公开(公告)号：US20150322798A1

公开(公告)日：2015-11-12

申请号：US14705315

申请日：2015-05-06

Applicant: ALSTOM Technology Ltd

Inventor： Rainer BAUER ,  Shailendra NAIK ,  Marc HENZE

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/141 ,  F01D5/186 ,  F05D2220/32 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2250/71 ,  F05D2260/20 ,  Y02T50/673 ,  Y02T50/676

Abstract: The present invention relates to an airfoil for a gas turbine, including an improved turbulator arrangement formed on an inner cooling channel of the airfoil. According to preferred embodiments of the invention, in order to ensure a constant angle of the cooling flow inside the channel relative to each turbulator, the angle formed between the turbulator and the vertical axis is advantageously adapted, in the curved area, for every single turbulator. Furthermore, the same principle may be applied to all the cooling channels present within the airfoil.

Abstract translation: 本发明涉及一种用于燃气轮机的翼型件，其包括形成在翼型件的内部冷却通道上的改进的湍流器装置。 根据本发明的优选实施例，为了确保通道内的相对于每个湍流器的冷却流的恒定角度，在湍流器和垂直轴之间形成的角度有利地在弯曲区域适用于每个单个湍流器 。 此外，相同的原理可以应用于存在于翼型内的所有冷却通道。

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。