| 摘要 |
A turbine engine component (10) having improved cooling is provided. The turbine engine component includes an airfoil portion (12) having a leading edge (18), a trailing edge (20), a pressure side (22), a suction side (24), a root (19), and a tip (21), and at least one cooling circuit (26, 42) in a wall of the airfoil portion (12). The at least one cooling circuit (26, 42) has at least one passageway extending between the root (19) and the tip (21). The at least one passageway has an aspect ratio of no greater than 2:1, and preferably substantially unity. |
