公开(公告)号：EP3418638A1

公开(公告)日：2018-12-26

申请号：EP17177065.4

申请日：2017-06-21

申请人： General Electric Company

发明人： BOLANOS, Felipe ,  BIAGIOLI, Fernando ,  WIND, Torsten

IPC分类号： F23R3/00 ,  F23R3/14 ,  F23R3/18 ,  F23R3/34

CPC分类号： F23R3/346 ,  F23C2201/401 ,  F23R3/005 ,  F23R3/14 ,  F23R3/18 ,  F23R2900/03341

摘要： A combustor (16) for a turbomachine includes a rich combustion zone (41) and a low temperature zone (43) downstream of the rich combustion zone. A heat exchanger (100) is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.

公开(公告)号：EP2971971B1

公开(公告)日：2018-11-28

申请号：EP14714511.4

申请日：2014-03-10

申请人： Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

发明人： LOEBIG, James C. ,  DEBRUHL, Christopher D. ,  HOLDCRAFT, John

IPC分类号： F23R3/06 ,  F23R3/04

CPC分类号： F02K7/02 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03341 ,  F23R2900/03342 ,  Y10T29/49229

摘要： A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate.

公开(公告)号：EP3401602A1

公开(公告)日：2018-11-14

申请号：EP18171676.2

申请日：2018-05-10

申请人： General Electric Company

发明人： GUBBA, Sreenivasa Rao ,  HUGHES, Michael John ,  AGARWAL, Krishna Kant

IPC分类号： F23R3/10 ,  F23R3/34 ,  F23D14/64 ,  F23R3/00

CPC分类号： F23R3/286 ,  F23D14/64 ,  F23R3/002 ,  F23R3/10 ,  F23R3/283 ,  F23R3/346 ,  F23R2900/03341

摘要： A fuel injector 100 includes a frame 304 and a pair of fuel injection bodies 340 coupled to the frame. The frame has interior sides that define an opening for passage of a first fluid. Inlet flow paths for the first fluid are defined at least between the interior sides of the frame and the respective fuel injection bodies. Each fuel injection body defines a fuel plenum 350 and includes at least one fuel injection surface that defines a plurality of fuel injection holes 354 in communication with the fuel plenum. An outlet member 310 is located downstream of, and in fluid communication, with the inlet flow paths. The outlet member is configured to produce discrete outlet flow paths exiting the outlet member via struts, flow diverters, and/or separate outlet members.

公开(公告)号：EP3306199A1

公开(公告)日：2018-04-11

申请号：EP16192707.4

申请日：2016-10-06

申请人： Ansaldo Energia Switzerland AG

发明人： IMFELD, Jost ,  SWIATEK, Slawomir ,  KONRADT, Oliver

IPC分类号： F23R3/60 ,  F23C6/04

CPC分类号： F23R3/08 ,  F01D9/023 ,  F02C3/205 ,  F02C7/28 ,  F23C6/047 ,  F23D2900/14004 ,  F23M2900/05002 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/03341

摘要： Combustor device (1) for a gas turbines engines (100) comprising a first (11) and a second (13) tubular members telescopically fitted in axially sliding manner to one another with the interposition of annular centering and sealing means (14, 15) which include at least a centring annular shoulder (14) and a sealing ring (15) arranged coaxial to one another; said sealing ring (15) being axially spaced apart from said centring annular shoulder (14) so that the axial distance (d) between the centring annular shoulder (14) and the sealing ring (15) is greater than the maximum axial movement (w) allowed between said first (11) and said second (13) tubular members.

摘要翻译： 用于燃气涡轮发动机（100）的燃烧器装置（1）包括第一（11）和第二（13）管状构件，所述第一（11）和第二（13）管状构件以轴向滑动的方式相互套叠地插入环形对中和密封装置（14,15） 其包括至少一个彼此同轴布置的对中环形肩部（14）和密封环（15）;其中， 所述密封环（15）与所述对中环形肩部（14）轴向间隔开，使得对中环形肩部（14）和密封环（15）之间的轴向距离（d）大于最大轴向运动（w） ）允许在所述第一（11）和所述第二（13）管状构件之间。

