A disclosed method is suitable for repairing a blade of a turbomachine rotor, particularly a turbomachine fan, that includes a vane made from an organic-matrix composite and a metallic shield that is bonded to a leading edge of the vane and has a damaged region. The method includes steps of resetting the leading edge of the vane cooling the entire vane, followed by a step of refilling the damaged region by adding a metallic material to this damaged region and melting the material using a laser, and a step of tailoring the damaged region by machining the molten material.

A method for additively printing extension segments on workpieces using an additive manufacturing machine includes controlling, with a computing system, an operation of a print head of the machine such that a region of interest of a build plate of the machine is scanned with an electromagnetic radiation beam. Additionally, the method includes receiving, with the computing system, data associated with reflections of the beam off of the build plate as the region interest is scanned. Furthermore, the method includes receiving, with the computing system, data associated with a location of the beam relative to the build plate. Moreover, the method includes determining, with the computing system, a location of a workpiece interface based on the received data. In addition, the method includes controlling, with the computing system, the operation of the print head such that an extension segment is additively printed on the determined workpiece interface.

The present invention relates to a method of manufacturing a wind turbine blade using a two-step curing process, wherein the second curing is performed in the presence of a resin flow medium (76) comprising a curing inhibitor.

A method for assembling a body and a cover of a vane by polymerisation of a resin. The covens positioned on a junction face of the body covered with this resin. A sheet is placed against a pressure side of the vane, formed by an outer face of the cover and an outer face of the body, so as to define a space sealed with a bead of mastic sealant. The bead of mastic sealant is deposited on the outer face of the body, around the junction face of this body. The space between the sheet and the pressure side of the vane is placed under vacuum during a heating operation of the vane in an autoclave, in order to press the cover against the body of the vane.

A method of assembling a member and a cap of a vane using a tool which allows the application of a pressing force of the cap against the member during a step of polymerisation by heating a resin for bonding these components. To this end, the tool includes an inflatable bladder and a pocket which surrounds the bladder and the vane so that the inflated bladder applies the pressing force. The heating can be carried out by resistors which are mounted in the bladder and/or using a device for supplying external heat.

A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

A method for additively printing extension segments on workpieces using an additive manufacturing machine includes controlling, with a computing system, an operation of a print head of the machine such that a region of interest of a build plate of the machine is scanned with an electromagnetic radiation beam. Additionally, the method includes receiving, with the computing system, data associated with reflections of the beam off of the build plate as the region interest is scanned. Furthermore, the method includes receiving, with the computing system, data associated with a location of the beam relative to the build plate. Moreover, the method includes determining, with the computing system, a location of a workpiece interface based on the received data. In addition, the method includes controlling, with the computing system, the operation of the print head such that an extension segment is additively printed on the determined workpiece interface.

An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

A method of manufacturing a fan blade for a gas turbine engine. The method includes providing a compression mould having an internal mould surface corresponding to an outer profile of a fan blade, providing opposing first and second laminates to form a shell corresponding to the mould surface, each laminate comprising a lay-up of plies of fibre reinforcement material, applying a core material comprising quasi-isotropic short fibre reinforced resin in the compression mould so that with the compression mould in a moulding configuration the core material is enclosed by the shell, the core material and the shell forming a pre-form for the fan blade, applying pressure to compress the pre-form so that it conforms to the mould surface, and applying heat to cure the pre-form.

A system for manufacturing a rotor blade comprises a first tooling, positioned at a factory location and configured to assemble a first blade module, comprising a first-module skin and a first-module spar, each comprising a first thermoplastic polymer and a first reinforcement material. The system also comprises a second tooling, configured to assemble a second blade module, comprising a second-module skin and a second-module spar, each comprising a second thermoplastic polymer and a second reinforcement material. The system further comprises a first support, positioned at a field location and configured to receive the first blade module, and a second support, positioned at the field location and configured to receive the second blade module. The system also comprises a spar welding assembly, positioned at the field location and configured to join the first-module spar with the second-module spar.