-
公开(公告)号：US20100154436A1
公开(公告)日：2010-06-24
申请号：US12656951
申请日：2010-02-22
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F05D2230/232
摘要： In a combustor section, wherein a forward sleeve is disposed to encircle a leading end of an impingement sleeve comprised of first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal junction. The retainer member is welded to at least one of said forward sleeve and the impingement sleeve. The retainer member has first and second axial end edges disposed transverse to the longitudinal junction, and at least one of the axial end edges has a cutout defined therein and disposed to overlie the longitudinal junction.
摘要翻译： 在燃烧器部分中，其中前套筒设置成环绕冲击套筒的前端，所述冲击套筒包括沿其纵向接合部邻接的第一和第二冲击套筒部件，设置成覆盖在纵向连接部上的保持器部件。 保持器构件焊接到所述前部套筒和冲击套筒中的至少一个上。 保持器构件具有横向于纵向接合部设置的第一和第二轴向端边缘，并且轴向端部边缘中的至少一个具有限定在其中的切口并且设置成覆盖纵向接合部。
-
公开(公告)号：US08122721B2
公开(公告)日：2012-02-28
申请号：US11325184
申请日：2006-01-04
IPC分类号： F02C1/00
CPC分类号： F23D14/48 , F23D2211/00 , F23R3/286 , F23R2900/00001 , F23R2900/00012
摘要： A method of assembling a combustion turbine engine in provided. The method includes coupling at least one fuel nozzle inner atomized air tube to a combustor end cover plate body. The method also includes assembling a fuel nozzle insert sub-assembly by inserting at least one flow control apparatus into a fuel nozzle insert sub-assembly body. The method further includes inserting at least one seal between the combustor end cover plate body and the fuel nozzle insert sub-assembly body as well as inserting at least one seal between the combustor end cover plate body and the fuel nozzle insert sub-assembly body. The method also includes coupling the fuel nozzle insert sub-assembly to the combustor end cover plate body. The method further includes inserting at least one bellows onto a bellows support fitting and inserting the bellows support fitting onto a fuel nozzle insert sub-assembly body support surface. The method also includes assembling a fuel nozzle sub-assembly. The method further includes assembling a fuel nozzle assembly by coupling the fuel nozzle sub-assembly to the combustor end cover plate body.
摘要翻译： 一种组装燃气涡轮发动机的方法。 该方法包括将至少一个燃料喷嘴内部雾化空气管连接到燃烧器端盖板主体。 该方法还包括通过将至少一个流量控制装置插入到燃料喷嘴插入子组件本体中来组装燃料喷嘴插入子组件。 该方法还包括在燃烧器端盖板主体和燃料喷嘴插件子组件主体之间插入至少一个密封件，以及在燃烧器端盖板主体和燃料喷嘴插件子组件主体之间插入至少一个密封件。 该方法还包括将燃料喷嘴插件子组件联接到燃烧器端盖板主体。 该方法还包括将至少一个波纹管插入到波纹管支撑配件上并将波纹管支撑配件插入到燃料喷嘴插件子组件主体支撑表面上。 该方法还包括组装燃料喷嘴子组件。 该方法还包括通过将燃料喷嘴子组件连接到燃烧器端盖板主体来组装燃料喷嘴组件。
-
公开(公告)号：US07681403B2
公开(公告)日：2010-03-23
申请号：US11402857
申请日：2006-04-13
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F05D2230/232
摘要： In a combustor section, having a forward sleeve is disposed to encircle a leading end of an impingement sleeve including first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal junction. The retainer member is welded to the forward sleeve and/or to the impingement sleeve. The retainer member has first and second axial end edges disposed transverse to the longitudinal junction, and at least one of the axial end edges has a cutout defined therein and disposed to overlie the longitudinal junction.
摘要翻译： 在具有前套筒的燃烧器部分中，设置有围绕冲击套筒的前端，包括沿着其纵向接合部邻接的第一和第二冲击套筒部件，设置成覆盖纵向连接部的保持器部件。 保持件被焊接到前套和/或冲击套上。 保持器构件具有横向于纵向接合部设置的第一和第二轴向端边缘，并且轴向端部边缘中的至少一个具有限定在其中的切口并且设置成覆盖纵向接合部。
-
公开(公告)号：US08327646B2
公开(公告)日：2012-12-11
申请号：US12656951
申请日：2010-02-22
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F05D2230/232
摘要： In a combustor section, wherein a forward sleeve is disposed to encircle a leading end of an impingement sleeve comprised of first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal junction. The retainer member is welded to at least one of said forward sleeve and the impingement sleeve. The retainer member has first and second axial end edges disposed transverse to the longitudinal junction, and at least one of the axial end edges has a cutout defined therein and disposed to overlie the longitudinal junction.
摘要翻译： 在燃烧器部分中，其中前套筒设置成环绕冲击套筒的前端，所述冲击套筒包括沿其纵向接合部邻接的第一和第二冲击套筒部件，设置成覆盖在纵向连接部上的保持器部件。 保持器构件焊接到所述前部套筒和冲击套筒中的至少一个上。 保持器构件具有横向于纵向接合部设置的第一和第二轴向端边缘，并且轴向端部边缘中的至少一个具有限定在其中的切口并且设置成覆盖纵向接合部。
-
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。
-
6.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。
-
公开(公告)号：US09121612B2
公开(公告)日：2015-09-01
申请号：US13409309
申请日：2012-03-01
CPC分类号： F23R3/286 , F02C3/30 , F23C2900/07022 , F23D14/62 , F23R3/002 , F23R3/32 , F23R3/54 , F23R2900/00013
摘要： A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend from the upstream surface through the downstream surface. A divider inside a tube bundle defines a diluent passage that extends axially through the downstream surface, and a diluent supply in fluid communication with the divider provides diluent flow to the diluent passage. A method for reducing combustion dynamics in a combustor includes flowing a fuel through tube bundles, flowing a diluent through a diluent passage inside a tube bundle, wherein the diluent passage extends axially through at least a portion of the end cap into a combustion chamber, and forming a diluent barrier in the combustion chamber between the tube bundle and at least one other adjacent tube bundle.