公开(公告)号：EP3306197A1

公开(公告)日：2018-04-11

申请号：EP16192964.1

申请日：2016-10-08

申请人： Ansaldo Energia Switzerland AG

发明人： WOOD, John Philip ,  CIANI, Andrea ,  EROGLU, Adnan

IPC分类号： F23R3/36

CPC分类号： F23R3/36 ,  F02C3/04 ,  F02C7/222 ,  F23N2035/26 ,  F23R3/286 ,  F23R2900/03341

摘要： A dual fuel concentric nozzle for a gas turbine, in particular for a dual fuel injector of a sequential burner of a sequential gas turbine; the dual fuel concentric nozzle (37) comprising:
- a nozzle downstream end configured to inject gas fuel, liquid fuel and carrier air along a hot gas main flow (M);
- a liquid fuel duct (43) defining a liquid fuel passage for connecting a liquid fuel supply (41) to the nozzle downstream end, the liquid fuel duct (43) comprising a downstream end edge at the nozzle downstream end;
- a gas fuel duct (44) concentrically surrounding the liquid fuel duct (43) and defining a gas fuel passage between the outer surface of the liquid fuel duct (43) and the inner surface of the gas fuel duct (44) for connecting a gas plenum to the nozzle downstream end, the gas fuel duct (44) comprising a downstream end edge at the nozzle downstream end;
- a lateral wall (42) concentrically surrounding the gas fuel duct (44) and defining a carrier air passage between the outer surface of the gas fuel duct (44) and the inner surface of the lateral surface (42) for connecting an air plenum (40) to the nozzle downstream end, the lateral surface (42) comprising a downstream end edge at the nozzle downstream end;
wherein the downstream end edge of the gas fuel duct (44) is recessed inside the nozzle downstream end with respect to the downstream end edge of the liquid fuel duct (43).

摘要翻译： 一种用于燃气轮机的双燃料同心喷嘴，特别是用于顺序燃气轮机的顺序燃烧器的双燃料喷射器; 所述双燃料同心喷嘴（37）包括：喷嘴下游端，所述喷嘴下游端构造成沿着热气主流（M）喷射气体燃料，液体燃料和载气; - 限定用于将液体燃料供应（41）连接到所述喷嘴下游端的液体燃料通道的液体燃料管道（43），所述液体燃料管道（43）包括在所述喷嘴下游端处的下游端部边缘; - 同心地围绕液体燃料导管（43）并在液体燃料导管（43）的外表面和气体燃料导管（44）的内表面之间限定气体燃料通道的气体燃料导管（44），用于连接 所述气体燃料导管（44）包括在所述喷嘴下游端处的下游端部边缘; - 同心地围绕气体燃料管道（44）并在气体燃料管道（44）的外表面和侧表面（42）的内表面之间限定载气通道的侧壁（42），用于连接空气增压室 （40）连接到所述喷嘴下游端，所述侧表面（42）包括在所述喷嘴下游端处的下游端部边缘; 其中所述气体燃料管道（44）的所述下游端部边缘相对于所述液体燃料管道（43）的所述下游端部边缘凹入所述喷嘴下游端部内部。

公开(公告)号：EP2420730B1

公开(公告)日：2018-03-07

申请号：EP11175604.5

申请日：2011-07-27

申请人： Ansaldo Energia IP UK Limited

发明人： Buss, Johannes ,  Ciani, Andrea ,  Benz, Urs ,  Düsing, Michael ,  Hutapea, Michael ,  Eroglu, Adnan

IPC分类号： F23C3/00 ,  F23D11/40 ,  F23R3/20 ,  F23R3/00 ,  F23R3/12

CPC分类号： F23D11/402 ,  F23C3/002 ,  F23D11/408 ,  F23R3/002 ,  F23R3/12 ,  F23R3/20 ,  F23R2900/03341

摘要： The reheat burner (1) comprises a channel (2) with a lance (3) projecting thereinto to inject a fuel over an injection plane (4) perpendicular to a channel longitudinal axis (15). The channel (2) and lance (3) define a vortex generation zone (6) upstream of the injection plane (4) and a mixing zone (9) downstream of the injection plane (4) in the hot gas (G) direction. The mixing zone (9) has a cross section with diverging side walls (20) in the hot gas (G) direction. The diverging side walls (20) define curved surfaces in the hot gas (G) direction having a constant radius (R).

