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11.发明申请公开(公告)号：US20100293954A1
公开(公告)日：2010-11-25
申请号：US12469910
申请日：2009-05-21
IPC分类号： F02C7/22
CPC分类号： F23R3/045 , F23C2900/07022 , F23D14/48 , F23D14/76 , F23D14/82 , F23D2900/00018 , F23R3/283 , F23R2900/00005
摘要： The structure and operation of a fuel nozzle for a gas turbine combustor is disclosed where the fuel nozzle provides for flameholding protection and, more specifically, to such a nozzle that provides for nondestructive protection from flamebolding. The nozzle provides for differential thermal expansion between tubes forming fuel passages to allowing for the nondestructive venting of fuel during a flameholding condition. Upon extinguishing the flameholding condition, the nozzle returns to normal operating condition.
摘要翻译： 公开了一种用于燃气轮机燃烧器的燃料喷嘴的结构和操作，其中燃料喷嘴提供阻燃保护，更具体地，涉及提供非破坏性保护以防止燃烧的喷嘴。 喷嘴提供形成燃料通道的管之间的差分热膨胀，以允许在保持静止状态期间燃料的非破坏性排气。 熄灭保护条件后，喷嘴返回正常工作状态。
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公开(公告)号：US20100239418A1
公开(公告)日：2010-09-23
申请号：US12407525
申请日：2009-03-19
IPC分类号： F01D9/00
CPC分类号： F01D9/04 , F02C3/14 , F04D29/547 , F05D2240/12 , F05D2250/52 , F23R3/60
摘要： A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body.
摘要翻译： 一种用于涡轮发动机的扩散器，包括用于密封压缩机排出空气的环形壳体和附接到壳体的支柱以限定支柱内区域的环形阵列，并且包括环部分，其包括环形环形体，其具有向前 所述环形部分可由一个或多个所述支柱支撑，所述分隔部分包括环形环形体，所述环形环体具有设置在其后侧上的后表面， 环形部分主体，分离器部分还包括引导边缘，位于分离器部分主体的前侧，其可延伸到压缩机排出空气的流动路径中，以将流动路径分成径向地在外部和内部限定的二次流动路径 的分离器部分主体。
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公开(公告)号：US07603863B2
公开(公告)日：2009-10-20
申请号：US11422123
申请日：2006-06-05
IPC分类号： F02C3/16
CPC分类号： F23R3/20 , F23C2900/07001 , F23R3/34
摘要： A secondary combustion system for a stage one turbine nozzle. The secondary combustion system may include a supply tube extending into the stage one nozzle, a number of injectors extending from the supply tube to an outer surface of the stage one nozzle, and an air gap surrounding each of the number of injectors.
摘要翻译： 一级涡轮喷嘴二次燃烧系统。 二级燃烧系统可以包括延伸到一级喷嘴的供给管，从供给管延伸到一级喷嘴的外表面的多个喷射器以及围绕多个喷射器中的每一个的气隙。
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公开(公告)号：US08522553B2
公开(公告)日：2013-09-03
申请号：US13232191
申请日：2011-09-14
IPC分类号： F02C7/08
CPC分类号： F23R3/34 , F02C3/14 , F05D2270/082 , F23R3/286 , F23R3/42
摘要： A system for conditioning a working fluid in a combustor includes a primary combustion chamber, a liner circumferentially surrounding the primary combustion chamber, and a primary nozzle in fluid communication with the primary combustion chamber. A secondary combustion chamber located outside of the primary combustion chamber includes a shroud that defines a fluid passage, a secondary nozzle, and means for igniting fuel in the secondary combustion chamber. A method for conditioning a working fluid in a combustor includes flowing the working fluid through a primary combustion chamber and flowing at least a portion of the working fluid through a secondary combustion chamber located outside of the primary combustion chamber. The method further includes flowing a fuel through the secondary combustion chamber, combusting the fuel, and flowing the combustion gases from the secondary combustion chamber into the primary combustion chamber.
