| 摘要 |
<p>An airfoil (42) for a gas turbine engine includes a leading edge (48), a trailing edge (50), a tip (54), a first side wall (46) that extends in radial span between an airfoil root (52) and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall (44) connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib (70) extending outwardly from at least one of the first side wall and the second side wall, wherein the rib is configured to reduce airflow spillage past the tip.</p> |
