A pad for disc brakes, a method for the manufacturing thereof, and a braking system with the pad are disclosed. The pad for disc brakes has a thickness y and a first surface cooperating with actuating means of a disc brake. The pad also has a second tribologically active friction surface that cooperates with the disc of the disc brake. The pad also has a first portion and a second portion, where the first portion of the pad extends for a thickness y.sub.1 from the first surface, and the second portion of the pad extends for a thickness y.sub.2 from the second tribologically active friction surface. The first surface and the first portion of the pad are made of carboceramic material, while the second surface and the second portion of the pad are made of carbonaceous material C/C.

A method of fabricating a composite component, includes forming a fibrous preform by forming a first ceramic particle layer over a first textile layer, the first ceramic particle layer having a first group of ceramic particles, disposing a second textile layer over the first ceramic particle layer, forming a second ceramic particle layer over the second textile layer, the second ceramic particle layer having a second group of ceramic particles, and disposing a third textile layer over the second ceramic particle layer. The method further includes densifying the fibrous preform.

A method is provided and suggests grading of a CMC (Ceramic Matrix Composite) structure as a function of dielectric constant by altering the solid loading (SL) ratio of the individual composite layers. The slurry is applied either by impregnation into the ceramic fabrics or by coating on ceramic fibers. The final structure is prepared by piling up prepregs or weaving ceramic fibers with specific SL ratio, drying and firing.

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

The present invention relates to a manufacturing process for a watch component (50) in composite material with a ceramic matrix comprising the following steps: depositing in a mould a succession of layers (10, 20, 30, 40) each comprising a ceramic powder (12), at least one layer (10; 10, 30; 10, 20, 30, 40) further including fibres (14) mixed with the ceramic powder (12), the fibres (14) being arranged randomly; performing a FAST/SPS sintering operation; demoulding the sintered watch component comprising the succession of layers (10, 20, 30, 40), and optionally machining the sintered component to the final dimensions of the watch component (50). The fibres (14) are visible on the surface of the watch component (50).

Composite components and methods for adding a composite material to a composite component are provided. For example, a method comprises positioning a composite material segment against the composite component to form a component layup; applying an insulating material around at least a portion of the component layup to form an insulated layup; and densifying the insulated layup, where the composite component was previously densified before positioning the composite material segment against the composite component. In some embodiments, the composite material is ceramic matrix composite (CMC) and the composite material segment is a plurality of CMC plies. The composite component may be a CMC gas turbine engine component that comprises an original CMC component and a new CMC material segment joined to the original CMC component through the transfer of silicon between the original CMC component and the new CMC material segment during melt infiltration.

A method of making a fiber preform for ceramic matrix composite (CMC) fabrication that utilizes a fugitive binder and a machining step is described. The method includes, according to one embodiment, laying up a plurality of plies to form a stack, where each ply comprises an arrangement of fibers. The stack is infiltrated with a polymer at an elevated temperature to form an infiltrated stack that is cooled to form a rigid preform. The rigid fiber preform is machined to have a predetermined shape, such that a machined fiber preform is formed. A composite assembly including the machined fiber preform is formed and then the composite assembly is heated at a sufficient temperature to pyrolyze the polymer. Thus, a porous preform of a predetermined geometry is formed for further processing into a CMC.

A method for forming a ceramic matrix composite bearing includes preparing a layup slurry from a mixture of water, pre-ceramic polymer and refractory filler. The method further includes forming a concentric stack of slurry-impregnated fabric sleeve layers over a rod-shaped inner mold and applying an outer mold to form a mold assembly. The method also includes heating the mold assembly to form a tubular green body and rough cutting the green body to bearing length. In addition, the method includes heat-treating the bearing and performing a polymer infiltration and pyrolysis treatment. The method further includes conducting dimensional stability treatment processes on the bearing and final grinding and machining to meet pre-determined specifications.

Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine, an airfoil having a root and a tip, and a pin extending through the root. The root is coupled to the rotary structure and has a bulbous shape, and the airfoil is formed from a plurality of composite plies. The pin defines both a planar first surface and a planar second surface on a pin body having a generally circular cross-section. Further, the pin includes a first end and a second end that contact the rotary structure. The first and second surfaces together form a point that is oriented toward the tip of the airfoil. In one embodiment, the rotary structure is an outer rotor of an interdigitated rotor assembly and the airfoil extends radially inward.

Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine and an airfoil having a root and a tip. The root is coupled to the rotary structure and has a bulbous shape. The airfoil is formed from a plurality of composite plies, a portion of which defines at the root first and second end surfaces, which are in contact with the rotary structure and together define a chisel-shaped end of the root. In another embodiment, a rotor assembly comprises an outer rotor extending circumferentially about an axial centerline of a gas turbine engine and a composite outer rotor blade having a root and a tip. The blade root is coupled to the outer rotor and extends inward along a radial direction toward the axial centerline.