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    Micromixer assembly for a turbine system and method of distributing an air-fuel mixture to a combustor chamber
    64.
    发明授权
    Micromixer assembly for a turbine system and method of distributing an air-fuel mixture to a combustor chamber 有权
    用于涡轮系统的微混合器组件和将空气 - 燃料混合物分配到燃烧室的方法

    公开(公告)号：US09416973B2

    公开(公告)日：2016-08-16

    申请号：US13735448

    申请日：2013-01-07

    Applicant: General Electric Company

    Inventor： Patrick Benedict Melton ,  Gregory Allen Boardman

    IPC: F23R3/28 ,  F23R3/46

    CPC classification number: F23R3/286 ,  F23R3/46 ,  F23R2900/00018

    Abstract: A micromixer assembly for a turbine system includes a plurality of pipes each having an inlet for receiving an airflow from an annulus defined by an inwardly disposed liner and an outwardly disposed sleeve, each of the plurality of pipes also including an outlet for dispersing an air-fuel mixture into a combustor chamber. Also included is a first portion of each of the plurality of pipes. Further included is a second portion of each of the plurality of pipes, the second portion comprising the inlet for receiving the airflow. Yet further included is at least one fuel receiving path in communication with at least one of the first portion and the second portion.

    Abstract translation: 用于涡轮系统的微混合器组件包括多个管，每个管具有用于接收来自由向内设置的衬套和向外设置的套筒限定的环的气流的入口，所述多个管中的每一个还包括用于分散空气 - 燃料混合物进入燃烧室。 还包括多个管道中的每一个的第一部分。 还包括多个管道中的每一个的第二部分，第二部分包括用于接收气流的入口。 还包括与第一部分和第二部分中的至少一个连通的至少一个燃料接收路径。

    System for supporting a bundled tube fuel injector within a combustor
    65.
    发明授权
    System for supporting a bundled tube fuel injector within a combustor 有权
    用于在燃烧器内支撑捆扎管式燃料喷射器的系统

    公开(公告)号：US09371997B2

    公开(公告)日：2016-06-21

    申请号：US13932301

    申请日：2013-07-01

    Applicant: General Electric Company

    Inventor： Jeffrey Scott LeBegue ,  Patrick Benedict Melton ,  James Harold Westmoreland, III ,  James Scott Flanagan

    IPC: F23R3/28

    CPC classification number: F23R3/28 ,  F23R3/283 ,  F23R3/286 ,  F23R2900/00017

    Abstract: A combustor includes an end cover having an outer side and an inner side, an outer barrel having a forward end that is adjacent to the inner side of the end cover and an aft end that is axially spaced from the forward end. An inner barrel is at least partially disposed concentrically within the outer barrel and is fixedly connected to the outer barrel. A fluid conduit extends downstream from the end cover. A first bundled tube fuel injector segment is disposed concentrically within the inner barrel. The bundled tube fuel injector segment includes a fuel plenum that is in fluid communication with the fluid conduit and a plurality of parallel tubes that extend axially through the fuel plenum. The bundled tube fuel injector segment is fixedly connected to the inner barrel.

    Abstract translation: 燃烧器包括具有外侧和内侧的端盖，外筒具有邻近端盖的内侧的前端和与前端轴向间隔开的后端。 内筒至少部分地同心地设置在外筒内并且固定地连接到外筒。 流体导管从端盖的下游延伸。 第一束管燃料喷射器段同心地设置在内筒内。 捆束管燃料喷射器部分包括与流体导管流体连通的燃料增压室和沿轴向延伸通过燃料增压室的多个平行的管。 捆扎管燃料喷射器部分固定地连接到内筒。

    End cover configuration and assembly
    67.
    发明授权
    End cover configuration and assembly 有权
    端盖配置和组装

    公开(公告)号：US09347668B2

    公开(公告)日：2016-05-24

    申请号：US13797896

    申请日：2013-03-12

    Applicant: General Electric Company

    Inventor： James Harold Westmoreland ,  Patrick Benedict Melton

    IPC: F23R3/12 ,  F23R3/28

    CPC classification number: F23R3/286 ,  F23R3/283 ,  F23R2900/00019 ,  Y10T29/494

    Abstract: A system includes an end cover for a multi-tube fuel nozzle. The end cover includes a first side, a second side disposed opposite the first side, a plurality of fuel injectors disposed on the first side, and at least one pre-orifice disposed within a passage within the end cover between the first and second sides. The pre-orifice is configured to be removed through the end cover from the second side.

