公开(公告)号：US20150308349A1

公开(公告)日：2015-10-29

申请号：US14259443

申请日：2014-04-23

Applicant: General Electric Company

Inventor： Robert Joseph Rohrssen ,  David William Cihlar ,  Patrick Benedict Melton ,  Lucas John Stoia

IPC: F02C7/32 ,  F23R3/28

CPC classification number: F02C7/32 ,  F02C7/222 ,  F23R3/002 ,  F23R3/28 ,  F23R3/283 ,  F23R3/34 ,  F23R3/346

Abstract: A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor.

Abstract translation: 提供了一种用于燃气轮机燃烧器的燃料输送系统。 燃料输送系统包括燃料管和附接组件。 燃料管从下游喷射器（例如，较晚的稀注射器）朝向燃烧器的安装环延伸，并且使用附接组件可移动地附接到安装环。 因此，示例性燃料输送系统可以向下游喷射器提供燃料，同时沿着燃烧器的轴向容纳燃料管的热膨胀或收缩。

公开(公告)号：US20150285501A1

公开(公告)日：2015-10-08

申请号：US14247509

申请日：2014-04-08

Applicant: General Electric Company

Inventor： Richard Martin DiCintio ,  Patrick Benedict Melton

IPC: F23R3/28 ,  B22F5/10 ,  B22F3/105

CPC classification number: F23R3/283 ,  B22F1/0011 ,  B22F3/1055 ,  B22F5/10 ,  B22F5/106 ,  B33Y10/00 ,  B33Y80/00 ,  C22C1/0433 ,  F23R3/14 ,  F23R3/34 ,  F23R3/346 ,  Y02P10/295

Abstract: A system for cooling a fuel injector extending into a combustion gas flow field includes a liner that defines a combustion gas flow path within a combustor and a fuel injector that extends through the liner. The fuel injector includes a main body having an annular first portion that extends outward from the liner and a second portion that extends from the first portion inward into the combustion gas flow path. The main body defines a cooling channel that is fully circumscribed within the main body and that extends between the first portion and the second portion. A cooling air inlet is defined within the annular first portion and is in fluid communication with the cooling channel. A cooling air outlet is in fluid communication with the cooling channel and is defined within the second portion downstream from the cooling air inlet.

Abstract translation: 用于冷却延伸到燃烧气体流场中的燃料喷射器的系统包括限定燃烧器内的燃烧气体流动路径和延伸穿过衬套的燃料喷射器的衬套。 燃料喷射器包括主体，其具有从衬套向外延伸的环形第一部分和从第一部分向内延伸到燃烧气体流动路径的第二部分。 主体限定了在主体内完全外接并在第一部分和第二部分之间延伸的冷却通道。 冷却空气入口限定在环形第一部分内并与冷却通道流体连通。 冷却空气出口与冷却通道流体连通并限定在冷却空气入口下游的第二部分内。

公开(公告)号：US20150198332A1

公开(公告)日：2015-07-16

申请号：US14157021

申请日：2014-01-16

Applicant: General Electric Company

Inventor： Richard Martin DiCintio ,  Patrick Benedict Melton

IPC: F23R3/20

CPC classification number: F23R3/20 ,  F23M11/00 ,  F23R3/283 ,  F23R3/34

Abstract: A combustion system is provided and includes an annular body defining a combustion zone and a fuel nozzle. The fuel nozzle includes a tubular element having a hollow interior and is disposable such that the hollow interior fluidly communicates with the combustion zone. The tubular element includes wall portions defining a channel disposable for fluid communication with at least one of the hollow interior and the combustion zone. The defined channel is pressurizable with coolant at a pressure exceeding that of the combustion zone.

Abstract translation: 提供燃烧系统并且包括限定燃烧区和燃料喷嘴的环形体。 燃料喷嘴包括具有中空内部并且是一次性的管状元件，使得中空内部与燃烧区流体连通。 管状元件包括限定通道的壁部分，该通道一次性用于与中空内部和燃烧区域中的至少一个流体连通。 限定的通道在压力超过燃烧区域的压力下可与冷却剂一起加压。

公开(公告)号：US20150159872A1

公开(公告)日：2015-06-11

申请号：US14102006

申请日：2013-12-10

Applicant: General Electric Company

Inventor： Patrick Benedict Melton ,  Richard Martin DiCintio

IPC: F23R3/08

CPC classification number: F23R3/08 ,  F23R3/06 ,  F23R3/16 ,  F23R3/283 ,  F23R3/346 ,  F23R2900/00018 ,  F23R2900/03043

Abstract: A wake reducing structure includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is a wake generating component boss operatively coupled to the combustor liner and disposed within a combustor liner aperture. Also included is a cooling channel extending through the wake generating component boss, the cooling channel having an air inlet on an upstream region of the wake generating component boss and an air outlet on a downstream region of the wake generating component boss, the cooling channel configured to supply air to the wake region.

Abstract translation: 尾流减少结构包括具有内表面和外表面的燃烧器衬套，内表面限定了燃烧室。 还包括沿着燃烧器衬套的外表面设置的气流路径。 进一步包括设置在气流路径中并且靠近燃烧器衬套的尾流产生部件，其中，尾流产生部件产生位于尾流产生部件下游的尾流区域。 另外还包括一个尾灯产生部件凸台，可操作地联接到燃烧器衬套并设置在燃烧器衬套孔内。 还包括延伸穿过尾流产生部件凸台的冷却通道，冷却通道在尾流产生部件凸台的上游区域上具有空气入口，在尾流产生部件凸起的下游区域具有空气出口，该冷却通道配置 向尾流区供应空气。

公开(公告)号：US20140260277A1

公开(公告)日：2014-09-18

申请号：US13845485

申请日：2013-03-18

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/20

CPC classification number: F23R3/20 ,  F02C7/22 ,  F23R3/005 ,  F23R3/34 ,  F23R3/46 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/03043 ,  F23R2900/03045

Abstract: A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.

