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公开(公告)号：US09296038B2
公开(公告)日：2016-03-29
申请号：US13560192
申请日：2012-07-27
申请人： Alexander Ilich Krichever , Mario Eugene Abreu , Norm Turoff , John Frederick Lockyer , Christopher Zdzislaw Twardochleb , David Marc Stansel
发明人： Alexander Ilich Krichever , Mario Eugene Abreu , Norm Turoff , John Frederick Lockyer , Christopher Zdzislaw Twardochleb , David Marc Stansel
CPC分类号： B21K25/00 , F02C7/22 , F23R3/14 , F23R3/283 , F23R3/286 , F23R2900/00005 , F23R2900/00017 , Y10T29/49231
摘要： A liquid fuel injection spoke for a gas turbine engine. The liquid fuel injection spoke may include an inlet end and an outlet end. The liquid fuel injection spoke may further include a head located at the inlet end and a stem extending along a longitudinal axis from the head to the outlet end. The stem may define a fluid passageway therein. The head may include a cavity with an inner wall. The inner wall may include an annular protrusion.
摘要翻译： 液体燃料喷射器用于燃气涡轮发动机。 液体燃料喷射轮辐可以包括入口端和出口端。 液体燃料喷射轮辐还可以包括位于入口端的头部和沿着从头部到出口端的纵向轴线延伸的杆。 杆可以在其中限定流体通道。 头部可以包括具有内壁的空腔。 内壁可以包括环形突起。
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82.发明授权System for reducing combustion dynamics by varying fuel flow axial distances 有权通过改变燃料流轴向距离来减少燃烧动力学的系统公开(公告)号：US09255711B2
公开(公告)日：2016-02-09
申请号：US14048252
申请日：2013-10-08
CPC分类号： F23R3/20 , F02C7/22 , F02C7/228 , F02C7/24 , F23D14/02 , F23R3/18 , F23R3/283 , F23R3/286 , F23R3/34 , F23R3/42 , F23R3/46 , F23R2900/00014
摘要： First and second combustors are provided, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each fuel nozzle includes an axially extending center body, a shroud that circumferentially surrounds at least a portion of the center body, and vanes that extend radially between the center body and the shroud. A first fuel port through at least one of the vanes is located at a first axial distance from the combustion chamber, a second fuel port through the center body is located at a second axial distance from the combustion chamber, and the vanes are located at a third axial distance from the combustion chamber. The system varies one or more of the first, second, and third axial distances from combustor-to-combustor to produce a combustion instability frequency in the first combustor that is different from the combustion instability frequency in the second combustor.
摘要翻译： 提供第一和第二燃烧器，并且每个燃烧器包括燃料喷嘴和燃料喷嘴下游的燃烧室。 每个燃料喷嘴包括轴向延伸的中心体，周向围绕中心体的至少一部分的护罩和在中心体和护罩之间径向延伸的叶片。 通过至少一个叶片的第一燃料端口位于离燃烧室的第一轴向距离处，通过中心体的第二燃料端口位于离燃烧室的第二轴向距离处，并且叶片位于 距燃烧室的第三轴向距离。 系统改变从燃烧室到燃烧器的第一，第二和第三轴向距离中的一个或多个，以在第一燃烧器中产生与第二燃烧器中的燃烧不稳定频率不同的燃烧不稳定频率。
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公开(公告)号：US09151502B2
公开(公告)日：2015-10-06
申请号：US14048272
申请日：2013-10-08
摘要： A system and method for reducing combustion dynamics includes first and second combustors, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each fuel nozzle includes an axially extending center body, a shroud that circumferentially surrounds at least a portion of the axially extending center body, a plurality of vanes that extend radially between the center body and the shroud, a first fuel port through at least one of the plurality of vanes at a first axial distance from the combustion chamber, the plurality of vanes being located at a second axial distance from the combustion chamber. A second fuel port is provided through the center body at a third axial distance from the combustion chamber. The system further includes structure for producing a combustion instability frequency in the first combustor that is different from the combustion instability frequency in the second combustor.
