Method for manufacturing a composite blade for an aircraft engine
A process for manufacturing a blade made of composite material for a turbomachine is provided. 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: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.
1 . A method for manufacturing a blade made of composite material for a turbomachine, said blade comprising a vane having a pressure side and a suction side which extend from a leading edge to a trailing edge of the vane, the blade further comprising a metal shield extending along the leading edge of the vane, the method comprising:
disposing a preform made by three-dimensionally weaving fibers in a mold, the shield being positioned on an edge of the preform to form the leading edge of the vane, and a polymerizable adhesive being interposed between the shield and the edge of the preform, said polymerizable adhesive having not reached a gel point of said polymerizable adhesive,
after the preform, the shield and the polymerizable adhesive interposed between the shield and the edge of the preform have been disposed into the mold, beginning injecting polymerizable resin into the mold before the polymerizable adhesive reaches a gel point of said polymerizable adhesive so that the polymerizable resin impregnates the preform to form the vane after solidification, and so that the polymerizable resin passes through the polymerizable adhesive to reach the shield,
wherein the polymerizable resin is injected for a period of time during which said polymerizable adhesive reaches the gel point so that the injection of the polymerizable resin is stopped after said adhesive has reached the gel point.
2 . The method according to claim 1 , wherein the polymerizable adhesive is in the form of an adhesive film.
3 . The method of claim 1 , wherein said polymerizable adhesive reaches the gel point in the middle of the period of time.
4 . The method according to claim 2 , wherein the period of time starts at least five minutes before the polymerizable adhesive reaches the gel point, and ends at least five minutes after the polymerizable adhesive reaches the gel point.
5 . The method according to claim 1 , wherein the temperature of the mold is regulated so that it is kept constant during the period of time.
6 . The method of claim 1 , wherein the temperature of the mold is maintained at a temperature of at least 160° C. during the period of time.
7 . The method of claim 1 , wherein the polymerizable resin is an epoxy resin.
8 . The method of claim 1 , wherein the polymerizable adhesive is an epoxy adhesive.
9 . A method for manufacturing a blade made of composite material for a turbomachine, said blade having a vane with a pressure side and a suction side which extend from a leading edge to a trailing edge of the vane, the blade further having a metal shield extending along the leading edge of the vane, the method comprising:
disposing a preform formed of a three-dimensional weave of fibers in a mold, the shield being positioned on an edge of the preform to form the leading edge of the vane, wherein a polymerizable adhesive is interposed between the shield and the edge of the preform, the polymerizable adhesive having a gel point;
injecting polymerizable resin into the mold to impregnate the preform to form the vane after solidification,
wherein the polymerizable resin is injected over a period of a time during which the polymerizable adhesive reaches the gel point, and
wherein the injection of polymerizable resin begins before the polymerizable adhesive reaches the gel point so that the injection of the polymerizable resin is stopped after said adhesive has reached the gel point.
10 . A method for manufacturing a blade made of composite material for a turbomachine, said blade having a vane with a pressure side and a suction side which extend from a leading edge to a trailing edge of the vane, the blade further having a metal shield extending along the leading edge of the vane, the method comprising:
obtaining a preform made by a three-dimensionally weave of fibers in a mold;
positioning the shield on an edge of the preform to form the leading edge of the vane;
placing a polymerizable adhesive between the shield and the edge of the preform, the polymerizable adhesive having a gel point;
disposing the preform, the shield and the polymerizable adhesive into a mold; and
prior to the gel point of the polymerizable adhesive, injecting polymerizable resin into the mold to impregnate the preform to form the vane after solidification,
wherein the polymerizable resin is continuously injected throughout a time period during which the polymerizable adhesive reaches the gel point so that the injection of the polymerizable resin is stopped after said adhesive has reached the gel point.
11 . The method according to claim 10 , wherein the polymerizable adhesive is in the form of an adhesive film, and wherein the adhesive film is placed into a groove of the shield, the groove being configured to receive the edge of the perform.
12 . The method according to claim 10 , wherein the time period starts at least five minutes before the polymerizable adhesive reaches the gel point, and ends at least five minutes after the polymerizable adhesive reaches the gel point.