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    Method and apparatus for gas turbine engines
    13.
    发明公开
    Method and apparatus for gas turbine engines 有权
    Gasturbinentriebwerk

    公开(公告)号：EP1826490A2

    公开(公告)日：2007-08-29

    申请号：EP07102366.7

    申请日：2007-02-14

    Applicant: General Electric Company

    Inventor： Devane, Shaun Michael ,  Show, Erika Suzanne ,  Wiehe, Glenn Edward ,  Umbaugh, Timothy Glen ,  Cooper, James Neil ,  Wenclik, Mateusz Pawel ,  Krol, Marek Krzysztof

    IPC: F23R3/00

    CPC classification number: F23R3/002 ,  F23R3/14 ,  F23R3/283 ,  F23R3/286 ,  F23R2900/00005 ,  F23R2900/00017 ,  F23R2900/03044

    Abstract: A heat shield assembly (100) for a gas turbine engine combustor is provided. The combustor (16) includes a domeplate (70) and at least one fuel injector (58) extending through an opening (80) in the domeplate. The heat shield assembly includes a heat shield (110) coupled against a downstream side of the domeplate, a threaded collar (124) extending upstream from the heatshield, the threaded collar received within the domeplate opening, and a retainer (112) coupled to the collar such that the domeplate is securely coupled between the heat shield and the retainer.

    Abstract translation: 提供了一种用于燃气涡轮发动机燃烧器的隔热罩组件（100）。 燃烧器（16）包括多孔板（70）和至少一个燃烧喷射器（58），该燃料喷射器（58）延伸穿过主体板中的开口（80）。 所述隔热罩组件包括联接到所述多孔板的下游侧的隔热罩（110），从所述遮光罩的上游延伸的螺纹轴环（124），所述螺纹轴环接收在所述多孔板开口内，以及保持器（112） 使得所述三脚架牢固地联接在所述隔热罩和所述保持器之间。

    Method for decreasing a heat load on a combustor liner
    14.
    发明公开
    Method for decreasing a heat load on a combustor liner 有权
    Verfahren zur Verminderung derWärmebelastungeiner Brennkammerwand

    公开(公告)号：EP1104872A1

    公开(公告)日：2001-06-06

    申请号：EP00310678.8

    申请日：2000-12-01

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Hagle, Michael P. ,  Cooper, James Neil ,  Jih, Junhaur

    IPC: F23R3/08

    CPC classification number: F23R3/08 ,  Y02T50/675

    Abstract: A combustor liner (60) has a stepped combustor liner surface (62) and an overhang portion (66) forming an air cooling slot (64). A contoured rear facing edge (70) of the overhang portion reduces turbulence of combustion gas flow and reduces a combustor liner surface area exposed to combustion gases. A thermal barrier coating (78) is also applied to the contoured rear facing edge, reducing heat flow into the overhang portion and hence reducing the operating temperature of the combustor liner. Thus, the amount of cooling air is reduced, which can reduce exhaust emissions, increase engine performance and extend a working life of the combustor assembly.

    Abstract translation: 燃烧器衬套（60）具有阶梯式燃烧器衬套表面（62）和形成空气冷却槽（64）的伸出部分（66）。 突出部分的轮廓形的后向边缘（70）减少燃烧气体流动的湍流并减少暴露于燃烧气体的燃烧室衬套表面积。 隔热涂层（78）也被施加到轮廓的后向边缘，减少进入悬垂部分的热量，从而降低燃烧器衬套的操作温度。 因此，冷却空气的量减少，这可以减少废气排放，增加发动机性能并延长燃烧器组件的使用寿命。

    Combustor dome assembly of a gas turbine engine having improved deflector plates
    18.
    发明公开
    Combustor dome assembly of a gas turbine engine having improved deflector plates 有权
    Brennkammerdomfüreine Gasturbine mit verbesserter Ablenkungsplatte

    公开(公告)号：EP1507121A2

    公开(公告)日：2005-02-16

    申请号：EP04254573.1

    申请日：2004-07-30

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： McMasters, Marie Ann ,  Cooper, James Neil ,  Thomsen, Duane Douglas ,  Vandike, John Lawrence ,  Vermeersch, Michael Louis ,  Danis, Allen Michael

    IPC: F23R3/60 ,  F23R3/10

    CPC classification number: F23R3/10 ,  F23R2900/00005

    Abstract: A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate (20) having an inner portion (30), an outer portion (32), a forward surface (34), and a plurality of circumferentially spaced openings (36) formed therein, wherein a radial section (37) defined between each of the openings (36) includes a cooling trough (35) formed therein; an outer cowl (38) connected to the dome plate outer portion (32) at a downstream end (39) thereof; an inner cowl (44) connected to the dome plate inner portion (30) at a downstream end (45) thereof; and, a deflector plate (28) connected to and positioned aft of each opening (36) in the dome plate (20).