摘要翻译： 用于调节燃烧器中的工作流体的系统包括主燃烧室，周向围绕主燃烧室的衬套和与主燃烧室流体连通的主喷嘴。 位于主燃烧室外的二次燃烧室包括限定流体通道的护罩，二次喷嘴和用于点燃二次燃烧室中的燃料的装置。 用于调节燃烧器中的工作流体的方法包括使工作流体流过初级燃烧室并使至少一部分工作流体通过位于主燃烧室外部的二级燃烧室。 该方法还包括使燃料流过二次燃烧室，燃烧燃料，并使燃烧气体从二级燃烧室流入主燃烧室。
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15.发明授权Fuse for flame holding abatement in premixer of combustion chamber of gas turbine and associated method 失效燃气轮机燃烧室预混合器火焰保护用保险丝及相关方法公开(公告)号：US08281595B2
公开(公告)日：2012-10-09
申请号：US12128231
申请日：2008-05-28
CPC分类号： F23R3/286 , F23D14/82 , F23D2900/00015 , F23R3/343
摘要： A fuel nozzle assembly for a combustor of a gas turbine including: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front proximate to a combustion section of the combustor; an outer casing around the inner tube, wherein an air passage is defined between the outer casing and the inner tube; a gas conduit arranged in the air passage and having an outlet proximate to the front of the nozzle body, wherein fuel starts flowing through the expandable conduit only after a flashback condition occurs in the combustor, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein the gas conduit has an inlet open to the premix fuel passage.
摘要翻译： 一种用于燃气轮机的燃烧器的燃料喷嘴组件，包括：喷嘴体，其具有限定通过所述喷嘴主体延伸的燃料通道的前部管和内部管，其中所述前部靠近所述燃烧器的燃烧部分; 围绕所述内管的外壳，其中在所述外壳和所述内管之间限定空气通道; 布置在所述空气通道中并且具有靠近所述喷嘴主体的前部的出口的气体导管，其中仅在所述燃烧器中发生回火状态之后燃料开始流过所述可膨胀导管，以及预燃燃料通道和将燃料喷射到 燃烧器的预混合部分，其中气体管道具有通向预混合燃料通道的入口。
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公开(公告)号：US08133017B2
公开(公告)日：2012-03-13
申请号：US12407525
申请日：2009-03-19
IPC分类号： F01D25/30
CPC分类号： F01D9/04 , F02C3/14 , F04D29/547 , F05D2240/12 , F05D2250/52 , F23R3/60
摘要： A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body.
摘要翻译： 一种用于涡轮发动机的扩散器，包括用于密封压缩机排出空气的环形壳体和附接到壳体的支柱以限定支柱内区域的环形阵列，并且包括环部分，其包括环形环形体，其具有向前 所述环形部分可由一个或多个所述支柱支撑，所述分隔部分包括环形环形体，所述环形环体具有设置在其后侧上的后表面， 环形部分主体，分离器部分还包括引导边缘，位于分离器部分主体的前侧，其可延伸到压缩机排出空气的流动路径中，以将流动路径分成径向地在外部和内部限定的二次流动路径 的分离器部分主体。
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公开(公告)号：US20110067406A1
公开(公告)日：2011-03-24
申请号：US12563599
申请日：2009-09-21
IPC分类号： F02C3/14
CPC分类号： F23R3/48 , F23R2900/03044
摘要： A crossfire tube assembly is configured for connecting adjacent combustion cans in a gas turbine, and includes a first tube segment having a first end and an opposite female end. A second tube segment has a first end and an opposite male end fitted concentrically within the female end with an overlap region between the female and male ends. Each of the first ends of the tube segments is configured for securing to a liner of a respective combustion can. Oppositely oriented first and second impingement sleeves extend from the female end of the first tube segment to the respective first ends of the tube segments, Combustion cooling air is directed through metering holes in the impingement sleeves and flows axially along concentric cavities defined between the impingement sleeves and the first and second tube segments. The combustion cooling air vents from the cavities into an axial combustion air flow stream between the respective combustion can liners and sleeves.
