| 摘要 |
<p>The invention is directed to a gas turbine blade (2) comprising a root (6), an airfoil (4) with a leading edge (16), a trailing edge (18), a radial outer tip (24), and a pressure side and a suction side between the leading edge (16) and the trailing edge (18), and a cooling air channel system (26, 28) extending from an air inlet opening (34, 44) in the root (6) throughout the airfoil (4) to a plurality of air outlets (38, 40, 42, 70) at the pressure side and the leading edge of the top of the tip (24) of the airfoil (4). For efficiently cooling the tip (24) of the blade (2) it is proposed that the concentration of air outlets (38, 40) at the top of the tip (24) of the airfoil (4) is higher on the pressure side than on the suction side.</p> |
