| 摘要 |
A turbine (1), particularly a blade or vane for a turbomachine, comprises a suction side wall (2) and a pressure side wall (3) bordering a airfoil cavity (4), which is adapted to be flowed through by a cooling fluid (7) for cooling of the side walls (2, 3) and therefore of the turbine airfoil (1), wherein the suction side wall (2) comprises at least one protrusion (9) extending therefrom inside the airfoil cavity (4), wherein the number, the distribution, the location and/or the shape of the at least one protrusion (9) are such that the heat transfer from the suction side wall (2) to the cooling fluid (7) is higher compared to the heat transfer from the pressure side wall (3) to the cooling fluid (7) during the operation of the turbomachine such that an excess of the heat transfer from the suction side wall (2) is generated. |
