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。