公开(公告)号：WO01029484A1

公开(公告)日：2001-04-26

申请号：PCT/JP1999/005779

申请日：1999-10-20

IPC: F23R3/12 ,  F23R3/28 ,  F23R3/34 ,  F23R3/30

CPC classification number: F23R3/34 ,  F23R3/12 ,  F23R3/286

Abstract: The purpose is to improve the mixture ratio of a pre-mixer by a simple arrangement to form a more uniform premixed gases so as to materialize low NOx combustion. Two fuel nozzles disposed circumferentially of a pre-mixer are combined with a single air intake window to make a set, which set is used to produce swirls in a pair, thereby expediting mixing. Further, the inlet window is shaped such that its circumferential width is changed axially of the combustor, thereby changing the strength and size of the swirls to achieve the greatest effect. By reducing both the pre-mixer inlet windows and the partition walls in number, the manufacturing cost can be reduced, and by strengthening and optimizing the swirls, a combustor with superior low NOx performance can be provided, while it is possible to reduce the length of the pre-mixer necessary to obtain the same mixture ration, leading to a cost reduction.

Abstract translation: 目的是通过简单的布置提高预混合器的混合比，以形成更均匀的预混合气体，以实现低NOx燃烧。 将预混合器周向设置的两个燃料喷嘴与单个进气窗口组合以制成一组，该组用于产生一对涡流，从而加速混合。 此外，入口窗口的形状使得其周向宽度沿着燃烧器的轴向改变，从而改变了涡流的强度和尺寸以达到最大的效果。 通过减少预混合器入口窗口和隔壁，可以降低制造成本，并且通过强化和优化涡流，可以提供具有优异的低NOx性能的燃烧器，同时可以减小长度 的预混合器，以获得相同的混合比例，导致成本降低。

公开(公告)号：WO99035441A1

公开(公告)日：1999-07-15

申请号：PCT/US1998/027715

申请日：1998-12-30

IPC: F23C99/00 ,  F23D23/00 ,  F23R3/30 ,  F23R3/34

CPC classification number: F23R3/34 ,  F23D23/00 ,  F23D2206/10

Abstract: A gas turbine combustor (110) is provided having a nozzle housing (6) adjacent to a main combustion zone (9), a diffusion fuel pilot nozzle (1), at least one main nozzle (2) extending through the nozzle housing (6) and attached thereto, and a parabolic pilot cone (120) projecting from the vicinity of an injection port (4) of the pilot nozzle (1). The parabolic pilot cone (120) has a diverged end (122) adjacent to the main combustion zone (9), and a parabolic profile (121) forming a pilot flame zone (123) adjacent to the injection port (4) and the diverged end (122). The increased volume of the pilot flame zone (123) provide a more stable pilot flame. The more stable pilot flame and leaner fuel/air mixture (103) reduce NOx/CO emissions. A second gas turbine combustor (130) is provided having a fluted pilot cone (220). The fluted pilot cone (220) has an undulated diverged end (222) adjacent to the main combustion zone (9) forming a pilot flame zone (223) adjacent to the injection port (4) and the undulated diverged end (222). The undulated diverged end (222) of the fluted pilot cone (220) creates turbulence in the main combustion zone (9). The turbulence results in greater interaction between main and pilot combustion zones, consequently reducing NOx/CO emissions.

Abstract translation: 一种燃气轮机燃烧器（110），其具有邻近主燃烧区（9）的喷嘴壳体（6），扩散燃料先导喷嘴（1），延伸穿过喷嘴壳体（6）的至少一个主喷嘴 ）和附接到其上的抛物面导向锥（120），其从所述先导喷嘴（1）的喷射口（4）附近突出。 抛物面导向锥（120）具有与主燃烧区（9）相邻的分叉端（122），和形成与喷射口（4）相邻的引燃火焰区（123）的抛物面轮廓（121） 结束（122）。 引导火焰区域（123）的增加的体积提供更稳定的引燃火焰。 更稳定的先导火焰和较稀燃的燃料/空气混合物（103）可以减少NOx / CO排放。 第二燃气轮机燃烧器（130）设置有带槽的先导锥（220）。 带槽的先导锥体（220）具有与主燃烧区域（9）相邻的起伏的发散端（222），形成邻近注入口（4）和波纹发散端（222）的引燃火焰区（223）。 带槽的先导锥体（220）的起伏的发散端（222）在主燃烧区（9）中产生湍流。 湍流导致主燃烧区和先导燃烧区之间的更大的相互作用，从而减少NOx / CO排放。

