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公开(公告)号：EP2532966A3
公开(公告)日：2015-04-22
申请号：EP12171075.0
申请日：2012-06-06
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F23R3/28 , F23R2900/00005
摘要： A combustor nozzle includes a downstream side (50) having an axial centerline (44). A plurality of passages (54) through the downstream side (50) provide fluid communication through the downstream side (50), and a downstream section (66) of each passage (54) has at least one of a frusto-conical (62) or frusto-spherical shape (74). A method for modifying a combustor nozzle includes machining the downstream side (50) of a body (46) to remove a recast surface (56) in a plurality of passages (54) that provide fluid communication through the body (46). The method may further include machining a downstream section (66) in each passage (54) to form at least one of a frusto-conical (62) or frusto-spherical surface in each passage proximate to the downstream side (50) of the body (46).
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公开(公告)号：EP2527739A3
公开(公告)日：2013-09-18
申请号：EP12168558.0
申请日：2012-05-18
摘要： A system includes a gas turbine combustor (16), which includes a combustion liner (42) disposed about a combustion region, a flow sleeve (44) disposed about the combustion liner (42), an air passage (46) between the combustion liner (42) and the flow sleeve (44), and a structure (66) between the combustion liner (42) and the flow sleeve (44). The structure (66) obstructs an airflow (64) through the air passage (46). The gas turbine combustor (16) also includes a wake reducer (71) disposed adjacent the structure (66). The wake reducer (71) directs a flow (78) into a wake region (67) downstream of the structure (66).
摘要翻译： 一种系统包括燃气轮机燃烧器（16），其包括围绕燃烧区域设置的燃烧衬套（42），布置在燃烧衬套（42）周围的流动套筒（44），位于燃烧衬套 （42）和流动套筒（44）之间，以及在燃烧衬套（42）和流动套筒（44）之间的结构（66）。 结构（66）阻挡通过空气通道（46）的气流（64）。 燃气轮机燃烧器（16）还包括邻近结构（66）设置的尾流减压器（71）。 尾流减少器（71）将流体（78）引导到结构（66）下游的尾流区域（67）中。
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公开(公告)号：EP2532961A2
公开(公告)日：2012-12-12
申请号：EP12170068.6
申请日：2012-05-30
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23R3/04 , F23R3/10 , F23R3/286 , F23R2900/03044 , Y10T29/49348
摘要： A combustor (10) having a pressure feed is provided and includes an outer vessel (20), an intermediate vessel (30) disposed within the outer vessel (20) to form an outer annulus (35), an inner vessel (40) disposed within the intermediate vessel (30) to form an inner annulus (45) between the intermediate and inner vessels, by which upstream portions (471) of fuel nozzles (47) disposed within the inner vessel are fed, and an internal volume (48) within the inner vessel about downstream portions (472) of the fuel nozzles (47) and a tubular assembly (50) by which the outer annulus (35) and the internal volume (48) are communicative.
摘要翻译： 提供了具有压力进料的燃烧器（10），其包括外部容器（20），设置在外部容器（20）内的中间容器（30），以形成外部环空（35），内部容器（40） 在所述中间容器（30）内形成在所述中间容器和所述内部容器之间形成的内部环（45），由此设置在所述内部容器内的燃料喷嘴（47）的上游部分（471）被供给，以及内部容积（48） 内部容器内的燃料喷嘴（47）的下游部分（472）和管状组件（50）之间，外环（35）和内部容积（48）通过该管状组件连通。
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公开(公告)号：EP2532836A2
公开(公告)日：2012-12-12
申请号：EP12169891.4
申请日：2012-05-29
IPC分类号： F01D9/02
CPC分类号： F01D9/023
摘要： An apparatus is disclosed which includes a body (102) configured to flow hot gases (42) of combustion between a forward end (104) and an aft end (106). Additionally, the body (102) includes a plurality of raised sections (116) spaced apart circumferentially around an outer perimeter of the body (102). The raised section (116) may generally extend lengthwise between the forward and aft ends (104, 106).