公开(公告)号：EP3168535A1

公开(公告)日：2017-05-17

申请号：EP15194429.5

申请日：2015-11-13

申请人： General Electric Technology GmbH

发明人： Baibuzenko, Igor ,  Mylnikov, Sergey ,  Petrunin, Dmitry ,  Stytsenko, Alexey ,  Maurer, Michael Thomas ,  Loeffel, Kaspar

IPC分类号： F23R3/20 ,  F23R3/36 ,  F23R3/28 ,  F23R3/16 ,  F01D5/18

CPC分类号： F23R3/283 ,  F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F02C7/22 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/202 ,  F23R3/16 ,  F23R3/36 ,  F23R2900/00018 ,  F23R2900/03341

摘要： Disclosed is an aerodynamically shaped body (1) for use in a hot fluid flow. The body (1) extends along a camber line (100) from a leading edge (11) to a trailing edge (12). The body comprises at least one coolant supply plenum (101) provided inside the body, wherein the coolant supply plenum is delimited by a body wall, wherein the body wall extends from a first side of the camber line (100) to a second side of the camber line (100) and extends over the leading edge (11), thereby providing a leading edge wall section. The wall further comprises an inner surface facing the coolant supply plenum (101) and an outer surface. At least one first leading edge cooling duct (20) extends from the inner surface to the outer surface and is in fluid communication with the coolant supply plenum (101) through an inlet opening (21) and opens out onto the outer surface through a discharge opening (22). The inlet opening (21) is provided on a first side of the camber line (100), the discharge opening (22) is provided on a second side of the camber line (100), and the leading edge cooling duct (20) is provided inside the wall and extending inside the wall from the first side of the camber line (100) to the second side of the camber line (100) and thereby crossing the camber line (100,) in a leading edge (11) region.

摘要翻译： 公开了一种用于在热流体流动中使用的空气动力学形状的主体（1）。 所述主体（1）沿着从前缘（11）到后缘（12）一弧线（100）延伸。 所述主体包括主体的内部，worin冷却剂供给腔室的至少一个冷却剂供给腔室（101）由主体壁界定，worin体壁从所述弧线（100）的第一侧延伸至第二侧 弧线（100）和延伸在所述前缘（11），从而提供一个前缘壁部。 的壁的面对冷却剂供给腔室（101）和上外表面内表面还包括。 至少一个第一前缘冷却管道（20）从所述内表面到外表面延伸，并与所述冷却剂供给腔室（101）通过在入口开口（21）流体连通，并且到外表面上通过排放通向 开口（22）。 入口开口（21）设置在所述弧线（100）的第一侧，所述排出开口（22）设置在所述弧线（100）和所述前缘冷却管道的第二侧（20）是 所述壁的内部，并且从所述弧线（100）中弧线（100），并由此在交叉的前缘（11）区域中的弧线（100）的第二侧的第一侧上的壁内延伸。

公开(公告)号：EP3130848A1

公开(公告)日：2017-02-15

申请号：EP15180787.2

申请日：2015-08-12

申请人： General Electric Technology GmbH

发明人： Reiter, Wilhelm ,  Hoffmann, Jürgen Gerhard

IPC分类号： F23C6/04 ,  F23R3/34

CPC分类号： F23R3/002 ,  F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2260/201 ,  F23C6/047 ,  F23R3/02 ,  F23R3/34 ,  F23R3/36 ,  F23R2900/03041 ,  F23R2900/03341 ,  Y02E20/16

摘要： The invention refers to a gas turbine (1) with a sequential combustor arrangement (4) comprising a first combustor with a first burner (106) for admitting a first fuel (28) into a combustor inlet gas during operation and a first combustion chamber (101) for burning the first fuel (28), a dilution gas admixer (27) for admixing a dilution gas (33) to the first combustor combustion products (35) leaving the first combustion chamber (101), a second burner (103) for admixing a second fuel (29) and a second combustion chamber (102). To assure a temperature profile after the dilution gas admixer (27) and to increase the gas turbine's (1) power and efficiency a vane (11) and/or blade (10) of the turbine (5) has a closed loop cooling. The outlet of the closed loop cooling (17) is connected to the dilution gas admixer (27) for admixing the heated cooling gas leaving the vane (11) and/or blade (10) into the first combustor combustion products (35).
The disclosure further refers to method for operating a gas turbine (1) with such a sequential combustor arrangement (4) and closed loop cooling (17).

