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    AIR SHIELD FOR A FUEL INJECTOR OF A COMBUSTOR
    113.
    发明申请
    AIR SHIELD FOR A FUEL INJECTOR OF A COMBUSTOR 审中-公开
    燃油喷射器的空气屏蔽

    公开(公告)号：US20160265781A1

    公开(公告)日：2016-09-15

    申请号：US14643732

    申请日：2015-03-10

    Applicant: General Electric Company

    Inventor： William Francis Carnell, JR. ,  Ronnie Ray Pentecost ,  Lucas John Stoia ,  Patrick Benedict Melton

    IPC: F23R3/34 ,  F23R3/26

    CPC classification number: F23R3/346 ,  F23R3/002 ,  F23R3/26

    Abstract: An air shield for an injector of a combustor includes a first section that extends axially from a first end to a second end, and a channel defined by the air shield. The channel includes at least one inlet proximate to the second end. The at least one inlet is configured to receive a channel airflow that is a portion of a surrounding airflow. The channel is configured to control a distribution of the channel airflow to the injector.

    Abstract translation: 用于燃烧器的喷射器的空气屏蔽包括从第一端轴向延伸到第二端的第一部分和由空气屏蔽件限定的通道。 通道包括靠近第二端的至少一个入口。 所述至少一个入口构造成接收作为周围空气流的一部分的通道气流。 通道被配置为控制到喷射器的通道气流的分布。

    FUEL INJECTOR ASSEMBLIES IN COMBUSTION TURBINE ENGINES
    114.
    发明申请
    FUEL INJECTOR ASSEMBLIES IN COMBUSTION TURBINE ENGINES 审中-公开
    燃油喷射器组件在燃油涡轮发动机

    公开(公告)号：US20160047317A1

    公开(公告)日：2016-02-18

    申请号：US14459397

    申请日：2014-08-14

    Applicant: General Electric Company

    Inventor： Christopher Paul Willis ,  William Michael Poschel ,  Lucas John Stoia ,  Patrick Benedict Melton ,  Vaibhav Nadkarni ,  Chandrasekhar Pushkaran

    IPC: F02C7/22

    CPC classification number: F02C7/22 ,  F23R3/283 ,  F23R3/346

    Abstract: A downstream nozzle for use in a combustor that includes an inner radial wall defining a combustion zone downstream of a primary nozzle and an outer radial wall surrounding the inner radial wall so to form a flow annulus therebetween. The downstream nozzle may include: an injector tube extending between the outer radial wall and the inner radial wall; a first plenum adjacent to the injector tube, and, inboard of the ceiling, a floor disposed between the inner radial wall and the outer radial wall. A feed passage may connect the first plenum to an inlet formed outboard of the outer radial wall and impingement ports may be formed through the floor of the first plenum.

    Abstract translation: 一种用于燃烧器的下游喷嘴，其包括限定主喷嘴下游的燃烧区的内部径向壁和围绕内部径向壁的外部径向壁，以在它们之间形成流动环空。 下游喷嘴可以包括：在外径向壁和内径向壁之间延伸的喷射管; 与喷射器管相邻的第一增压室，以及天花板的内侧，设置在内径向壁和外径向壁之间的地板。 进料通道可以将第一增压室连接到外径向壁外部形成的入口，并且冲击口可形成在第一增压室的底板上。

    SUPPORT FRAME AND METHOD FOR ASSEMBLY OF A COMBUSTION MODULE OF A GAS TURBINE
    115.
    发明申请
    SUPPORT FRAME AND METHOD FOR ASSEMBLY OF A COMBUSTION MODULE OF A GAS TURBINE 有权
    支撑框架和组装燃气涡轮机燃烧模块的方法

    公开(公告)号：US20140360193A1

    公开(公告)日：2014-12-11

    申请号：US13845661

    申请日：2013-03-18

    Applicant: General Electric Company

    Inventor： Lucas John Stoia ,  Richard Martin DiCintio ,  William Michael Poschel ,  Patrick Benedict Melton

    IPC: F23R3/00 ,  B23P19/04

    CPC classification number: F23R3/00 ,  B25B11/02 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/00019 ,  Y10T29/4932 ,  Y10T29/53961

    Abstract: A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate.

