Vane arc segment formed of fiber-reinforced composite
A method of fabricating an airfoil fairing for a vane arc segment includes providing a mandrel that necks down through a mandrel neck portion, providing fiber plies around the mandrel to form a tube that defines at least a portion of an airfoil profile of an airfoil section of an airfoil fairing, the fiber plies following the mandrel neck portion such that the tube has a corresponding tube neck portion that necks down to a collar, and removing the mandrel from the tube.
1. A method of fabricating an airfoil fairing for a vane arc segment, the method comprising:
providing a mandrel that necks down through a mandrel neck portion;
providing fiber plies around the mandrel to form a tube that defines at least a portion of an airfoil profile of an airfoil section of an airfoil fairing, the fiber plies following the mandrel neck portion such that the tube has a corresponding tube neck portion that necks down to a collar; and
removing the mandrel from the tube, wherein the fiber plies include inner and outer cavity fiber plies, and further comprising providing a noodle interposed between the inner and outer cavity fiber plies.
2. The method as recited in claim 1 , wherein the mandrel is tapered.
3. The method as recited in claim 1 , further including consolidating the fiber plies with a matrix material.
4. The method as recited in claim 1 , wherein the fiber plies in the neck portion are sloped at an angle of at least 15 degrees relative to the fiber plies in the collar.
5. The method as recited in claim 1 , wherein the noodle includes a curved finger that extends in the neck portion between the inner and outer cavity fiber plies.
6. The method as recited in claim 5 , further comprising a support noodle abutting the outer cavity fiber ply at the neck portion.
7. The vane arc segment as recited in claim 6 , wherein the fiber plies include at least one over-layer ply that extends from the airfoil section and turns into a fairing platform, the support noodle abutting the at least one over-layer ply at a location where the at least one over-layer ply turns.
8. The method as recited in claim 7 , wherein the fiber plies include cover plies that extend into the fairing platform and turn into the collar.
9. The method as recited in claim 6 , wherein the support noodle extends around the airfoil section and has a variable cross-sectional geometry.
10. The method as recited in claim 1 , wherein the fiber plies include cover plies that extend into a fairing platform and turn into the collar.