Abstract: A method is provided in which a resin coating is applied to a surface of a preform. The resin coating includes a carbonaceous resin and a particulate. The preform is added to a tooling. The preform, which is positioned in the tooling, is cured. The tooling is removed. The resin coating on the surface of the preform is pyrolyzed to form a resin carbon-char layer on the surface of the preform. The preform and the resin carbon-char layer are infiltrated with silicon to form a ceramic matrix composite (CMC) component including a layer of silicon carbide. During the infiltration, the silicon reacts with carbon in the resin carbon-char layer to form the layer of silicon carbide on the preform.

Abstract: A method for infiltrating a porous preform for a gas turbine engine is provided, which comprises providing a chamber for infiltrating a porous preform. The porous preform is positioned within a slurry confinement fixture within the chamber. A vacuum is created in the chamber. A solvent is added to the slurry confinement fixture until a pressure in the chamber is substantially equal to an equilibrium partial pressure of the solvent. A slurry is added to the slurry confinement fixture. The slurry includes the solvent and a particulate. The pressure in the chamber is increased, and the slurry is urged into the porous preform.

Abstract: A method is provided in which a resin coating is applied to a surface of a preform. The resin coating includes a carbonaceous resin and a particulate. The preform is added to a tooling. The preform, which is positioned in the tooling, is cured. The tooling is removed. The resin coating on the surface of the preform is pyrolyzed to form a resin carbon-char layer on the surface of the preform. The preform and the resin carbon-char layer are infiltrated with silicon to form a ceramic matrix composite (CMC) component including a layer of silicon carbide. During the infiltration, the silicon reacts with carbon in the resin carbon-char layer to form the layer of silicon carbide on the preform.

Abstract: A method for infiltrating a porous preform for a gas turbine engine is provided, which comprises providing a chamber for infiltrating a porous preform. The porous preform is positioned within a slurry confinement fixture within the chamber. A vacuum is created in the chamber. A solvent is added to the slurry confinement fixture until a pressure in the chamber is substantially equal to an equilibrium partial pressure of the solvent. A slurry is added to the slurry confinement fixture. The slurry includes the solvent and a particulate. The pressure in the chamber is increased, and the slurry is urged into the porous preform.