公开(公告)号：WO99019674A1

公开(公告)日：1999-04-22

申请号：PCT/US1998/021335

申请日：1998-10-09

IPC: F02C7/22 ,  F23C6/04 ,  F23R3/28 ,  F23R3/34

CPC classification number: F23R3/286 ,  F02C7/222 ,  F23C6/047 ,  F23R3/34

Abstract: A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages for pre-mixing primary fuel and air to be supplied to the primary combustion zone. Each of the pre-mixing passages has a circumferential array of swirl vanes. A plurality of primary fuel tube assemblies extend through both pre-mixing passages, with each primary fuel tube assembly located between a pair of swirl vanes. Each primary fuel tube assembly is comprised of two tubular members. The first member supplies fuel to the first pre-mixing passage, while the second member, which extends through the first member, supplies fuel to the second pre-mixing passage. An annular fuel manifold is divided into first and second chambers by a circumferentially extending baffle. The proximal end of the first member is attached to the manifold itself while the proximal end of the second member is attached to the baffle. The distal end of the first member is attached directly to the second member at around its mid-point. The inlets of the first and second members are in flow communication with the first and second manifold chambers, respectively. Control valves separately regulate the flow of fuel to the two chambers and, therefore, to the two members of the fuel tube assemblies, thereby allowing the flow of fuel to the first and second pre-mixing passages to be separately controlled.

Abstract translation: 一种用于燃气轮机的燃烧器，其具有位于中心的燃料喷嘴和内部，中部和外部同心圆柱形衬套，内衬层封装有主燃烧区。 燃烧器具有形成两个通道的空气入口，用于预混合一次燃料和要供应到主燃烧区的空气。 每个预混合通道具有旋转叶片的圆周阵列。 多个主燃料管组件延伸穿过两个预混合通道，每个主燃料管组件位于一对旋流叶片之间。 每个主燃料管组件由两个管状构件组成。 第一构件向第一预混合通道供应燃料，而延伸穿过第一构件的第二构件将燃料供应到第二预混合通道。 环形燃料歧管通过周向延伸的挡板分成第一和第二腔室。 第一构件的近端附接到歧管本身，而第二构件的近端附接到挡板。 第一构件的远端在其中点附近直接附接到第二构件。 第一和第二构件的入口分别与第一和第二歧管腔流动连通。 控制阀单独地调节到两个室的燃料流，并因此分配调节到燃料管组件的两个构件，从而允许单独控制到第一和第二预混合通道的燃料流。

公开(公告)号：WO1985000199A1

公开(公告)日：1985-01-17

申请号：PCT/US1984000935

申请日：1984-06-20

Applicant: PAUL, Marius, A.

IPC: F02C07/20

CPC classification number: F23R3/38 ,  F01D5/081 ,  F02C7/16 ,  F02K7/16 ,  F23R3/34 ,  Y02T50/676

Abstract: The process of increasing the efficiency and output of a gas-turbine having blades in a combustion chamber (7) which includes cooling the gas-turbine blades (10) with a liquid-fuel and mixing the fuel used for cooling with air in the combustion chamber (7) and burning the mixture and driving the turbine (15) by the exhaust from the combustion chamber (7). This allows the fuel and air to be in stoichiometric mixture. Preferably the fuel is a liquid-gas such as hydrogen. The turbine (15) may be cooled by injecting liquid-fuel onto its disk (11) to provide a film coating which is centrifuged around the blades whereby the liquid will cool both the interior and exterior of the blades and the absorbed heat is introduced into the combustion chamber (7). The combustion chamber (7) includes a plurality of air inlets (8). The turbine (15) drives a compressor, and the compressor and the air inlet may be cooled with the liquid-fuel, which may be cryogenically cooled. An improved jet engine which is convertible from a turbo to a ram-jet is provided.