Abstract translation: 用于燃气轮机的燃烧器的燃烧模块包括设置在燃烧模块的上游端的环形燃料分配歧管。 燃料分配歧管包括具有内表面的环形支撑套筒。 燃烧模块还包括燃料喷射组件，该燃料喷射组件具有环形燃烧衬套，所述环形燃烧衬套从燃料分配歧管的下游延伸并终止在后部框架处;以及环形流动套筒，其环绕燃烧衬套。 流动套筒从燃料分配歧管的下游延伸并终止于后部框架。 流动套筒在支撑套筒和后架之间连续延伸。 流动套筒的前部部分同心地定位在支撑套筒内，其中前部部分与支撑套筒的内表面滑动接合。

公开(公告)号：US20140260274A1

公开(公告)日：2014-09-18

申请号：US13845422

申请日：2013-03-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Lucas John Stoia ,  Patrick Benedict Melton ,  Stanley Kevin Widener ,  William Michael Poschel

IPC: F02C7/22

CPC classification number: F02C7/222 ,  F02C7/22 ,  F23R3/28

Abstract: A fuel distribution manifold for a combustor of a gas turbine includes an annular flange having an outer surface that extends circumferentially around the flange. A primary fuel plenum extends circumferentially within the flange. A first orifice and a second orifice extend radially through the outer surface of the flange to provide for fluid communication into the primary fuel plenum. The first orifice includes an inlet that is adjacent to the outer surface. The second orifice includes an inlet that is adjacent to the outer surface. A fuel distribution cap extends partially across the outer surface of the flange. The fuel distribution cap includes an inlet port. A fuel distribution plenum is at least partially defined within the fuel distribution cap. The fuel distribution plenum is in fluid communication with the inlet port and with the first orifice inlet and the second orifice inlet.

Abstract translation: 用于燃气涡轮机的燃烧器的燃料分配歧管包括具有围绕凸缘周向延伸的外表面的环形凸缘。 主燃料增压室在凸缘内周向延伸。 第一孔口和第二孔口径向延伸穿过凸缘的外表面以提供流体连通到主燃料增压室中。 第一孔包括邻近外表面的入口。 第二孔包括与外表面相邻的入口。 燃料分配帽部分地延伸穿过凸缘的外表面。 燃料分配盖包括入口端口。 燃料分配室至少部分地限定在燃料分配盖内。 燃料分配气室与入口端口和第一孔口入口和第二孔口入口流体连通。

公开(公告)号：US20140260272A1

公开(公告)日：2014-09-18

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: F02C7/22

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。

公开(公告)号：US20140144122A1

公开(公告)日：2014-05-29

申请号：US13688625

申请日：2012-11-29

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Brandon Taylor Overby ,  Keith Cletus Belsom ,  Jonathan Kay Allen ,  Kyle Eric Benson ,  Patrick Benedict Melton ,  Richard Martin DiCintio ,  Lucas John Stoia ,  Ronnie Ray Pentecost

IPC: F23R3/48

CPC classification number: F23R3/48

Abstract: A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.

Abstract translation: 相邻燃烧器之间的交火管组件包括适于提供来自第一燃烧器和适于连接以提供来自第二燃烧器的流体连通的第一燃烧器和第二套管的流体连通的第一套筒。 第二套筒至少部分地在第一套筒内部延伸。 偏置在第一和第二袖之间。

公开(公告)号：US20140116060A1

公开(公告)日：2014-05-01

申请号：US13663730

申请日：2012-10-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Patrick Benedict Melton ,  Bryan Wesley Romig ,  Lucas John Stoia

IPC: F02C7/18

CPC classification number: F23R3/283 ,  F23D11/36 ,  F23D14/78 ,  F23D2214/00 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: A combustor includes a first shroud extending circumferentially inside the combustor and at least partially defining an inlet passage. A second shroud extends circumferentially inside the combustor. The second shroud defines an outlet passage. A first plate extends radially inside the second shroud downstream from the inlet passage of the first shroud and upstream from the outlet passage of the second shroud. The first plate generally defines an inlet port and an outlet port. A second plate extends radially around the first plate downstream from the inlet port and upstream from the outlet port of the first plate. A first fluid flow path extends from the inlet passage to the inlet port. A second fluid flow path extends from the outlet port to the outlet passage. A baffle extends from the first shroud to the first plate. The baffle separates the first and second fluid flow paths.

Abstract translation: 燃烧器包括在燃烧器内周向延伸并且至少部分地限定入口通道的第一罩。 第二护罩在燃烧器内周向延伸。 第二护罩限定出口通道。 第一板在第二护罩的径向内部延伸，从第一护罩的入口通道下游和第二护罩的出口通道的上游延伸。 第一板通常限定入口和出口。 第二板在入口端口的下游和第一板的出口的上游围绕第一板径向延伸。 第一流体流动路径从入口通道延伸到入口端口。 第二流体流动路径从出口延伸到出口通道。 挡板从第一护罩延伸到第一板。 挡板分离第一和第二流体流动路径。

公开(公告)号：US10436445B2

公开(公告)日：2019-10-08

申请号：US13845565

申请日：2013-03-18

Applicant: General Electric Company

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

IPC: F01D9/02 ,  F23R3/60 ,  F23R3/00 ,  F01D11/18 ,  F01D25/24

Abstract: An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell.