Patent attributes
An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and a root section in a spanwise direction. The airfoil section defines pressure and suction sides separated in a thickness direction. A sheath extends in the spanwise direction along at least one of the pressure and suction sides of the airfoil section. A tip cap extends in the chordwise direction along the at least one of the pressure and suction sides. The sheath includes a first set of interface members. The tip cap includes a second set of interface members interleaved with the first set of interface members to establish at least one joint along an external surface of the at least one of the pressure and suction sides. A method of assembly for an airfoil is also disclosed.