Abstract translation: 在燃烧室（7）中增加具有叶片的燃气轮机的效率和输出的过程，其包括用液体燃料冷却燃气涡轮叶片（10）并将用于冷却的燃料与燃烧中的空气混合 燃烧混合物并通过来自燃烧室（7）的排气驱动涡轮机（15）。 这允许燃料和空气在化学计量混合物中。 优选地，燃料是诸如氢的液体气体。 涡轮机（15）可以通过将液体燃料喷射到其盘（11）上来冷却，以提供薄膜涂层，其在叶片周围离心，由此液体将冷却叶片的内部和外部，吸收的热量被引入 燃烧室（7）。 燃烧室（7）包括多个空气入口（8）。 涡轮（15）驱动压缩机，并且压缩机和空气入口可以用可能被低温冷却的液体燃料冷却。 提供了一种从涡轮转换成冲压射流的改进的喷气发动机。

公开(公告)号：WO2019135918A1

公开(公告)日：2019-07-11

申请号：PCT/US2018/066571

申请日：2018-12-19

Applicant: WOODWARD, INC.

Inventor： KLECKLER, Joel W. ,  DAM, Bidhan

IPC: F23R3/34 ,  F23R3/28 ,  F02C7/22 ,  F02C7/26

CPC classification number: F02C7/232 ,  F02C3/06 ,  F02C7/22 ,  F02C7/222 ,  F02C7/228 ,  F02C7/26 ,  F02C9/263 ,  F02C9/36 ,  F23R3/28 ,  F23R3/34

Abstract: A gas turbine combustor assembly (200) includes: a primary combustion chamber (214) in fluid communication with a primary fuel outlet of a primary fuel injector (204); a torch igniter (212) coupled to the primary combustion chamber, the torch igniter including an auxiliary combustion chamber (220) and an auxiliary fuel injector (222) having an auxiliary fuel outlet in fluid communication with the auxiliary combustion chamber; and a fuel circuit including a first supply flowpath (246) between a fuel inlet and the primary fuel injector, a second supply flowpath (250) between the fuel inlet and the auxiliary fuel injector, and a bypass flowpath (252) between the auxiliary fuel injector and the primary fuel injector.

公开(公告)号：WO2017120035A1

公开(公告)日：2017-07-13

申请号：PCT/US2016/067794

申请日：2016-12-20

Applicant: SOLAR TURBINES INCORPORATED

Inventor： SPIVEY, Sean Kelly ,  CRAMB, Donald James ,  PIPER, James Scott ,  RAMOTOWSKI, Michael John

IPC: F23R3/28 ,  F23R3/42 ,  F02C7/22

CPC classification number: F02C7/222 ,  F05D2220/32 ,  F23R3/28 ,  F23R3/286 ,  F23R3/34 ,  F23R3/36 ,  F23R2900/00004 ,  F23R2900/03343

Abstract: A fuel injector (600) for a gas turbine engine (100) is disclosed. The fuel injector (600) includes a flange assembly (610) with a distribution block (612), three main gas tubes, and an injector head (630). The distribution block (612) evenly distributes a main gas fuel to the three main gas tubes. The injector head (630) includes an injector body (640) with a primary gas gallery (643) including an annular shape. The three main gas tubes are connected in a parallel configuration between the distribution block (612) and the primary gas gallery (643). The three main gas tubes are all in flow communication with the primary gas gallery (643) and provide the main gas fuel from the same main gas fuel source.

