公开(公告)号：US20120070309A1

公开(公告)日：2012-03-22

申请号：US13245707

申请日：2011-09-26

申请人： Chiara ZAMBETTI ,  Sergei RIAZANTSEV ,  Hélène SAXER-FELICI

发明人： Chiara ZAMBETTI ,  Sergei RIAZANTSEV ,  Hélène SAXER-FELICI

IPC分类号： F01D5/18 ,  F01D5/20

CPC分类号： F01D5/225 ,  F05D2240/81 ,  F05D2260/202

摘要： A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage. The side rails include rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.

摘要翻译： 用于燃气轮机的叶片包括具有布置在其上端上的护罩段的叶片翼型件。 护罩部分与叶片排的其它叶片的护罩部分一起形成环形护罩，其限定燃气轮机的热气体通道，并且所述护罩段在其邻接环形护罩的相邻护罩段的侧面上设置有 向上突出的侧轨，其沿着侧边缘延伸，以改善对热气体通道的密封。 侧轨包括轨道平行或基本上轨道平行的向上开口的狭槽，经由护罩段从叶片翼型的内部引入的冷却空气通过该槽排放到护罩段上方的空间中。