A method is provided for producing a composite molded body for forming first and second composite molded bodies by molding the first and second composite materials, respectively. The first and second composite molded bodies include joint portions that can be joined to one another. The joint portions are joined together to form a composite material joint body. The first and second composite materials include to-be-joined portions corresponding to the joint portions of the first and second composite molded bodies, respectively. In the space sandwiched between the first and second composite materials a mandrel and a pressing portion are disposed in the mold, a mandrel, and the pressing portion presses the mandrel against the to-be-joined portion of the second composite material.

A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.

A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including, along a span direction, a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile preform parts being connected to one another by three-dimensional weaving. The root includes a plurality of branches. The root preform part of the fiber preform includes a plurality of branches each extending in a branch of the root.

A carbon-fiber-reinforced resin cylinder for propeller shafts includes a first-carbon-fiber-reinforced resin layer having a first carbon fiber, and a second-carbon-fiber-reinforced resin layer having a second carbon fiber and being higher in strength and lower in elastic modulus than the first-carbon-fiber-reinforced resin layer. The first carbon fiber is arranged so as to extend along a longitudinal direction of the cylinder.

A propeller blade or airfoil of a turboprop of composite material includes a fibrous reinforcement densified by a matrix, the propeller blade or airfoil including, in a span direction, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having a three-dimensional weave with a root preform portion present in the root and an aerodynamic preform portion present in the aerodynamic profile, the root and aerodynamic preform portions being linked to one another by the three-dimensional weave. The root preform portion of the fibrous preform includes an unlinked area delimiting an internal root recess forming a cavity opening at a free end of the root.

A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.

A blade spar for a rotor blade for a rotor of an aircraft or vessel, preferably wherein the rotor is a propeller, the blade spar comprising a laminate structure. The laminate structure includes a plurality of plies of fibres in a matrix, wherein the blade spar has generally a longitudinal axis defining a longitudinal direction, the longitudinal axis extending along a radial direction of the rotor. The blade spar includes at least a portion that is curved from the longitudinal axis, wherein the plurality of plies comprises a first ply comprising a plurality of first fibres, wherein an alignment of the first fibres varies along the longitudinal direction to align the first fibres to the curved blade spar.

A method of bonding a composite vane to at least one support. The method includes positioning an end of a vane within a support, causing an adhesive to flow between the vane and the support from an inlet to an outlet, and reversing the flow of adhesive from the outlet towards the inlet.

Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.

A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including, along a span direction, a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile preform parts being connected to one another by three-dimensional weaving. The root includes a plurality of branches. The root preform part of the fiber preform includes a plurality of branches each extending in a branch of the root.