摘要翻译： 交火管组件构造成用于连接燃气轮机中的相邻燃烧罐，并且包括具有第一端和相对的母端的第一管段。 第二管段具有第一端和相对的阳端，同心地嵌入阴端内，在阴端和阳端之间具有重叠区域。 管段的每个第一端构造成用于固定到相应燃烧罐的衬套。 相对定向的第一和第二冲击套筒从第一管段的阴端延伸到管段的相应的第一端，燃烧冷却空气被引导通过冲击套管中的计量孔，并且沿着在冲击套筒之间限定的同心腔轴向流动 以及第一和第二管段。 燃烧的冷却空气从空腔排出到相应的燃烧罐衬套和套筒之间的轴向燃烧空气流。
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18.发明授权Method and apparatus for cooling combustor liner and transition piece of a gas turbine 有权一种用于冷却燃气轮机的燃烧器衬套和过渡件的方法和装置公开(公告)号：US07493767B2
公开(公告)日：2009-02-24
申请号：US10907866
申请日：2005-04-19
申请人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson , John C Intile
发明人： Ronald Scott Bunker , Jeremy Clyde Bailey , Stanley Kevin Widener , Thomas Edward Johnson , John C Intile
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.
摘要翻译： 一种用于冷却燃烧器衬套和燃气轮机的过渡件的方法和设备包括具有多个湍流器的燃烧器衬套，该多个湍流器沿着限定燃烧器衬套的长度并位于其外表面上的长度轴向排列; 围绕所述燃烧器衬套的第一流动套筒，其间具有第一流动环空，所述第一流动套筒具有围绕所述第一流动套筒的圆周形成的多排冷却孔，用于将冷却空气从所述压缩机排出口引导到所述第一流动环空中; 连接到所述燃烧器衬套并适于将热燃烧气体运送到所述涡轮机的级的过渡件; 围绕所述过渡件的第二流动套筒，用于将冷却空气引导到所述第二流动套筒和所述过渡件之间的第二流动环空中的第二多排冷却孔; 其中所述第一多个冷却孔和第二多个冷却孔分别配置有有效区域以将小于50％的压缩机排出空气分配到所述第一流动套筒并与来自所述第二流动环的冷却空气混合。
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公开(公告)号：US07373778B2
公开(公告)日：2008-05-20
申请号：US10711131
申请日：2004-08-26
IPC分类号： F02C1/00
CPC分类号： F02C7/12 , F01D25/12 , F01D25/14 , F02C7/18 , F05D2240/35 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F23R3/005
摘要： A combustor liner for a gas turbine includes a body having a plurality of angled strips on an outside surface of the combustor liner. The plurality of angled strips are arranged in an array about the outside surface. A space is disposed between each of said plurality of angled strips so as to create vortices in a cooling air flowing in a longitudinal direction across said outside surface of said combustor liner. A method of fabricating a combustor liner includes forming a plurality of angled strips on an outside surface of the combustor liner and arranged in an array about the outside surface, each of the angled strips is disposed so as to be spaced apart to create vortices in a cooling air flowing across the outside surface of the combustor liner.
摘要翻译： 用于燃气轮机的燃烧器衬套包括在燃烧器衬套的外表面上具有多个成角度的条带的主体。 多个成角度的条带围绕外表面布置成阵列。 在所述多个成角度的条带中的每一个之间设置一个空间，以便在穿过所述燃烧器衬套的所述外表面沿纵向方向流动的冷却空气中产生涡流。 一种制造燃烧器衬套的方法包括在燃烧器衬套的外表面上形成多个成角度的带，并围绕外表面排列成阵列，每个成角度的带被设置为间隔开以形成涡流 流过燃烧器衬套的外表面的冷却空气。
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公开(公告)号：US20070277531A1
公开(公告)日：2007-12-06
申请号：US11422123
申请日：2006-06-05
CPC分类号： F23R3/20 , F23C2900/07001 , F23R3/34
摘要： A secondary combustion system for a stage one turbine nozzle. The secondary combustion system may include a supply tube extending into the stage one nozzle, a number of injectors extending from the supply tube to an outer surface of the stage one nozzle, and an air gap surrounding each of the number of injectors.
摘要翻译： 一级涡轮喷嘴二次燃烧系统。 二级燃烧系统可以包括延伸到一级喷嘴的供给管，从供给管延伸到一级喷嘴的外表面的多个喷射器以及围绕多个喷射器中的每一个的气隙。
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