| 摘要 |
A blade (62) includes an airfoil section (64) extending between leading and trailing edges (66,68), first and second opposed sides (70,72) each joining the leading and trailing edges (66,68), and an inner end (74) and a free tip end (76). The airfoil section (64) is formed of a metal-based material with a polymeric overcoat (62a) on at least one of the leading edge (66), trailing edge (68), first side (70) and second side (72). The airfoil section (64) includes an abrasive tip (78) at the free tip end (76). The abrasive tip (78) has a composition selected with respect to heat-induced delamination of the polymeric overcoat (62a) from frictional heat generated during rubbing of the abrasive tip (78). A corresponding gas turbine engine (20) comprising such a fan blade (62), and a fan rotor system comprising such a blade (62). |