摘要翻译： 用于减少燃烧器中的燃烧动力学的系统包括具有从下游表面轴向分离的上游表面的端盖，并且管束从上游表面延伸穿过下游表面。 管束内的分隔器限定了一个沿轴向延伸穿过下游表面的稀释剂通道，与分隔器流体连通的稀释剂供应器提供稀释剂流向稀释剂通道。 一种用于减少燃烧动力学的方法，包括使燃料通过管束流动，使稀释剂流过管束内的稀释剂通道，其中稀释剂通道轴向延伸通过端盖的至少一部分进入燃烧室，以及 在管束与至少一个其它相邻管束之间的燃烧室中形成稀释剂阻挡层。
-
公开(公告)号：US08794545B2
公开(公告)日：2014-08-05
申请号：US12567022
申请日：2009-09-25
IPC分类号： F23D11/10
CPC分类号： F23D14/02 , F23C2900/9901 , F23D14/78 , F23D2214/00 , F23R3/286
摘要： A fuel injector includes a fuel delivery tube; a plurality of pre-mixing tubes, each pre-mixing tube comprising at least one fuel injection hole; an upstream tube support plate that supports upstream ends of the plurality of pre-mixing tubes; a downstream tube support plate that supports downstream ends of the plurality of pre-mixing tubes; an outer wall connecting the upstream tube support plate and the downstream tube support plate and defining a plenum therewith; and a baffle provided in the plenum. The baffle includes a radial portion. A fuel delivered in the upstream direction by the fuel delivery tube is directed radially outwardly in the plenum between the radial portion of the baffle and the downstream tube support plate, then in the downstream direction around an outer edge portion of the radial portion, and then radially inwardly between the radial portion and the upstream tube support plate.
摘要翻译： 燃料喷射器包括燃料输送管; 多个预混合管，每个预混合管包括至少一个燃料喷射孔; 上游管支撑板，其支撑所述多个预混合管的上游端; 下游管支撑板，其支撑所述多个预混合管的下游端; 连接所述上游管支撑板和所述下游管支撑板并且与所述下游管支撑板连接的外壁; 以及设置在气室中的挡板。 挡板包括径向部分。 通过燃料输送管沿上游方向输送的燃料径向向外指向在挡板的径向部分和下游管支撑板之间的增压室中，然后在径向部分的外边缘部分的下游方向上，然后 在径向部分和上游管支撑板之间径向向内。
-
公开(公告)号：US08733108B2
公开(公告)日：2014-05-27
申请号：US12833237
申请日：2010-07-09
CPC分类号： F23R3/28 , F23C5/08 , F23R2900/00014
摘要： The present application provides for a combustor for use with a gas turbine engine. The combustor may include a cap member and a number of fuel nozzles extending through the cap member. One or more of the fuel nozzles may be provided in a non-flush position with respect to the cap member.
摘要翻译： 本申请提供了一种与燃气涡轮发动机一起使用的燃烧器。 燃烧器可以包括盖构件和延伸穿过帽构件的多个燃料喷嘴。 一个或多个燃料喷嘴可以相对于盖构件设置在非冲洗位置。
-
10.发明授权Turbine combustor with fuel nozzles having inner and outer fuel circuits 有权具有燃料喷嘴的涡轮机燃烧器具有内部和外部燃料回路公开(公告)号：US08613197B2
公开(公告)日：2013-12-24
申请号：US12850763
申请日：2010-08-05
申请人： Jong Ho Uhm , Thomas Edward Johnson , Kwanwoo Kim
发明人： Jong Ho Uhm , Thomas Edward Johnson , Kwanwoo Kim
CPC分类号： F23R3/34 , F02C7/222 , F05D2260/96 , F23N1/002 , F23N2037/02 , F23R3/28 , F23R3/46 , F23R2900/00013
摘要： A combustor cap assembly for a turbine engine includes a combustor cap and a plurality of fuel nozzles mounted on the combustor cap. One or more of the fuel nozzles would include two separate fuel circuits which are individually controllable. The combustor cap assembly would be controlled so that individual fuel circuits of the fuel nozzles are operated or deliberately shut off to provide for physical separation between the flow of fuel delivered by adjacent fuel nozzles and/or so that adjacent fuel nozzles operate at different pressure differentials. Operating a combustor cap assembly in this fashion helps to reduce or eliminate the generation of undesirable and potentially harmful noise.
摘要翻译： 用于涡轮发动机的燃烧器盖组件包括燃烧器盖和安装在燃烧器盖上的多个燃料喷嘴。 一个或多个燃料喷嘴将包括可独立控制的两个单独的燃料回路。 将控制燃烧器盖组件，使得燃料喷嘴的各个燃料回路被操作或故意切断以提供由相邻燃料喷嘴输送的燃料流之间的物理分离和/或使得相邻燃料喷嘴在不同的压差下工作 。 以这种方式操作燃烧器盖组件有助于减少或消除不期望的和潜在的有害噪声的产生。
-
-
-
-
-
-
-
-
-
搜索结果
143 条记录 (耗时 0.023 秒)
