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    Transition duct assembly with modified trailing edge in turbine system
    3.
    发明授权
    Transition duct assembly with modified trailing edge in turbine system 有权
    在涡轮机系统中具有改进的后缘的过渡管道组件

    公开(公告)号：US09458732B2

    公开(公告)日：2016-10-04

    申请号：US14063358

    申请日：2013-10-25

    Applicant: General Electric Company

    Inventor： Kevin Weston McMahan ,  Carl Gerard Schott ,  Clint Luigie Ingram ,  Gunnar Leif Siden ,  Sylvain Pierre

    IPC: F01D9/02 ,  F01D5/14

    CPC classification number: F01D9/023 ,  F01D5/141 ,  F05D2240/122 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/71

    Abstract: Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.

    Abstract translation: 提供了用于涡轮机系统和涡轮机械的过渡管道组件。 在一个实施例中，过渡管道组件包括设置在大致环形阵列中并包括第一过渡管道和第二过渡管道的多个过渡管道。 多个过渡管道中的每一个包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 每个过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 过渡管道组件还包括由第一过渡管道和第二过渡管道的通道限定的空气动力学结构。 空气动力学结构包括压力侧，吸力侧和后缘，后缘具有改进的空气动力学轮廓。

    Transition duct with divided upstream and downstream portions
    4.
    发明授权
    Transition duct with divided upstream and downstream portions 有权
    过渡管具有分开的上游和下游部分

    公开(公告)号：US09080447B2

    公开(公告)日：2015-07-14

    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 ,  F23R3/00 ,  F23R3/42

    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。

    CLOCKED COMBUSTOR CAN ARRAY
    5.
    发明申请
    CLOCKED COMBUSTOR CAN ARRAY 有权

    公开(公告)号：US20140137535A1

    公开(公告)日：2014-05-22

    申请号：US13681453

    申请日：2012-11-20

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Won-Wook Kim ,  Kevin Weston McMahan ,  Shiva Kumar Srinivasan

    IPC: F23R3/46 ,  F02C7/24

    CPC classification number: F02C7/24 ,  F23C5/08 ,  F23R3/46 ,  F23R2900/00014

    Abstract: The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation.

    Abstract translation: 本申请提供了一种用于燃气涡轮发动机中的相干减少的时钟燃烧室阵列。 时钟式燃烧室阵列可以包括定位在圆周阵列中的多个燃烧器罐。 燃烧器罐的第一组可以具有第一取向，并且第二组燃烧器罐可具有第二取向。

    Aft frame assembly for gas turbine transition piece
    6.
    发明授权
    Aft frame assembly for gas turbine transition piece 有权

    公开(公告)号：US11215072B2

    公开(公告)日：2022-01-04

    申请号：US15783321

    申请日：2017-10-13

    Applicant: General Electric Company

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

    IPC: F01D25/00 ,  F01D25/12 ,  F01D9/02 ,  F01D25/24

    Abstract: An aft frame assembly for a gas turbine transition piece includes a main body having an upstream facing surface and a downstream facing surface. A plurality of feed hole inlets are located on the upstream facing surface. The feed hole inlets are coupled to a plurality of cooling channels that pass through the main body towards the downstream facing surface. A plurality of plenums are located in or near the downstream facing surface, and each cooling channel is connected to and terminates in one of the plenums. The cooling channels are inputs to the plenums. A plurality of microchannel cooling slots are formed in or near the downstream facing surface, and each microchannel cooling slot is connected to one of the plenums. The microchannel cooling slots are outputs of the plenums. Two or more cooling channels and two or more microchannel cooling slots are connected to one of the plenums.

    AFT FRAME ASSEMBLY FOR GAS TURBINE TRANSITION PIECE
    7.
    发明申请
    AFT FRAME ASSEMBLY FOR GAS TURBINE TRANSITION PIECE 审中-公开

    公开(公告)号：US20190113230A1

    公开(公告)日：2019-04-18

    申请号：US15783291

    申请日：2017-10-13

    Applicant: General Electric Company

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

    IPC: F23R3/04 ,  F02C7/18

    Abstract: An aft frame assembly for a gas turbine transition piece has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. A plurality of feed hole inlets are located on the upstream facing surface. Each of the feed hole inlets are coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface. A plurality of microchannels are formed near the radially inner facing surface and extend at least partially along the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. A pre-sintered preform is located on the radially inner facing surface of the main body.

    Transition duct assembly
    8.
    发明授权
    Transition duct assembly 有权

    公开(公告)号：US10227883B2

    公开(公告)日：2019-03-12

    申请号：US15079083

    申请日：2016-03-24

    Applicant: General Electric Company

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

    IPC: F01D9/02 ,  F01D11/00 ,  F01D25/28 ,  F01D25/26

    Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array and including a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage 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 offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine further 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.

    TRANSITION DUCT ASSEMBLY
    9.
    发明申请
    TRANSITION DUCT ASSEMBLY 审中-公开

    公开(公告)号：US20170276002A1

    公开(公告)日：2017-09-28

    申请号：US15079101

    申请日：2016-03-24

    Applicant: General Electric Company

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

    IPC: F01D9/02 ,  F01D25/28 ,  F01D5/02

    CPC classification number: F01D9/023 ,  F01D25/28 ,  F05D2220/32 ,  F05D2260/30

    Abstract: A turbomachine includes a plurality of transition ducts and a support ring assembly. The outlet of a transition duct includes an inner flange and an outer flange. The turbomachine includes bore holes defined in the inner flange and outer flange, mating bore holes defined in the support ring assembly, and mechanical fasteners connecting the inner flange and the outer flange to the support ring assembly. A first one of the bore holes or mating bore holes has a first maximum radial gap and a first maximum tangential gap relative to an associated mechanical fastener. A second one of the bore holes or mating bore holes has a second maximum radial gap and a second maximum tangential gap relative to an associated mechanical fastener. The second maximum radial gap is greater than the first maximum radial gap or the second maximum tangential gap is greater than the first maximum tangential gap.

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