| 摘要 |
<p>The invention is directed to a gas turbine blade (2) comprising a root (6) and an air foil (4) with a leading edge (16) and a trailing edge (18), a cooling air channel system (28) extending from a cooling air opening (44) in the root (6) via a winding serpentine channel (50) to a trailing edge channel (56) at the trailing edge (18) comprising an air outlet (62) at the trailing edge (18), For efficiently cooling the trailing edge (18) of the blade (2) it is proposed that the cooling air channel system (28) comprises an air bypass channel (54) connecting said cooling air opening (44) in the root (6) with the trailing edge channel (56) bypassing the serpentine channel (50).</p> |
