| 摘要 |
An airfoil (18) for a gas turbine engine includes a root (28), a tip (30), a leading edge (24), a trailing edge (26), and opposed pressure (20) and suction sidewalk (22) extending generally along a radial axis. The airfoil (18) includes a tip cap (32) extending between the pressure (20) and suction (22) sidewalk; and spaced-apart suction-side (34) and pressure-side tip (36) walls extending radially outward from the tip cap (32 ) to define a tip cavity (38) therebetween. The pressure-side tip wall (34) includes a continuously concave curved arcuate portion (52), at least a section of which extends circumferentially outward from a radial axis of the airfoil (18). At least a portion of the pressure-side tip wall (34) is recessed from the pressure sidewall (20) to define an outwardly facing tip shelf (56), such that the pressure-side tip wall (34) and the tip shelf (56) define a trough (58) therebetween.
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