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公开(公告)号：EP1493965A2
公开(公告)日：2005-01-05
申请号：EP04016648.0
申请日：1999-06-22
CPC分类号： B05B1/3489 , B05B7/10 , F23C7/002 , F23D11/107 , F23D11/383
摘要： A fuel injector including an injector tip 160 that has annular fuel flow passages and a stem 172 containing at least one fuel flow passage 174 extending from a stem fuel inlet 140 to a fuel delivery outlet 186. A first annular fuel flow cavity 142 provided in the stem near the fuel stem inlet 140, an inlet conduit 144 extends from the fuel stem inlet 140 to the annular cavity 142, the inlet conduit 144 being angled to provide a tangential flow direction to the fuel passing through the conduit 144 to the annular cavity 142. An outlet conduit 146 extends at an acute angle from the first annular cavity 142 to receive the fuel therefrom in a tangential direction. A first linear fuel conduit 148 is provided extending from the outlet conduit 146, extending axially of the stem and communicating with an injector inlet conduit 186 at the fuel delivery outlet. The injector inlet conduit 186 is angled to direct the fuel flow to a first annular passage 168 in the injector tip 160 in a tangential direction to provide a swirl to the fuel flow entering the annular passage 168 in the injector tip 160.
摘要翻译： 燃料喷射器包括具有环形燃料流动通道的喷射器尖端160和包含从杆燃料入口140延伸到燃料输送出口186的至少一个燃料流动通道174的杆172.设置在第一环形燃料流动空腔142 在燃料杆入口140附近的阀杆，入口导管144从燃料杆入口140延伸到环形空腔142，入口管道144成角度以向通过管道144的燃料提供切向流动方向到环形空腔142 出口导管146与第一环形空腔142成锐角地延伸，从而沿切线方向接收燃料。 第一线性燃料管道148被设置成从出口管道146延伸，在杆的轴向延伸并与燃料输送出口处的喷射器入口管道186连通。 注射器入口管道186成角度以将燃料流引向注射器末端160中的切向方向上的第一环形通道168，以向进入喷射器末端160中的环形通道168的燃料流提供涡流。
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公开(公告)号：EP1342950A2
公开(公告)日：2003-09-10
申请号：EP02025968.5
申请日：2002-11-21
IPC分类号： F23D11/10
CPC分类号： F23D11/107 , F23D2900/11101
摘要： Eine Zerstäuberdüse für einen Brenner, insbesondere für ein Fahrzeugheizgerät, umfasst ein eine Strömungsführungsoberfläche (28) bereitstellendes Strömungsführungselement (16), das in einem Endbereich (34) eine Zerstäuberlippe (36) aufweist, sowie eine Brennstoffzuführanordnung (52, 50) zum Zuführen von Brennstoff zu der Strömungsführungsoberfläche (28) in Abstand von der Zerstäuberlippe (36). Dabei ist vorgesehen, dass die Brennstoffzuführanordnung (52, 50) in dem Strömungsführungselement (16) eine Brennstoffabgabeeinsenkung (50) umfasst, in welche eine Brennstoffzuführkanalanordnung (52) in einem Einmündungsbereich einmündet.
摘要翻译： 喷嘴具有提供表面（28）的流动引导单元（16），并且在端部区域（34）中包括雾化唇缘。 进料装置在与唇缘隔开的位置处将燃料供给到引导表面中，并且包括燃料释放凹部（50），燃料供给通道装置（52）在连接区域处打开。
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公开(公告)号：EP1245900A3
公开(公告)日：2003-05-07
申请号：EP02252319.5
申请日：2002-03-28
IPC分类号： F23D11/10
CPC分类号： F23D11/107 , F05B2220/50 , F23D11/103 , F23D11/383
摘要： An airblast fuel injector assembly (10) for use in conjunction with a gas turbine is disclosed which includes an elongated tubular body having first and second concentric tubes (12, 14) separated from one another by a helical spacer wire (16) so as to define a fuel passage (18) therebetween. The injector assembly is situated in a fuel nozzle (20) such that fuel flow exiting the fuel passage is intersected by an air flow at a predetermined angle of incidence so as to atomize the fuel flow.
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公开(公告)号：EP1286111A2
公开(公告)日：2003-02-26
申请号：EP02016506.4
申请日：2002-07-23
申请人： Delavan Inc.
