Abstract: A mould for obtaining an element is provided. The mould includes an outer face and a plurality of parallel ribs and/or grooves formed on the outer face. One of the walls of the mould includes ribs and/or grooves of which at least a portion of the ribs and/or grooves can be retracted, at least temporarily, such that at least a portion of the surface of the wall is smooth.

Abstract: The invention concerns an aircraft propulsion system comprising at least one member (1, 3, 4, 8) in contact with a turbulent flow of a stream (F), characterised in that said member is covered, at least partially, by a piezoelectric structure (S) such as a piezoelectric film, said structure (S) comprising a grooved structure (5, 6, 7, 9) comprising a series of grooves, in contact with the flow of the stream, the grooves extending in the direction of flow of the stream, the grooved structure comprising at least one geometric parameter (h, s, w) configured to adapt depending on at least one parameter of the flow of the stream and/or an operating point of the propulsion system and/or an engine speed of the propulsion system.

Abstract: A method includes obtaining an image of a composite material part, each pixel of the image representing material density at a point of the part represented by that pixel; extracting from the image, for at least one fiber element of the part, a line that is representative of that element along its length; for each extracted line extending this line in width at reference points in compliance with the width of the fiber element, this extension resulting, for each reference point, in extended points; and associating an orientation with each extended point associated with a reference point, which orientation is parallel to the direction of the line at that reference point; evaluating, for a plurality of extended points, a mean orientation of the fiber elements at those points; and determining, for a plurality of orientations, a proportion of elements having those orientations from among the evaluate mean orientations.

Abstract: A method for manufacturing of a part made of composite material including pre-compacting to a predetermined shape of a mixture of a first thermosetting resin with discontinuous long fibers so as to form a first preform, pre-curing the first preform until an intermediate conversion stage corresponding to a solidification of said first resin, contacting the first preform with a second preform including a fiber structure of continuous fibers impregnated with a second thermosetting resin, polymerizing the first and second preforms so as to form a part made of composite material including a body made of composite material including reinforcement made of continuous fibers consolidated by an organic matrix provided with a portion made of composite material including reinforcement made of discontinuous long fibers consolidated by an organic matrix.

Abstract: The invention relates to a method for fire protection (S) of a part (1) of a gas-turbine engine made of a composite material comprising a main fibrous reinforcement compregnated by a main matrix, the protection method (S) comprising the following steps: preforming (S1) a panel of prepreg (20) such as to grant same a shape corresponding to the shape of a surface (3) of the part (1) to be protected against fire, said panel of prepreg (20) comprising a secondary fibrous reinforcement compregnated by a secondary matrix; applying (S2) the panel of prepreg (20) thus preformed to the part (1); and securing (S3) the panel of prepreg (20) to the surface (3) by thermal treatment of the part (1) provided with said panel of prepreg (20) in order to obtain a fire-protection layer (2).

Abstract: A method includes obtaining an image of a composite material part, each pixel of the image representing material density at a point of the part represented by that pixel; extracting from the image, for at least one fiber element of the part, a line that is representative of that element along its length; for each extracted line extending this line in width at reference points in compliance with the width of the fiber element, this extension resulting, for each reference point, in extended points; and associating an orientation with each extended point associated with a reference point, which orientation is parallel to the direction of the line at that reference point; evaluating, for a plurality of extended points, a mean orientation of the fiber elements at those points; and determining, for a plurality of orientations, a proportion of elements having those orientations from among the evaluate mean orientations.

Abstract: The method including defining a volume element and packing the volume element with digital elements modelling fiber elements of the composite material, and extending longitudinally along a main axis, the packing including associating each digital element with a position in a plane in three-dimensional space and with an orientation of its main axis; and successively positioning each digital element in the volume element in compliance with the position and the orientation that are associated therewith, this positioning including putting the digital element into contact with a wall of the volume element and/or a previously-positioned digital element, and geometrically adapting the digital element to the wall and/or to the previously-positioned element with which it is in contact; a portion of a digital element being subjected to a deformation other than having its longitudinal axis inclined relative to the main axis of the digital element.

Abstract: A mould for obtaining an element is provided. The mould includes an outer face and a plurality of parallel ribs and/or grooves formed on the outer face. One of the walls of the mould includes ribs and/or grooves of which at least a portion of the ribs and/or grooves can be retracted, at least temporarily, such that at least a portion of the surface of the wall is smooth.

