| 摘要 |
A fan blade (15) for a gas turbine engine is disclosed. The disclosed fan blade (15) includes an airfoil having a leading edge (16), a trailing edge (18), a convex side (35), a concave side (36) and a distal tip (14). The leading edge (16), trailing edge (17), convex side (35) and concave side (36) of the airfoil is at least partially coated with an erosion resistant coating (32). The distal tip (14) of the airfoil is coated with a bonded abrasive coating (33). The bonded abrasive coating (32) engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip (14) of the fan blade (15). The reduction in heat transfer to the distal tip (14) of the fan blade (15) preserves the integrity of erosion resistant coatings (32) that may be applied to the body or the airfoil of the fan blade (15). |
