Abstract: A process for depositing a coating on a continuous fibre of carbon or silicon carbide from a precursor of the coating, includes heating a segment of the fibre in the presence of the coating precursor in a microwave field so as to bring the surface of the segment to a temperature allowing the coating to form on the segment from the coating precursor, wherein the segment of fibre is in the presence of a supercritical phase of the precursor of the coating in the reactor and the coating is formed by supercritical phase chemical deposition in the reactor.

Abstract: The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

Abstract: A process for depositing a coating on a continuous carbon or silicon carbide fibre from a coating precursor, includes at least heating a segment of the fibre in the presence of the coating precursor in a microwave field so as to bring the surface of the segment to a temperature enabling the coating to be formed on the segment from the coating precursor.

Abstract: A process for manufacturing pyrocarbon, includes forming pyrocarbon by a calefaction process from at least one C2 to C6 alcohol or polyalcohol precursor, the precursor being ethanol, rough laminar pyrocarbon being obtained by imposing a temperature of between 1250° C. and 1325° C. during calefaction.

Abstract: A process for manufacturing a composite material part including a particulate reinforcement densified by a ceramic matrix, the process including: formation of a blank of the part to be manufactured by shaping a mixture including a binder, first ceramic or carbon particles intended to form the particulate reinforcement of the part and second ceramic or carbon particles distinct from the first particles, removal or pyrolysis of the binder present in the blank to obtain a porous preform of the part to be manufactured, and infiltration of the porosity of the preform by a molten composition including a metal in order to obtain the part.

Abstract: A method for producing an acoustic attenuation panel from a composite material with a ceramic oxide matrix is provided that includes draping a plurality of plies having fibrous reinforcements including fibers of ceramic material in a mold to define a first skin, depositing blocks made of fugitive material on the first skin such that a space between two blocks is defined, and draping a second plurality of plies on a surface formed by the blocks such that a second skin is defined. Rounded corners of the blocks define radii for connecting the first and second skins with walls of a honeycomb core of the acoustic panel. The method further includes using a liquid medium to infiltrate the skins and spaces with a precursor of a ceramic phase, removing the liquid medium by evaporation or polymerization, and sintering to consolidate the ceramic oxide material and removal the fugitive material.

Abstract: A method of fabricating a composite part, includes forming a fiber preform for the part that is to be obtained by depositing a plurality of fiber structures impregnated with a thermoplastic polymer onto a surface, with deposition being performed by automated fiber placement; eliminating the thermoplastic polymer present in the preform by dissolution with a solvent; and injecting a liquid impregnation composition into the pores of the fiber preform after eliminating the thermoplastic polymer in order to form a matrix in the pores of the fiber preform.

Abstract: An installation for depositing a shaped filled roving intended to be used to manufacture a composite-material component, includes a device for feeding a fibrous roving impregnated with a composition including a binder and ceramic or carbon fillers, a die for shaping and draining the binder defined by at least one porous surface, the die having an evolving section between an inlet section and an outlet section, the inlet section being larger than the outlet section, a support in communication with the die outlet on which the shaped roving is to be deposited, and a first conveying device configured to convey the roving from the feed device through the die and to the support.

Abstract: A process for depositing a coating on a continuous carbon or silicon carbide fibre from a coating precursor, includes at least heating a segment of the fibre in the presence of the coating precursor in a microwave field so as to bring the surface of the segment to a temperature enabling the coating to be formed on the segment from the coating precursor.

Abstract: The present disclosure concerns a porous body made of a ceramic-matrix composite material for an acoustic attenuation panel and a method of manufacturing the porous body. The porous body includes a plurality of interwoven ceramic fibers, a metal oxide matrix, and a plurality of channels interwoven with the ceramic fibers and interconnected together. The channels define at least one cavity. In one form, at least one channel is wrapped around a ceramic fiber. In another form, at least one ceramic fiber and at least one channel are twisted together. In yet another form, at least one channel is wrapped around a ceramic fiber and twisted with the ceramic fiber. The present disclosure also concerns an acoustic attenuation panel including the porous body and an aircraft propulsion unit having such a panel.

