Single ply having plurality of fiber angles

1. A composite airfoil, comprising:

a first ply having a first plurality of strips of fiber oriented at a first angle with respect to a longitudinal axis and a second plurality of strips of fiber oriented at a second angle with respect to the longitudinal axis,

wherein at least one strip of the first plurality of strips intersects at least one strip of the second plurality of strips at a common intersection line within the first ply and without a gap or a space between the at least one strip of the first plurality of strips and the at least one strip of the second plurality of strips.

2. The composite airfoil of claim 1 , wherein the composite airfoil includes a root region and a tip region and wherein the first ply extends along the composite airfoil from the root region to the tip region.

3. The composite airfoil of claim 2 , wherein the composite airfoil defines a spanwise direction and wherein the longitudinal axis extends substantially parallel to the spanwise direction.

4. The composite airfoil of claim 3 , wherein the first angle is zero degrees.

5. The composite airfoil of claim 4 , wherein the second angle is ninety degrees.

6. The composite airfoil of claim 5 , wherein the root region comprises at least a subset of the first plurality of strips of fiber.

7. The composite airfoil of claim 5 , wherein the tip region comprises at least a subset of the second plurality of strips of fiber.

8. The composite airfoil of claim 5 , wherein the tip region comprises a first subset of the first plurality of strips of fiber and a second subset of the second plurality of strips of fiber.

9. The composite airfoil of claim 5 , further comprising a second ply having a third plurality of strips of fiber oriented at the first angle and a fourth plurality of strips of fiber oriented at the second angle, the second ply stacked adjacent the first ply.

10. The composite airfoil of claim 9 , wherein the first plurality of strips of fiber includes at least one strip of fiber that is staggered a longitudinal offset from an adjacent strip of fiber in the third plurality of strips of fiber.

11. The composite airfoil of claim 10 , wherein the second plurality of strips of fiber includes at least one strip of fiber that is staggered a lateral offset from an adjacent strip of fiber in the fourth plurality of strips of fiber.

12. The composite airfoil of claim 2 , wherein the first plurality of strips of fiber comprises carbon prepreg.

13. The composite airfoil of claim 2 , wherein each strip of fiber within the first plurality of strips of fiber has a first width equal to one-eight inch to one-quarter inch.

14. The composite airfoil of claim 13 , wherein each strip of fiber within the second plurality of strips of fiber has a second width equal to one-eight inch to one-quarter inch.

15. A method of forming a composite fan blade, the method comprising:

loading a prepreg material in a form of strips into an automated fiber placement (“AFP”) machine;

positioning a composite tooling mold having a fan blade shape relative to the AFP machine; and

fabricating a first ply by placing a first plurality of strips of prepreg on a surface of the mold by manipulating a mold position relative to the AFP machine and placing a second plurality of strips of prepreg on the surface of the mold by manipulating the mold position relative to the AFP machine,

wherein the first plurality of strips of prepreg is oriented at a first angle with respect to a longitudinal axis extending between a root and a tip of the composite fan blade and the second plurality of strips of prepreg is oriented at a second angle with respect to the longitudinal axis,

wherein at least a first subset of the first plurality of strips of prepreg has fibers intersecting and oriented perpendicular to the fibers in at least a second subset of the second plurality of strips of prepreg, and

wherein at least one strip of the first plurality of strips of prepreg intersects at least one strip of the second plurality of strips of prepreg at a common intersection line within the first ply and without a gap or a space between the at least one strip of the first plurality of strips and the at least one strip of the second plurality of strips.

16. The method of claim 15 , further comprising fabricating a second ply stacked upon the first ply by placing a first adjacent plurality of strips of prepreg on a ply surface defined by the first ply by manipulating the mold position relative to the AFP machine and placing a second adjacent plurality of strips of prepreg on the ply surface defined by the first ply by manipulating the mold position relative to the AFP machine, wherein at least a first subset of the first adjacent plurality of strips of prepreg has the fibers intersecting and oriented perpendicular to the fibers in at least a second subset of the second adjacent plurality of strips of prepreg within the second ply.

17. The method of claim 16 , further comprising repeatedly fabricating plies, stacked upon one another, until a layup of the composite fan blade is complete.

18. The method of claim 17 , wherein the first plurality of strips of prepreg includes at least one strip of prepreg that is staggered a longitudinal offset from an adjacent strip of prepreg in the first adjacent plurality of strips of prepreg.

19. The method of claim 18 , wherein the second plurality of strips of prepreg includes at least one strip of prepreg that is staggered a lateral offset from an adjacent strip of prepreg in the second adjacent plurality of strips of strips of prepreg.

20. The method of claim 15 , wherein a multi-axis robot is used to position the composite tooling mold relative to the AFP machine.