摘要翻译： 用于减少燃烧动力学的系统和方法包括第一和第二燃烧器，并且每个燃烧器包括燃料喷嘴和燃料喷嘴下游的燃烧室。 每个燃料喷嘴包括轴向延伸的中心体，周向围绕轴向延伸的中心体的至少一部分的护罩，在中心体和护罩之间径向延伸的多个叶片，第一燃料口通过至少一个 所述多个叶片处于距燃烧室第一轴向距离处，所述多个叶片位于距燃烧室第二轴向距离处。 第二燃料口通过中心体设置在离燃烧室第三轴向距离处。 该系统还包括用于在第一燃烧器中产生与第二燃烧器中的燃烧不稳定频率不同的燃烧不稳定频率的结构。
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公开(公告)号：US09097184B2
公开(公告)日：2015-08-04
申请号：US12981451
申请日：2010-12-29
摘要： In certain exemplary embodiments, a system includes an annular duct having an inner annular wall and an outer annular wall. The system also includes a plurality of injector vanes configured to mix air and fuel to produce an air-fuel mixture, and configured to inject the air-fuel mixture into a central chamber between the inner and outer annular walls.
摘要翻译： 在某些示例性实施例中，系统包括具有内环形壁和外环形壁的环形管道。 该系统还包括多个喷射器叶片，其构造成混合空气和燃料以产生空气 - 燃料混合物，并且构造成将空气 - 燃料混合物喷射到内部和外部环形壁之间的中心室中。
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公开(公告)号：US09080772B2
公开(公告)日：2015-07-14
申请号：US13917053
申请日：2013-06-13
申请人： Delavan Inc
CPC分类号： F23R3/20 , F23C2900/03005 , F23D2207/00 , F23D2900/11401 , F23N2027/02 , F23R3/14 , F23R3/28
摘要： An ignition system includes a housing defining an interior and an exhaust outlet. The housing is configured and adapted to be mounted to a combustor to issue flame from the exhaust outlet into the combustor for ignition and flame stabilization within the combustor. A fuel injector is mounted to the housing with an outlet of the fuel injector directed to issue a spray of fuel into the interior of the housing. An igniter is mounted to the housing with an ignition point of the igniter proximate the outlet of the fuel injector for ignition within the interior of the housing.
摘要翻译： 点火系统包括限定内部和排气出口的壳体。 壳体被构造和适于安装到燃烧室，以将火焰从排气出口发射到燃烧器中，用于燃烧器内的点燃和火焰稳定。 燃料喷射器安装到壳体上，燃料喷射器的出口被引导以将燃料喷射发射到壳体的内部。 点火器被安装到壳体上，点火器的点火点靠近燃料喷射器的出口，用于在壳体的内部点燃。
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公开(公告)号：US08991189B2
公开(公告)日：2015-03-31
申请号：US12914776
申请日：2010-10-28
摘要： A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.
摘要翻译： 燃气涡轮发动机增压器包括至少一个基于流体的增压器起动器，其限定与空气源和燃料源流动连通的室。 该腔室包括与排气流路流动连通的多个喷射口。 所述至少一个基于流体的增压器引发器没有任何排气流路突起，从而使在操作的干燥工作阶段期间的任何压力下降和推力损失最小化。 燃料源可操作以将燃料喷射到室中，使得燃料流的至少一部分在多个喷射口处被点燃以产生多个富燃料的热喷射流体径向地进入排气流路。
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公开(公告)号：US20140366551A1
公开(公告)日：2014-12-18
申请号：US13917053
申请日：2013-06-13
申请人： Delavan Inc.
CPC分类号： F23R3/20 , F23C2900/03005 , F23D2207/00 , F23D2900/11401 , F23N2027/02 , F23R3/14 , F23R3/28
摘要： An ignition system includes a housing defining an interior and an exhaust outlet. The housing is configured and adapted to be mounted to a combustor to issue flame from the exhaust outlet into the combustor for ignition and flame stabilization within the combustor. A fuel injector is mounted to the housing with an outlet of the fuel injector directed to issue a spray of fuel into the interior of the housing. An igniter is mounted to the housing with an ignition point of the igniter proximate the outlet of the fuel injector for ignition within the interior of the housing.
