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51. 发明公开

EP2257738A1 SWIRLER WITH GAS INJECTORS 审中-公开
标题翻译：带气体喷射器的旋流器
公开(公告)号：EP2257738A1
公开(公告)日：2010-12-08
申请号：EP09727558.0
申请日：2009-03-26
申请人： Siemens Aktiengesellschaft
发明人： MILOSAVLJEVIC, Vladimir , PERSSON, Allan , PERSSON, Magnus
IPC分类号： F23C7/00 , F23D14/02 , F23D14/70 , F23R3/14 , F23R3/28
CPC分类号： F23C7/004 , F23C2900/07001 , F23D14/02 , F23D14/70 , F23D2900/14021 , F23R3/14 , F23R3/286
摘要： The invention relates to a swirler for premixing a flow of fuel (14) and a flow of air (12) provided to a burner (1) for a gas turbine engine, which burner (1) is provided with a swirler (3) for mixing the air (12) and the fuel (14) and wherein the swirler (3) is provided with swirler wings (3a), wherein a channel formed between two adjacent swirler wings (3a) defines a passage. It is one object of the invention to provide stability to a lean premixed combustion. This is achieved by a swirler of the above mentioned type having one fuel tube (15) for gaseous fuel positioned in parallel on each side of a mixing rod (15b) in said passage, wherein said fuel tubes (15) are provided with a plurality of diffuser holes (15a) distributed along the tube (15) acting as gas injectors for efficiently distributing fuel (14) in a flow of air passing through said swirler (3) passage.
摘要翻译：本发明涉及一种用于将燃料流（14）和提供给用于燃气涡轮发动机的燃烧器（1）的空气流（12）预混的旋流器，该燃烧器（1）设置有旋流器（3）混合空气（12）和燃料（14），并且其中旋流器（3）设置有旋流器翼（3a），其中形成在两个相邻旋流器旋翼（3a）之间的通道限定通道。本发明的一个目的是为贫燃预混燃烧提供稳定性。这通过上述类型的旋流器实现，其具有用于气体燃料的一个燃料管（15），所述燃料管在所述通道中的混合杆（15b）的每侧上平行定位，其中所述燃料管（15）设置有多个沿着作为气体喷射器的管（15）分布的扩散器孔（15a），用于在通过所述旋流器（3）通道的空气流中有效地分配燃料（14）。

52. 发明公开

EP1801503A3 Combustor nozzle 审中-公开
标题翻译：燃烧喷嘴
公开(公告)号：EP1801503A3
公开(公告)日：2010-07-07
申请号：EP06256345.7
申请日：2006-12-13
申请人： United Technologies Corporation
发明人： Graves, Charles B.
IPC分类号： F23R3/28 , F23C7/00 , F23D11/38
CPC分类号： F23R3/286 , F23C7/004 , F23C2900/07001 , F23D11/383 , F23R2900/00016
摘要： A gas turbine engine swirler/nozzle apparatus (200) has a swirler having a central axis (510) and a nozzle. The nozzle has an outlet end with a plurality of outlets (210...; 215) about said axis (510) and having an asymmetry about said axis. The apparatus may be formed as a reengineering of a baseline apparatus having a symmetric nozzle.

