Composite blade for an aircraft engine and methods for manufacturing and repairing same
A process for manufacturing a blade made of composite material for a turbomachine. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: placing a preform, produced by three-dimensionally weaving fibers, in a mold, the sheath being positioned on an edge of the preform intended to form the leading edge of the airfoil; and injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying. At least one double-sided adhesive film may be inserted between the sheath and the edge of the preform prior to injection of the resin.
1. A method for repairing a blade that includes a vane having a pressure side and a suction side which extend from a leading edge to a trailing edge of the vane, a metal sheath extending along the leading edge of the vane, at least one adhesive film interposed between the sheath and the leading edge of the vane, and at least one interface fabric interposed between the vane and the adhesive film, wherein the sheath of the blade is damaged and needing to be replaced, the method comprising:
removing the sheath and the adhesive film, and maintaining the interface fabric on the leading edge of the vane; and
gluing a new sheath on the interface fabric.
2. The method according to claim 1 , wherein said adhesive film is cut according to a shape of an edge of a preform utilized to form the blade of the vance and/or the sheath.
3. The method according to claim 1 , wherein the adhesive film is glued on an edge of a preform prior to the positioning of the sheath on said edge, the preform utilized to form the blade of the vane.
4. The method according to claim 1 , wherein the sheath is dihedral in shape and defines a groove with a V-shaped cross-section, said at least one adhesive film being glued on the sheath within the groove.
5. The method according to claim 4 , wherein a first adhesive film is glued in the groove on a first longitudinal wall of the sheath and a second adhesive film is glued in the groove on a second longitudinal wall of the sheath.
6. The method according to claim 4 , wherein, prior to the positioning of the sheath on an edge of a preform utilized to form the blade of the vane, the edge is compressed.
7. The method according to claim 6 , wherein the edge of the preform is compressed until the edge reaches a thickness representing 75% to 95% of a maximum transverse width or dimension of the groove.
8. The method according to claim 6 , wherein the preform is moistened prior to compressing its edge.
9. The method according to claim 1 , wherein the sheath defines a groove, and wherein a single the interface fabric is folded and inserted within the groove.
10. The method according to claim 1 , wherein the adhesive film or the interface fabric is/are heated to promote adhesion.
11. The method according to claim 1 , wherein the adhesive film protrudes from the sheath and extends onto surfaces of a preform not covered by the sheath, the preform utilized to form the blade of the vane.
12. The method according to claim 1 , wherein, prior to the positioning of the sheath on an edge of a preform, the edge is compressed, wherein the preform is utilized to form the blade of the vane.
13. The method according to claim 12 , wherein the preform is moistened prior to compressing the edge.