Abstract: A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tube of a second individual module and the gas inlet opening of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.

Abstract: An assembly for a turbomachine includes at least a first part and a second part, and at least one bolt including a screw engaging with a nut. The screw extends through respective openings in the first part and in the second part. The bolt includes a support member having an annular collar mounted between the screw or the nut, and the first part. The collar has a support surface abutting, at least partially, on a complementary support surface of the first part. The collar also includes a recessed annular groove extending at the inner periphery of the collar.

Abstract: A method for manufacturing a composite panel is described. The method includes producing a first wall, a second wall, a third wall and a fourth wall from composite materials including an oxide matrix and long oxide fibres; from the first and second walls, producing a cellular core including a plurality of cells, each cell including a first end and an opposing second end, covering the first and second ends of the cells of the cellular core with the third wall and the fourth wall, respectively, so as to close the ends of said cells.

Abstract: An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.

Abstract: The invention relates to a three-dimensionally woven multilayer fibrous structure (20) having the same number of warp yarns woven at any level along the warp direction, the fibrous structure (20) comprising, in the warp direction, a first part (22) and a second part (24), the first part (22) having a thickness measured in a direction perpendicular to the warp and weft directions, greater than the second part (24), characterised in that the spacing between two weft planes along the warp direction is greater in the second part than in the first part (22), and in that the number of weft yarns is lower in the second part (24) than in the first part (22).

Abstract: An abradable coating includes a tubular cell structure, wherein the the tubular cell structure includes a fibrous reinforcement of discontinuous short fibers which is densified by a ceramic matrix.

Abstract: A method including a step of forming a bond coating on a surface of a substrate, and a step of forming a barrier coating on the bond coating. The bond coating is formed by chemical vapor deposition, at a deposition temperature higher than 150° C., in particular 1200° C. or higher, of a precursor including silicon, and includes columnar grains of crystalline silicon.

Abstract: A turbomachine turbine assembly having a longitudinal axis and including an exhaust casing, an ejection cone arranged downstream of the exhaust casing, the ejection cone having an outer annular wall for the flow of a primary air stream and an acoustic box arranged radially inside said outer annular wall. The acoustic box can include a radially inner annular wall and a connection member interposed longitudinally between the exhaust casing and the inner annular wall of the ejection cone. The connection member can be fastened to the exhaust casing and to the inner annular wall. The upstream end of the outer annular wall can be connected to the connection member with a degree of freedom in the radial direction and a degree of freedom in the longitudinal direction.

Abstract: A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.

Abstract: A method for impregnating an oxide fibre roving with a matrix of alumina and silica includes a introducing an oxide fibre roving into an impregnation bath, wherein the impregnation bath is prepared by sol-gel process and includes a silica precursor in the form of a hybrid polymeric sol, an alumina precursor in the form of a colloidal sol and ceramic particles.

Abstract: A method of consolidation includes placing a fibrous preform in the shaping recess of a shaping tool, and supplying the shaping tool with a gas phase to obtain a deposit in the fibrous preform, the shaping tool for the vapor phase chemical infiltration including first and second portions, having respectively first and second shaping zones surrounded by a first and second edge zones, the first and the second shaping zone defining a shaping recess to receive the fibrous preform. A gas injection port is present at least partially in the first or second edge zone and a gas outlet port is present at least partially in the first or second edge zone, the gas injection port and the gas outlet port placing the shaping recess in fluid communication with the outside of the shaping tool. Outer faces of the first and second portion are impermeable to gas.

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: The invention relates to a method for depositing an environmental barrier on a part made of composite material having a ceramic matrix comprising silicon carbide fibres. The method comprises the deposition of a joining layer on at least one surface of the part, the joining layer comprising mullite or a mullite precursor, and the deposition of a protective layer on the joining layer, the protective layer comprising a rare earth disilicate.

Abstract: A tool for manufacturing a ceramic matrix composite part by injecting a slurry, the tool includes an injection chamber intended to receive at least one fibrous preform to be densified, wherein the injection chamber includes first injection ports which are formed in a first side of the injection chamber for injecting the slurry into the injection chamber, the first injection ports being distributed along the first side of the injection chamber; the injection chamber includes first drainage ports which are formed on the first side of the injection chamber for draining a liquid phase of the slurry from the injection chamber, the first drainage ports being distributed along the first side of the injection chamber; and the tool includes a first filtration element which is located on the first side of the injection chamber and which is located opposite the first drainage ports.

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 method for manufacturing a panel for a nacelle of an aircraft propulsion assembly includes: preparing mold elements each including lateral faces, an upper face, and a lower face; draping a material on a portion of the upper face and/or the lower face and at least one of the lateral faces of each of the mold elements to form at least one fold; and extracting the mold elements such that the at least one fold forms a cellular structure of the panel. The portion of the material on the upper face and/or the lower face forms a peripheral portion of the fold. The portion on the at least one of the lateral faces of each of the mold elements forms a central portion of the fold. The central portion is a portion of transverse partition walls of the panel, which define a plurality of cells.

Abstract: A method for injecting ceramic particles into a fibrous texture includes placing a fibrous texture in a mould, injecting from one side a first suspension including a powder of large filtration particles to form a filtration layer, injecting from the opposite side a second suspension into the fibrous texture, the second suspension including a powder of small refractory ceramic particles, then draining through the filtration layer the liquid phase of the second suspension having passed through the fibrous texture and retaining the refractory ceramic particle powder inside the fibrous texture by the filtration layer of so as to obtain a fibrous preform including at least the fibrous texture filled with refractory ceramic particles and the filtration layer.

Abstract: A process for manufacturing a part made of composite material with a matrix at least predominantly made of ceramic includes producing a fibrous structure by three-dimensional or multilayer weaving; shaping the fibrous structure to form a fibrous preform core; depositing an interphase on the fibers of the preform core; consolidating the preform core by partial densification of the core including the formation of a matrix phase by chemical vapor infiltration or by a liquid process; depositing a powder of ceramic particles in the porosity of the preform core; draping one or more layers of pre-impregnated non-woven fibers over all or part of the outer surface of the preform core; heat treatment of the preform core and of the pre-impregnated layer(s) to form a hybrid fibrous preform; further densifying by infiltration of the hybrid fibrous preform with an infiltration composition containing at least silicon to obtain a ceramic matrix composite part.

Abstract: An assembly for a turbine includes a plurality of sectors which are adjacent to one another, each sector including at least one connecting edge of composite material with a ceramic matrix, each connecting edge including at least one groove and a sealing tongue present in each groove. Each sealing tongue has a laminated structure comprising a plurality of strips the lower strip and the upper strip of the laminated structure, each being formed by a film of monolithic ceramic material.

Abstract: A support tooling for porous preforms intended to be infiltrated by a molten metal includes a rack including two suspension bars each extending longitudinally along a first direction, the suspension bars being held spaced apart from one another along a second direction perpendicular to the first direction; a plurality or porous preform supports removably mounted on the suspension bars, each support including a first portion connected to one of the suspension bars by a connection sliding along a third direction perpendicular to the first and second directions and a second portion extending from the first portion and including support elements which are able to hold a porous preform by point or linear contact.