    Abstract translation: 一种系统包括用于多管燃料喷嘴的端盖。 端盖包括第一侧，与第一侧相对设置的第二侧，设置在第一侧上的多个燃料喷射器，以及设置在第一侧和第二侧之间的端盖内的通道内的至少一个预孔。 预孔被构造成从第二侧通过端盖移除。

    Flow sleeve assembly for a combustion module of a gas turbine combustor
    68.
    发明授权
    Flow sleeve assembly for a combustion module of a gas turbine combustor 有权
    用于燃气轮机燃烧器的燃烧模块的流动套筒组件

    公开(公告)号：US09322556B2

    公开(公告)日：2016-04-26

    申请号：US13845378

    申请日：2013-03-18

    Applicant: General Electric Company

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

    IPC: F02C1/00 ,  F23R3/20 ,  F23R3/00 ,  F01D9/02 ,  F23R3/60

    CPC classification number: F23R3/20 ,  F01D9/023 ,  F23R3/002 ,  F23R3/60

    Abstract: A flow sleeve assembly for a combustor of a gas turbine includes an annular support sleeve disposed at a forward end of the flow sleeve assembly. The support sleeve includes a forward portion axially separated from an aft portion. An aft frame is disposed at an aft end of the flow sleeve assembly. An annular flow sleeve extends from the aft portion of the support sleeve towards the aft frame. The flow sleeve includes a forward end that is axially separated from an aft end. The forward end of the flow sleeve circumferentially surrounds the aft end of the support sleeve. An annular impingement sleeve extends between the aft end of the flow sleeve and the aft frame. A forward end of the impingement sleeve is connected to the aft end of the flow sleeve, and an aft end of the impingement sleeve is connected to the aft frame.

    Abstract translation: 用于燃气涡轮机的燃烧器的流动套筒组件包括设置在流动套筒组件的前端处的环形支撑套筒。 支撑套筒包括从后部轴向分离的前部。 后框架设置在流动套筒组件的后端。 环形流动套筒从支撑套筒的后部向后框架延伸。 流动套筒包括从后端轴向分离的前端。 流动套筒的前端周向地包围支撑套筒的后端。 环形冲击套筒在流动套筒的后端和后框架之间延伸。 冲击套筒的前端连接到流动套筒的后端，并且冲击套筒的后端连接到后架。

    System for providing fuel to a combustor
    69.
    发明授权
    System for providing fuel to a combustor 有权
    用于向燃烧器提供燃料的系统

    公开(公告)号：US09316155B2

    公开(公告)日：2016-04-19

    申请号：US13845365

    申请日：2013-03-18

    Applicant: General Electric Company

    Inventor： Richard Martin DiCintio ,  Patrick Benedict Melton ,  Lucas John Stoia ,  Christopher Paul Willis

    IPC: F02C1/00 ,  F02C7/22 ,  F01D9/02 ,  F23R3/34

    CPC classification number: F02C7/222 ,  F01D9/023 ,  F23R3/34

    Abstract: A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold.

    Abstract translation: 用于向燃气涡轮机的燃烧器提供燃料的系统包括至少部分地限定燃料增压室的环形燃料分配歧管。 燃料分配歧管包括从后端轴向分离的前端，沿着前端径向向外且周向延伸的凸缘以及从凸缘的下游延伸的环形支撑环。 LLI组件从燃料分配歧管的下游延伸。 LLI组件包括至少部分地限定燃烧器内的主燃烧区域和二次燃烧区域的单体衬套。 LLI注射器基本上径向地延伸通过单体衬套并且提供通过单体衬套到二次燃烧区域的流体连通。 与燃料增压室流体连通的流体导管在LLI喷射器和燃料分配歧管之间延伸。

    COMBUSTOR CAP ASSEMBLY
    70.
    发明申请
    COMBUSTOR CAP ASSEMBLY 有权

    公开(公告)号：US20160054002A1

    公开(公告)日：2016-02-25

    申请号：US14462637

    申请日：2014-08-19

    Applicant: General Electric Company

    Inventor： Carolyn Ashley Antoniono ,  Jonathan Hale Kegley ,  Lucas John Stoia ,  Patrick Benedict Melton ,  William Francis Carnell, JR.

    IPC: F23R3/28 ,  F02C7/18

    CPC classification number: F23R3/283 ,  F02C7/18 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate to form an impingement air plenum therebetween. The combustor cap assembly further includes a flow conditioning plate coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion. The annular portion defines a plurality of flow conditioning passages. The inner band portion at least partially defines a cooling air plenum within the combustor cap assembly. The inner band portion defines an exhaust channel which is in fluid communication with the impingement air plenum and an exhaust outlet. The flow conditioning plate further defines a cooling air passage which provides for cooling air flow into the cooling air plenum.

    Abstract translation: 燃烧器盖组件包括联接到环形护罩的冲击板和联接到冲击板的盖板，以在它们之间形成冲击空气增压室。 燃烧器盖组件还包括联接到护罩的前端部分的流动调节板。 流量调节板包括内带部分，外带部分和环形部分。 环形部分限定多个流动调节通道。 内带部分至少部分地限定在燃烧器盖组件内的冷却空气室。 内带部分限定了与冲击空气室和排气出口流体连通的排气通道。 流量调节板还限定了冷却空气通道，其提供冷却空气流入冷却空气通风室。

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