    Abstract translation: 用于组装用于燃气轮机的燃烧模块的支撑框架包括设置在支撑框架的底端处的基板和通过一个或多个垂直支撑构件与基板垂直分离的支撑板。 支撑板限定了一个开口，其尺寸被设计成允许燃烧模块的一部分通过。 支撑块从基板向支撑板垂直延伸，其中支撑块限定一个或多个紧固件孔，用于将燃烧模块的燃烧衬套的后端连接到支撑块。 中心支撑柱从基板向支撑板垂直延伸。 水平支撑件从中心支撑柱径向向外延伸，以将燃烧衬套与支撑板中的开口对准。

    Combustor cap assembly
    116.
    发明授权
    Combustor cap assembly 有权
    燃烧器盖组件

    公开(公告)号：US08756934B2

    公开(公告)日：2014-06-24

    申请号：US13663712

    申请日：2012-10-30

    Applicant: General Electric Company

    Inventor： Patrick Benedict Melton ,  Bryan Wesley Romig ,  Lucas John Stoia

    IPC: F23R3/28 ,  F02C7/22 ,  F02C7/18 ,  F23R3/14

    CPC classification number: F23R3/286 ,  F23D11/36 ,  F23D14/78 ,  F23D2214/00 ,  F23R3/14 ,  F23R3/28 ,  F23R3/283 ,  F23R2900/03043 ,  F23R2900/03044

    Abstract: A combustor generally includes a shroud that that defines at least one inlet passage extends circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port, at least one outlet port and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve may extend through the fuel nozzle passage. The tube, the sleeve, and the first plate may at least partially define an outlet passage. A first fluid flow path generally extends from the at inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.

    Abstract translation: 燃烧器通常包括护罩，其限定在燃烧器内周向延伸的至少一个入口通道。 第一板在入口通道下游的护罩的径向内部延伸。 第一板限定至少一个入口端口，至少一个出口端口，并且至少部分地限定至少一个燃料喷嘴通道。 护罩至少部分地围绕围绕燃料喷嘴通道延伸的套筒。 至少部分地被套筒包围的管可延伸穿过燃料喷嘴通道。 管，套筒和第一板可以至少部分地限定出口通道。 第一流体流动路径通常从入口通道延伸到入口端口，并且第二流体流动路径大体上从出口延伸到出口通道。

    ENHANCEMENT FOR FUEL INJECTOR
    118.
    发明申请
    ENHANCEMENT FOR FUEL INJECTOR 审中-公开
    燃油喷射器增强

    公开(公告)号：US20140123653A1

    公开(公告)日：2014-05-08

    申请号：US13672147

    申请日：2012-11-08

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Lucas John Stoia ,  Gregory Allen Boardman ,  Wei Chen

    IPC: F02C7/22

    CPC classification number: F02C7/22 ,  F23R3/28 ,  F23R3/34

    Abstract: A fuel injector is provided and includes a surface disposed proximate to a flow of a first fluid and a delta wing feature. The surface has upstream and downstream portions defined relative to the flow and defines an injector hole in the downstream portion by which a jet of a second fluid is injectable into the flow. The delta wing feature is disposed on the surface at the upstream portion and is configured to lift an oncoming portion of the flow off the surface and to cause the oncoming portion of the flow to form a pair of counter-rotating vortices that respectively co-rotate with the jet in a cross-flow direction.

    Abstract translation: 燃料喷射器被设置并且包括邻近第一流体和三角翼特征的流动设置的表面。 表面具有相对于流动限定的上游部分和下游部分，并且在下游部分中限定了第二流体的射流通过该喷射器孔注入到流体中。 三角翼特征设置在上游部分的表面上，并且构造成将流出的部分离开表面提升，并使流动的迎面部分形成一对反向旋转涡旋，其分别共同旋转 喷流在横流方向。

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