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公开(公告)号：US08028529B2
公开(公告)日：2011-10-04
申请号：US12219929
申请日：2008-07-30
IPC分类号： F02C1/00
CPC分类号： F23R3/10 , F23D2900/00008 , F23R3/06 , F23R3/286 , F23R3/343
摘要： A gas turbine combustor including: a primary combustion chamber; a secondary combustion chamber downstream of the primary combustion chamber; a venturi having a venturi throat; a transition piece; a cap assembly attached to the primary combustion chamber, and an external turbulator member in operable communication with the cap assembly, wherein the primary combustion chamber includes a mixing hole arrangement for improving homogeneity of an air and fuel mixture in the combustor; the venturi throat is disposed within a predetermined distance upstream from the downstream end of the primary combustion chamber; the transition piece is composed of a duct body, with a plurality of dilution holes formed in the duct body; and the external turbulator member includes a step positioned at the second end of the centerbody, the step defining a radial distance about the second end of the centerbody.
摘要翻译： 一种燃气轮机燃烧器，包括：主燃烧室; 主燃烧室下游的二次燃烧室; 文丘里有文丘里喉咙; 过渡片 附接到所述主燃烧室的盖组件和与所述盖组件可操作地连通的外部湍流器构件，其中所述主燃烧室包括用于改善所述燃烧器中的空气和燃料混合物的均匀性的混合孔装置; 文丘里喉部设置在主燃烧室的下游端上游的预定距离内; 过渡件由管体构成，多个稀释孔形成在管体内; 并且所述外部紊流器构件包括位于所述中心体的第二端的台阶，所述台阶限定围绕所述中心体的第二端的径向距离。
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公开(公告)号：US20100018211A1
公开(公告)日：2010-01-28
申请号：US12219534
申请日：2008-07-23
CPC分类号： F01D9/023 , F05D2250/74 , F23R3/06
摘要： A gas turbine transition piece includes a duct body having a forward end and an aft end, the duct body defining an enclosure for confining a flow of combustion products from a combustor to a turbine first stage nozzle. A plurality of dilution holes are formed in the duct body, located at selected X, Y, Z coordinates measured from a zero reference point at a center of an exit plane of the transition piece.
摘要翻译： 燃气涡轮机过渡件包括具有前端和后端的管道主体，管道主体限定用于限制来自燃烧器的燃烧产物流到涡轮机第一级喷嘴的外壳。 多个稀释孔形成在管体中，位于从过渡件的出口平面的中心处的零参考点测量的所选X，Y，Z坐标处。
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公开(公告)号：US20090019855A1
公开(公告)日：2009-01-22
申请号：US12219929
申请日：2008-07-30
CPC分类号： F23R3/10 , F23D2900/00008 , F23R3/06 , F23R3/286 , F23R3/343
摘要： A gas turbine combustor including: a primary combustion chamber; a secondary combustion chamber downstream of the primary combustion chamber; a venturi having a venturi throat; a transition piece; a cap assembly attached to the primary combustion chamber, and an external turbulator member in operable communication with the cap assembly, wherein the primary combustion chamber includes a mixing hole arrangement for improving homogeneity of an air and fuel mixture in the combustor; the venturi throat is disposed within a predetermined distance upstream from the downstream end of the primary combustion chamber; the transition piece is composed of a duct body, with a plurality of dilution holes formed in the duct body; and the external turbulator member includes a step positioned at the second end of the centerbody, the step defining a radial distance about the second end of the centerbody.
