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公开(公告)号：US09562692B2
公开(公告)日：2017-02-07
申请号：US14164791
申请日：2014-01-27
发明人： Steven Williams , Timothy A. Fox , Reinhard Schilp
IPC分类号： F23R3/34 , F23R3/36 , F23R3/38 , F23R3/22 , F23R3/28 , F23D14/22 , F23D14/24 , F02C7/266 , F23D11/38 , F23D11/42 , F23D3/22
CPC分类号： F23R3/343 , F02C7/266 , F23D3/22 , F23D11/38 , F23D11/42 , F23D14/22 , F23D14/24 , F23D2207/00 , F23R3/36 , F23R3/38
摘要： A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body.
摘要翻译： 用于燃烧器的先导燃料喷嘴包括形成沿着喷嘴的纵向中心延伸的中心体的点火器。 喷嘴尖端包括多个周向间隔开的燃料通道和多个周向隔开的空气通道，其延伸到喷嘴尖端的外侧。 中心体延伸穿过喷嘴尖端的中心，用于产生火花以点燃与喷嘴尖端相邻的燃料/空气混合物。 多个燃料管沿着中心体延伸，每个燃料管具有接合在喷嘴尖端上的出口端，用于将燃料从喷嘴尖端输送到燃烧室的燃烧室中。外套管包围燃料管并限定一个 环形空间与外套筒和中心体之间的喷嘴尖端的空气通道流体连通。
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公开(公告)号：US09518743B2
公开(公告)日：2016-12-13
申请号：US14074292
申请日：2013-11-07
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。
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公开(公告)号：US09494174B2
公开(公告)日：2016-11-15
申请号：US14201680
申请日：2014-03-07
IPC分类号： F16L55/04 , F15D1/02 , F02C7/22 , F02C9/40 , F23R3/36 , F23K5/00 , F23K5/14 , F23N1/00 , F23R3/28 , F02M21/02
CPC分类号： F15D1/025 , F02C7/22 , F02C9/40 , F02M21/0224 , F23K5/007 , F23K5/14 , F23N1/00 , F23N2021/10 , F23N2041/20 , F23R3/28 , F23R3/36
摘要： A system includes an inlet pipe configured to convey a fluid and a buffer volume configured to buffer the fluid. The buffer volume includes a smallest diameter tube having a smallest diameter, a first inlet end, and a first outlet end. The first inlet end is configured to receive the fluid from the inlet pipe. The buffer volume also includes an intermediate tube surrounding the smallest diameter tube having a first capped end and a second outlet end. The first capped end is positioned next to the outlet end of the smallest diameter tube. The buffer volume also includes a largest diameter tube surrounding the intermediate tube second capped end and a third outlet end. The second capped end is positioned next to the second outlet end of the intermediate tube. The system also includes an outlet pipe configured to convey the fluid from the buffer volume.
摘要翻译： 系统包括被配置为输送流体的入口管和被配置为缓冲流体的缓冲体积。 缓冲体积包括具有最小直径的最小直径管，第一入口端和第一出口端。 第一入口端构造成从入口管接收流体。 缓冲体积还包括围绕具有第一封端和第二出口端的最小直径管的中间管。 第一个封盖端靠近最小直径管的出口端。 缓冲体积还包括围绕中间管第二封端的最大直径管和第三出口端。 第二封盖端位于中间管的第二出口端附近。 该系统还包括配置成从缓冲体积输送流体的出口管。
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公开(公告)号：US09476592B2
公开(公告)日：2016-10-25
申请号：US13956921
申请日：2013-09-19
摘要： A combustion system uses a fuel nozzle with an inner wall having a fuel inlet in fluid communication with a fuel outlet in a fuel cartridge. The inner wall defines a mounting location for inserting the fuel cartridge. A pair of annular lip seals around the cartridge outer wall on both sides of the fuel outlet seals the fuel passage between the fuel inlet and the fuel outlet.
摘要翻译： 燃烧系统使用燃料喷嘴，其内壁具有与燃料盒中的燃料出口流体连通的燃料入口。 内壁限定用于插入燃料盒的安装位置。 在燃料出口两侧的盒外壁周围的一对环形唇形密封件密封在燃料入口和燃料出口之间的燃料通道。
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45.发明授权Method for operating a gas turbine engine, power supplying device for conducting such method and aircraft using such method 有权用于操作燃气涡轮发动机的方法，用于进行这种方法的供电装置和使用这种方法的飞行器公开(公告)号：US09464573B2
公开(公告)日：2016-10-11
申请号：US12679821
申请日：2008-09-24
申请人： Sebastien Remy , Jean Botti
发明人： Sebastien Remy , Jean Botti
CPC分类号： F02C7/22 , F02C3/22 , F02C3/30 , F02C9/26 , F02C9/28 , F02C9/40 , F05D2220/50 , F05D2270/082 , F23C2900/9901 , F23R3/06 , F23R3/36 , F23R2900/00002 , H01M8/04156 , H01M8/0612 , H01M2250/20 , Y02T50/675 , Y02T50/677 , Y02T50/678 , Y02T90/32
摘要： A power supply device or system for aeronautics, having a hydrocarbon supply for supplying an engine with hydrocarbon fuel and a hydrogen supply having a fuel reformer for producing hydrogen from hydrocarbon fuel from said hydrocarbon supply. The hydrogen supply is connected to a hydrogen-powered fuel cell for producing electric power and to a hydrogen injecting system for injection of hydrogen into a combustion chamber of the engine. Further, the invention relates to an aircraft having an engine that can be supplied by that power supplying device or system, and to a method for operating said engine.