Abstract translation: 公开了用于燃气涡轮发动机（100）的燃料喷射器（600）。 燃料喷射器（600）包括具有分配块（612）的法兰组件（610），三个主燃气管以及喷射器头（630）。 分配块（612）将主气体燃料均匀地分配到三个主气管。 注射头（630）包括具有包括环形形状的主气体通道（643）的注射器主体（640）。 三个主气管在分配块（612）和主气体通道（643）之间以平行配置连接。 三个主要气体管与主要气体通道（643）全部流动连通，并提供来自同一主要气体燃料源的主要气体燃料。

公开(公告)号：WO2017002074A1

公开(公告)日：2017-01-05

申请号：PCT/IB2016/053942

申请日：2016-06-30

Applicant: ANSALDO ENERGIA IP UK LIMITED

Inventor： MCNALLY, Joshua R. ,  PENNEL, Douglas ,  GAUTHIER, Donald ,  MATYS, Pawel ,  PASKIN, Marc ,  RUCK, Thomas R. ,  STUTTAFORD, Peter John ,  SAM, Bernard Tam-Yen ,  JORGENSEN, Stephen W.

IPC: F23R3/16 ,  F23R3/28 ,  F23R3/34 ,  F23R3/54 ,  F23R3/14

CPC classification number: F23R3/16 ,  F23R3/14 ,  F23R3/286 ,  F23R3/34 ,  F23R3/343 ,  F23R3/54

Abstract: Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.

Abstract translation: 提供燃气轮机燃烧系统和燃料盒组件。 示例性燃烧系统可包括包括一个或多个部件的燃烧器，例如圆柱形燃烧衬套，流动套筒，主混合器，径向流入旋流器，燃烧器圆顶和燃料盒组件。 示例性的燃料盒组件可以包括第一和第二燃料歧管，其连接到通过燃料盒组件内的多个燃料通道或相关燃烧器内的其它位置供应诸如液体燃料的燃料的各个燃料回路。 燃料盒组件还可以包括位于燃料盒组件的顶板处的多个燃料喷射器尖端，燃料可以通过燃料喷射器提供给相关联的燃烧器。

公开(公告)号：WO2016032436A1

公开(公告)日：2016-03-03

申请号：PCT/US2014/052626

申请日：2014-08-26

Applicant: SIEMENS ENERGY, INC.

Inventor： LASTER, Walter Ray ,  MARTIN, Scott M. ,  PORTILLO BILBAO, Juan Enrique ,  HARDES, Jacob William ,  FOX, Timothy A.

IPC: F23R3/28 ,  F23R3/34 ,  F23R3/04

CPC classification number: F23R3/283 ,  F02C3/30 ,  F23R3/045 ,  F23R3/34

Abstract: A cooling system (10) for a fuel system in a turbine engine (14) that is usable to cool a fuel nozzle (16) is disclosed. The cooling system (10) may include one or more cooling system housings (18) positioned around the fuel nozzle (16), such that the cooling system housing (18) forms a cooling chamber (20) defined at least partially by an inner surface (22) of the cooling system housing (18) and an outer surface (24) of the fuel nozzle (16). The fuel nozzle (16) may extend into a combustor chamber (26) formed at least in part by a combustor housing (32). The fuel nozzle (16) may include one or more fuel exhaust orifices (28) with an opening (30) in an outer surface (24) of the fuel nozzle (16) and configured to exhaust fluids unrestricted by the housing (18) forming the cooling system cooling chamber (20). The cooling system (10) may provide cooling fluids to cool the fuel nozzle (16) within the cooling system cooling chamber (20) regardless of whether the fuel nozzle (16) is in use.

Abstract translation: 公开了一种用于涡轮发动机（14）中用于冷却燃料喷嘴（16）的燃料系统的冷却系统（10）。 冷却系统（10）可以包括围绕燃料喷嘴（16）定位的一个或多个冷却系统壳体（18），使得冷却系统壳体（18）形成至少部分地被内表面限定的冷却室（20） （18）的外表面（24）和所述燃料喷嘴（16）的外表面（24）之间。 燃料喷嘴（16）可以延伸到至少部分由燃烧器壳体（32）形成的燃烧室（26）中。 燃料喷嘴（16）可以包括在燃料喷嘴（16）的外表面（24）中具有开口（30）的一个或多个燃料排出口（28），并且构造成排出不受壳体（18）形成的流体 冷却系统冷却室（20）。 无论燃料喷嘴（16）是否在使用中，冷却系统（10）可以提供冷却流体以冷却冷却系统冷却室（20）内的燃料喷嘴（16）。