摘要翻译： 一种燃气轮机燃烧器，包括：主燃烧室; 主燃烧室下游的二次燃烧室; 文丘里有文丘里喉咙; 过渡片 附接到所述主燃烧室的盖组件和与所述盖组件可操作地连通的外部湍流器构件，其中所述主燃烧室包括用于改善所述燃烧器中的空气和燃料混合物的均匀性的混合孔装置; 文丘里喉部设置在主燃烧室的下游端上游的预定距离内; 过渡件由管体构成，多个稀释孔形成在管体内; 并且所述外部紊流器构件包括位于所述中心体的第二端的台阶，所述台阶限定围绕所述中心体的第二端的径向距离。
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公开(公告)号：US08397512B2
公开(公告)日：2013-03-19
申请号：US12197838
申请日：2008-08-25
IPC分类号： F02C1/00
CPC分类号： F02C7/18 , F01D9/023 , Y10T29/49245
摘要： A method for assembling a gas turbine engine includes coupling a transition piece between a combustor liner and a nozzle assembly. The method also includes extending a first portion of a flow sleeve from the transition piece about at least a portion of the combustor liner. The method further includes coupling a second portion of the flow sleeve to the first portion of the flow sleeve such that the flow sleeve second portion extends from the flow sleeve first portion and at least partially about at least a portion of the transition piece. The flow sleeve second portion includes a scoop that cooperates with the transition piece to at least partially define a unitary cooling air passage that includes a unitary scoop-shaped opening. The scoop is oriented to introduce a substantially uniform cooling air flow to the transition piece.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将过渡件联接在燃烧器衬套和喷嘴组件之间。 该方法还包括将过渡件的第一部分从燃烧器衬套的至少一部分延伸出来。 该方法还包括将流动套筒的第二部分联接到流动套筒的第一部分，使得流动套筒第二部分从流动套筒第一部分延伸并且至少部分地围绕过渡件的至少一部分延伸。 流动套筒第二部分包括与过渡件配合以至少部分地限定包括整体式勺状开口的整体冷却空气通道的勺子。 勺子被定向成将大致均匀的冷却空气流引入过渡件。
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公开(公告)号：US08020385B2
公开(公告)日：2011-09-20
申请号：US12180879
申请日：2008-07-28
IPC分类号： F02C1/00
摘要： A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage defined by a gap between the wall of the centerbody and the external turbulator. The external turbulator member includes a step positioned at the second end of the centerbody. The step defines a radial distance about the second end of the centerbody. The external turbulator member is formed having a step-to-gap ratio relative to the centerbody in a range of about 0.8 to about 1.2.
摘要翻译： 涡轮机包括燃烧器组件，附接到燃烧器组件的帽组件，帽组件内的中心体，中心体的壁，其具有第一端，第二端和中间部分，以及外部湍流构件，其可操作地与 盖组件。 外部紊流器构件与壁间隔开以形成由中心体的壁和外部湍流器之间的间隙限定的通道。 外部湍流器构件包括位于中心体的第二端的台阶。 该步骤限定了围绕中心体的第二端的径向距离。 外部紊流器构件形成为具有在约0.8至约1.2的范围内的相对于中心体的台阶间隙比。
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公开(公告)号：US20100018181A1
公开(公告)日：2010-01-28
申请号：US12180879
申请日：2008-07-28
摘要： A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage defined by a gap between the wall of the centerbody and the external turbulator. The external turbulator member includes a step positioned at the second end of the centerbody. The step defines a radial distance about the second end of the centerbody. The external turbulator member is formed having a step-to-gap ratio relative to the centerbody in a range of about 0.8 to about 1.2.
摘要翻译： 涡轮机包括燃烧器组件，附接到燃烧器组件的帽组件，帽组件内的中心体，中心体的壁，其具有第一端，第二端和中间部分，以及外部湍流构件，其可操作地与 盖组件。 外部紊流器构件与壁间隔开以形成由中心体的壁和外部湍流器之间的间隙限定的通道。 外部湍流器构件包括位于中心体的第二端的台阶。 该步骤限定了围绕中心体的第二端的径向距离。 外部紊流器构件形成为具有在约0.8至约1.2的范围内的相对于中心体的台阶间隙比。
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公开(公告)号：US20110041507A1
公开(公告)日：2011-02-24
申请号：US12543066
申请日：2009-08-18
IPC分类号： F23R3/42
CPC分类号： F23R3/002 , F23R2900/00016
摘要： A combustion liner assembly for a gas turbine combustor includes a plurality of fuel nozzles disposed circumferentially about a central axis of the combustor, and a venturi section disposed downstream of the fuel nozzles and connected to a head end of the liner assembly. The venturi section defines an annular throat area downstream of the fuel nozzles. A liner sleeve is connected to and commences at a downstream end of the venturi section. At least a portion of the venturi section serves as a liner upstream of the liner sleeve.