53. 发明公开

EP1933007A2 Gas turbine guide vanes with tandem airfoils and fuel injection and method of use 审中-公开
标题翻译： GasturbinenführungsschaufelnmitTandemflächenund Brennstoffeinspritzung sowie Verwendungsverfahrendafür
公开(公告)号：EP1933007A2
公开(公告)日：2008-06-18
申请号：EP07121734.3
申请日：2007-11-28
申请人： General Electric Company
发明人： Bunker, Ronald Scott , Evulet, Andrei Tristan
IPC分类号： F01D5/14 , F01D9/04 , F02K3/08
CPC分类号： F01D5/146 , F01D9/041 , F01D9/065 , F02K3/08 , F23C2900/07001 , F23R3/20 , Y02T50/673
摘要： Gas turbine engine guide vanes (12) that include a first flange (26) connected with a casing (18) of a gas turbine engine, a second flange (28) connected with the casing, a first airfoil (22) disposed between the first and second flanges and connected thereto, and a second airfoil (24) disposed between the first and second flanges and connected thereto so as to form a gap (34) extending radially between a first trailing portion of the first airfoil and a second leading portion of the second airfoil, the hollow portion being in flow communication with the gap so as to allow a gaseous fuel (26) to flow from the hollow portion through the gap and into a fluid flowing over the guide vane. Gas turbines that use the guide vanes and methods for injecting a gaseous fuel for combustion in a gas turbine engine are also disclosed.
摘要翻译：包括与燃气涡轮发动机的壳体（18）连接的第一凸缘（26）的燃气涡轮发动机导向叶片（12），与壳体连接的第二凸缘（28），设置在第一和第二凸缘并连接到其上，第二翼型件（24）设置在第一和第二凸缘之间并与之连接，以形成在第一翼型件的第一尾部之间径向延伸的间隙（34）所述第二翼型件，所述中空部分与所述间隙流动连通，以允许气体燃料（26）从所述中空部分流过所述间隙并流入流过所述导向叶片的流体。还公开了使用引导叶片的燃气轮机和用于在燃气涡轮发动机中燃烧气体燃料的方法。

54. 发明公开

EP1806535A1 Système d'injection multimode pour chambre de combustion, notamment d'un turboréacteur 有权转让
标题翻译：多模式Einspritzsystemfüreine Brennkammer，insbesonderefüreine Gasturbine
公开(公告)号：EP1806535A1
公开(公告)日：2007-07-11
申请号：EP07100246.3
申请日：2007-01-08
申请人： SNECMA
发明人： Hernandez, Didier , Noel, Thomas
IPC分类号： F23R3/14 , F23R3/28 , F23R3/34
CPC分类号： F23R3/14 , F23C2900/07001 , F23D2900/14021 , F23D2900/14701 , F23R3/286 , F23R3/346 , Y02T50/675
摘要： Le dispositif comporte un système de pulvérisation périphérique ayant une pluralité de trous d'éjection de carburant (31) régulièrement repartis circonférentiellement et un déflecteur giratoire d'air, annulaire, comprenant des canaux d'éjection d'air (36) tels que, pour chaque axe d'éjection de carburant défini par un trou d'éjection (31), il existe un canal d'éjection d'air correspondant dont au moins la partie radialement la plus interne possède une médiane (M) coupant sensiblement cet axe d'éjection de carburant.
摘要翻译：用于燃烧室的多模式注射器具有至少两个同轴燃料雾化系统。它具有外围系统，其具有与一系列相等间隔的燃料喷射孔（31）连通的环形分配室和具有用于每个孔的空气喷射通道（36）的翅片（35）的环形空气导流器。通道数等于孔的数量的倍数，并且至少穿过每个通道的内端的中线（M）与其中一个孔相交。

55. 发明公开

EP1445466A3 Compact afterburners for gas turbine engines 审中-公开
标题翻译：一种用于燃气涡轮发动机紧凑燃烧装置
公开(公告)号：EP1445466A3
公开(公告)日：2007-01-10
申请号：EP04002689.0
申请日：2004-02-06
申请人： PRATT & WHITNEY ROCKETDYNE, INC.
发明人： Schmotolocha, Stephen N. , Morris, Donald H. , Pederson, Robert J. , Edelman, Raymond Bernard , Morrison, Calvin Q. Jr.
IPC分类号： F02K9/78 , F02K3/08 , F02K7/16 , F02K7/18 , F02K9/72 , F23R3/18 , F23R3/14
CPC分类号： F23R3/286 , F02K3/10 , F23C7/006 , F23C9/006 , F23C2900/07001 , F23C2900/09002 , F23R3/14 , F23R3/20 , F23R3/22 , Y02T50/672 , Y02T50/675
摘要： An afterburner apparatus (10) that utilizes a novel swirl generator (30) for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator (30) converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator (30) effects a toroidal outer recirculation zone (640) and a central recirculation zone (610), which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length. Inherent with this swirl afterburner concept are design compactness, light weight, lower cost, smooth and efficient combustion, high thrust output, wide flammability limits, continuous operation at stoichiometric fuel/oxidizer mixture ratios, no combustion instabilities, and relatively low pressure losses.

