| 摘要 |
The present invention relates to a turbine assembly (10) comprising a basically hollow aerofoil (12, 12a-12d), with at least a leading edge (14), a trailing edge (16), a pressure side (18) and a suction side (20), which are forming at least a cavity (22) within the hollow aerofoil (12, 12a-12d), and with at least a deflection structure (24, 24e-241) that is arranged in the at least one cavity (22) and that has a cross section (26), which is oriented basically perpendicular to a direction (28) pointing from the pressure side (18) to the suction side (20). According the invention the cross section (26) of the at least one deflection structure (24, 24e-241) has an aerofoil contour (30) and has a curved mean camber line (32). |
