Structurally reinforced composite components are disclosed having access openings reinforced to increase strain load and buckling load without adding weight to the composite components by inducing out-of-plane regions proximate to the access opening during composite prepreg laminate layup.

Structurally reinforced composite components are disclosed having access openings reinforced to increase strain load and buckling load without adding weight to the composite components by inducing out-of-plane regions proximate to the access opening during composite prepreg laminate layup.

Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together.

A laying head for manufacturing a three-dimensional preform includes an inlet configured to feed in a plurality of dry rovings. A fiber conveying device simultaneously and mutually-independently conveys, in a fiber supplying direction, the rovings fed-in via the inlet. An outlet is arranged downstream of the fiber conveying device in the fiber supplying direction and simultaneously lays the plurality of rovings on a workpiece carrier to manufacture the three-dimensional preform. A fiber-cutting device is disposed downstream of the fiber conveying device and upstream of the outlet in the fiber supplying direction and cuts the rovings. A nozzle applies a medium onto the rovings. A slit-shaped through gap of the nozzle has a height is equal to the height of the dry rovings in the thickness direction plus a margin that is sufficiently small so as to cause the medium to be forcibly embedded into the dry rovings.

A laying head for manufacturing a three-dimensional preform includes an inlet configured to feed in a plurality of dry rovings. A fiber conveying device simultaneously and mutually-independently conveys, in a fiber supplying direction, the rovings fed-in via the inlet. An outlet is arranged downstream of the fiber conveying device in the fiber supplying direction and simultaneously lays the plurality of rovings on a workpiece carrier to manufacture the three-dimensional preform. A fiber-cutting device is disposed downstream of the fiber conveying device and upstream of the outlet in the fiber supplying direction and cuts the rovings. A nozzle applies a medium onto the rovings. A slit-shaped through gap of the nozzle has a height is equal to the height of the dry rovings in the thickness direction plus a margin that is sufficiently small so as to cause the medium to be forcibly embedded into the dry rovings.

The invention provides a powder pre-preg comprising as sole resin a vinyl ester resin having a Tg in the range of −5 to +30° C. and a melt viscosity @100° C. in the range of 2 to 75 dPa.Math.s, which can be used in making a composite at a temperature as low as 80° C.

The invention provides a powder pre-preg comprising as sole resin a vinyl ester resin having a Tg in the range of −5 to +30° C. and a melt viscosity @100° C. in the range of 2 to 75 dPa.Math.s, which can be used in making a composite at a temperature as low as 80° C.

A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).

A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).

A method of producing a composite article is disclosed that includes generating composite plies from a low tack composite prepreg material, connecting, by an ultrasonic welding device, two or more of the composite plies by increasing their tackiness to form a composite stack, and forming, by a compression molding device, a composite article from the composite stack.