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公开(公告)号：US20130115566A1
公开(公告)日：2013-05-09
申请号：US13289567
申请日：2011-11-04
IPC分类号： F23C6/04
CPC分类号： F23R3/002 , F23R3/54 , F23R2900/03044
摘要： A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.
摘要翻译： 提供了具有尾气喷射的燃烧器。 燃烧器包括燃料喷嘴，第一和第二容器形成并设置成限定第一流体朝着燃料喷嘴沿第一和第二相反方向流动的流动路径，设置在流路中的叶片和喷射器 由设置在叶片上游的流动路径中的障碍物形成的流体进入尾流。
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公开(公告)号：US20110265482A1
公开(公告)日：2011-11-03
申请号：US12768758
申请日：2010-04-28
CPC分类号： F23R3/286
摘要： An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define a ring-like, annular path for the flow of fuel between the two hollow cylinders in each mixing tube, a plurality of air injection slots formed in the concentric hollow cylinders defining corresponding air flow paths from the outside into the interior of each mixing tube, and one or more fuel injection ports formed in selected ones of the plurality of air injection slots that allow for the flow of fuel from the annular path formed by the hollow cylinders into the air flow path, resulting in significantly better mixing and improved thermodynamic behavior of the fuel and air mixture downstream of the nozzle and upstream of the combustor.
摘要翻译： 一种改进的混合管设计和燃料喷嘴，其允许将燃料和空气进一步均匀且充分地混合到燃气涡轮发动机的燃烧器中，其中多个混合管中的每一个包括一对同心的中空圆筒， 在每个混合管中的两个中空圆柱体之间的用于燃料流动的环形环形路径，形成在同心中空圆柱体中的多个空气注入槽限定从外部到每个混合管的内部的相应空气流动路径，以及 一个或多个燃料喷射口形成在多个空气喷射槽中的选定的空气喷射槽中，允许燃料从由中空圆筒形成的环形路径流入空气流动路径，导致显着更好的混合和改进的热力学行为 燃料和空气混合物在喷嘴下游和燃烧器的上游。
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公开(公告)号：US08850822B2
公开(公告)日：2014-10-07
申请号：US13012746
申请日：2011-01-24
CPC分类号： F23R3/36 , F23C2900/07001 , F23R3/14 , F23R3/286
摘要： A system includes a fuel nozzle. The fuel nozzle includes a hub having an axis, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple vanes extending between the hub and the shroud, and a first fuel path leading to multiple first fuel outlets disposed on the multiple vanes. The fuel nozzle also includes a second fuel path leading to multiple second fuel outlets disposed on at least one of the hub and/or the shroud, wherein the multiple second fuel outlets are disposed at an axial distance upstream from a downstream end of the hub.
摘要翻译： 系统包括燃料喷嘴。 燃料喷嘴包括具有轴线的轮毂，围绕毂设置的护罩，轮毂和护罩之间的气流路径，在轮毂和护罩之间延伸的多个叶片，以及通向多个第一燃料出口的第一燃料路径， 多叶片。 燃料喷嘴还包括通向设置在轮毂和/或护罩中的至少一个上的多个第二燃料出口的第二燃料通路，其中多个第二燃料出口设置在距毂的下游端的上游轴向距离处。
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公开(公告)号：US20120023951A1
公开(公告)日：2012-02-02
申请号：US12845986
申请日：2010-07-29
IPC分类号： F02C7/22
CPC分类号： F23D14/62 , F23C7/004 , F23C2900/07001 , F23D14/02 , F23R3/286
摘要： A fuel nozzle for a turbine engine includes an air admission shroud which admits a flow of air from an exterior of the fuel nozzle into an interior of the fuel nozzle at a position along the length of the fuel nozzle. A plurality of air admission apertures in the air admission shroud could be arranged to cause the air being admitted into the interior of the fuel nozzle to swirl around the interior of the fuel nozzle in a rotational fashion. If the fuel nozzle also includes swirler vanes located upstream of the air admission shroud, which also induce air within the fuel nozzle to swirl around the interior of the fuel nozzle in a rotational fashion, then the air admission apertures of the air admission shroud preferably cause the air admitted through the air admission shroud to swirl in a rotational direction which is opposite to the swirl induced by the swirler vanes. This helps to better mix the air and the fuel within the nozzle.
