Composite airfoil assembly having a tip cap

1 . A composite airfoil assembly for a turbine engine, the turbine engine having a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, the composite airfoil assembly comprising:

an outer wall extending between a leading edge and a trailing edge in a chordwise direction and between a root and a tip in a spanwise direction, the outer wall defining a pressure side and a suction side, and defining a camber line extending equidistant between the pressure side and the suction side;

a composite body at least partially defining the outer wall and terminating at a distal end; and

a tip cap defining at least a portion of the outer wall and extending axially over at least a portion of the composite body corresponding to the pressure side and the suction side, and radially over at least a portion of the composite body, the tip cap comprising a plurality of ribs formed along at least one of the outer wall or a surface of the tip cap extending along a respective portion of the composite body, each rib of the plurality of ribs defining a continuous protrusion formed along a respective portion of the tip cap that extends radially towards or away from a respective portion of the tip cap, with respect to the camber line.

2 . The composite airfoil assembly of claim 1 , wherein at least one rib of the plurality of ribs is an external rib extending along the outer wall radially away from the respective portion of the tip cap, with respect to the camber line.

3 . The composite airfoil assembly of claim 2 , wherein the external rib at least partially defines the tip.

4 . The composite airfoil assembly of claim 3 , wherein the tip cap comprises a forward face and an aft face, and the external rib extends continuously between the forward face and the aft face.

5 . The composite airfoil assembly of claim 2 , wherein the external rib is included in a plurality of external ribs, with at least two external ribs of the plurality of external ribs being spaced in the spanwise direction with respect to one another.

6 . The composite airfoil assembly of claim 2 , wherein the external rib extends along a reference line in the chordwise direction.

7 . The turbine engine of claim 6 , wherein the reference line forms a non-zero angle with respect to a straight line intersecting the reference line and extending in the chordwise direction.

8 . The composite airfoil assembly of claim 7 , wherein the non-zero angle is greater than or equal to −30 degrees and less than or equal to 30 degrees.

9 . The composite airfoil assembly of claim 1 , wherein the tip cap extends between a forward face and an aft face, and at least one rib of the plurality of ribs extends continuously between the forward face and the aft face.

10 . The composite airfoil assembly of claim 9 , wherein the tip cap extends between a forward face and an aft face, and the at least one rib extends less than an entirety of a distance between the forward face and the aft face.

11 . The composite airfoil assembly of claim 1 , wherein the tip cap is formed as a unitary body extending continuously along the tip between the suction side and the pressure side.

12 . The composite airfoil assembly of claim 1 , wherein the body includes a composite material, and the tip cap includes a metallic material.

13 . The composite airfoil assembly of claim 1 , wherein the plurality of ribs are axially spaced from the leading edge with respect to the camber line.