A method of fabricating a brake component made from a ceramic matrix composite is disclosed. In various embodiments, the method includes infiltrating a carbon fabric with a slurry containing a ceramic powder and a sintering aid; laying up the carbon fabric in a desired geometry to form a raw component; warm pressing the raw component to form a green component; and sintering the green component via a spark plasma sintering process to form a sintered component.

A fiber preform defining an annulus extending along a central longitudinal axis. The fiber preform includes a plurality of layers extending in an axial direction and a circumferential direction relative to the longitudinal axis. Each layer of the plurality of layers includes a plurality of elongate fibers. The plurality of elongate fibers include a plurality of elongate axial fibers extending substantially in the axial direction and a plurality of elongate circumferential fibers extending substantially in the circumferential direction. The fiber preform also includes a plurality of radial fibers extending substantially in the radial direction. The plurality of radial fibers mechanically bind one or more adjacent layers of the plurality of layers. At least 40% of the plurality of elongate fibers extend substantially in the axial direction.

A method that includes winding a composite fabric around a mandrel to form a plurality of layers defining an annulus extending along a central longitudinal axis, where the composite fabric includes a plurality of elongate axial fibers extending substantially in an axial direction relative to the longitudinal axis and a plurality of elongate circumferential fibers extending substantially in a circumferential direction relative to the longitudinal axis; and introducing, into at least a portion of the plurality of layers, a plurality of radial fibers extending substantially in the radial direction relative to the longitudinal axis, where the plurality of radial fibers mechanically bind one or more adjacent layers of the plurality of layers.

A seal plate disposable between a pair of preforms for chemical vapor infiltration is disclosed. The seal plate may include a plurality of first channels that extend completely through the seal plate and that are located between an inner annulus and outer annulus of the seal plate. The seal plate may further include a plurality of second channels that also extend completely through the seal plate and that are located also between an inner annulus and outer annulus. The first channels may differ from the second channels in at least one respect (e.g., the first channels may be of a different width than the second channels). The first channels may provide an inlet for the chemical vapor infiltration of the preform, while the second channels may provide an outlet for the chemical vapor infiltration of the preform.

A clip assembly for a rotor disk of a brake assembly, the clip assembly comprising: a half-cap clip arranged to fit over an end of a lug of the rotor disk, the half-cap clip having two opposing sides and an end across the two opposing sides, and a top and bottom surface, the top and bottom surfaces, the sides and the end defining a receptacle to receive the rotor lug, the half-cap clip having an aperture in each of the sides; and a pin having a pin head and a pin body extending from the pin head along an axis (A) of the pin, the pin having a cross-section defining an elongate shape having rounded ends; and wherein the apertures in the sides of the half-cap clip are shaped to receive the pin body.

A clip for a rotor disk of a brake assembly, the clip arranged to fit over an end of a lug of the rotor disk, the clip having two opposing sides and an end portion across the two opposing sides, and a top portion, the top portion, the sides and the end portion each having an inner surface and an outer surface, and the inner surface of the top portion, the sides and the end portion together defining a receptacle to receive the rotor lug, in use, the clip having at least one aperture in each of the sides; the clip further comprising a reinforcement member extending from the inner surface of the end portion internal of the receptacle, between the two sides.

A method of manufacturing a carbon structure can comprise: infiltrating the carbon structure with a silicon oxycarbide (SiOC) precursor sol; and densifying the carbon structure by chemical vapor infiltration (CVI) to form a carbon and ceramic matrix composite material, the carbon and ceramic matrix composite material comprising between 0% and 15% by weight of a plurality of ceramic particles from the ceramic compound, densifying the carbon structure including adjusting a temperature gradient across the carbon structure.

A friction disk includes a friction disk core having an inner diameter edge, an outer diameter edge, and a first surface with multiple mortises extending radially across the first surface. The friction disk further includes a first wear liner having two wear liner segments each including a wear surface and a non-wear surface having a tenon with a complimentary shape to each of the multiple mortises, the tenon of each wear liner segment being configured to be received by a corresponding mortise of the multiple mortises to couple the wear liner segments to the friction disk core to form an annular liner.

A method of manufacture for a carbon/carbon part including a method to remove contamination from an intermediate product of the carbon/carbon part and furnace utilizing a gaseous reducing agent hydrogen gas to reduce the contaminates, thereby causing the contaminates to transition to a gaseous state at relatively lower temperatures. A method to remove contamination from an intermediate product of the carbon/carbon part and furnace utilizing hydrogen gas to reduce the contaminates, thereby causing the contaminates to transition to a gaseous state at relatively lower temperatures.

A method of treating a carbon/carbon composite is provided. The method may include infiltrating a carbonized fibrous structure with hydrocarbon gas to form a densified fibrous structure. The method may include treating the densified fibrous structure with heat at a first temperature range from about 1600 to about 2400 C. to form a heat treated densified fibrous structure. The method may include infiltrating the heat treated densified fibrous structure with silicon to form a silicon carbide infiltrated fibrous structure.