Method and apparatus for cooling combustor liner and transition piece of a gas turbine
    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

    IPC分类号: F02C1/00 F02G3/00

    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。