| 摘要 |
The invention relates to a gas turbine blade (1), cooled in separate cavities (16, 17, 18) by air and steam. The sweep edge (10), in particular is air-cooled, whereby the sweep edge (10) may be embodied so thin as to be aerodynamically advantageous. The large part of the gas turbine blade (1) is steam cooled to save compressor air. |
