Abstract: A turbomachine subassembly including a first component forming a portion of a wall of a combustion chamber of the turbomachine and a second component forming a connecting member connecting the first component to a structural element of the combustion chamber, wherein the two components are made from materials having different coefficients of expansion, and wherein the two components are elements of revolution coaxial with a main axis A of the subassembly, and each including an annular radial wall, the radial walls facing one another and bearing against one another axially in a first direction, wherein the second component includes a plurality of clamping tabs, with the clamping tabs collaborating with the first component in order to produce an axial force causing the radial walls to bear against one another.

Abstract: The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner ann

Abstract: Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge, and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.

Abstract: A process for manufacturing a composite material part includes formation of a fibrous texture from refractory ceramic fibres, placement of the fibrous texture in a mould with interposition of a filtration layer between the fibrous texture and a discharge port, the filtration layer including a partially densified fibrous structure, pressure injection of a slurry containing a powder of refractory ceramic particles into the fibrous texture, drainage by the filtration layer of the slurry solvent having passed through the fibrous texture and retention of the powder of refractory ceramic particles within the texture by the filtration layer to obtain a fibrous preform including the fibrous texture filled with refractory ceramic particles and the filtration layer, heat treatment of the refractory ceramic particles present in the fibrous texture of the preform to form a composite material part including the fibrous texture densified by a refractory ceramic matrix and the filtration layer.

Abstract: A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.

Abstract: A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.

Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.

Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.

Abstract: A method for manufacturing a turbomachine blade made of ceramic matrix composite component includes at least a structural part and a functional part secured to the structural part, the method including obtaining an assembly including a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform including a fibrous reinforcement of short fibres, and the second preform or the structural part comprising a woven fibrous reinforcement, and densification of the first preform of the assembly by infiltration with a molten composition.

Abstract: An annular or semi-annular acoustic attenuation structure includes an inner skin and an outer skin, defining between them an annular or semi-annular volume, and a plurality of partitions extending in the space in a radial direction perpendicular to the inner and outer skins and in a circumferential direction. The inner and outer skins and the partitions are made of composite material including a fibrous reinforcement densified by a matrix. The fibrous reinforcement of each partition includes yarns or fibers extending into the fibrous reinforcement of at least one of the inner or outer skins.

Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.

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: A combustion module for a turbomachine is provided and includes an annular casing extending about a longitudinal axis; an annular combustion chamber located inside the casing and comprising coaxial annular walls connected to one another by an annular chamber dome, the walls and the chamber dome consisting of at least two annular envelopes, which are made of a ceramic-matrix composite material. The module can include anti-disengagement devices to keep the annular edges pressing axially against one another and fuel injectors borne by the casing and engaged in apertures of one of the envelopes.

Abstract: A process for manufacturing a part made of a ceramic matrix composite material, includes coating an outer surface of a porous preform with a layer of a fugitive material to form a model of the part to be obtained, the fugitive material being wax or resin, the fugitive material layer in the model not exceeding the highest peak of surface undulations of the preform, and ceramic and/or carbon particles being present in the porosity of the preform, coating the model formed with a ceramic powder composition, heat treating the coated model to remove the fugitive material and form a ceramic shell mold by sintering of the ceramic powder composition, introducing a molten composition including silicon into the shell mold to obtain the part in the shell mold, the molten composition infiltrating the porosity of the preform to form the ceramic matrix, and separating the shell mold from the part obtained.

Abstract: A turbomachine subassembly including a first component forming a portion of a wall of a combustion chamber of the turbomachine and a second component forming a connecting member connecting the first component to a structural element of the combustion chamber, wherein the two components are made from materials having different coefficients of expansion, and wherein the two components are elements of revolution coaxial with a main axis A of the subassembly, and each including an annular radial wall, the radial walls facing one another and bearing against one another axially in a first direction, wherein the second component includes a plurality of clamping tabs, with the clamping tabs collaborating with the first component in order to produce an axial force causing the radial walls to bear against one another.

Abstract: Method for manufacturing a part made from CMC for improving control of the step of densifying the part, and intermediate part for implementing said method, the intermediate part comprising a reinforcement, a matrix comprising a ceramic material, and at least one insert, which is made from a material different from that of the reinforcement and the matrix and which is designed to promote migration of liquid silicon within the intermediate part during a step of densifying the intermediate part.

Abstract: A method for coating fibers, includes desizing sized short fibers having an average length less than or equal to 5 mm, the short fibers being made of ceramic material or carbon, sieving the desized short fibers in order to separate them from any agglomerates of sized short fibers still present, introducing the desized and sieved short fibers into a reactor, and coating the short fibers in the reactor by chemical vapor deposition in a fluidized bed.

Abstract: A nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.

Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.

Abstract: A method for treating a carbon or ceramic yarn includes forming a coating on the yarn in a reaction zone of a reactor by heating a segment of the yarn in the presence of a gas phase in a microwave field, wherein the gas phase includes a mixture of a diluent gas and a coating precursor in the vapor state, and wherein the gas phase is formed at least by introducing the diluent gas into the reactor and mixing the introduced diluent gas with the coating precursor in the reactor before the reaction zone.