| 摘要 |
A cooled vane 1, for a gas turbine or similar device, comprises a suction side wall 12 and a pressure side wall 14 that are connected via a leading edge 16, and a trailing edge 18, and has an essentially radially extending cavity 30 through which a cooling medium is able to flow. Multiple cooling channels 32, 34, start from the cavity 30, and extend through a vane section 20, that adjoins the trailing edge and is formed by sections of the suction side wall 12, and the pressure side wall 14. The cooling channels end at the trailing edge 18, whereat a first row 33, of cooling channels 32, is associated with the suction side SS, and a second row 35, of cooling channels 34, is associated with the pressure side DS. The channels in one row may be offset from those in the other row, and the cross-sectional area and spacing of the channels in each row may be varied. The channels may be triangular or trapezoidal in cross-section. Such a vane has an improved cooling efficiency and can be produced entirely with a casting process.
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