摘要翻译： 公开了一种装置，其包括构造成在前端（104）和后端（106）之间流动燃烧的热气体（42）的主体（102）。 另外，主体（102）包括围绕主体（102）的外周缘周向间隔开的多个凸起部分（116）。 升高部分（116）可以大体上在前端和后端（104,106）之间的纵向延伸。
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公开(公告)号：EP2527739B1
公开(公告)日：2018-07-11
申请号：EP12168558.0
申请日：2012-05-18
摘要： A system includes a gas turbine combustor (16), which includes a combustion liner (42) disposed about a combustion region, a flow sleeve (44) disposed about the combustion liner (42), an air passage (46) between the combustion liner (42) and the flow sleeve (44), and a structure (66) between the combustion liner (42) and the flow sleeve (44). The structure (66) obstructs an airflow (64) through the air passage (46). The gas turbine combustor (16) also includes a wake reducer (71) disposed adjacent the structure (66). The wake reducer (71) directs a flow (78) into a wake region (67) downstream of the structure (66).
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公开(公告)号：EP2532836A3
公开(公告)日：2014-04-09
申请号：EP12169891.4
申请日：2012-05-29
CPC分类号： F01D9/023
摘要： An apparatus is disclosed which includes a body (102) configured to flow hot gases (42) of combustion between a forward end (104) and an aft end (106). Additionally, the body (102) includes a plurality of raised sections (116) spaced apart circumferentially around an outer perimeter of the body (102). The raised section (116) may generally extend lengthwise between the forward and aft ends (104, 106).
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公开(公告)号：EP2532967A3
公开(公告)日：2014-01-08
申请号：EP12171076.8
申请日：2012-06-06
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F23R3/002 , F23R2900/00005 , Y10T29/49348
摘要： A combustor nozzle (14) includes a downstream surface (52) having an axial centerline (44). A plurality of passages (54) extend through the downstream surface (52) and provide fluid communication through the downstream surface (52). A plurality of slits (56, 58) are included in the downstream surface (52), and each slit (56, 58) connects to at least two passages (54). A method for modifying a combustor nozzle (14) includes machining a plurality of slits (56, 58) in a downstream side (50) of a body (46). The method further includes connecting each slit (56, 58) to at least two passages (54) that pass through the body (46).
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公开(公告)号：EP2532969A2
公开(公告)日：2012-12-12
申请号：EP12169990.4
申请日：2012-05-30
发明人： Melton, Patrick Bendict , Belsom, Keith Cletus , Johnson, Thomas Edward , Byrne, William Lawrence , Rohrssen, Robert Joseph
IPC分类号： F23R3/60
CPC分类号： F23R3/60 , F23R2900/00012
摘要： A flexible annular seal (10) for insertion between concentrically assembled turbine combustor components includes an annular inner seal portion (12) having a first solid annular edge (16) and first plurality of spring fingers (14) extending axially from the first solid annular edge; and an annular outer seal portion (18) having a second solid annular edge (22) and a second plurality of spring fingers (20) extending axially from the second solid edge and overlying the first plurality of spring fingers such that the inner and outer seal portions are substantially fully engaged along an entire length dimension of the flexible annular seal. The second plurality of spring fingers (20) are circumferentially offset from the first plurality of spring fingers, and free ends of the first plurality of spring fingers (14) are bent around and over free ends of the second plurality of spring fingers (20).
