Abstract: A method of making a ceramic matrix composite article includes fabricating a preform comprising a plurality of fibers arranged in an arrangement, wherein there are spaces between adjacent ones of the fibers; providing particles to the preform, whereby the particles are situated in the spaces; and applying a matrix material to the preform by atomic layer deposition to make a ceramic matrix composite article. A ceramic matrix composite article is also disclosed.

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Abstract: A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a healing silica matrix and at least one oxygen scavenger forming a metal silicide network dispersed within the healing silica matrix; and a top coat layer disposed upon the oxidation resistant bond coat layer, whereby the oxidation resistant bond coat layer is operable to seal a crack in the top coat layer.

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

Abstract: A method of making an ceramic article according to an exemplary embodiment of this disclosure, among other possible things includes arranging fiber plies into a preform, inserting one or more sacrificial springs to the preform, infiltrating the preform with a matrix material to form an article, and thermally degrading the one or more sacrificial springs to form cooling holes. A ceramic article and a gas turbine engine component are also disclosed.

Abstract: A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a healing silica matrix and at least one oxygen scavenger forming a metal silicide network dispersed within the healing silica matrix; and a top coat layer disposed upon the oxidation resistant bond coat layer, whereby the oxidation resistant bond coat layer is operable to seal a crack in the top coat layer.

Abstract: A method of making an ceramic article according to an exemplary embodiment of this disclosure, among other possible things includes arranging fiber plies into a preform, inserting one or more sacrificial springs to the preform, infiltrating the preform with a matrix material to form an article, and thermally degrading the one or more sacrificial springs to form cooling holes. A ceramic article and a gas turbine engine component are also disclosed.

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

Abstract: An apparatus for making a composite article includes a monofilament feed track adapted to carry a spaced array of ceramic monofilament strands, a fiber yarn feed track adapted to carry a spaced array of fiber yarn tows impregnated with a plurality of glass particulates, a mandrel, and a heater assembly. The mandrel is adapted to wind together individual glass-impregnated fiber yarn strands and individual ceramic monofilament strands to form a dual-fiber weave. The heater assembly is adapted to heat at least the glass particulates such that pressure from the wound array of ceramic monofilaments is sufficient to consolidate the glass particulates and the dual-fiber weave into a dual-fiber ceramic matrix composite (CMC).

Abstract: A method of making a ceramic matrix composite is disclosed. According to the method, a first preform comprising fibers is formed, and a second preform including a helical surface portion is inserted into the first preform. The first preform with the inserted second preform is infiltrated with a matrix material comprising a ceramic to form the ceramic matrix composite. A ceramic matrix composite is also disclosed. The ceramic matrix composite includes a first portion including a matrix comprising a ceramic, and a reinforcement including fibers derived from the first preform in the matrix. A second portion including a helical surface portion interface with the first portion is disposed within the first portion.

Abstract: A method of making an ceramic article according to an exemplary embodiment of this disclosure, among other possible things includes arranging fiber plies into a preform, inserting one or more sacrificial springs to the preform, infiltrating the preform with a matrix material to form an article, and thermally degrading the one or more sacrificial springs to form cooling holes. A ceramic article and a gas turbine engine component are also disclosed.

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Abstract: An apparatus for making a composite article includes a monofilament feed track adapted to carry a spaced array of ceramic monofilament strands, a fiber yarn feed track adapted to carry a spaced array of fiber yarn tows impregnated with a plurality of glass particulates, a mandrel, and a heater assembly. The mandrel is adapted to wind together individual glass-impregnated fiber yarn strands and individual ceramic monofilament strands to form a dual-fiber weave. The heater assembly is adapted to heat at least the glass particulates such that pressure from the wound array of ceramic monofilaments is sufficient to consolidate the glass particulates and the dual-fiber weave into a dual-fiber ceramic matrix composite (CMC).

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Abstract: An apparatus for making a composite article includes a monofilament feed track adapted to carry a spaced array of ceramic monofilament strands, a fiber yarn feed track adapted to carry a spaced array of fiber yarn tows impregnated with a plurality of glass particulates, a mandrel, and a heater assembly. The mandrel is adapted to wind together individual glass-impregnated fiber yarn strands and individual ceramic monofilament strands to form a dual-fiber weave. The heater assembly is adapted to heat at least the glass particulates such that pressure from the wound array of ceramic monofilaments is sufficient to consolidate the glass particulates and the dual-fiber weave into a dual-fiber ceramic matrix composite (CMC).

Abstract: Methods for fabricating a ceramic matrix composite are disclosed. A fiber preform may be placed in a mold. An aqueous solution may be added to the fiber preform. The aqueous solution may include water, carbon nanotubes, and a binder. The preform may be frozen. Freezing the preform may cause the water to expand and separate fibers in the fiber preform. The carbon nanotubes may bond to the fibers. The preform may be freeze dried to remove the water. The preform may then be processed according to standard CMC process.

Abstract: One exemplary embodiment of this disclosure relates to a transfer molding assembly including a chamber, a die within the chamber, a first gas control device configured to provide a first gas into the chamber, and a second gas control device configured to provide a second gas into the die.

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.