-
1.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。
-
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。
-
公开(公告)号：US20070277530A1
公开(公告)日：2007-12-06
申请号：US11443724
申请日：2006-05-31
IPC分类号： F02C1/00
摘要： A method of operating a gas turbine engine includes providing an inlet flow conditioner (IFC). The IFC has an annular chamber defined therein by at least one wall wherein the wall includes a plurality of perforations extending therethrough. The perforations are spaced in at least two axially-spaced rows that extend circumferentially about the wall. The method also includes channeling a fluid into the IFC and discharging the fluid from the IFC with a substantially uniform flow profile.
摘要翻译： 一种操作燃气涡轮发动机的方法包括提供入口流调节器（IFC）。 IFC具有由至少一个壁限定在其中的环形室，其中壁包括穿过其延伸的多个穿孔。 所述穿孔在至少两个轴向隔开的行中间隔开，所述列围绕所述壁周向延伸。 该方法还包括将流体引导到IFC中并以基本上均匀的流动廓线从IFC排出流体。
-
公开(公告)号：US07082766B1
公开(公告)日：2006-08-01
申请号：US10906688
申请日：2005-03-02
摘要： A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary embodiment, the transition piece is jointless.
摘要翻译： 用于工业涡轮机的罐式燃烧器包括使用单件式过渡件直接从燃烧器头端转换到涡轮入口的过渡件。 在示例性实施例中，过渡件是无接头的。
-
公开(公告)号：US07966822B2
公开(公告)日：2011-06-28
申请号：US11160596
申请日：2005-06-30
IPC分类号： F02C1/00
CPC分类号： F02C3/145
摘要： A gas turbine combustion system for burning air and fuel into exhaust gases. The gas turbine combustion system may include a combustor, a turbine nozzle integral with the combustor for providing the air to the combustor, and a fuel injector for providing the fuel to the combustor. The turbine nozzle and the fuel injector are positioned within the combustor such that a mixture of the air and the fuel flows in a first direction and the exhaust gases flow in a second direction.
摘要翻译： 一种用于将空气和燃料燃烧成废气的燃气轮机燃烧系统。 燃气轮机燃烧系统可以包括燃烧器，与燃烧器成一体的涡轮喷嘴，用于向燃烧器提供空气，以及用于将燃料提供给燃烧器的燃料喷射器。 涡轮喷嘴和燃料喷射器定位在燃烧器内，使得空气和燃料的混合物沿第一方向流动并且废气沿第二方向流动。
-
6.发明申请公开(公告)号：US20100236249A1
公开(公告)日：2010-09-23
申请号：US12408326
申请日：2009-03-20
IPC分类号： F02C1/00
摘要： A system and method for reintroducing gas turbine combustion bypass flow. The system may include a combustor body, wherein the combustor body includes a reaction zone for primary combustion of fuel and air, and a casing enclosing the combustor body and defining an annular passageway for carrying compressor discharge air into the combustor body at one end. The system further may include a reintroduction manifold for receiving combustor bypass air extracted from the compressor discharge air in the annular passageway, and one or more reintroduction slots in communication with the reintroduction manifold for injecting the combustor bypass air into the combustor body downstream of the reaction zone. The method may include extracting combustor bypass air from the annular passageway, transporting the combustor bypass air to a reintroduction manifold, and reintroducing the combustor bypass air into the combustor body through one or more reintroduction slots in communication with the reintroduction manifold.
摘要翻译： 一种用于重新引入燃气轮机燃烧旁路流的系统和方法。 该系统可以包括燃烧器主体，其中燃烧器主体包括用于燃料和空气的初级燃烧的反应区，以及包围燃烧器主体并且限定一个环形通道的壳体，该环形通道在一端承载压缩机排放空气进入燃烧器主体。 该系统还可以包括用于接收从环形通道中的压缩机排出空气抽出的燃烧器旁路空气的再引入歧管，以及与再引入歧管连通的一个或多个再引入槽，用于将燃烧器旁路空气喷射到反应下游的燃烧器体中 区。 该方法可以包括从环形通道提取燃烧器旁路空气，将燃烧器旁路空气输送到再引入歧管，以及通过与再引入歧管连通的一个或多个再引入槽将燃烧器旁路空气重新引入燃烧器主体。
-
7.发明授权公开(公告)号：US06993916B2
公开(公告)日：2006-02-07
申请号：US10862427
申请日：2004-06-08
CPC分类号： F23R3/14 , F23C2900/07001 , F23R3/286
摘要： A hybrid structure that combines characteristics of the DACRS and Swozzle burners to provide the high mixing ability of an axial flowing counter rotating vane swirler with good dynamic flame stability characteristics of a bluff center body.
