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1. 发明授权

US08495881B2 System and method for thermal control in a cap of a gas turbine combustor 有权
标题翻译：在燃气轮机燃烧器的盖中进行热控制的系统和方法
公开(公告)号：US08495881B2
公开(公告)日：2013-07-30
申请号：US12476926
申请日：2009-06-02
申请人： Kara Johnston Edwards , Kevin Weston McMahan , Thomas Edward Johnson , Jonathan Dwight Berry
发明人： Kara Johnston Edwards , Kevin Weston McMahan , Thomas Edward Johnson , Jonathan Dwight Berry
IPC分类号： F02C1/00
CPC分类号： F23R3/10 , F23R2900/03041
摘要： A system comprises a turbine combustor cap. The turbine combustor cap includes a plurality of segments. Each segment of the plurality of segments has edges abutting at least two fuel nozzle receptacles. Moreover, each segment of the plurality of segments does not completely surrounding any one fuel nozzle receptacle.
摘要翻译：一种系统包括涡轮机燃烧器盖。涡轮机燃烧器盖包括多个段。多个段的每个段具有邻接至少两个燃料喷嘴容器的边缘。此外，多个段的每个段都不完全围绕任何一个燃料喷嘴容器。

2. 发明授权

US08276391B2 Combustor liner cooling at transition duct interface and related method 有权
标题翻译：过渡管道界面的燃烧器衬管冷却及相关方法
公开(公告)号：US08276391B2
公开(公告)日：2012-10-02
申请号：US12762842
申请日：2010-04-19
申请人： Jonathan Dwight Berry , Kara Johnston Edwards , Heath Michael Ostebee
发明人： Jonathan Dwight Berry , Kara Johnston Edwards , Heath Michael Ostebee
IPC分类号： F02C7/18 , F23R3/46
CPC分类号： F23R3/002 , F23R3/04
摘要： A resilient annular seal structure is disposed radially between an aft end portion of a combustor liner and a forward end portion of a transition piece, the resilient annular seal structure configured to form a first annular cavity radially between the forward end portion of the transition piece and the aft end portion of said combustor. At least one transfer tube radially extends from the second flow sleeve through the second flow annulus to the transition piece, and is arranged to supply compressor discharge cooling air radially from an area outside the first and second substantially axially extending flow annuli directly to the resilient annular seal structure and to the aft end of the combustor liner.
摘要翻译：弹性环形密封结构径向设置在燃烧器衬套的后端部分与过渡件的前端部分之间，该弹性环形密封结构构造成在过渡件的前端部分和所述燃烧器的后端部分。至少一个传送管从第二流动套管径向地延伸穿过第二流动环到过渡件，并且被布置成将压缩机排出冷却空气从第一和第二大致轴向延伸的流动环的外部径向径向地供应到弹性环密封结构和燃烧器衬套的后端。

3. 发明申请

US20100263386A1 TURBINE ENGINE HAVING A LINER 审中-公开
标题翻译：具有内衬的涡轮发动机
公开(公告)号：US20100263386A1
公开(公告)日：2010-10-21
申请号：US12425229
申请日：2009-04-16
申请人： Kara Johnston Edwards , Thomas Edward Johnson
发明人： Kara Johnston Edwards , Thomas Edward Johnson
IPC分类号： F02C7/20 , F02C1/00
CPC分类号： F23R3/60 , F23R3/002
摘要： In one embodiment, a combustor of a turbine system may include a liner disposed inside the combustor. The lining element may include a heat shield having a mounting stud extending along an axis and a shell having an inner surface oriented towards the heat shield. The shell may include a passage configured to receive the mounting stud, and the mounting stud may include a structure configured to hold the heat shield apart from the inner surface of the shell along the axis of the mounting stud.
摘要翻译：在一个实施例中，涡轮机系统的燃烧器可以包括设置在燃烧器内部的衬套。衬里元件可以包括具有沿轴线延伸的安装螺柱的隔热罩和具有朝向隔热罩定向的内表面的外壳。外壳可以包括构造成接收安装螺柱的通道，并且安装螺柱可以包括构造成沿着安装螺柱的轴线将隔热罩与壳体的内表面隔开的结构。