摘要翻译： 本发明涉及具有连续燃烧器装置（4）的燃气轮机（1），其包括具有第一燃烧器（106）的第一燃烧器（106），用于在操作期间将第一燃料（28）引入燃烧器入口气体和第一燃烧室 101），用于燃烧第一燃料（28）的稀释气体混合器（27），用于将稀释气体（33）与离开第一燃烧室（101）的第一燃烧器燃烧产物（35）混合的第二燃烧器（103） 用于混合第二燃料（29）和第二燃烧室（102）。 为了确保在稀释气体混合器（27）之后的温度分布，并且为了增加燃气轮机（1）的功率和效率，涡轮机（5）的叶片（11）和/或叶片（10）具有闭环冷却。 闭环冷却出口17连接到稀释气体混合器27，用于将离开叶片（11）和/或叶片（10）的加热的冷却气体混合到第一燃烧器燃烧产物（35）中。 本公开还涉及用这种顺序的燃烧器装置（4）和闭环冷却（17）来操作燃气轮机（1）的方法。

公开(公告)号：EP3115693A1

公开(公告)日：2017-01-11

申请号：EP15176259.8

申请日：2015-07-10

申请人： General Electric Technology GmbH

发明人： Syed, Khawar ,  Poyyapakkam, Madhavan Narasimhan ,  Genin, Franklin Marie

IPC分类号： F23R3/20 ,  F23R3/34

CPC分类号： F02C3/14 ,  F05B2240/35 ,  F05D2240/35 ,  F23R3/20 ,  F23R3/346 ,  F23R2900/03341

摘要： The present invention generally relates to a sequential combustor for a gas turbine. The invention additionally refers to a method for operating the same. Specifically, the invention concerns the second and/or subsequent stages of a re-heat, sequential or axiallystaged combustion system. According to the invention, variation in Mach number along the flow path is used to control static temperature variation, which in turn influences the progress of auto-ignition reactions that eventually lead to the onset of combustion.

摘要翻译： 本发明一般涉及燃气轮机的顺序燃烧器。 本发明还涉及一种用于操作该方法的方法。 具体地，本发明涉及再热，顺序或轴向阶段燃烧系统的第二和/或其后阶段。 根据本发明，沿着流路的马赫数的变化用于控制静态温度变化，这进而影响最终导致燃烧开始的自燃反应的进程。

公开(公告)号：EP3091288A1

公开(公告)日：2016-11-09

申请号：EP15166956.1

申请日：2015-05-08

申请人： General Electric Technology GmbH

发明人： Wysocki, Stefan ,  Luebcke, Holger

IPC分类号： F23R3/06 ,  F23R3/16 ,  F23R3/28

CPC分类号： F02C7/22 ,  F02C7/04 ,  F23R3/06 ,  F23R3/16 ,  F23R3/286 ,  F23R2900/03341

摘要： This application describes a mixing system 32 for a gas turbine combustor arrangement, the mixing system 32 comprising a lobed mixer 10 and a wall 40, 42 enclosing a fluid flow path 34, wherein the lobed mixer 10 is arranged in the wall 40, 42 between a first part of the wall 40 and a second part of the wall 42, and wherein the first part of the wall 40 and the second part of the wall 42 are spaced apart in the direction of a lobed mixer axis 50. Details of the lobed mixer 10 and a method of mixing two flows in a mixing system are also described.

摘要翻译： 该申请描述了用于燃气轮机燃烧器装置的混合系统32，混合系统32包括叶状混合器10和封闭流体流动路径34的壁40,42，其中叶状混合器10布置在壁40,42之间 壁40的第一部分和壁42的第二部分，并且其中壁40的第一部分和壁42的第二部分在叶状混合器轴线50的方向上间隔开。 还描述了混合器10和混合系统中的两个流的混合方法。