
申请号：US13664705
申请日：2012-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： Gregory Scott Means , Gregory Allen Boardman , Jonathan Dwight Berry
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23D11/24 , F23D11/38 , F23D14/00 , F23D2900/00015 , F23R3/283 , F23R3/286 , F23R3/343 , F23R3/46 , F23R2900/00012 , F23R2900/03044
摘要： A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.
摘要翻译：用于燃气轮机的燃烧器通常包括具有燃料分配歧管的径流式燃料喷嘴和与燃料分配歧管轴向分离的燃料喷射歧管。燃料喷射歧管通常包括延伸穿过外侧部分的内侧部分，外侧部分和多个周向间隔开的燃料端口。多个管在燃料分配歧管和燃料喷射歧管之间提供轴向间隔。每个管限定在燃料分配歧管和燃料喷射歧管之间的流体连通路径。

8. 发明申请

US20140041390A1 LEAN BURN INJECTORS HAVING MULTIPLE PILOT CIRCUITS 有权
标题翻译： AN AN。。。。。。。。。。。。。。。。。。。
公开(公告)号：US20140041390A1
公开(公告)日：2014-02-13
申请号：US14057511
申请日：2013-10-18
申请人： Delavan Inc.
发明人： Brandon P. Williams , Jeremy T. Rhyan
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F23D2900/00015 , F23R3/343
摘要： A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit.
摘要翻译：一种用于燃气涡轮发动机的燃料喷射器包括限定中心轴线并具有主燃料回路的喷嘴体。在主燃料回路内的喷嘴体内部形成有空气回路。在空气回路的内部的喷嘴体内形成有主要的先导燃料回路。二次引燃燃料电路形成在空气回路内部的喷嘴体内部和主导向燃料回路外侧。

9. 发明申请

US20140026579A1 BURNER FOR A GAS TURBINE 审中-公开
标题翻译：燃气轮机
公开(公告)号：US20140026579A1
公开(公告)日：2014-01-30
申请号：US13876594
申请日：2011-09-27
申请人： Andreas Karlsson , Magnus Persson
发明人： Andreas Karlsson , Vladimir Dusan Milosavljevic , Magnus Persson
IPC分类号： F23R3/34
CPC分类号： F23R3/343 , F23D2900/00014 , F23D2900/00015 , F23R3/20 , F23R3/286
摘要： A burner for a gas turbine includes a burner housing, and a pilot combustor having a supply module providing pilot fuel and pilot air into a pilot combustion room being enclosed by a pilot combustor housing having a tapered exit with a throat of a defined length into the resulting main flow direction. The throat discharges a concentration of radicals are and heat generated in the pilot combustion room into a main combustion room enclosed by the burner housing. The interior cross section area of the throat deviates from a circle by means of flow guiding elements provided as protrusions with a defined radial height or as recesses with a defined depth extending longitudinally along the direction of the burner axis to give the discharging flow a defined velocity distribution with regard to a circumferential direction.
摘要翻译：一种用于燃气轮机的燃烧器包括燃烧器壳体和引燃燃烧器，其具有向导向燃烧室提供引燃燃料和先导空气的供给模块，该引燃燃烧室由具有限定长度的喉部的具有锥形出口的先导燃烧器壳体包围，主要流向。喉部将先导燃烧室中产生的自由基浓度和热量排放到由燃烧器壳体包围的主燃烧室中。喉部的内部横截面区域通过作为具有限定的径向高度的突起的流动引导元件而偏离圆形，或者具有沿着燃烧器轴线的方向纵向延伸的限定深度的凹部，以使排出流具有限定的速度关于圆周方向的分布。

10. 发明授权

US08499564B2 Pilot burner for gas turbine engine 有权
标题翻译：燃气轮机的先导燃烧器
公开(公告)号：US08499564B2
公开(公告)日：2013-08-06
申请号：US12233713
申请日：2008-09-19
申请人： Scott M. Martin , Robert J. Bland , Anil Gulati
发明人： Scott M. Martin , Robert J. Bland , Anil Gulati
IPC分类号： F02C7/264
CPC分类号： F23R3/14 , F23C2900/07001 , F23D2900/00008 , F23D2900/00015 , F23D2900/14701 , F23R3/286 , F23R3/343 , F23R2900/03343
摘要： A pilot burner (150, 350) for a gas turbine engine delivers an inner non-swirling fuel-oxidant mixture surrounded by an outer swirling fuel-oxidant mixture, thereby providing enhanced mixing with no recirculation zone. At least one fluid-restricting inlet port (166, 366) provides an oxidant to an inner mixing passage (160, 360). The inner mixing passage (160, 360) includes a plurality of fuel outlets (168). An outer annular mixing passage (180) receives oxidant from an upstream port (181) surrounding the inner mixing passage and includes at least one swirler element (186, 386) and fuel outlets (188).
摘要翻译：用于燃气涡轮发动机的引燃燃烧器（150,350）输送由外部旋转燃料 - 氧化剂混合物包围的内部非旋转燃料 - 氧化剂混合物，从而提供与不再循环区域的增强混合。至少一个流体限制入口（166,366）向内部混合通道（160,360）提供氧化剂。内部混合通道（160,360）包括多个燃料出口（168）。外部环形混合通道（180）从围绕内部混合通道的上游端口（181）接收氧化剂，并且包括至少一个旋流器元件（186,386）和燃料出口（188）。

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