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.

The invention relates to a pre-impregnated fibre-reinforced composite material in laminar form, obtained impregnating a fibrous mass with a polymeric binder composition and intended to be subjected to successive forming and pyrolysis operations to produce a fibre-reinforced composite ceramic material. The polymeric binder composition is based on one or more resins chosen from the group consisting of siloxane resins and silsesquioxane resins, and can optionally comprise one or more organic resins. The polymeric binder composition is a liquid with viscosity between 55000 and 10000 mPas at temperatures between 50° C. and 70° C. The polymeric binder composition forms a polymeric binding matrix, not cross-linked or only partially cross-linked that fills the interstices of the fibrous mass. The invention also relates to a method for making said pre-impregnated fibre-reinforced composite material in laminar form. The invention further relates to a fibre-reinforced composite ceramic material, obtained by forming and subsequent pyrolysis of a pre-impregnated fibre-reinforced composite material, as well as a method for making said material.

A method for constructing a plurality of ceramic layers by winding continuous ceramic filaments to prepare RF-transparent structures is provided. Dielectric properties of each layer of the plurality of ceramic layers are characterized by an inter-filament spacing, a filament count and thickness. Once the plurality of ceramic layers are constructed, a structure is removed from a winding surface, wherein the winding surface is a mandrel, infiltrated with a resin in a separate set up and fired.

Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.

A ceramic fiber preform includes a plurality of ceramic fiber plies arranged to define a wall, a void adjacent the wall, and an insert positioned within the void. The insert includes a first region having a first porosity and a second region in physical contact with the first region and having a second porosity. The first region and second region are formed from a woven ceramic material, the wall has a wall porosity, and the first porosity is less than at least one of the second porosity and the wall porosity.

A method for forming a ceramic matrix composite (CMC) component with an internal cooling channel includes partially densifying a first fiber preform to form a portion of a final ceramic matrix volume, machining a first channel into a surface of the partially densified first fiber preform, covering the first channel with a fibrous member to form a near net shape fiber preform with an internal passage formed by the first channel and the fibrous member, and densifying the near net shape fiber preform.

A method of fabricating a fiber preform filled with refractory ceramic particles, includes placing a fiber texture including refractory ceramic fibers in a mold cavity; injecting a slip including a powder of refractory ceramic particles present in a liquid medium, the slip being injected into the pores of the fiber texture present in the mold cavity, injection being performed through at least a first face or a first edge of the fiber texture; and draining the liquid medium of the slip that has penetrated into the fiber texture through the porous material part, the draining being performed at least through a second face or a second edge of the fiber texture different from the first face or the first edge, the porous material part also serving to retain the refractory particle powder in the pores of the fiber texture to obtain a fiber preform filled with refractory particles.

The present invention relates to a method for producing a three-dimensional macroporous filament construct having interconnected microporous filaments showing a suitable surface roughness and microporosity. The method includes the steps of: a) preparing a suspension having particles of a predetermined material, a liquid solvent, one or more binders and optionally one or more dispersants, b) depositing the suspension in the form of filaments in a predetermined three-dimensional pattern, preferably in a non-solvent environment, thereby creating a three-dimensional filament-based porous structure, c) inducing phase inversion, whereby said filaments are transformed from a liquid to a solid state, by exposing the filaments during the deposition of the filaments with a non-solvent vapour and to a liquid non-solvent, d) thermally treating the structure of step d) by calcining and sintering the structure. The invention further provides a three-dimensional macroporous filament construct having interconnected microporous filaments showing a specific surface roughness and microporosity. The invention also relates to various uses of the construct, including its use for the manufacture of a biomedical product, such as a synthetic bone implant or bone graft.

A method for manufacturing a part made of composite material includes forming a ceramic matrix phase in pores of a fibrous preform by pyrolysis of a cross-linked copolymer ceramic precursor, the cross-linked copolymer including a first precursor macromolecular chain of a first ceramic having free carbon, and a second precursor macromolecular chain of a second ceramic having free silicon, the first macromolecular chain being bonded to the second macromolecular chain by cross-linking bridges including a bonding structure of formula *.sup.1—X—*.sup.2; in this formula, X designates boron or aluminium, -*.sup.1 designates the bond to the first macromolecular chain and -*.sup.2 the bond to the second macromolecular chain.

A method for manufacturing a turbine nozzle vane made of ceramic matrix composite material, wherein the vane is manufactured using a first fibrous preform including a hollow central section intended to form a fibrous reinforcement of an airfoil of the vane to be obtained, and a pair of second fibrous preforms each having an opening with a shape of the airfoil of the vane to be obtained.