Abstract: A process for coating an aircraft turbomachine component with an erosion-resistant coating, includes depositing the erosion-resistant coating by hot powder-coating on an aircraft turbomachine component made of an organic-matrix composite material or of a metallic material, the erosion-resistant coating including a polyurethane or silicone polymer, the polymer having a glass transition temperature of less than or equal to ?30° C.

Abstract: A method for repairing a part for an aircraft turbine engine, the part including a lower panel, an upper panel and a core having a honeycomb structure arranged between the lower panel and the upper panel, the part having an unimpaired portion and an at least partially impaired portion, the repair method including the following steps: (a) removing at least one portion of the lower panel or the upper panel from an area to be repaired; (b) removing at least one portion of the core from the area to be repaired; (c) reforming the core in the area to be repaired directly on the part by additive manufacturing; (d) reforming the lower panel or the upper panel in the area to be repaired, directly on the part.

Abstract: A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part.

Abstract: A method for removing a component fixed to an aeronautical part, the aeronautical part comprising a first material, and the component comprising a second material different from the first material, the method comprising steps of determining the thicknesses of the component as a function of the position on the component, and of removing the component by means of a pressurized water jet moving over the component as a function of the thicknesses determined in the determination step.

Abstract: A weaving installation (400) comprises a loom (100) for making a woven texture by weaving between a plurality of threads, at least part of the plurality of threads being carbon threads (210, 211, 212, 213, 214, 215), the carbon threads each being individually stored on one bobbin of a plurality of carbon thread storage bobbins (220, 221, 222, 223, 224, 225) present upstream of the loom. The installation further comprises a plurality of pairs of first and second electrical contacts (301, 302; 303, 304; 305, 306; 307, 308; 309, 310; 311, 312) present between the storage bobbins (220, 221, 222, 223, 224, 225) and the loom (100). Each pair of first and second electrical contacts is present in the path of a carbon thread, the first and second contacts of each pair being intended to be in electrical contact with a given carbon thread. The contacts of each pair of first and second contacts are further connected to an open-circuit detection circuit (230).

Abstract: A process for coating an aircraft turbomachine component with an erosion-resistant coating, includes depositing the erosion-resistant coating by hot powder-coating on an aircraft turbomachine component made of an organic-matrix composite material or of a metallic material, the erosion-resistant coating including a polyurethane or silicone polymer, the polymer having a glass transition temperature of less than or equal to ?30° C.

Abstract: A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part.

Abstract: The invention relates to a method of separating at least one portion of a metallic part (3) glued to a composite material part (2) of the carbon-epoxy type, comprising a step to degrade the glued interface between the metallic part (3) and the composite material part (2). The metallic part (3) and the composite material part (2) are electrically connected to a dc electrical voltage generator so that an electrical potential difference can be applied to them to generate partial discharges in the glued interface to degrade the interface.

Abstract: A process for repairing a part made of organic matrix composite material coated with at least one layer of paint includes removing the paint at a damaged area of the part, removing the composite material at the damaged area so as to form a recessed portion, depositing a repair resin in the recessed portion, curing the repair resin, applying at least one layer of paint to the repair area. The repair resin is loaded with magnetically detectable particles.

Abstract: A turbomachine blade including a blade body made of fiber-reinforced organic matrix composite material, the blade body having a pressure side and a head provided with an apex; an erosion protection film which is made of a thermoplastic polymer and adhered to the blade body; a reinforcement layer which is made of a thermosetting polymer and positioned on the erosion protection film on the head of the blade.

Abstract: A tool enables non-destructive inspection of a flat part by ultrasonic transmission. The tool includes a clamp with a first arm pivotally coupled to a second arm about a pivot connection. An ultrasound transmitter is coupled to a first end of the first arm by a first ball joint connection, and an ultrasound receiver coupled to a first end of the second arm by a second ball joint connection. The transmitter has an active face for transmitting a sound signal that is received by an active face of the receiver. The active faces of the transmitter and the receiver are substantially at the same distance from the pivot connection. The tool further includes an alignment device that maintains the active faces of the transmitter and the receiver oriented towards each other and substantially parallel.

Abstract: The invention relates to a method of separating at least one portion of a metallic part (3) glued to a composite material part (2) of the carbon-epoxy type, comprising a step to degrade the glued interface between the metallic part (3) and the composite material part (2). The metallic part (3) and the composite material part (2) are electrically connected to a dc electrical voltage generator so that an electrical potential difference can be applied to them to generate partial discharges in the glued interface to degrade the interface.

Abstract: A tool enables non-destructive inspection of a flat part by ultrasonic transmission. The tool includes a clamp with a first arm pivotally coupled to a second arm about a pivot connection. An ultrasound transmitter is coupled to a first end of the first arm by a first ball joint connection, and an ultrasound receiver coupled to a first end of the second arm by a second ball joint connection. The transmitter has an active face for transmitting a sound signal that is received by an active face of the receiver. The active faces of the transmitter and the receiver are substantially at the same distance from the pivot connection. The tool further includes an alignment device that maintains the active faces of the transmitter and the receiver oriented towards each other and substantially parallel.