| 摘要 |
The invention related to an airfoil (27) of a turbomachine, particularly a gas turbine (1), the airfoil (27) particularly being arranged in a compressor section (5) of the gas turbine (1), the airfoil (27) comprising a platform (25), a pressure surface (42) and a suction surface (43), and a tip region (29). The pressure surface (42) and the suction surface (43), extend substantially perpendicular to the platform (25) along a first direction (D), the first direction (D) being defined as a direction substantially perpendicular to the platform (25) and progressing with a distance to the platform (25). The tip region (29) is located between the pressure (42) and the suction surface (43) opposite to the platform (25) in respect of the pressure (42) and the suction surfaces (43), being a distant end of the airfoil (27) in direction along the first direction (D). The tip region (29) is configured such that the tip region (29) comprises a first surface (70) with a first surface expanse less than a cross sectional plane of the airfoil (27) perpendicular to the first direction (D) and with a first distance (D1) to the platform (25) along the first direction (D), and a second surface (71) with a second surface expanse and with a second distance (D2) to the platform (25) along the first direction (D), whereas the first distance (D1) is greater than the second distance (D2) and the first surface (70) and the second surface (71) together build a profiled surface, particularly a ribbed surface. |
