公开(公告)号：EP1826490B1

公开(公告)日：2015-09-30

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 ,  F23R3/14 ,  F23R3/28

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

公开(公告)号：EP1826490A3

公开(公告)日：2013-11-06

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 ,  F23R3/14 ,  F23R3/28

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.

公开(公告)号：EP1507118A3

公开(公告)日：2013-01-16

申请号：EP04254712.5

申请日：2004-08-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： McMasters, Maria Ann ,  Thompson, James Edward ,  Cimmarusti, Gregory Allen ,  Cooper, James Neil ,  Wiehe, Glenn Edward

IPC: F23R3/14 ,  F23R3/10

CPC classification number: F23R3/14 ,  F23D2211/00 ,  F23R3/10 ,  F23R3/60

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 formed therein, wherein a radial section is defined between adjacent openings; an annular outer cowl (38) connected to the outer portion (32) of the dome plate (20); an annular inner cowl (44) connected to the inner portion (30) of the dome plate (20); and, a swirler (26) located between the forward surface (34) of the dome plate (20) and the inner and outer cowls (44,38) in substantial alignment with each of the openings (36) in the dome plate (20). Each swirler (26) further includes a forward portion (50) and an aft portion (52) and is retained by at least one tab member (54, 56) located upstream thereof so as to be movable in a radial and axial direction.

公开(公告)号：EP1510759A1

公开(公告)日：2005-03-02

申请号：EP04254713.3

申请日：2004-08-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： McMasters, Marie Ann ,  Vermeersch, Michael Louis ,  Danis, Allen Michael ,  Cooper, James Neil ,  Thomsen, Duane Douglas ,  Cimmarusti, Gregory Allen

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R3/10 ,  F23R3/50

Abstract: A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough includes: an annular dome plate (20) having an inner portion (30), an outer portion (32), a forward surface, and a plurality of circumferentially spaced openings (36) formed therein, wherein a radial section defined between each of the openings (36) includes a cooling trough (35) formed therein; and, a free floating swirler (26) located upstream of the dome plate (20) in substantial alignment with each of the openings (36) in the dome plate (20), the swirler (26) including a forward portion (50) and an aft portion (52). The aft portion (52) of each swirler (26) is configured so as to permit air flow to the cooling trough (35) during operation of the gas turbine engine. In particular, the swirler aft portion (52) includes a substantially annular flange (74) extending adjacent to the forward surface of the dome plate (20), wherein opposing portions of a circumference for the flange (74) adjacent the radial sections of the dome plate (20) are substantially linear.

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），前表面和多个周向间隔开 在其中形成的开口（36），其中限定在每个开口（36）之间的径向部分包括形成在其中的冷却槽（35） 以及位于所述圆顶板（20）上游的与所述圆顶板（20）中的每个所述开口（36）大致对准的自由浮动旋流器（26），所述旋流器（26）包括前部（50）和 后部（52）。 每个旋流器（26）的后部（52）构造成在燃气涡轮发动机的操作期间允许空气流到冷却槽（35）。 特别地，旋流器后部部分（52）包括邻近圆顶板（20）的前表面延伸的大致环形的凸缘（74），其中用于凸缘（74）的圆周的相对部分邻近圆顶板 圆顶板（20）基本上是线性的。

公开(公告)号：EP1507118A2

公开(公告)日：2005-02-16

申请号：EP04254712.5

申请日：2004-08-05

Applicant: General Electric Company

Inventor： McMasters, Maria Ann ,  Thompson, James Edward ,  Cimmarusti, Gregory Allen ,  Cooper, James Neil ,  Wiehe, Glenn Edward

IPC: F23R3/14

CPC classification number: F23R3/14 ,  F23D2211/00 ,  F23R3/10 ,  F23R3/60

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 formed therein, wherein a radial section is defined between adjacent openings; an annular outer cowl (38) connected to the outer portion (32) of the dome plate (20); an annular inner cowl (44) connected to the inner portion (30) of the dome plate (20); and, a swirler (26) located between the forward surface (34) of the dome plate (20) and the inner and outer cowls (44,38) in substantial alignment with each of the openings (36) in the dome plate (20). Each swirler (26) further includes a forward portion (50) and an aft portion (52) and is retained by at least one tab member (54, 56) located upstream thereof so as to be movable in a radial and axial direction.

Abstract translation: 一个环形设计圆顶板（20）上具有外部部分（32）的内部部分（30），前表面（34）和多个：具有纵向中心轴线延伸穿过那里，包括燃烧器圆顶组件用于燃气涡轮发动机 的周向间隔开的开口形成于其中，worin的径向截面被相邻的开口之间限定; 环形设计外部整流罩（38），其连接到圆顶板（20）的外部分（32）; 环形设计内罩（44），其连接到圆顶板（20）的内部分（30）; 并且，位于圆顶板（20）和所述内和外整流罩（44,38）基本对准与每个在圆顶板中的开口（36）的所述前表面（34）之间的旋流器（26）（20 ）。 每个旋流器（26）还包括一个前部（50）和后部（52），并且通过位于其上游的至少一个翼片部件（54,56）保持，以便在径向和轴向方向上移动。

公开(公告)号：EP1186832A3

公开(公告)日：2002-04-24

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.

Abstract translation: 一种用于燃气涡轮发动机的两级燃料喷嘴组件（56）。 主燃烧区域（120）位于中央，并且包括被一个或多个涡流室（132,160）包围的燃料喷射器（122），以提供被点燃以限定第一阶段燃烧区域的燃料空气混合物。 二次燃烧区域由围绕主燃烧区域（120）的环形壳体（168）提供，并且其包括具有径向向外指向的开口（172）并且被环形圈（120）包围的次级燃料喷射器（126） 128），其包括用于为所述第二燃烧区域（124）提供涡流室的开口（194）。 冷却空气在初级燃烧区和次级燃烧区之间有角度地引导，以延迟混合，从而允许相应区在更下游的聚结之前更完全地燃烧。 在怠速和低发动机功率状态期间主燃烧区域（120）被激活，并且在高发动机功率状态期间主燃烧区域（120）和次燃烧区域（124）都被激活。

公开(公告)号：EP0564170A1

公开(公告)日：1993-10-06

申请号：EP93302309.5

申请日：1993-03-25

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Falls, Stephen Winthrop ,  Roberts Jr, Hubert Smith ,  Cooper, James Neil ,  Melton, Stephen Eugene

IPC: F23R3/34

CPC classification number: F23R3/50 ,  F23R3/34

Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes (22,21). A centerbody (50) is disposed between the inner and outer domes (22,21) and is constructed of a plurality of closed cell segments (51). Each segment includes an upper face (52), a lower face (53), an upstream face (54) and a downstream end (55). The upper and lower faces include flanges (56,57) extending therefrom to form cavities (58,59), within which are cooling holes (60,61). Pins are also provided which extend between the upper and lower faces of the centerbody to augment the cooling and structural connection thereof.

Abstract translation: 具有同心配置的内外环形燃烧器的双环形燃烧器设置有内圆顶和外圆顶（22,21）。 中心体（50）设置在内圆顶（22,21）之间，并由多个闭孔单元（51）构成。 每个部分包括上表面（52），下表面（53），上游面（54）和下游端（55）。 上表面和下表面包括从其延伸的凸缘（56,57）以形成空腔（58,59），其中是冷却孔（60,61）。 还提供了在中心体的上表面和下表面之间延伸的销以增加其冷却和结构连接。