Abstract: The invention concerns an aircraft propulsion system comprising at least one member (1, 3, 4, 8) in contact with a turbulent flow of a stream (F), characterised in that said member is covered, at least partially, by a piezoelectric structure (S) such as a piezoelectric film, said structure (S) comprising a grooved structure (5, 6, 7, 9) comprising a series of grooves, in contact with the flow of the stream, the grooves extending in the direction of flow of the stream, the grooved structure comprising at least one geometric parameter (h, s, w) configured to adapt depending on at least one parameter of the flow of the stream and/or an operating point of the propulsion system and/or an engine speed of the propulsion system.

Abstract: Provided is a method of fabricating a force transfer part including at least one lug made of composite material that is to receive a pin for making a pivot connection with another part. The method includes making a fiber preform for a main body of the part and making a preform for a reinforcing ring out of discontinuous long fibers, making the reinforcing ring preform to match the dimensions of at least one bore in the preform of the main body, inserting the reinforcing ring preform in the bore of the preform of the main body, and polymerizing the reinforcing ring and main body preforms in injection tooling. A force transfer part obtained by such a method is also provided.

Abstract: A method for manufacturing of a part made of composite material including pre-compacting to a predetermined shape of a mixture of a first thermosetting resin with discontinuous long fibers so as to form a first preform, pre-curing the first preform until an intermediate conversion stage corresponding to a solidification of said first resin, contacting the first preform with a second preform including a fiber structure of continuous fibers impregnated with a second thermosetting resin, polymerizing the first and second preforms so as to form a part made of composite material including a body made of composite material including reinforcement made of continuous fibers consolidated by an organic matrix provided with a portion made of composite material including reinforcement made of discontinuous long fibers consolidated by an organic matrix.

Abstract: The method including defining a volume element and packing the volume element with digital elements modelling fiber elements of the composite material, and extending longitudinally along a main axis, the packing including associating each digital element with a position in a plane in three-dimensional space and with an orientation of its main axis; and successively positioning each digital element in the volume element in compliance with the position and the orientation that are associated therewith, this positioning including putting the digital element into contact with a wall of the volume element and/or a previously-positioned digital element, and geometrically adapting the digital element to the wall and/or to the previously-positioned element with which it is in contact; a portion of a digital element being subjected to a deformation other than having its longitudinal axis inclined relative to the main axis of the digital element.

Abstract: The invention relates to a method for fire protection (S) of a part (1) of a gas-turbine engine made of a composite material comprising a main fibrous reinforcement compregnated by a main matrix, the protection method (S) comprising the following steps: preforming (S1) a panel of pre-preg (20) such as to grant same a shape corresponding to the shape of a surface (3) of the part (1) to be protected against fire, said panel of prepreg (20) comprising a secondary fibrous reinforcement compregnated by a secondary matrix; applying (S2) the panel of prepreg (20) thus preformed to the part (1); and securing (S3) the panel of prepreg (20) to the surface (3) by thermal treatment of the part (1) provided with said panel of prepreg (20) in order to obtain a fire-protection layer (2).

Abstract: The invention provides a method of fabricating a force transfer part (100) including at least one lug (108) made of composite material that is to receive a pin for making a pivot connection with another part, the method comprising making a fiber preform for a main body of the part and making a preform for a reinforcing ring out of discontinuous long fibers, making the reinforcing ring preform to match the dimensions of at least one bore in the preform of the main body, inserting the reinforcing ring preform in the bore of the preform of the main body, and polymerizing the reinforcing ring and main body preforms in injection tooling. The invention also provides a force transfer part obtained by such a method.

Abstract: A device for protecting a computer of an aircraft turbine engine, the device comprising a box containing the computer and a cover covering the box, the box being supported by tabs forming integral portions of the box and maintaining a flow of air between the bottom of the box and a portion of the casing of the engine on which they are to come into secure contact via resilient studs, the box being made of a composite material.

Abstract: A turbine engine support part including a main structure made of composite material and a reinforcing secondary structure made of metal and integrated in the main structure, the secondary structure presenting a geometrical shape and dimensions configured to impart mechanical strength to the support part in event of the main structure being destroyed.

Abstract: A device for protecting a computer of an aircraft turbine engine, the device comprising a box containing the computer and a cover covering the box, the box being supported by tabs forming integral portions of the box and maintaining a flow of air between the bottom of the box and a portion of the casing of the engine on which they are to come into secure contact via resilient studs, the box being made of a composite material.