| 摘要 |
The present invention relates to a turbine assembly (10) comprising a basically hollow aerofoil (12), at least a wall segment (14, 14') arranged at a side (16, 16') of the hollow aerofoil (12) oriented basically perpendicular to a span wise direction (18) of the hollow aerofoil (12) and with at least an insertion aperture (20) in said at least one wall segment (14, 14') providing access to the hollow aerofoil (12) and at least an impingement tube (22, 22a) to be inserted via the insertion aperture (20) in the wall segment (14, 14') into the hollow aerofoil (12) to be located within the hollow aerofoil (12) and extending in at least the span wise direction (18) of the hollow aerofoil (12). According the invention in an assembled state of the impingement tube (22, 22a) in the hollow aerofoil (12) at least a protrusion section (24, 24a) of the impingement tube (22, 22a) extends in a direction (26) oriented basically perpendicular to the span wise direction (18) over an edge (28) of the insertion aperture (20) in the wall segment (14, 14'), wherein the protrusion section (24, 24a) is overlapped by at least a part (30) of the wall segment (14, 14') and wherein adjacent to the protrusion section (24, 24a) an overlap section (76) of the impingement tube (22, 22a) is arranged which abuts the edge (28) of the insertion aperture (20) in the wall segment (14, 14') and wherein the protrusion section (24, 24a) and the overlap section (76) are formed integrally with each other in one piece. |