摘要翻译： 一种混合结构，结合了DACRS和Swozzle燃烧器的特性，提供了具有良好动态火焰稳定性的非流线型中心体的轴流式逆向旋转叶片旋流器的高混合能力。
-
8.发明授权公开(公告)号：US08281601B2
公开(公告)日：2012-10-09
申请号：US12408326
申请日：2009-03-20
IPC分类号： F02C1/00
摘要： A system and method for reintroducing gas turbine combustion bypass flow. The system may include a combustor body, wherein the combustor body includes a reaction zone for primary combustion of fuel and air, and a casing enclosing the combustor body and defining an annular passageway for carrying compressor discharge air into the combustor body at one end. The system further may include a reintroduction manifold for receiving combustor bypass air extracted from the compressor discharge air in the annular passageway, and one or more reintroduction slots in communication with the reintroduction manifold for injecting the combustor bypass air into the combustor body downstream of the reaction zone. The method may include extracting combustor bypass air from the annular passageway, transporting the combustor bypass air to a reintroduction manifold, and reintroducing the combustor bypass air into the combustor body through one or more reintroduction slots in communication with the reintroduction manifold.
摘要翻译： 一种用于重新引入燃气轮机燃烧旁路流的系统和方法。 该系统可以包括燃烧器主体，其中燃烧器主体包括用于燃料和空气的初级燃烧的反应区，以及包围燃烧器主体并且限定一个环形通道的壳体，该环形通道在一端承载压缩机排放空气进入燃烧器主体。 该系统还可以包括用于接收从环形通道中的压缩机排出空气抽出的燃烧器旁路空气的再引入歧管，以及与再引入歧管连通的一个或多个再引入槽，用于将燃烧器旁路空气喷射到反应下游的燃烧器体中 区。 该方法可以包括从环形通道提取燃烧器旁路空气，将燃烧器旁路空气输送到再引入歧管，以及通过与再引入歧管连通的一个或多个再引入槽将燃烧器旁路空气重新引入燃烧器主体。
-
公开(公告)号：US09506654B2
公开(公告)日：2016-11-29
申请号：US13213460
申请日：2011-08-19
申请人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , Shiva Srinivasan , William David York
发明人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , Shiva Srinivasan , William David York
摘要： A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes.
摘要翻译： 用于减少燃烧器中的燃烧动力学的系统包括：端盖，其径向延伸穿过燃烧器并且包括与下游表面轴向分离的上游表面。 燃烧室在端盖的下游，并且管从上游表面延伸穿过下游表面。 每个管提供通过端盖到燃烧室的流体连通。 该系统还包括用于减少燃烧器中的燃烧动力学的装置。 用于减少燃烧器中的燃烧动力学的方法包括使工作流体通过管轴流动，所述管道轴向延伸穿过径向延伸穿过燃烧器的端盖，并阻塞流过第一组管的至少一部分工作流体。
-
10.发明授权Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same 有权涡轮机燃烧器喷嘴包括单片喷嘴部件及其形成方法公开(公告)号：US09267690B2
公开(公告)日：2016-02-23
申请号：US13482540
申请日：2012-05-29
申请人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
发明人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
CPC分类号： F23R3/283 , F23R3/286 , F23R2900/00017 , F23R2900/00018 , Y10T29/49323
摘要： A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.
摘要翻译： 涡轮机燃烧器喷嘴包括具有板元件和多个喷嘴元件的单片喷嘴部件。 多个喷嘴元件中的每一个包括从板元件延伸到第二端的第一端。 板元件和多个喷嘴元件形成为整体部件。 板构件与喷嘴部件接合。 板构件包括限定第一和第二表面的外边缘和在第一和第二表面之间延伸的多个开口。 多个开口被配置和设置成与多个喷嘴元件中对应的喷嘴元件的对应的第二端对准并接收。
-
-
-
-
-
-
-
-
-
搜索结果
143 条记录 (耗时 0.037 秒)
