A method of treating at least one silicon carbide fibre, the method including a) formation of a silica layer at the surface of a silicon carbide fibre having an oxygen content less than or equal to 1% in atomic percentage, the silica layer being formed by contacting this fibre with an oxidizing medium having a temperature greater than or equal to 50° C. and pressure greater than or equal to 1 MPa, and b) removal of the silica layer formed by hydrothermal treatment of the fibre obtained after implementation of step a) in which the fibre is treated with water at a pressure between saturating vapour pressure and 30 MPa and at a temperature less than or equal to 400° C.

A method for forming a hole in a ceramic matrix composite component includes providing a first tool component with a first hole, providing a fiber preform of the ceramic matrix composite component on the first tool component, positioning a second tool component on the fiber preform, such that the fiber preform is disposed between the first and second tool components, inserting a rod into the first and second holes and through the fiber preform, and performing a densification step of the fiber preform in the first and second tool components. The second tool component has a second hole coaxial with the first hole. The fiber preform is densified with a ceramic matrix.

A method of forming a ceramic matrix composite component. The ceramic matrix composite component is adapted for use in a gas turbine engine. The method including forming the component using ceramic materials and infiltrating the component with a matrix material.

A method of manufacturing ceramic matrix composites includes producing chemical vapor deposition functionalized ceramic particles before injecting the functionalized ceramic particles into the CMC fabric. The functionalized ceramic particles are mixed with a binder solution and then dispensed into voids present between adjacent tows of the CMC fabric. Injecting the particles in the center of the voids reduces the size and volume fraction of the voids/defects, improving the homogeneity of surface texture, homogeneity of microstructure, and part model shape conformity.

A method for producing a hollow part made of a ceramic matrix composite material. The method includes shaping a hollow fibrous preform. A core of oxidizable material is housed or inserted into the preform. The method also includes consolidating the preform and extracting the core by oxidising the core.

A method of forming a ceramic matrix composite component having an internal cooling circuit includes wrapping at least a first sheet around a first mandrel, wrapping at least a second sheet around a second mandrel, creating a first plurality of holes in the first sheet corresponding to a plurality of openings in the first mandrel, creating a second plurality of holes in the second sheet corresponding to a plurality of openings in the second mandrel, aligning the first mandrel and the second mandrel such that the first plurality of holes face and are aligned with the second plurality of holes, wrapping at least a third sheet around both the first mandrel and second mandrel to form a preform, the preform comprising each of the first sheet, the second sheet, and the third sheet, and densifying the preform. The first sheet, second sheet, and third sheet are formed from a ceramic fiber material.

Method for the preparation, by means of a heating technique, of a composite material composed of a matrix of at least a first oxide of at least one metal and/or at least one metalloid reinforced by reinforcements in at least a second oxide of at least one metal and/or at least one metalloid, characterised in that the following successive steps are carried out: the reinforcements are placed in at least one liquid precursor of the first oxide of at least one metal and/or at least one metalloid; said reinforcements and the liquid precursor are heated so as to form the first oxide by means of the thermal decomposition of said liquid precursor, and to deposit the first oxide thus formed around the reinforcements and between the reinforcements thus forming the matrix.

A method for fabricating a component according to an example of the present disclosure includes the steps of depositing a stoichiometric precursor layer onto a preform, and densifying the preform by depositing a matrix material onto the stoichiometric precursor layer. An alternate method and a component are also disclosed.

A method of infiltrating a fiber preform comprises positioning an assembly in a process chamber, where the assembly includes a tool comprising through-holes, a fiber preform constrained within the tool, and a sacrificial preform disposed between the fiber preform and the tool. The sacrificial preform is gas permeable. The process chamber is heated, and gaseous reactants are delivered into the process chamber during the heating. The gaseous reactants penetrate the through-holes of the tool and infiltrate the sacrificial preform and the fiber preform. Deposition of reaction products occurs on exposed surfaces of the fiber preform and the sacrificial preform, and a coating is formed thereon. In addition, the sacrificial preform accumulates excess coating material formed from increased reactions at short diffusion depths. Accordingly, the coating formed on the fiber preform exhibits a thickness variation of about 10% or less throughout a volume of the fiber preform.

A method of forming a ceramic matrix composite includes applying a tackifier of ethanol and 3% to 12% polyvinyl butyral to a ceramic material, removing the ethanol from the ceramic material, and removing the polyvinyl butyral. The step of applying the tackifier includes one of a spraying, pipetting, painting, and immersing technique.