Blade wedge attachment lay-up
A blade for a gas turbine engine includes composite layers including neck plies and tooth plies that are flared relative to the neck plies. The neck plies and tooth plies respectively provide a neck and a root. The root includes a tooth. A Wedge is provided by wedge plies adhered over the root and the tooth.
1. A blade for a gas turbine engine comprising:
composite layers including neck plies and tooth plies that are flared relative to the neck plies, the neck plies and tooth plies respectively providing a neck and a root, the root including a tooth;
a wedge provided by wedge plies adhered over the root and the tooth;
the neck plies extend in a radial direction to provide an airfoil; and
all of the tooth plies are arranged at a tooth ply angle, and the wedge plies are arranged at a wedge ply angle, the wedge ply angle is at an angle that lies between the radial direction and the tooth ply angle.
2. The blade according to claim 1 , wherein the composite layers are provided by a matrix composite material.
3. The blade according to claim 2 , wherein the matrix composite material is integrated with fibers.
4. The blade according to claim 2 , wherein the neck plies, the tooth plies and the wedge plies are integrated into a unitary matrix composite structure.
5. The blade according to claim 1 , wherein neck plies include a matrix composite material having fibers extending in the radial direction, and the wedge plies include a matrix composite material having fibers extending in a direction transverse to the radial direction.
6. The blade according to claim 1 , wherein the wedge plies extend axially to an end face of the root.
7. The blade according to claim 1 , wherein the wedge plies have a different thickness than the tooth plies.
8. The blade according to claim 1 , wherein the wedge plies extend from a tangent point on the tooth to the neck.
9. The blade according to claim 1 , wherein the wedge is covered in a coating.
10. The blade according to claim 1 , wherein the wedge includes a crowned feature.
11. A rotating stage of a gas turbine engine comprising:
a rotor including a slot;
a blade having a root received in the slot, the blade having composite layers including neck plies and tooth plies that are flared relative to the neck plies, the neck plies and tooth plies respectively providing a neck and a root, the root including a tooth, and a wedge provided by wedge plies adhered over the root and the tooth, the wedge configured to transfer a pulling load on the blade to the rotor; and
all of the tooth plies are arranged at a tooth ply angle, and the wedge plies are arranged at a wedge ply angle, the wedge ply angle is at an angle that lies between a radial direction of the blade and the tooth ply angle.
12. The rotating stage according to claim 11 , wherein the composite layers are provided by a matrix composite material, the matrix composite material is integrated with fibers, wherein the neck plies, the tooth plies and the wedge plies are integrated into a unitary matrix composite structure.
13. The rotating stage according to claim 11 , wherein the neck plies extend in a radial direction to provide an airfoil, and the neck plies include a matrix composite material having fibers extending in the radial direction, and the wedge plies include a matrix composite material having fibers extending in a direction transverse to the radial direction.
14. The rotating stage according to claim 11 , wherein the wedge plies extend axially to an end face of the root.
15. The rotating stage according to claim 11 , wherein the wedge plies extend from a tangent point on the tooth to the neck.
16. The rotating stage according to claim 11 , wherein the wedge includes at least one of a coating and a crowned feature.