摘要翻译： 用于涡轮发动机的燃料喷嘴包括进气罩，其允许空气从燃料喷嘴的外部流入沿着燃料喷嘴长度的位置的燃料喷嘴的内部。 空气入口护罩中的多个进气孔可以被布置成使空气进入燃料喷嘴的内部以旋转的方式围绕燃料喷嘴的内部旋转。 如果燃料喷嘴还包括位于进气罩上游的旋流器叶片，这也使得燃料喷嘴内的空气以旋转的方式围绕燃料喷嘴的内部旋转，则进气罩的进气孔优选地 通过进气罩进入的空气沿着与由旋流叶片引起的涡流相反的旋转方向旋转。 这有助于更好地混合喷嘴内的空气和燃料。
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公开(公告)号：US20110016866A1
公开(公告)日：2011-01-27
申请号：US12507298
申请日：2009-07-22
摘要： In one embodiment, a system includes a fuel injector including a liquid fuel passage extending to a first port in a tip portion. The fuel injector also includes a selectable flow passage extending to a second port in the tip portion. The selectable flow passage surrounds the liquid fuel passage to the tip portion, the selectable flow passage is configured to selectively receive a gas fuel flow and an air flow, and the selectable flow passage has a flow temperature configured to cool a liquid fuel flowing through the liquid fuel passage to reduce coking.
摘要翻译： 在一个实施例中，系统包括燃料喷射器，其包括延伸到尖端部分中的第一端口的液体燃料通道。 燃料喷射器还包括延伸到尖端部分中的第二端口的可选择的流动通道。 可选择的流动通道围绕到顶部的液体燃料通道，可选择的流动通道构造成选择性地接收气体燃料流和空气流，并且可选择的流动通道具有被配置为冷却流过 液体燃料通道减少焦化。
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公开(公告)号：US09046262B2
公开(公告)日：2015-06-02
申请号：US13170133
申请日：2011-06-27
CPC分类号： F23C7/004 , F23C2900/07001 , F23R3/286
摘要： In an embodiment, a system includes a turbine fuel nozzle having a hub with an axis, a shroud surrounding the hub along the axis, an air flow path between the hub and the shroud, and a fuel flow path. The turbine fuel nozzle also includes a swirl vane extending between the hub and the shroud in a radial direction relative to the axis. The swirl vane includes a fuel inlet coupled to the fuel flow path, a fuel chamber extending from the fuel inlet, and a plurality of fuel outlets extending from the fuel chamber to the air flow path. The plurality of fuel outlets is positioned at an axial distance of at least approximately ⅔ of an axial length of the fuel chamber downstream from an upstream point along an upstream edge of the fuel chamber.
摘要翻译： 在一个实施例中，系统包括涡轮燃料喷嘴，其具有带有轴的轮毂，围绕轴线的轮毂的护罩，轮毂和护罩之间的空气流动路径以及燃料流动路径。 涡轮燃料喷嘴还包括在毂和护罩之间沿相对于轴线的径向方向延伸的旋流叶片。 涡旋叶片包括联接到燃料流动路径的燃料入口，从燃料入口延伸的燃料室和从燃料室延伸到空气流动路径的多个燃料出口。 多个燃料出口被定位在燃料室的沿着燃料室的上游边缘的上游点下游的燃料室的轴向长度的至少近似⅔的轴向距离处。
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公开(公告)号：US08899975B2
公开(公告)日：2014-12-02
申请号：US13289567
申请日：2011-11-04
CPC分类号： F23R3/002 , F23R3/54 , F23R2900/03044
摘要： A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.