摘要翻译： 用于插入在同心组装的涡轮机燃烧器部件之间的柔性环形密封件（10）包括具有第一固体环形边缘（16）的环形内密封部分（12）和从第一固体环形边缘轴向延伸的第一多个弹簧指 ; 以及具有第二固体环形边缘（22）和第二多个弹簧指（20）的环形外密封部分（18），所述第二固定环形边缘（22）和所述第二多个弹簧指（20）从所述第二实心边缘轴向延伸并且覆盖所述第一多个弹簧指， 部分沿着柔性环形密封件的整个长度尺寸基本上完全接合。 所述第二多个弹簧指（20）在周向上偏离所述第一多个弹簧指，并且所述第一多个弹簧指（14）的自由端在所述第二多个弹簧指（20）的自由端周围和上方弯曲， 。
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9.发明公开Integrated late lean injection on a combustion liner and late lean injection sleeve assembly 审中-公开集成，延迟贫喷射到燃烧室外套和套筒组件，用于延迟贫喷射
公开(公告)号：EP2532968A2
公开(公告)日：2012-12-12
申请号：EP12170621.2
申请日：2012-06-01
摘要： A late lean injection sleeve assembly (25) allows the injection of fuel at the aft end of a gas turbine liner (23), before the transition piece (24), into the combustion gases downstream of a turbine combustor's fuel nozzles (21). The late lean injection enables fuel injection downstream of the fuel nozzles (21) to create a secondary/tertiary (with quaternary injection upstream of the fuel nozzles (21)) combustion zone while reducing/eliminating the risk of fuel leaking into the combustion discharge case. The fuel is delivered by the flow sleeve (25) into one or more nozzles (30) that mix the fuel (13) with CDC air before injecting it into the combustor's liner (23).
摘要翻译： 延迟贫喷射套筒组件（25），允许燃料在燃气涡轮机衬套（23）的后端的注射，所述过渡件（24）到涡轮机燃烧器的燃料喷嘴（21）的下游的燃烧气体之前。 延迟贫喷射启用燃料喷嘴的下游的燃料喷射（21）至燃烧区，同时减少/消除燃料泄漏到燃烧放电情况下的风险（燃料喷嘴（21）的上游与季注射）来创建第二/第三 ， 燃料通过流动套管（25）输送到一个或多个喷嘴（30），确实将其注入之前混合与CDC空气燃料（13）的燃烧器衬套的（23）。
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10.发明公开System and method for turbine combustor mounting assembly 审中-公开System and Verfahrenfüreine Turbinenbrennkammermonnamanordnung
公开(公告)号：EP2527744A2
公开(公告)日：2012-11-28
申请号：EP12168511.9
申请日：2012-05-18
CPC分类号： F23R3/60 , F23D2900/14004 , F23R3/002 , F23R2900/03043 , Y02T50/675
摘要： A system includes a gas turbine combustor (16), which includes a combustion liner (42) disposed about a combustion region, a flow sleeve (44) disposed about the combustion liner (42), an air passage (46) between the combustion liner (42) and the flow sleeve (44), and an aerodynamic mounting assembly (66) disposed in the air passage (46). The aerodynamic mounting assembly (66) is configured to retain the combustion liner (42) within the flow sleeve (44). The aerodynamic mounting assembly (66) includes a flow sleeve mount (68) coupled to the flow sleeve (44) and a liner stop (70) coupled to the combustion liner (42). The flow sleeve mount (68) includes a first portion of an aerodynamic shape and the liner stop (70) includes a second portion of the aerodynamic shape, which is configured to direct an airflow (82) into a wake region (67) downstream of the aerodynamic mounting assembly (66). The flow sleeve mount (68) and the liner stop (70) couple with one another to define the aerodynamic shape.
摘要翻译： 一种系统包括燃气轮机燃烧器（16），其包括围绕燃烧区域设置的燃烧衬套（42），围绕燃烧衬套（42）设置的流动套管（44），在燃烧衬套 （42）和流动套筒（44）以及设置在空气通道（46）中的空气动力学安装组件（66）。 空气动力学安装组件（66）构造成将燃烧衬套（42）保持在流动套管（44）内。 空气动力学安装组件（66）包括联接到流动套管（44）的流动套管安装件（68）和联接到燃烧衬套（42）的衬套止动件（70）。 流动套管安装件（68）包括空气动力学形状的第一部分，并且衬套止动件（70）包括空气动力学形状的第二部分，其被构造成将气流（82）引导到尾流区域（67） 空气动力学安装组件（66）。 流动套筒安装件（68）和衬套止动件（70）彼此联接以限定空气动力学形状。
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