| 摘要 |
The present invention relates to aerofoil-shaped gas turbine components such as gas turbine rotor blades and stator vanes, and to impingement tubes used in such components for cooling purposes. The present invention further relates to a method for assembling impingement tubes in such components. According the invention an impingement tube is being formed from at least two separate sections each extending span wise through a hollow aerofoil. The first of said at least two sections of the impingement tube is inserted first into the hallow aerofoil and manoeuvred into position. The second of said at least two sections of the impingement tube is inserted into the hallow aerofoil adjacent to said first section second. The first section and second section of said impingement tube are connected together by a locking means, wherein said locking means locking said impingement tube into place in the hollow aerofoil. |