公开(公告)号：WO2016021390A1

公开(公告)日：2016-02-11

申请号：PCT/JP2015/070502

申请日：2015-07-17

Applicant: 三菱日立パワーシステムズ株式会社

Inventor： 中川　丈太郎

IPC: F02C9/28 ,  F02C7/228 ,  F02C9/00 ,  F02C9/34 ,  F23R3/34

CPC classification number: F02C9/34 ,  F02C7/228 ,  F02C9/26 ,  F02C9/28 ,  F02C9/32 ,  F05D2270/303 ,  F05D2270/306 ,  F23R3/34

Abstract: 　ガスタービンは、複数の燃料系統と、複数の燃料系統からの燃料を圧縮空気中で燃焼させて燃焼ガスを生成する燃焼器と、燃焼ガスにより駆動するタービンと、を備える。複数の燃料系統を流れる燃料の流量比を算出する流量比算出装置（１４０）は、燃焼器での燃焼状態を表すことができる第一パラメータ（ＣＬＣＳＯ）及び第二パラメータ（％Ｌｏａｄ）の値を受け付け、二つのパラメータと流量比との予め定められた関係を用いて、受け付けた二つのパラメータの値に対する流量比を算出する算出器（１４０ｐ，１４０ｔ）を備える。

Abstract translation: 一种配备有多条燃料管线的燃气轮机; 燃烧器，其通过在压缩空气中燃烧来自多个燃料管路的燃料而产生燃烧气体; 和由燃烧气体驱动的涡轮。 计算在多条燃料管线中流动的燃料的流量比的流量体积比计算装置（140）装备有接收第一参数（CLCSO）和第二参数值的计算器（140p，140t） （％负载），可以表示燃烧器的燃烧状态，并且使用两个参数之间的预定关系和流量比来计算相对于两个参数的接收值的流量比。

公开(公告)号：WO2015182154A1

公开(公告)日：2015-12-03

申请号：PCT/JP2015/002714

申请日：2015-05-28

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA ,  B&B AGEMA GMBH

Inventor： HORIKAWA, Atsushi ,  KAZARI, Masahide ,  OKADA, Kunio ,  KITAJIMA, Junichi ,  FUNKE, Harald ,  KUSTERER, Karsten ,  AYED, Anis Haj

IPC: F23R3/18 ,  F23R3/34 ,  F23D14/70

CPC classification number: F23R3/286 ,  F02C7/222 ,  F05D2220/32 ,  F05D2240/35 ,  F23C2900/9901 ,  F23D14/70 ,  F23R3/002 ,  F23R3/10 ,  F23R3/16 ,  F23R3/18 ,  F23R3/34 ,  Y02T50/678

Abstract: A combustor including a combustion liner (13) having a combustion chamber (11) formed therein; and a fuel injector (15) mounted to a top portion of the combustion liner, and including a fuel injection member (34) having a plurality of fuel injection annular portions (33) and an air guide member (36) including a plurality of combustion air annular portions (35) that guide air for combustion. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel (F) and air (A) into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes (39) that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide grooves (41) that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

Abstract translation: 一种燃烧器，包括其中形成有燃烧室（11）的燃烧衬套（13） 和燃料喷射器（15），其安装在燃烧衬套的顶部，并且包括具有多个燃料喷射环形部分（33）的燃料喷射构件（34）和包括多个燃烧的空气引导构件（36） 引导空气进行燃烧的空气环形部分（35）。 燃料喷射环形部分和燃烧空气环形部分同心地和交替地布置。 燃料喷射器将燃料（F）和空气（A）喷射到燃烧室中。 每个燃料喷射环形部分包括沿其径向开口的多个燃料喷射孔（39），并且每个燃烧空气环形部分包括多个沿轴向开口的空气引导槽（41） 并且将空气引导到从燃料喷射孔喷射的燃料。