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    AFT frame assembly for gas turbine transition piece
    32.
    发明授权
    AFT frame assembly for gas turbine transition piece 有权

    公开(公告)号：US10718224B2

    公开(公告)日：2020-07-21

    申请号：US15783256

    申请日：2017-10-13

    Applicant: General Electric Company

    Inventor： Charles Lewis Davis, III ,  Kevin Weston McMahan ,  Wei Chen ,  Scott Robert Simmons

    IPC: F02C7/18 ,  F01D9/06 ,  F01D9/02 ,  F01D25/12 ,  F02C3/04 ,  F02C7/12

    Abstract: An aft frame assembly has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. Feed hole inlets are located on the upstream facing surface and radially outward of the outer sleeve so that the feed hole inlets are located to receive input from a high pressure plenum. The feed hole inlets are coupled to cooling channels that pass through the main body. Microchannels are formed in or near the radially inner facing surface and the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. Exit holes are connected to the plurality of microchannels, and the exit holes are located radially outward of the transition piece and radially inward of the outer sleeve. The exit holes are located to exhaust into the cooling annulus.

    AFT FRAME ASSEMBLY FOR GAS TURBINE TRANSITION PIECE
    34.
    发明申请
    AFT FRAME ASSEMBLY FOR GAS TURBINE TRANSITION PIECE 审中-公开

    公开(公告)号：US20190112936A1

    公开(公告)日：2019-04-18

    申请号：US15783256

    申请日：2017-10-13

    Applicant: General Electric Company

    Inventor： Charles Lewis Davis, III ,  Kevin Weston McMahan ,  Wei Chen ,  Scott Robert Simmons

    IPC: F01D9/06 ,  F02C3/04 ,  F02C7/12

    Abstract: An aft frame assembly has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. Feed hole inlets are located on the upstream facing surface and radially outward of the outer sleeve so that the feed hole inlets are located to receive input from a high pressure plenum. The feed hole inlets are coupled to cooling channels that pass through the main body. Microchannels are formed in or near the radially inner facing surface and the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. Exit holes are connected to the plurality of microchannels, and the exit holes are located radially outward of the transition piece and radially inward of the outer sleeve. The exit holes are located to exhaust into the cooling annulus.

    Transition duct assembly with late injection features
    35.
    发明授权
    Transition duct assembly with late injection features 有权

    公开(公告)号：US10260752B2

    公开(公告)日：2019-04-16

    申请号：US15079091

    申请日：2016-03-24

    Applicant: General Electric Company

    Inventor： Jeffrey Scott LeBegue ,  Kevin Weston McMahan ,  James Scott Flanagan

    IPC: F23R3/34 ,  F23R3/42 ,  F23R3/46

    Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each of the plurality of transition ducts is offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly. The turbomachine includes a late injection assembly providing fluid communication for an injection fluid to flow into the interior downstream of the inlet of at least one transition duct of the plurality of transition ducts.

    BUSHING FOR JOINING TURBOMACHINE COMPONENTS
    37.
    发明申请
    BUSHING FOR JOINING TURBOMACHINE COMPONENTS 审中-公开
    搭接涡轮机组件

    公开(公告)号：US20160047313A1

    公开(公告)日：2016-02-18

    申请号：US14460470

    申请日：2014-08-15

    Applicant: General Electric Company

    Inventor： Mark Carmine Bellino ,  Kevin Weston McMahan ,  Lucas John Stoia ,  Christopher Paul Willis

    IPC: F02C7/20 ,  F16B43/00 ,  F02C3/04

    CPC classification number: F16B43/00 ,  F01D9/023 ,  F01D25/28 ,  F05D2230/64 ,  F05D2240/91 ,  F05D2250/312 ,  F05D2260/36 ,  F16B37/122 ,  Y02T50/675

    Abstract: A bushing includes a body extending from a first end to a second end through an intermediate portion. The body includes a passage having a first centerline extending from the first end to the second end. A first alignment member is formed on a first section of the intermediate portion at the first end. The first alignment member includes an outer surface having a plurality of splines configured to be received by a first component to be joined. A second alignment member is formed on a second section of the intermediate portion. The second alignment member includes a second centerline that is off-set relative to the first centerline and is configured to be received by a second component to be joined with the first component.

    Abstract translation: 衬套包括从第一端延伸到第二端穿过中间部分的主体。 主体包括具有从第一端延伸到第二端的第一中心线的通道。 第一对准部件在第一端部的中间部分的第一部分上形成。 第一对准构件包括具有多个花键的外表面，该多个花键构造成被待接合的第一构件接收。 第二对准构件形成在中间部分的第二部分上。 第二对准构件包括相对于第一中心线偏移的第二中心线，并且构造成由第二部件接收以与第一部件接合。

    TRANSITION DUCT WITH IMPROVED COOLING IN TURBOMACHINE
    39.
    发明申请
    TRANSITION DUCT WITH IMPROVED COOLING IN TURBOMACHINE 有权
    在涡轮机中改进冷却的过渡管

    公开(公告)号：US20140283520A1

    公开(公告)日：2014-09-25

    申请号：US13848204

    申请日：2013-03-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Kevin Weston McMahan ,  Jeffrey Scott LeBegue ,  Jaime Javier Maldonado ,  Daniel Jackson Dillard ,  James Scott Flanagan

    IPC: F01D9/02

    CPC classification number: F01D9/023 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  F23R3/002 ,  F23R3/425 ,  F23R2900/03043 ,  F23R2900/03044

    Abstract: Turbine systems are provided. In one embodiment, a turbine system includes a transition duct comprising an inlet, an outlet, and a duct passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The duct passage includes an upstream portion extending from the inlet and a downstream portion extending from the outlet. The turbine system further includes a rib extending from an outer surface of the duct passage, the rib dividing the upstream portion and the downstream portion.

    Abstract translation: 提供涡轮机系统。 在一个实施例中，涡轮机系统包括过渡管道，其包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切向轴线的管道通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 管道通道包括从入口延伸的上游部分和从出口延伸的下游部分。 涡轮机系统还包括从管道通道的外表面延伸的肋，肋分隔上游部分和下游部分。

    Multi-premixer fuel nozzle support system
    40.
    发明授权
    Multi-premixer fuel nozzle support system 失效
    多预混合燃料喷嘴支撑系统

    公开(公告)号：US08769956B2

    公开(公告)日：2014-07-08

    申请号：US14015322

    申请日：2013-08-30

    Applicant: General Electric Company

    Inventor： Jonathan Dwight Berry ,  Kevin Weston McMahan ,  Carl Robert Barker

    IPC: F23R3/28 ,  F23R3/14

    CPC classification number: F23R3/10 ,  F23R3/286

    Abstract: A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.

    Abstract translation: 一种包括燃料喷嘴的系统。 燃料喷嘴包括安装基座和沿着下游方向从安装基座直接延伸的入口流动调节器。 此外，入口流动调节器结构地支撑燃料喷嘴，而没有直接从入口流动调节器内的安装基座延伸的中心支撑构件。

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