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1.发明授权公开(公告)号：US08276391B2
公开(公告)日：2012-10-02
申请号：US12762842
申请日：2010-04-19
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。
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2.发明申请公开(公告)号：US20100300106A1
公开(公告)日：2010-12-02
申请号：US12476926
申请日：2009-06-02
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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3.发明授权公开(公告)号：US08495881B2
公开(公告)日：2013-07-30
申请号：US12476926
申请日：2009-06-02
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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公开(公告)号：US20100263386A1
公开(公告)日：2010-10-21
申请号：US12425229
申请日：2009-04-16
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。
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