| 摘要 |
A turbine blade (12) of a gas turbine comprises a radially extending airfoil (29) having a suction side(26) and a pressure side (27) which extend in an axial direction between a leading edge (24) and a trailing edge of the airfoil (29). The leading edge (24) is cooled by a means of impingement cooling with rows of radially distributed jets of a cooling medium impinging on the inner side of the leading edge (24). The rows of radially distributed jets are generated on an internal web (16, 16′) which divides a hollow interior of the airfoil (29) into a first and a second cavity (15, 17). The second cavity (17) is arranged on the leading edge (24). An improvement is achieved by the internal web (16, 17) which comprises two rows of radially distributed cooling medium supply holes (18, 19), through which the cooling medium enters the second cavity (17) in a form of impinging jets, and the cooling medium supply holes (18, 19) which are oriented to allow the directions of the jets of one row to cross the directions of the jets of the other row. |