摘要翻译： 点火系统包括限定内部和排气出口的壳体。 壳体被构造和适于安装到燃烧室，以将火焰从排气出口发射到燃烧器中，用于燃烧器内的点火和火焰稳定。 燃料喷射器安装到壳体上，燃料喷射器的出口被引导以将燃料喷射发射到壳体的内部。 点火器被安装到壳体上，点火器的点火点靠近燃料喷射器的出口，用于在壳体的内部点燃。
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公开(公告)号：US08893504B2
公开(公告)日：2014-11-25
申请号：US13225996
申请日：2011-09-06
摘要： An igniter arranged to ignite combustion in a primary flow including a fuel and air mixture, the igniter including one or more geometric features arranged to: induce a shockwave flow structure at least partially disposed in the primary flow; and ignite the fuel and air mixture by virtue of the shockwave flow structure. The present disclosure also relates to a method of igniting combustion in a primary flow including a fuel and air mixture, the method including: providing one or more geometric features arranged to induce a shockwave flow structure; inducing the shockwave flow structure at least partially in the primary flow; and igniting the fuel and air mixture by virtue of the shockwave flow structure.
摘要翻译： 点火器，其被布置成在包括燃料和空气混合物的一次流中点燃燃烧，所述点火器包括一个或多个几何特征，其布置成：诱导至少部分地设置在所述主流中的冲击波流结构; 并通过冲击波流结构点燃燃料和空气混合物。 本公开还涉及一种点燃包括燃料和空气混合物的一次流中的燃烧的方法，所述方法包括：提供布置成引起冲击波流结构的一个或多个几何特征; 至少部分地在初级流中引起冲击波流结构; 并通过冲击波流结构点燃燃料和空气混合物。
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公开(公告)号：US20140099591A1
公开(公告)日：2014-04-10
申请号：US14048780
申请日：2013-10-08
申请人： Nooter/Eriksen, Inc.
发明人： Vladimir S. Polonsky
CPC分类号： F01K23/103 , F02C6/003 , F02C7/228 , F22B1/1815 , F23D14/10 , F23D14/70 , F23D14/76 , F23D14/78 , F23D2900/21003 , F23R3/20 , Y02E20/16
摘要： A duct burner assembly for a HRSG having a casing that defines a combustion chamber with a liner for communicating an exhaust gas. A firing runner attaches to the liner and extends through the combustion chamber. The firing runner defines a plurality of orifices for emitting combustible gas and sustaining a flame. A flame stabilizer attaches to the firing runner and is configured to at least partially shield the plurality of orifices from the exhaust gas. A guide plate attaches to the firing runner and is configured to define a slot between the liner and the guide plate. The guide plate has an upstream end and a downstream end wherein the downstream end is closer to the lining than the upstream end to reduce turbulent flow of the exhaust gas through the slot and cool the liner.
摘要翻译： 一种用于HRSG的管道燃烧器组件，其具有限定具有用于连通废气的衬套的燃烧室的壳体。 发射流道附着在衬套上并延伸穿过燃烧室。 射出流道限定了用于发射可燃气体并维持火焰的多个孔。 火焰稳定器附接到发射流道，并且构造成至少部分地将多个孔与废气屏蔽。 引导板附接到击发流道并且构造成在衬垫和引导板之间限定狭槽。 引导板具有上游端和下游端，其中下游端比上游端更靠近衬里，以减少废气通过狭槽的湍流并冷却衬套。
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90.发明申请TEMPERATURE MIXING ENHANCEMENT WITH LOCALLY CO-SWIRLING QUENCH JET PATTERN FOR GAS TURBINE ENGINE COMBUSTOR 有权燃气涡轮发动机燃烧器的本地混合燃油喷射模式的温度混合增强公开(公告)号：US20130025293A1
公开(公告)日：2013-01-31
申请号：US13194182
申请日：2011-07-29
申请人： Won-Wook Kim , James B. Hoke , Timothy S. Snyder
发明人： Won-Wook Kim , James B. Hoke , Timothy S. Snyder
CPC分类号： F23R3/06 , F23R3/08 , Y02T50/675
摘要： A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.
摘要翻译： 用于涡轮发动机的燃烧器包括围绕具有第一排第一燃烧空气孔的轴限定的第一衬套，沿着多个燃料喷射器零间距线中的每一个限定第一燃烧空气孔中的一个。 围绕所述轴限定第二排第二燃烧空气孔的第二衬套，每个所述第二燃烧空气孔相对于所述多个燃料喷射器零间距线中的每一个周向地偏移。
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