    Abstract translation: 一种用于燃气涡轮发动机的燃烧器圆顶组件，其具有延伸穿过其中的纵向中心线轴线，包括：环形圆顶板（20），其具有内部部分（30），外部部分（32），前表面（34）和 在其中形成有多个周向间隔开的开口（36），其中限定在每个开口（36）之间的径向部分（37）包括形成在其中的冷却槽（35） 在所述圆顶板外部部分（32）的下游端（39）连接有外罩（38） 在其下游端（45）处连接到所述圆顶板内部（30）的内​​罩（44） 以及连接到所述圆顶板（20）中的每个开口（36）的后部并定位的偏转板（28）。

    Fuel nozzle assembly for reduced exhaust emissions
    19.
    发明公开
    Fuel nozzle assembly for reduced exhaust emissions 有权
    用于减少废气排放的燃料喷射器喷嘴组合件

    公开(公告)号：EP1186832A2

    公开(公告)日：2002-03-13

    申请号：EP01307493.5

    申请日：2001-09-04

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Hura, Harjit Singh ,  Cooper, James Neil ,  Mongia, Hukam Chand ,  Sabla, Paul Edward ,  Duncan, Beverly Stephenson ,  Lohmueller, Steven Joseph

    IPC: F23R3/34

    CPC classification number: F23R3/346 ,  F23C2201/20 ,  F23C2201/401

    Abstract: A two-stage fuel nozzle assembly (56) for a gas turbine engine. The primary combustion region (120) is centrally positioned and includes a fuel injector (122) that is surrounded by one or more swirl chambers (132, 160) to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing (168) that surrounds the primary combustion region (120) and it includes a secondary fuel injector (126) having a radially-outwardly-directed opening (172) and surrounded by an annular ring (128) that includes openings (194) for providing a swirl chamber for the secondary combustion region (124). Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region (120) is activated during idle and low engine power conditions, and both the primary (120) and secondary (124) combustion regions are activated during high engine power conditions.

    Apparatus for flanging a separating crown between concentric rings of burners in a multiple combustor
    20.
    发明公开
    Apparatus for flanging a separating crown between concentric rings of burners in a multiple combustor 有权
    用于多级燃烧室的燃烧器同心环之间分离冠法兰装置

    公开(公告)号：EP0907053A2

    公开(公告)日：1999-04-07

    申请号：EP98308035.9

    申请日：1998-10-02

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael ,  Legger, David Brian ,  Albers, Robert Joseph ,  Cimmarusti, Gregory Allen ,  Cooper, James Neil

    IPC: F23R3/60 ,  F23R3/34

    CPC classification number: F23R3/60 ,  F23R3/10 ,  F23R3/50

    Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors including an inner dome having an inner portion and an outer portion (28), an outer dome having an inner portion and an outer portion (25), wherein the outer dome inner portion (25) is connected to the inner dome outer portion (28), and a substantially annular centerbody (50) disposed between the inner dome and the outer dome. The centerbody includes a plurality of structurally independent arcuate segments (51), wherein each centerbody segment is retained in position via an interference fit between a first flange (59) of such centerbody extending downstream and a hook (58) in the inner dome outer portion and/or via a clamping fit of a second flange of the centerbody extending upstream to a flange of the inner dome outer portion.

    Abstract translation: 双环形燃烧室具有同心地设置内部和外部环形燃烧器包括在内部穹顶具有在内侧部分和上外侧部分（28），（在外圆顶具有在内侧部分和上外侧部分（25），其中所述外圆顶内部分 25）被连接到所述内圆顶外部分（28），和一个基本为环形的设计中心体（50），设置在内部穹顶和外圆顶之间。 所述中心体包括结构上独立的弧形段（51）worin每个中心主体部分的多个通孔在过盈配合的搜索中心体的第一凸缘（59）之间被保持在位置延伸在所述内圆顶外部下游和一个钩（58） 和/或经由中心主体延伸上游到内圆顶外部的凸缘的第二凸缘的夹紧配合。

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