摘要翻译： 提供了具有尾气喷射的燃烧器。 燃烧器包括燃料喷嘴，第一和第二容器形成并设置成限定第一流体朝着燃料喷嘴沿第一和第二相反方向流动的流动路径，设置在流路中的叶片和喷射器 由设置在叶片上游的流动路径中的障碍物形成的流体进入尾流。
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公开(公告)号：US20130186094A1
公开(公告)日：2013-07-25
申请号：US13354897
申请日：2012-01-20
IPC分类号： F23R3/14
摘要： An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings.
摘要翻译： 用于燃气轮机的轴流式燃料喷嘴包括用于输送用于燃烧的材料的多个环形通道。 环形空气通道接收压缩机排放空气，并且多个旋流器叶片槽邻近环形空气通道的轴向端定位。 第一个下一个环形通道设置在环形空气通道的径向内侧，并且包括邻近第一环形通道的轴向端部并且位于旋流器叶片槽的下游的第一开口。 第二个下一个环形通道设置在第一环形通道的径向内侧，并且包括邻近第二环形通道的轴向端部和第一开口下游定位的第二开口。
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公开(公告)号：US08418469B2
公开(公告)日：2013-04-16
申请号：US12890903
申请日：2010-09-27
IPC分类号： F02C1/00
CPC分类号： F23R3/14 , F23D11/402 , F23D14/64 , F23D2900/00008 , F23D2900/14701 , F23R3/286 , F23R3/343 , F23R3/36
摘要： A fuel nozzle assembly is disclosed. The fuel nozzle assembly comprises an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween. The fuel nozzle assembly further comprises a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus. The fuel nozzle assembly further comprises an air injection feature configured to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube.
摘要翻译： 公开了一种燃料喷嘴组件。 燃料喷嘴组件包括外部燃烧器管和在其间限定预混合环的内部燃烧器管。 所述燃料喷嘴组件还包括旋流器组件，所述旋流器组件包括围绕所述内部燃烧器管设置成环形阵列并被配置为与所述预混合环空上游的一次空气相互作用的多个旋流器叶片。 燃料喷嘴组件还包括空气喷射特征，该空气喷射特征构造成将二次空气流入旋流器组件下游的预混合环空，使得二次空气相对于预混气环纵向流动，并且至少相邻 外部燃烧器管和内部燃烧器管之一。
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公开(公告)号：US08590311B2
公开(公告)日：2013-11-26
申请号：US12768758
申请日：2010-04-28
CPC分类号： F23R3/286
摘要： An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define a ring-like, annular path for the flow of fuel between the two hollow cylinders in each mixing tube, a plurality of air injection slots formed in the concentric hollow cylinders defining corresponding air flow paths from the outside into the interior of each mixing tube, and one or more fuel injection ports formed in selected ones of the plurality of air injection slots that allow for the flow of fuel from the annular path formed by the hollow cylinders into the air flow path, resulting in significantly better mixing and improved thermodynamic behavior of the fuel and air mixture downstream of the nozzle and upstream of the combustor.
摘要翻译： 一种改进的混合管设计和燃料喷嘴，其允许将燃料和空气进一步均匀且充分地混合到燃气涡轮发动机的燃烧器中，其中多个混合管中的每一个包括一对同心的中空圆筒， 在每个混合管中的两个中空圆柱体之间的用于燃料流动的环形环形路径，形成在同心中空圆柱体中的多个空气注入槽限定从外部到每个混合管的内部的相应空气流动路径，以及 一个或多个燃料喷射口形成在多个空气喷射槽中的选定的空气喷射槽中，允许燃料从由中空圆筒形成的环形路径流入空气流动路径，导致显着更好的混合和改进的热力学行为 燃料和空气混合物在喷嘴下游和燃烧器的上游。
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