发明人： Mao, Chien-Pei , Thomson, Neal , Short, John Earl
CPC分类号： F23R3/28 , F23D11/107 , F23D2204/00 , F23D2206/10
摘要： A multiplex injector system comprising an injector head, a first fuel path located in the injector head, and a first set of injector tips located in the injector head and in fluid communication with the first fuel path. The first set of injector tips includes at least one first injector tip. The multiplex injector further includes a second fuel path located in the injector head and a second set of injector tips located in the injector head and in fluid communication with the second fuel path. The second set of injector tips includes at least one second injector tip. A flow of fuel in each of the first and second fuel paths can be selectively controlled to control the flow of fuel through the first and second sets of injector tips.
摘要翻译： 一种多重注射器系统，包括注射器头部，位于注射器头部中的第一燃料路径以及位于注射器头部并与第一燃料路径流体连通的第一组喷射器尖端。 第一组注射器尖端包括至少一个第一注射器尖端。 所述多路喷射器还包括位于所述喷射器头部中的第二燃料路径和位于所述喷射器头部并与所述第二燃料路径流体连通的第二组喷射器尖端。 第二组注射器尖端包括至少一个第二注射器尖端。 可以选择性地控制第一和第二燃料路径中的每一个中的燃料流，以控制通过第一组和第二组喷射器尖端的燃料流。
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公开(公告)号：EP0910775A4
公开(公告)日：2002-05-02
申请号：EP97932492
申请日：1997-07-08
申请人： CORNING INC
发明人： SKEATH PERRY R , SAYLOR JOHN R , ROVELSTAD AMY L
IPC分类号： B05B1/08 , B05B7/00 , B05B7/04 , B05B7/08 , B05B15/00 , B05B17/06 , B05D1/02 , C03B19/14 , F23D11/10 , B05B1/00
CPC分类号： B05B15/008 , B05B1/08 , B05B7/00 , B05B7/0433 , B05B7/0458 , B05B7/0884 , B05B17/0692 , C03B19/1423 , C03B2207/02 , C03B2207/06 , C03B2207/08 , C03B2207/34 , F23D11/107 , Y10T29/49432
摘要： Gas-assisted atomizing devices are provided that include liquid orifices, which release liquid, and gas orifices, which release gas to atomize the liquid into droplets. The atomizing devices are formed by at least a first layer and a second layer. The atomizing devices can include a gas supply network and a liquid supply network that supply gas and liquid to the gas and liquid orifices.
摘要翻译： 提供了燃气辅助雾化装置（40），其包括释放液体的液体孔口（64）和释放气体以将液体雾化成液滴的气体孔口（66）。 雾化装置（40）至少由第一层（42）和第二层（44）形成。 雾化装置（40）可以包括气体供应网络和供应气体和液体到气体和液体孔（分别为64和66）的液体供应网络。
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公开(公告)号：EP1199522A2
公开(公告)日：2002-04-24
申请号：EP01308860.4
申请日：2001-10-18
CPC分类号： F23R3/343 , F23D11/107 , F23D2900/11101
摘要： A duplex fuel injector has concentric arrangement of an inner air swirler 3, an inner fuel injection port 13, an intermediate axial air filmer 5, a second air swirler 6, an outer fuel injection port 23 and an outer air swirler 28. The intermediate air filmer 5 produces a curtain of air separating an outer air and fuel spray from an inner air and fuel spray. The outer spray is used in a pilot combustion zone P whereas the inner spray is used in a main combustion zone M.
摘要翻译： 双重燃料喷射器具有内部空气旋流器3，内部燃料喷射端口13，中间轴向空气滤波器5，第二空气旋流器6，外部燃料喷射端口23和外部空气旋流器28的同心布置。中间空气 压滤机5产生一个从内部空气和燃料喷雾分离外部空气和燃料喷雾的空气幕。 外喷雾剂在先导燃烧区域P中使用，而内部喷雾剂用于主燃烧区域M.
