The disclosed embodiment is related to a manufacturing method of a die-formed 3-dimensional plastic impeller of a centrifugal pump and the impeller manufactured thereby, including a mold for twisted blade and a mold for impeller outlet, the mold for twisted blade is configured to form a twisted blade portion of each blade of the impeller, the mold for impeller outlet is configured to form a rear portion of each blade, a hub rim part of the impeller, and a shroud rim part of the impeller so that the hub rim part, the shroud rim part, and the blades are formed in a single piece at the same molding process.

A gas turbine component made of composite material includes a fiber reinforcement having a three-dimensional weave between a plurality of warp threads and a plurality of weft threads, the fiber reinforcement being densified by a matrix. The densified fiber reinforcement extends in width between a downstream end and an upstream end in an axial direction and in thickness between an inner surface and an outer surface in a radial direction. The fiber reinforcement densified by the matrix has a hollowed-out portion extending through the entire thickness of the fiber reinforcement. A composite material filler piece is present in the free volume of the component delimited by the hollowed-out portion, the filler piece including a fiber preform having a three-dimensional weave, the fiber preform being densified by a matrix.

A thrust reverser blocker door includes a body portion and a mounting structure coupled to the body portion. The body portion includes a facesheet, a backsheet, and a honeycomb core. The facesheet and/or the backsheet comprises a first thermoplastic material and the mounting structure comprises a second thermoplastic material. A method for manufacturing a thrust reverser blocker door may comprise thermoforming a sandwich panel comprising a facesheet, a backsheet, and a honeycomb core. The method may further comprising overmolding a mounting structure onto the backsheet. The first thermoplastic material may comprise a continuous fiber reinforced thermoplastic composite material. The second thermoplastic material may comprise a discontinuous fiber reinforced thermoplastic composite material.

Sandwich-structured noise-attenuating and/or structural panels and methods of manufacturing such panels using ultrasonic welding are described. The method includes: receiving a backing member, a sheet and a cellular structure; assembling the cellular structure between the backing member and the sheet; and ultrasonically welding the backing member and the sheet together.

A tooling for injecting a polymer resin into a fibrous preform for the manufacture of a revolution part in composite material including a barrel shape with an inside diameter of smaller diameter delimiting the revolution part into an upstream portion and a downstream portion of the inside diameter, the upstream portion including a back-draft intermediate portion, injection tooling wherein, to allow a demolding of the barrel-shaped part once the injection and the polymerization of the polymer resin are carried out, the injection tooling includes on the one hand a frustoconical drum comprising a first drum portion in direct contact with an inner surface of the portion of the revolution part downstream of the inside diameter and a second drum portion and on the other hand a segmented insert whose outer surface matches an inner surface of the portion of the revolution part upstream of the inside diameter.

A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.

A gas turbine casing made of composite material from fiber reinforcement densified by a matrix. The casing includes at least one stiffener portion extending at a radius greater than the radius of upstream and downstream portions of the casing that are adjacent to the stiffener portion so as to form an annular recess in the inside surface of the casing.

Various components and methods related to a leading edge assembly are disclosed. The leading edge assembly can include an outer strike shell and a foam core. The foam core can be located inside the outer strike shell. The leading edge assembly can include a heating element with a plurality of sensors and wires. A method of manufacturing a leading edge assembly can include forming a composite layer, applying a metallic layer to the composite layer, installing an electronic device, and inserting a foam core into a cavity bounded by the composite layer and/or the electronic device.

A method is for fabricating a part by additive manufacturing while sparing certain particularly sensitive surfaces of the part, and in particular surfaces that have an influence on the aerodynamics of the final part. The method includes the following steps: providing a digital model of a part that is to be fabricated, the part that is to be fabricated including at least one surface that is to be spared, and orienting the digital model relative to a construction direction wherein the part is to be constructed in such a manner that the surface that is to be spared presents a construction angle greater than 30°, preferably greater than 50°.

A process for shaping a fibrous preform includes the insertion of each attachment tab of a fibrous texture into a corresponding aperture of an impregnation mandrel, the attachment by a removable retaining device of each tab inserted into each aperture against a surface of the impregnation mandrel, the winding under tension of the fibrous texture on the impregnation mandrel in order to obtain a fibrous preform.