4. 发明申请

US20110252805A1 COMBUSTOR LINER COOLING AT TRANSITION DUCT INTERFACE AND RELATED METHOD 有权
标题翻译：过渡管接口中的COMBUSTOR LINER冷却及相关方法
公开(公告)号：US20110252805A1
公开(公告)日：2011-10-20
申请号：US12762842
申请日：2010-04-19
申请人： Jonathan Dwight BERRY , Kara Johnston EDWARDS , Heath Michael OSTEBEE
发明人： Jonathan Dwight BERRY , Kara Johnston EDWARDS , Heath Michael OSTEBEE
IPC分类号： F02C7/18
CPC分类号： F23R3/002 , F23R3/04
摘要： A combustor assembly for a turbine includes a combustor and a combustor liner; a first flow sleeve surrounding the combustor liner forming a first substantially axially-extending flow annulus radially therebetween. The first flow sleeve has a first plurality of apertures formed about a circumference thereof for directing compressor discharge air as cooling air radially into said first flow annulus. A transition piece is connected to the combustor liner, the transition piece adapted to carry hot combustion gases to the turbine, and a second flow sleeve surrounds the transition piece forming a second substantially axially-extending flow annulus radially therebetween. The second flow sleeve has a second plurality of apertures for directing compressor discharge air as cooling air radially into the second flow annulus, the first substantially axially-extending flow annulus connecting with the second substantially axially-extending flow annulus. A resilient annular seal structure is disposed radially between an aft end portion of the combustor liner and a forward end portion of said transition piece, the resilient annular seal structure configured to form a first annular cavity radially between the forward end portion of the transition piece and the aft end portion of said combustor liner. At least one transfer tube radially extends from the second flow sleeve through the second flow annulus to the transition piece, and is arranged to supply compressor discharge cooling air radially from an area outside the first and second substantially axially extending flow annuli directly to the resilient annular seal structure and to the aft end of the combustor liner.
摘要翻译：用于涡轮机的燃烧器组件包括燃烧器和燃烧器衬套; 围绕所述燃烧器衬套的第一流动套筒在其间径向形成第一基本上轴向延伸的流动环形空间。第一流动套筒具有围绕其圆周形成的第一多个孔，用于将压缩机排放空气作为冷却空气径向地引导到所述第一流动环空中。过渡件连接到燃烧器衬套，过渡件适于将热的燃烧气体运送到涡轮机，并且第二流动套管围绕过渡件，在其之间径向形成第二基本轴向延伸的流动环形空间。第二流动套管具有第二多个孔，用于将冷却空气径向地引导到第二流动环空中的压缩机排放空气，第一大致轴向延伸的流动环与第二大致轴向延伸的流动环形空间连接。弹性环形密封结构径向设置在燃烧器衬套的后端部和所述过渡件的前端部分之间，该弹性环形密封结构构造成在过渡件的前端部分和所述燃烧器衬套的后端部分。至少一个传送管从第二流动套管径向延伸穿过第二流动环到过渡件，并且被布置成将压缩机排出冷却空气从第一和第二大致轴向延伸的流动环的外部的区域径向地直接供应到弹性环密封结构和燃烧器衬套的后端。

5. 发明申请

US20100300106A1 SYSTEM AND METHOD FOR THERMAL CONTROL IN A CAP OF A GAS TURBINE COMBUSTOR 有权
标题翻译：一种气体涡轮机燃烧器中的热控制系统和方法
公开(公告)号：US20100300106A1
公开(公告)日：2010-12-02
申请号：US12476926
申请日：2009-06-02
申请人： Kara Johnston Edwards , Kevin Weston McMahan , Thomas Edward Johnson , Jonathan Dwight Berry
发明人： Kara Johnston Edwards , Kevin Weston McMahan , Thomas Edward Johnson , Jonathan Dwight Berry
IPC分类号： F02C1/00
CPC分类号： F23R3/10 , F23R2900/03041
摘要： A system comprises a turbine combustor cap. The turbine combustor cap includes a plurality of segments. Each segment of the plurality of segments has edges abutting at least two fuel nozzle receptacles. Moreover, each segment of the plurality of segments does not completely surrounding any one fuel nozzle receptacle.
摘要翻译：一种系统包括涡轮机燃烧器盖。涡轮机燃烧器盖包括多个段。多个段的每个段具有邻接至少两个燃料喷嘴容器的边缘。此外，多个段的每个段都不完全围绕任何一个燃料喷嘴容器。

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