摘要翻译： 用于燃气轮机燃烧器的燃烧衬套组件包括围绕燃烧器的中心轴线周向设置的多个燃料喷嘴，以及设置在燃料喷嘴下游并连接到衬套组件的头端的文丘里管部分。 文丘里管部分限定在燃料喷嘴下游的环形喉部区域。 衬套套筒连接到文氏管部分的下游端并开始。 文氏管部分的至少一部分用作衬套上游的衬垫。
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公开(公告)号：US20100043441A1
公开(公告)日：2010-02-25
申请号：US12197838
申请日：2008-08-25
CPC分类号： F02C7/18 , F01D9/023 , Y10T29/49245
摘要： A method for assembling a gas turbine engine includes coupling a transition piece between a combustor liner and a nozzle assembly. The method also includes extending a first portion of a flow sleeve from the transition piece about at least a portion of the combustor liner. The method further includes coupling a second portion of the flow sleeve to the first portion of the flow sleeve such that the flow sleeve second portion extends from the flow sleeve first portion and at least partially about at least a portion of the transition piece. The flow sleeve second portion includes a scoop that cooperates with the transition piece to at least partially define a unitary cooling air passage that includes a unitary scoop-shaped opening. The scoop is oriented to introduce a substantially uniform cooling air flow to the transition piece.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将过渡件联接在燃烧器衬套和喷嘴组件之间。 该方法还包括将过渡件的第一部分从燃烧器衬套的至少一部分延伸出来。 该方法还包括将流动套筒的第二部分联接到流动套筒的第一部分，使得流动套筒第二部分从流动套筒第一部分延伸并且至少部分地围绕过渡件的至少一部分延伸。 流动套筒第二部分包括与过渡件配合以至少部分地限定包括整体式勺状开口的整体冷却空气通道的勺子。 勺子被定向成将大致均匀的冷却空气流引入过渡件。
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9.发明授权Method and arrangement for expanding a primary and secondary flame in a combustor 失效用于在燃烧器中膨胀一次和二次火焰的方法和装置公开(公告)号：US08156743B2
公开(公告)日：2012-04-17
申请号：US11418239
申请日：2006-05-04
IPC分类号： F02C1/00
CPC分类号： F23R3/16
摘要： Disclosed is an arrangement for expanding an annular fluid flow and a center fluid flow, comprising a combustor including a venturi and a centerbody, the centerbody including an upstream end and a downstream end, and a venturi throat defined by the venturi and disposed upstream of 0.19 inches downstream of the downstream end of the centerbody.
摘要翻译： 公开了一种用于扩展环形流体流和中心流体流的装置，其包括包括文丘里管和中心体的燃烧器，该中心体包括上游端和下游端，以及由文氏管限定的文丘里喉部并且设置在0.19 在中心体的下游端下游。
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10.发明申请Systems, Methods, and Apparatus Providing a Secondary Fuel Nozzle Assembly 审中-公开提供二次燃料喷嘴组件的系统，方法和装置公开(公告)号：US20100205970A1
公开(公告)日：2010-08-19
申请号：US12388855
申请日：2009-02-19
IPC分类号： F02C7/22
CPC分类号： F23R3/343
摘要： Provided are systems, methods, and apparatus providing secondary fuel nozzle assemblies. For example, a secondary fuel nozzle assembly can include a central portion having a proximal end and distal end, and defining a central passage therethrough, which can include at least one coiled tube extending through the central passage from the proximal end to the distal end; a flange having at least one main secondary fuel orifice in fluid communication with the central passage at the proximal end and at least one pilot orifice in fluid communication with the at least one coiled tube at the proximal end; and a tip portion having a proximal end and distal end, and defining at least one passage therethrough, which can be in fluid communication with the distal end of the at least one coiled tube and at least one orifice formed in the distal end of the tip portion.
摘要翻译： 提供了提供二次燃料喷嘴组件的系统，方法和装置。 例如，次级燃料喷嘴组件可以包括具有近端和远端的中心部分，并且限定穿过其中的中心通道，该中心通道可包括从近端延伸到远端延伸穿过中心通道的至少一个螺旋管; 具有至少一个主中间燃料孔口的凸缘，所述至少一个主次级燃料孔口在近端处与中心通道流体连通，以及至少一个引导孔口，其在近端与所述至少一个螺旋管道流体连通; 以及尖端部分，其具有近端和远端，并且限定穿过其中的至少一个通道，其可以与所述至少一个盘管的远端流体连通，并且形成在尖端的远端中的至少一个孔口 一部分。
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