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公开(公告)号：EP0886744B1
公开(公告)日：2001-05-23
申请号：EP97916752.5
申请日：1997-03-13
CPC分类号： F23D11/107 , F23D11/36 , F23D2206/10 , F23D2211/00 , F23D2900/11101
摘要： A fuel injector (30) for a gas turbine engine of an aircraft has an inlet fitting (36), a fuel nozzle (40), and a housing stem (42) fluidly interconnecting and supporting the nozzle on the fitting. An internal heatshield assembly comprising an internal fuel conduit (140) extends in a bore (82) in the housing stem. An upper end of the fuel conduit has a rigid, fluid-tight connection (142) with a fuel inlet passage in the fitting, while the lower end of the fuel conduit has a rigid, fluid-tight connection (144) with the fuel nozzle. The bore closely surrounds the fuel conduit and a stagnant air gap is provided between the internal walls of the bore and the outer surface of the fuel conduit. The bore can be completely enclosed with a vacuum drawn in the bore, or can be open at its lower end to an air swirler in the fuel nozzle. The fuel conduit can have a single or dual internal fuel flow passages, and a coiled portion (150) within an enlarged cavity in the bore to allow for thermal expansion of the fuel conduit. The fuel injector can be easily assembled with the engine combustor using a flange (90) extending outwardly from the housing stem, and can be easily disassembled for inspection or replacement.
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公开(公告)号：EP0644375B1
公开(公告)日：2001-04-11
申请号：EP94109705.7
申请日：1994-06-23
CPC分类号： F02B77/04 , F02C7/22 , F02C7/232 , F05D2260/602 , F23D11/107 , F23D2209/30 , F23D2900/11101 , F23K5/18
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公开(公告)号：EP1080327A1
公开(公告)日：2001-03-07
申请号：EP99920473.8
申请日：1999-05-07
CPC分类号： F23C7/02 , F05B2250/25 , F23C7/002 , F23D11/107 , F23D23/00 , F23D2900/00014 , F23D2900/11101
摘要： A fuel injector (22) for a combustor and a gas turbine engine, comprises a nozzle tip assembly protruding through the combustor wall (28) into the chamber, the nozzle tip (26) including a first air passage (60) forming an annular array, a second air passage made up of an annular array of individual air passages (62) spaced radially from the first air passage (60), both communicating the pressurized air from outside the combustor wall (28) into the combustor. Fuel is injected through an annular fuel nozzle (54) between the first air passage (60) and the second air passages (62). Third air passages (64) are arranged in annular array in the injector tip (26) spaced radially outwardly from the second air passages (62) whereby the third passages (64) are arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture.
摘要翻译： 一种用于燃烧器和燃气涡轮发动机的燃料喷射器（22），包括突出穿过燃烧器壁（28）进入腔室的喷嘴尖端组件，喷嘴尖端（26）包括第一空气通道（60），该第一空气通道形成环形阵列 第二空气通道由环形阵列的独立空气通道（62）构成，所述空气通道径向与第一空气通道（60）隔开，二者均将来自燃烧器壁（28）外部的加压空气连通到燃烧器中。 燃料通过第一空气通道（60）和第二空气通道（62）之间的环形燃料喷嘴（54）喷射。 第三空气通道（64）以环形阵列布置在喷射器尖端（26）中与第二空气通道（62）径向向外间隔开，由此设置第三通道（64）以使雾化燃料和空气的混合物成形并且添加 补充空气混合物。
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公开(公告)号：EP1069377A3
公开(公告)日：2001-03-07
申请号：EP00122123.3
申请日：1994-06-23
CPC分类号： F02B77/04 , F02C7/22 , F02C7/232 , F05D2260/602 , F23D11/107 , F23D2209/30 , F23D2900/11101 , F23K5/18
摘要： A self-purging fuel injector for a combustor of a gas turbine engine is disclosed wherein the fuel injector comprises an injector body (10) having one or more, preferably two, air discharge orifices (122c) for discharging air to the combustor and first (130) and second (150) fuel passage means having respective first (132c) and second (162c) fuel discharge orifices for discharging fuel to the combustor. The first and second fuel passages are in communication upstream of the fuel discharge orifices. If the supply of fuel to the first and second fuel discharge orifices is interrupted, a pneumatic pressure is applied at the first fuel discharge orifice and a different pneumatic pressure is applied at the second fuel discharge orifice such that the fuel residing in the fuel passages between the first and second fuel discharge orifices is subjected to a pressure differential effective to purge the resident fuel into the combustor.
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