公开(公告)号：US20150004001A1

公开(公告)日：2015-01-01

申请号：US14490813

申请日：2014-09-19

Applicant: ALSTOM Technology Ltd

Inventor： Martin SCHNIEDER ,  Sergey SHCHUKIN

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F05C2251/02 ,  F05D2250/71 ,  F05D2300/501

Abstract: A turbine vane for a rotary turbomachine is described having a turbine blade which is delimited by a concave pressure-side wall and a convex suction-side wall which are connected in the region of a vane front edge which can be assigned to the turbine blade and enclose a cavity which extends in the longitudinal extent of the vane front edge and is delimited on the inner wall by the pressure-side wall and the suction-side wall in the region of the vane front edge and by an intermediate wall which extends in the longitudinal direction to the vane front edge and connects the suction-side wall and the pressure-side wall on the inner wall. The disclosed vane is distinguished by the fact that the intermediate wall has a perforation at least in sections in the connecting region to the suction-side wall and/or pressure-side wall, in order to increase the elasticity of the intermediate wall.

Abstract translation: 描述了一种用于旋转涡轮机的涡轮叶片，其具有涡轮叶片，该涡轮叶片由可被分配给涡轮叶片的叶片前缘区域中连接的凹压力侧壁和凸形吸入侧壁限定， 包围在叶片前缘的纵向延伸部分延伸的空腔，并且在叶片前缘的区域中的压力侧壁和吸力侧壁以及在内壁上延伸的中间壁在内壁上限定 并且连接吸入侧壁和内壁上的压力侧壁。 所公开的叶片的特征在于中间壁在与吸入侧壁和/或压力侧壁的连接区域中至少具有穿孔，以增加中间壁的弹性。

公开(公告)号：US20140037460A1

公开(公告)日：2014-02-06

申请号：US13933548

申请日：2013-07-02

Applicant: ALSTOM Technology Ltd.

Inventor： Helen Marie SAXER-FELICI ,  Shailendra NAIK ,  Martin SCHNIEDER

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/185 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

Abstract: The invention relates to a cooled blade for a gas turbine that includes a radially extending aerofoil with a leading edge, a trailing edge, a suction side and a pressure side, and wherein a lip overhang is provided on the suction side of the trailing edge The blade also includes a plurality of radial internal flow channels connected via flow bends to form a multi-pass serpentine for a coolant flow, whereby a trailing edge ejection region is provided for cooling said trailing edge, said trailing edge ejection region comprising a trailing edge passage of said multi-pass serpentine running essentially parallel to said trailing edge and being connected over its entire length with a pressure side bleed. An optimized cooling is achieved by mainly determining the cooling flow from the trailing edge passage to the pressure side bleed by means of a staggered field of pins, which is provided between said pressure side bleed and said trailing edge passage, with the lateral dimension of said pins increasing in coolant flow direction.

Abstract translation: 本发明涉及一种用于燃气轮机的冷却叶片，其包括具有前缘，后缘，吸力侧和压力侧的径向延伸的翼面，并且其中在后缘的吸力侧设置有唇突出部 叶片还包括多个通过流动弯曲连接的径向内部流动通道，以形成用于冷却剂流动的多通蛇形结构，由此提供后缘喷射区域用于冷却所述后缘，所述后缘喷射区域包括后缘通道 的所述多通蛇形运行基本上平行于所述后缘并且在其整个长度上与压力侧渗流连接。 通过主要通过在所述压力侧排出物和所述后缘通道之间设置的交错的引脚区域来确定从后缘通道到压力侧排出物的冷却流量的优化冷却，其中所述 冷却剂流动方向上的销增加。