Abstract: A process for manufacturing a composite material part including a particulate reinforcement densified by a ceramic matrix, the process including: formation of a blank of the part to be manufactured by shaping a mixture including a binder, first ceramic or carbon particles intended to form the particulate reinforcement of the part and second ceramic or carbon particles distinct from the first particles, removal or pyrolysis of the binder present in the blank to obtain a porous preform of the part to be manufactured, and infiltration of the porosity of the preform by a molten composition including a metal in order to obtain the part.

Abstract: An installation for depositing a shaped filled roving intended to be used to manufacture a composite-material component, includes a device for feeding a fibrous roving impregnated with a composition including a binder and ceramic or carbon fillers, a die for shaping and draining the binder defined by at least one porous surface, the die having an evolving section between an inlet section and an outlet section, the inlet section being larger than the outlet section, a support in communication with the die outlet on which the shaped roving is to be deposited, and a first conveying device configured to convey the roving from the feed device through the die and to the support.

Abstract: A process for depositing a coating on short fibres of carbon or silicon carbide from a coating precursor, the short fibres having a length of between 50 ?m and 5 mm, the process including at least heating the short fibres by placing a mixture including the fibres and a liquid phase of the coating precursor in a microwave field so as to bring the surface of the fibres to a temperature allowing the coating on the fibres from the coating precursor to be formed by calefaction.

Abstract: A process for manufacturing a friction component made of composite material, includes the densification of a fibrous preform of carbon yarns by a matrix including at least pyrocarbon and at least one ZrOxCy phase, where 1?x?2 and 0?y?1, the matrix being formed by chemical vapor infiltration at least from a first gaseous precursor of pyrocarbon and a second gaseous precursor including zirconium, the second precursor being an alcohol or a C1 to C6 polyalcohol modified by linking the oxygen atom of at least one alcohol function to a group of formula —Zr—R3, the substituents R being identical or different, and R being selected from: —H, C1 to C5 carbon chains and halogen atoms.

Abstract: A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

Abstract: The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

Abstract: An rear fairing for a pylon supporting an aircraft turbojet engine forms an aerodynamic surface covering the base of the pylon. The rear fairing is elongated in a longitudinal direction and includes a floor arranged opposite the hot gases exiting the turbojet engine and side walls constituting aerodynamic surfaces. The floor and the side walls include ceramic matrix composite materials made from preforms formed by layers of superimposed warp and weft yarns, the preforms have interlayer weaving yarns connecting the layers to one another.

Abstract: A method of fabricating a composite part, includes forming a fiber preform for the part that is to be obtained by depositing a plurality of fiber structures impregnated with a thermoplastic polymer onto a surface, with deposition being performed by automated fiber placement; eliminating the thermoplastic polymer present in the preform by dissolution with a solvent; and injecting a liquid impregnation composition into the pores of the fiber preform after eliminating the thermoplastic polymer in order to form a matrix in the pores of the fiber preform.

Abstract: A front lip of a turbofan engine nacelle is provided, defined at the rear by a partition wall, the lip comprising an annular de-icing space including a tube for supplying hot air in order to de-ice the outer walls thereof, said lip also including acoustic panels arranged on the wall thereof substantially radially facing the axis of the nacelle. The front lip includes hot-air outlet bores/piercings which are arranged between the front end of the lip and said acoustic panels, which allow a flow of hot air, from said annular space, forming a substantially regular film which covers said acoustic panels with a boundary layer in order to heat said acoustic panels.

Abstract: The present disclosure relates to a part made from composite material that includes a base and a T-shaped reinforcement. The T-shaped reinforcement includes a first L-shaped element having a first right-angled connection portion and a second L-shaped element having a second right-angled connection portion. The part further includes a plurality of needles, each connecting the base to the T-shaped reinforcement of the part, close to the connection portions and extending in multiple directions so as to oppose, in particular, the separation of the base from the T-shaped reinforcement.