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。

公开(公告)号：US20110268582A1

公开(公告)日：2011-11-03

申请号：US13115505

申请日：2011-05-25

申请人： Sergei RIAZANTSEV ,  Thomas WILHELM

发明人： Sergei RIAZANTSEV ,  Thomas WILHELM

IPC分类号： F01D5/18

CPC分类号： F01D5/082 ,  Y02T50/673 ,  Y02T50/676

摘要： A blade for a gas turbine, is provided and includes a blade airfoil which extends in a blade longitudinal direction and at the lower end merges into a shank which terminates in a blade root for fastening the blade on a blade carrier, particularly on a rotor disk. Devices for cooling the blade, which are supplied with a cooling medium, especially cooling air, via a feed hole arranged on the shank at the side, are arranged inside the blade airfoil. In the region of the feed hole provision is made for a planar stiffening element which reaches beyond the immediate region of the feed hole for reducing peaks of mechanical stress.

摘要翻译： 提供了一种用于燃气轮机的叶片，其包括沿叶片纵向方向延伸并且在下端处的叶片翼型，该叶片翼型终止于叶片根部的柄部，用于将叶片紧固在叶片载体上，特别是在转子盘 。 用于通过布置在柄上的进料孔在侧面冷却供给有冷却介质，特别是冷却空气的叶片的装置设置在叶片翼型的内部。 在供给孔的区域中，为了减小机械应力的峰值而使平面加强元件达到超过进料孔的直接区域。

公开(公告)号：US20120036864A1

公开(公告)日：2012-02-16

申请号：US13197840

申请日：2011-08-04

申请人： Sergei RIAZANTSEV ,  Holger Kiewel ,  Sven Olmes ,  Thomas Kramer ,  Sergey Shchukin

发明人： Sergei RIAZANTSEV ,  Holger Kiewel ,  Sven Olmes ,  Thomas Kramer ,  Sergey Shchukin

IPC分类号： F02C7/18 ,  F02C7/141

CPC分类号： F01D5/084 ,  F01D5/3007 ,  F04D29/321 ,  F04D29/584 ,  F05D2220/32

摘要： A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.

摘要翻译： 燃气涡轮发动机包括具有转子叶片的压缩机，转子叶片具有连接到压缩机鼓的座中的根部。 转子叶片根部和/或压缩机滚筒具有用于冷却流体的纵向通道，将较高压力区域连接到燃气涡轮发动机的较低压力区域。