| 摘要 |
The present invention relates to a cooled blade (10) for a gas turbine, comprising a radially extending aerofoil (11) with a leading edge (15), a trailing edge (16), a suction side (17) and a pressure side (18), whereby a lip overhang is provided on the suction side of the trailing edge (16), further comprising a plurality of radial internal flow channels (19, 19a,b) connected via flow bends to form a multi-pass serpentine for a coolant flow, whereby a trailing edge ejection region (21) is provided for cooling the trailing edge (16), the trailing edge ejection region (21) comprising a trailing edge passage of the multi-pass serpentine running essentially parallel to the trailing edge (16) and being connected over its entire length with a pressure side bleed (28). An optimized cooling is achieved by mainly determining the cooling flow from the trailing edge passage (19b) to the pressure side bleed (28) by means of a staggered field of pins, which is provided between the pressure side bleed (28) and the trailing edge passage (19b), with the lateral dimension of the pins increasing in coolant flow direction. |
