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    MICROMIXER SYSTEM FOR A TURBINE SYSTEM AND AN ASSOCIATED METHOD THEREOF
    1.
    发明申请
    MICROMIXER SYSTEM FOR A TURBINE SYSTEM AND AN ASSOCIATED METHOD THEREOF 审中-公开
    用于涡轮机系统的MICROMIXER系统及其相关方法

    公开(公告)号：US20160290650A1

    公开(公告)日：2016-10-06

    申请号：US14675827

    申请日：2015-04-01

    Applicant: General Electric Company

    Inventor： Bassam Sabry Mohammad Abd El-Nabi ,  Gregory Allen Boardman ,  Gerardo Antonio Salazar Lois

    IPC: F23R3/28

    CPC classification number: F23R3/286 ,  F02C7/222 ,  F23D14/62 ,  F23D2900/00008 ,  F23R3/32 ,  F23R3/36

    Abstract: A micromixer system includes a casing having a first side wall and a second side wall. Further, the micromixer system includes a plurality of pipes spaced apart from each other and disposed within the casing. Each pipe includes an inlet and an outlet formed in the first and second side walls respectively. The micromixer system includes a first plenum having a first inlet formed in the casing. The first plenum is disposed around a first portion of the plurality of pipes and fluidically coupled to the plurality of pipes. The micromixer system includes a second plenum having a second inlet formed in the casing and disposed around a second portion of the plurality of pipes. Further, the micromixer system includes a plurality of openings formed in the second side wall, surrounding the outlets of at least some pipes of the plurality of pipes, and fluidically coupled to the second plenum.

    Abstract translation: 微混合器系统包括具有第一侧壁和第二侧壁的壳体。 此外，微混合器系统包括彼此间隔开并设置在壳体内的多个管。 每个管道分别包括形成在第一和第二侧壁中的入口和出口。 微混合器系统包括具有形成在壳体中的第一入口的第一增压室。 第一增压室设置在多个管的第一部分周围并流体耦合到多个管。 微混合器系统包括第二增压室，其具有形成在壳体中并设置在多个管道的第二部分周围的第二入口。 此外，微混合器系统包括形成在第二侧壁中的多个开口，围绕多个管道中的至少一些管道的出口，并且流体耦合到第二增压室。

    COMBUSTOR SWIRLER TO CMC DOME ATTACHMENT
    3.
    发明申请
    COMBUSTOR SWIRLER TO CMC DOME ATTACHMENT 有权

    公开(公告)号：US20230114116A1

    公开(公告)日：2023-04-13

    申请号：US17499085

    申请日：2021-10-12

    Applicant: General Electric Company

    Inventor： Gerardo Antonio Salazar Lois ,  Daniel J. Kirtley ,  Nicholas John Bloom ,  Shai Birmaher ,  Ryan Christopher Jones

    IPC: F23R3/16 ,  F23R3/00 ,  F23R3/60

    Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.

    SYSTEM AND METHOD HAVING ANNULAR FLOW PATH ARCHITECTURE
    4.
    发明申请
    SYSTEM AND METHOD HAVING ANNULAR FLOW PATH ARCHITECTURE 审中-公开
    具有流动路径结构的系统和方法

    公开(公告)号：US20170067635A1

    公开(公告)日：2017-03-09

    申请号：US14849552

    申请日：2015-09-09

    Applicant: General Electric Company

    Inventor： Nan Zong ,  Ahmed Mostafa ELKady ,  Mark Anthony Mueller ,  Pradeep Naik ,  Gerardo Antonio Salazar Lois ,  Rishikesh Prakash Karande ,  Jeffrey Michael Martini

    IPC: F23R3/00 ,  F23R3/28 ,  F23R3/10

    CPC classification number: F23R3/002 ,  F04D29/542 ,  F23R3/04 ,  F23R3/10 ,  F23R3/28 ,  F23R3/44 ,  F23R3/46 ,  F23R3/50 ,  F23R3/54 ,  Y02T50/675

    Abstract: A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.

    Abstract translation: 一种包括环形燃烧器的系统，其具有围绕轴线周向设置的第一衬套壁，围绕第一衬里壁周向设置的燃烧室和围绕燃烧室周向设置的第二衬套壁。 环形燃烧器被配置成将下游方向的燃烧气体流引导通过燃烧室远离头端朝向涡轮机。 该系统还包括供应通道，其构造成将来自压缩机的流体流供应到燃烧室。 供给通道具有流路结构，其具有将流体流从压缩机排出方向转动到与燃烧气体流动的下游方向大致相反的上游侧的转向部。

    COMBUSTOR SWIRLER TO DOME ATTACHMENT
    6.
    发明申请
    COMBUSTOR SWIRLER TO DOME ATTACHMENT 有权

    公开(公告)号：US20230112757A1

    公开(公告)日：2023-04-13

    申请号：US17499083

    申请日：2021-10-12

    Applicant: General Electric Company

    Inventor： Gerardo Antonio Salazar Lois ,  Nicholas John Bloom ,  Daniel J. Kirtley ,  Shai Birmaher ,  Ryan Christopher Jones

    IPC: F23R3/60 ,  F23R3/00 ,  F23R3/14

    Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome including a swirler opening therethrough with a flare interface surface surrounding the swirler opening, a swirler assembly including (a) a secondary swirler having a threaded flare attachment portion, and (b) a flare having (i) a threaded secondary swirler attachment portion, and (ii) a dome interface wall that interfaces with the flare interface surface of the CMC dome, and a swirler-dome attachment member. The flare is connected to the secondary swirler via the threaded flare attachment portion and the threaded secondary swirler attachment portion, and the swirler-dome attachment member applies a force to the CMC dome to engage the dome interface wall and the flare interface surface so as to connect the CMC dome and the swirler assembly.

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