FIELD: turbines.
SUBSTANCE: turbine assembly comprises a basically hollow aerofoil, at least a wall segment arranged at a side of hollow aerofoil oriented basically perpendicular to a span wise direction of hollow aerofoil, and with at least an insertion aperture in at least one wall segment providing access to hollow aerofoil and at least an impingement tube to be inserted via insertion aperture in wall segment into hollow aerofoil to be located within hollow aerofoil and extending in at least span wise direction of hollow aerofoil. In an assembled state of impingement tube in hollow aerofoil at least a protrusion section of impingement tube extends in a direction oriented basically perpendicular to span wise direction over an edge of insertion aperture in wall segment. Protrusion section is overlapped by at least a part of wall segment. Adjacent to protrusion section an overlap section of impingement tube is arranged which abuts edge of insertion aperture in wall segment. Protrusion section and overlap section are formed integrally with each other in one piece.
EFFECT: invention is aimed at improving cooling efficiency and ease of assembly of impingement cooling tube.
14 cl, 5 dwg
