A method of manufacturing a wind turbine blade shell part is described. Fibre mats and a root end insert are laid up in a mould part in a layup procedure by use of an automated layup system. The fibre mats are laid up by use of a buffer so that the fibre mats may continuously be laid up on the mould surface, also during a cutting procedure. The root end insert is prepared in advance and mounted on a mounting plate. The root end insert is lowered onto the mould by use of the mounting plate and a lowering mechanism. After the wind turbine blade shell has been moulded, the mounting plate is removed.

A method of mounting a replacement tip section to an exposed end of a rotor blade includes removing an existing tip section from the rotor blade to create the exposed end of the rotor blade, installing the rotor blade having the exposed end onto a holding fixture, assembling the replacement tip section about the exposed end of the rotor blade, positioning a bonding fixture about the replacement tip section, and curing the replacement tip section to the exposed end of the rotor blade.

A composite blade made of prepreg obtained by impregnating reinforcement fibers with resin and curing the resin-impregnated reinforcement fibers, the composite blade including: a blade root provided on a base end and fitted into a blade groove; an airfoil provided extending from the blade root toward a tip end; and a metal patch provided between the blade groove and the blade root and placed on the blade root. The metal patch includes a plurality of projections protruding toward the blade root.

An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

The present invention relates to a blower vane of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement and a matrix in which the fibrous reinforcement is embedded. The vane comprises a first rigidification insert which extends in a first direction and at least one second insert which is connected to the first in a second direction which is non-collinear with the first direction, the first insert projecting from the vane in order to be connected to a disc of a turbomachine element.

A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

A method for processing a part (10) with an energy beam A mask (70, 80) is arranged between a source of the energy beam and the part. The mask is configured with a beam-transmissive portion (71) in correspondence with mutually opposed portions (12, 14) of the part. Simultaneously heating the mutually opposed portions of the part is performed with energy beamlets passing through the beam-transmissive portions of the mask This simultaneous heating is configured to keep a thermally-induced distortion of the part within a predefined tolerance. Scanning of the mask with the energy beam may be performed without precisely tracking the mutually opposed portions of the part, thereby avoiding a need for complicated numerical programming for tracking a relatively complex geometry defined by the mutually opposed portions of the part.

Methods for manufacturing a turbomachine composite part, such as a fan blade, are provided. The composite part has a fibrous structure with a three-dimensional fibrous preform coated with a surface fibrous web, and which is embedded in a polymer matrix The methods include: forming the surface web in a cavity of a mold in order to shape it, wetting and forming the preform on the surface web in order to shape it, and closing the mold, drying the fibrous structure, and injecting thermosetting resin into the mold in order to form said polymer matrix. The surface web is wetted before and/or during the forming thereof.

The present disclosure is directed to a method for manufacturing a thermoset component having a weldable thermoplastic interface. The method includes forming a polymerized thermoplastic component having a removable protective layer on a portion thereof. Another step includes placing a plurality of dry plies and the thermoplastic component into a mold of the thermoset component with the removable protective layer facing an outer surface of the thermoset component mold. Thus, the method further includes co-infusing the dry plies and thermoplastic component with a resin material so as to form the thermoset component having a weldable thermoplastic interface.

A guide vane for a gas turbine engine, the guide vane including an airfoil made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers agglomerated in the form of a mat, the airfoil being provided at least on a leading edge with a reinforcing strip, the reinforcing strip being made from a single strip of unidirectional fabric or of textile, or by stacking a plurality of pre-impregnated plies of unidirectional fabric or of textile made of carbon fibers or of glass fibers, and at least one platform positioned at a radial end of the airfoil, the platform being made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers.