| 摘要 |
A turbine airfoil (1), particularly a blade or a vane for a turbomachine, comprises a suction side wall (2) and a pressure side wall (3) bordering an 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 airfoil (1), wherein the suction side wall (2) comprises at least one protrusion (9) extending therefrom inside the airfoil cavity (4), characterized in that the number of the at least one protrusion (9) on the suction side wall (2) is higher than the number of protrusions on the pressure side wall (3), the density of the at least one protrusion (9) on the suction side wall (2) is higher than the density of protrusions on the pressure side wall (3) and/or the surface of the at least one protrusion (9) on the suction side wall (2) is larger than the surface of protrusions on the pressure side wall (3), so 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. |
