公开(公告)号：US20160169113A1

公开(公告)日：2016-06-16

申请号：US14568394

申请日：2014-12-12

Applicant: General Electric Company

Inventor： Mark Carmine Bellino ,  Lucas John Stoia ,  Christopher Paul Willis

IPC: F02C7/24 ,  F01D25/14 ,  F02C7/32

CPC classification number: F02C7/24 ,  F01D9/023 ,  F01D25/145 ,  F02C7/28 ,  F02C7/32 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2240/90 ,  F05D2260/30 ,  Y02T50/675

Abstract: Aft frame assemblies for aft ends of gas turbine transition pieces comprise a body comprising a downstream facing seal surface on an aft end, wherein at least a portion of the downstream facing seal surface configured to be exposed to a combustion discharge stream, a heat shield disposed proximate the aft end of the body, wherein the heat shield is configured to deflect at least a portion of the combustion discharge stream away from the aft end of the body, and, one or more heat shield supports connected to the body and configured to at least partially restrict deflection of the heat shield back towards the body.

Abstract translation: 用于燃气轮机过渡件的后端的后框架组件包括主体，该主体包括位于后端的下游面对的密封表面，其中下游侧面向密封表面的至少一部分构造成暴露于燃烧排放流， 靠近所述主体的后端，其中所述隔热罩构造成使所述燃烧排放流的至少一部分偏离所述主体的后端，以及一个或多个隔热支撑件，其连接到所述主体并且被配置为 至少部分地限制隔热板向身体的偏转。

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。

公开(公告)号：US20150082806A1

公开(公告)日：2015-03-26

申请号：US14032225

申请日：2013-09-20

Applicant: General Electric Company

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

IPC: F02C7/32 ,  B23K1/00

CPC classification number: F23R3/286 ,  B23K1/0018 ,  F23R3/283 ,  F23R2900/00017 ,  F23R2900/00018

Abstract: The present application provides a fuel plenum for a micro-mixer combustor. The fuel plenum may include a first assembly plate with a first assembly plate aperture, a second assembly plate with a second assembly plate aperture, a fuel tube extending through the first assembly plate aperture of the first assembly plate and the second assembly plate aperture of the second assembly plate, and an installation insert positioned between the fuel tube and the first assembly plate aperture.

Abstract translation: 本申请提供了一种用于微型混合器燃烧器的燃料增压室。 燃料增压室可以包括具有第一组件板孔的第一组件板，具有第二组件板孔的第二组件板，延伸穿过第一组件板的第一组件板孔的燃料管和第二组合板孔 第二组装板和位于燃料管和第一组装板孔之间的安装插入件。

公开(公告)号：US20140260318A1

公开(公告)日：2014-09-18

申请号：US13845617

申请日：2013-03-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Christopher Paul Willis ,  Richard Martin DiCintio ,  Ronnie Ray Pentecost ,  Christopher Crookshanks

IPC: F02C7/20

CPC classification number: F02C7/20 ,  F01D9/023 ,  F01D11/003 ,  F23R3/002 ,  F23R3/46 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017

Abstract: A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall that extend outward from the first side of the aft frame. A first segment of the upstream wall extends from an inner portion of the aft frame towards an outer portion of the aft frame at a first outward distance from the first side. A second segment of the upstream wall extends from the first segment to the outer portion of the aft frame at a second outward distance from the first side. The second segment of the upstream wall at least partially defines a side seal guide feature to allow for axial insertion of a bottom portion of a side seal into the side seal slot.

Abstract translation: 侧密封槽沿着用于燃气轮机的燃烧衬套的后框架的一侧延伸。 侧密封槽至少部分地限定在从后框架的第一侧向外延伸的下游壁和上游壁之间。 上游壁的第一段从后框架的内部部分朝着离开第一侧的第一向外的距离朝向后部框架的外部部分延伸。 上游壁的第二段从第一侧面以第二向外的距离从后框架的第一部分延伸到外部部分。 上游壁的第二段至少部分地限定侧密封引导件特征，以允许侧密封件的底部部分轴向插入到侧密封槽中。

公开(公告)号：US20140260280A1

公开(公告)日：2014-09-18

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: F23R3/00

CPC classification number: F23R3/002 ,  F01D9/023 ,  F01D11/18 ,  F01D25/24 ,  F05D2230/642 ,  F05D2300/50212 ,  F23R3/005 ,  F23R3/60 ,  F23R2900/00012

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.

Abstract translation: 用于控制燃气涡轮机内的衬套和静止喷嘴之间的间隙的组件包括具有设置在衬套的后端的后框架的环形衬套和联接到后架的安装支架。 组件还包括涡轮机，其具有至少部分地限定涡轮机入口的外涡轮机外壳和内涡轮机外壳。 固定喷嘴设置在后框架和入口之间。 固定喷嘴包括顶部平台部分，其具有朝向后部框架延伸的前缘和底部平台部分。 在后框架的后端和顶部平台部分的前缘之间限定间隙。 安装支架联接到外涡轮机外壳，而固定喷嘴与内涡轮机外壳相连。