摘要翻译： 一种用于航空的供电装置或系统，具有用于向发动机提供碳氢化合物燃料的碳氢化合物供应和具有用于从所述烃供应的烃燃料产生氢气的燃料重整器的氢气供应。 氢气供应连接到用于产生电力的氢动力燃料电池和用于将氢气注入发动机的燃烧室的氢气注入系统。 此外，本发明涉及具有可由该供电装置或系统提供的发动机的飞行器以及用于操作所述发动机的方法。
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公开(公告)号：US09441835B2
公开(公告)日：2016-09-13
申请号：US13647359
申请日：2012-10-08
发明人： Brandon Taylor Overby , David Leach
CPC分类号： F23R3/02 , F23L7/00 , F23L2900/07002 , F23L2900/07009 , F23R3/286 , F23R3/36
摘要： A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as O2 and O2 mixtures. The system also includes an aerodynamic peg disposed in the gas turbine combustor. The aerodynamic peg includes a first passage configured to convey a first fluid into the gas turbine combustor and a second passage configured to convey a second fluid into the gas turbine combustor. The first fluid and second fluid are different from one another.
摘要翻译： 一种系统包括配置成燃烧燃料和氧化剂如O2和O2混合物的燃气轮机燃烧器。 该系统还包括设置在燃气轮机燃烧器中的空气动力学栓塞。 空气动力学栓塞包括构造成将第一流体输送到燃气涡轮机燃烧器中的第一通道和被构造成将第二流体输送到燃气涡轮机燃烧器中的第二通道。 第一流体和第二流体彼此不同。
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公开(公告)号：US20160123597A1
公开(公告)日：2016-05-05
申请号：US14925527
申请日：2015-10-28
发明人： Douglas Anthony PENNELL , Urs BENZ , Adnan EROGLU , Ewald FREITAG , Mirko Ruben BOTHIEN , Andrea CIANI
CPC分类号： F23R3/346 , F23C6/042 , F23C6/045 , F23C6/047 , F23C2900/07021 , F23D2900/14004 , F23R3/06 , F23R3/283 , F23R3/34 , F23R3/36 , F23R2900/03341
摘要： A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.
摘要翻译： 用于燃气轮机的燃烧器装置包括第一燃烧器，第一燃烧室，混合器，用于将稀释气体混合到在运行期间离开第一燃烧室的气体;第二燃烧器和第二燃烧室，其依次布置在流体流中 连接。 燃烧器装置的这些元件被排列成一行以形成在第一燃烧室和第二燃烧器之间延伸的流路。 燃烧器装置包括设置在流动路径内并且从第一燃烧器通过第一燃烧室延伸到混合器中并进入第二燃烧器的中心喷枪体，其中喷枪体包括用于为第一燃烧器提供燃料的燃料管道和/或 为第二个燃烧器。
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公开(公告)号：US09285123B2
公开(公告)日：2016-03-15
申请号：US11693951
申请日：2007-03-30
CPC分类号： F23R3/346 , F02C7/228 , F02C9/34 , F02C9/40 , F23N5/022 , F23N2025/04 , F23N2025/06 , F23N2025/26 , F23N2037/02 , F23R3/36
摘要： A burner system with staged fuel injection includes at least one burner with a mixing zone. A combustion chamber is disposed downstream of the mixing zone and a first fuel introduction device is provided upstream of the mixing zone. Furthermore, a second fuel introduction device for the direct injection of fuel into the combustion chamber, is disposed downstream of the mixing zone. In addition, at least one sensor for determining combustion parameters is connected to a control device. The control device is designed to control the second fuel introduction device as a function of the parameters determined by the sensors.
摘要翻译： 具有分级燃料喷射的燃烧器系统包括具有混合区域的至少一个燃烧器。 燃烧室设置在混合区的下游，并且第一燃料引入装置设置在混合区的上游。 此外，用于将燃料直接喷射到燃烧室中的第二燃料引入装置设置在混合区的下游。 此外，用于确定燃烧参数的至少一个传感器连接到控制装置。 控制装置被设计成根据由传感器确定的参数来控制第二燃料引入装置。
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公开(公告)号：US09261278B2
公开(公告)日：2016-02-16
申请号：US13683061
申请日：2012-11-21
CPC分类号： F23R3/28 , F02C9/26 , F05D2270/31 , F23N1/00 , F23N5/242 , F23N2041/20 , F23R3/36
摘要： A method and apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L).
摘要翻译： 公开了用于在瞬态操作期间操作燃烧装置的方法和装置。 燃烧装置供给至少一种燃料。 瞬态操作包括具有以低于指定（例如临界）量（Mc）的量供给燃料的周期长度（T）的周期。 对于周期长度（T）定义极限值（L），并且调节燃料供给以使周期长度（T）小于或等于极限值（L）。
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公开(公告)号：US20160010548A1
公开(公告)日：2016-01-14
申请号：US14771450
申请日：2013-02-28
发明人： Almaz Kamilevich Valeev , Leonid Yul'evich Ginesin , Borys Borysovich Shershnyov , Igor Petrovich Sidko , Sergey Anatolievich Meshkov
摘要： A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.
摘要翻译： 一种系统包括涡轮机燃烧器，其包括具有头端室的头端部分。 前端部包括排气路径，燃料路径和氧化剂路径。 涡轮机燃烧器还包括具有设置在头端室下游的燃烧室的燃烧部分，设置在头端室和燃烧室之间的盖，以及端板，其具有联接到排气路径或 氧化剂路径。 头端室轴向地设置在盖和端板之间。
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