56. 发明公开

EP1371906A2 Gas turbine engine combustor can with trapped vortex cavity 有权
标题翻译： Gasturbinenbrennkammer mit Hohlraumfüreingeschlossene Wirbel
公开(公告)号：EP1371906A2
公开(公告)日：2003-12-17
申请号：EP03252293.0
申请日：2003-04-10
申请人： GENERAL ELECTRIC COMPANY
发明人： Haynes, Joel Meier , Feitelberg, Alan S. , Burrus, David Louis , Joshi, Narendra Digamber
IPC分类号： F23R3/14 , F23R3/20 , F23R3/28 , F23R3/34
CPC分类号： F23R3/346 , F23C2900/07001 , F23D2900/14004 , F23R3/283 , F23R3/286 , F23R3/58 , F23R2900/00015
摘要： A gas turbine engine combustor can (23) downstream of a pre-mixer (28) has a pre-mixer flowpath (134) therein and circumferentially spaced apart swirling vanes (32) disposed across the pre-mixer flowpath (134). A primary fuel injector (68) is positioned for injecting fuel into the pre-mixer flowpath (134). A combustion chamber (26) is surrounded by an annular combustor liner (27) disposed in supply flow communication with the pre-mixer (28). An annular trapped dual vortex cavity (40) located at an upstream end (30) of the combustor liner (27) is defined between an annular aft wall (44), an annular forward wall (46), and a circular radially outer wall (48) formed therebetween. A cavity opening (42) at a radially inner end (39) of the cavity (40) is spaced apart from the radially outer wall (48). Air injection first holes (112) are disposed through the forward wall (46) and air injection second holes are disposed through the aft wall (44). Fuel injection holes (70) are disposed through at least one of the forward and aft walls (46, 44).
摘要翻译：在预混合器（28）下游的燃气涡轮发动机燃烧室（23）在其中具有预混合器流动路径（134），并且跨过预混合器流动路径（134）设置周向间隔开的涡流叶片（32）。主燃料喷射器（68）被定位成用于将燃料喷射到预混合器流路（134）中。燃烧室（26）被设置成与预混合器（28）供应流动连通的环形燃烧器衬套（27）包围。位于燃烧器衬套（27）的上游端（30）处的环形捕获双涡流腔（40）被限定在环形后壁（44），环形前壁（46）和圆形径向外壁 48）。在空腔（40）的径向内端（39）处的空腔开口（42）与径向外壁（48）间隔开。空气注入第一孔（112）穿过前壁（46）设置，空气注入第二孔穿过后壁（44）设置。燃料喷射孔（70）穿过前壁和后壁（46,44）中的至少一个设置。

57. 发明授权

EP0747636B1 Dry low emission combustor for gas turbine engines 失效
标题翻译：低排放的工业燃气涡轮机预混合
公开(公告)号：EP0747636B1
公开(公告)日：2003-03-05
申请号：EP96304162.9
申请日：1996-06-05
申请人： Rolls-Royce Corporation
发明人： Razdan, Mohan K. , McLeroy, Jacob T. , Smith, Duane A.
IPC分类号： F23R3/14
CPC分类号： F23R3/343 , F23C2900/07001 , F23D14/02 , F23D2206/10 , F23D2900/00008 , F23D2900/00015 , F23R3/14 , F23R3/286 , F23R2900/03041 , Y02T50/675

58. 发明授权

EP0956475B1 BRENNER FÜR FLUIDISCHE BRENNSTOFFE 失效
标题翻译：燃烧器在液体燃料
公开(公告)号：EP0956475B1
公开(公告)日：2001-09-26
申请号：EP97951835.4
申请日：1997-12-08
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： POESCHL, Gerwig , HOFFMANN, Stefan , GANZMANN, Ingo
IPC分类号： F23D14/62 , B01F5/06
CPC分类号： F23D17/00 , F23C2900/07001 , F23D14/02 , F23D2206/10 , F23D2900/00008 , F23R3/14
摘要： The invention concerns a burner (1), in particular for a gas turbine, combustion air (10) being swirled by means of a swirling element (4) and fuel (11) being admitted into the swirled combustion air (10). At the same time, the pressure loss caused by the swirling element (4) is low. As a result of the invention, NOx emission is low whilst the degree of efficiency is almost the same as with conventional burners.

59. 发明公开

EP0747636A2 Dry low emission combustor for gas turbine engines 失效
标题翻译： Vormischbrennkammer mit Niedrigem Ausstossfürindustrielle Gasturbinen
公开(公告)号：EP0747636A2
公开(公告)日：1996-12-11
申请号：EP96304162.9
申请日：1996-06-05
申请人： ALLISON ENGINE COMPANY, INC.
发明人： Razdan, Mohan K. , McLeroy, Jacob T. , Smith, Duane A.
IPC分类号： F23R3/14
CPC分类号： F23R3/343 , F23C2900/07001 , F23D14/02 , F23D2206/10 , F23D2900/00008 , F23D2900/00015 , F23R3/14 , F23R3/286 , F23R2900/03041 , Y02T50/675
摘要： The present invention relates generally to a low emission can-annular combustion system for an industrial gas turbine engine to satisfy increasingly stringent environmental requirements. The combustion system of the present invention employs a dual mode combustion technique to meet engine operability requirements and high power emission targets without the use of combustor diluent injection or post combustor exhaust treatment. A lean premix combustion mode is utilized to minimize primary zone combustion temperatures and limit the oxide of nitrogen production during high power engine operation. A pilot-starting auxiliary fueling system is utilized to augment the main premix fueling system. The lean premix combustion mode is enabled by a lean premix dome having a fixed axial swirler with radial fuel pathways connecting to a circumferential main fuel manifold for distributing the fuel more uniformly across the flow path. A converging portion in the lean premix dome accelerates the fluid flow to prevent flashback from the primary combustion zone.
摘要翻译：本发明一般涉及一种用于工业燃气涡轮发动机的低排放罐环式燃烧系统，以满足越来越严格的环境要求。本发明的燃烧系统采用双模燃烧技术，以满足发动机的可操作性要求和高功率发射目标，而不需要使用燃烧器稀释剂喷射或后燃烧器排气处理。利用稀薄预混合燃烧模式来最小化初级区域燃烧温度并限制高功率发动机运行期间氮气生产的氧化物。采用先导起动辅助加油系统来增加主要的预混燃料供给系统。贫预混合燃烧模式由具有固定轴向旋流器的稀薄预混合圆顶实现，其具有连接到周向主燃料歧管的径向燃料通路，用于在整个流动路径上更均匀地分配燃料。贫预混合圆顶中的会聚部分加速流体流动，以防止从初级燃烧区闪回。

60. 发明公开

EP0707698A1 APPARATUS AND METHOD FOR REDUCING NO x , CO AND HYDROCARBON EMISSIONS WHEN BURNING GASEOUS FUELS 失效
标题翻译：设备和Vera费用降低NOx，CO和碳氢化合物的排放量使用气体燃料
公开(公告)号：EP0707698A1
公开(公告)日：1996-04-24
申请号：EP94923414.0
申请日：1994-07-12
申请人： RADIAN CORPORATION
发明人： BORTZ, Steven, Jay
IPC分类号： F23C6 , F23C7 , F23D14 , F23D17 , F23D23
CPC分类号： F23C6/045 , F23C7/004 , F23C2201/20 , F23C2202/30 , F23C2900/07001 , F23D14/02 , F23D14/24 , F23D17/002 , F23D23/00
摘要： A forced draft burner apparatus for burning a gaseous fuel while producing low levels of NOx, CO and hydrocarbon emissions; comprising: an outer shell (8) including a windbox and a constricted tubular section (13) in fluid communication therewith; a generally cylindrical body (16) mounted in said shell coaxially with and spaced inwardly from said tubular section; an annular flow channel being defined between said body and the inner wall of said tubular section, said channel constituting a throat (14) for oxidant gases provided thereto from said windbox, and having a downstream outlet end for said gases; means for providing a flow of said oxidant gases to said throat from said windbox; a divergent quarl (28) being adjoined to said outlet end of said throat and defining a combustion zone for said burner; a plurality of curved axial swirl vanes (20) being mounted in said annular flow channel to impart swirl to said oxidant gases flowing downstream in said throat; fuel gas injection means being provided in said annular flow channel proximate to said swirl vanes for injecting said gas into the flow of oxidant gases at a point upstream of said outlet end.

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