A process of producing a porous electrode substrate, including: dispersing first short carbon fibers and producing a first precursor sheet not having a three-dimensional entangled structure of the first short carbon fibers; treating the first precursor sheet such that the first short carbon fibers in the first precursor sheet are entangled and that a second precursor sheet having a three-dimensional entangled structure of the first short carbon fibers is obtained; dispersing second short carbon fibers on the second precursor sheet such that a porous electrode precursor sheet including the second precursor sheet and a third precursor sheet not having a three-dimensional entangled structure of the second short carbon fibers and stacked on the second precursor sheet is obtained; and carbonization treating the porous electrode substrate precursor sheet at a temperature of at least 1000° C. to obtain the porous electrode substrate.

A carbon-carbon composite preform including a plurality of layers including carbon fibers or carbon-precursor fibers, the layers include a first exterior layer defining a first major surface, a second exterior layer defining a second major surface, and at least one interior layer disposed between the first exterior layer and the second exterior layer, the at least one interior layer having a peripheral region that forms a portion of an outer surface of the preform. The preform includes needled fibers, where at least some needled fibers extend through two or more layers. The preform has an exterior region and a core region, where the exterior region includes at least the peripheral region of at least one interior layer. The needled fibers define a first needled fiber number density (NFND) in the exterior region and a second greater NFND in at least a portion of the core region.

A carbon ceramic brake disc according to the present invention includes: a support body having cooling channels at the center portion; and friction layers directly attached to the top and the bottom of the support body without a bonding layer and having components different from the components of the support body, in which the support body is composed of a plurality of layers having components similar to the friction layers, gradually toward the friction layers from the cooling channels as the center. Accordingly, the support body can perform thermomechanical shock absorbing that is an original function and the friction layers and the support body can be prevented from separating while the carbon ceramic brake disc is manufactured.

A method for producing a component includes a) providing at least two preforms each made of a carbon composite material, b) joining the at least two preforms at least at one respective connecting surface to form a composite, in which a joining compound is introduced between the joining surfaces of the preforms and then cured and the joining compound contains silicon carbide and at least one polymer adhesive, and c) siliconizing the composite to form the component. A component, such as an optical component produced thereby, is also provided.

A fibrous preform (1) is produced, provided with a sandwich structure comprising an intermediate flexible core (4) and two outer fibrous frames (2, 3), respectively arranged on opposing outer faces of said flexible core (4) and assembled by sections of wire (8, 9) passing through said fibrous frames (2, 3), said preform (1) being impregnated with resin. Said preform is then hardened and the core (4) is removed, preferably by pre-densification with chemical vapour infiltration, and the structure produced is then densified with liquid-phase infiltration.

An oxidation protection system disposed on a substrate is provided, which may comprise a base layer comprising a first pre-slurry composition comprising a first phosphate glass composition, and/or a sealing layer comprising a second pre-slurry composition comprising a second phosphate glass composition and a strengthening compound comprising boron nitride, a metal oxide, and/or silicon carbide.

A compact, a superabrasive compact and a method of making the compact and superabrasive compact are disclosed. A compact may include a plurality of carbide particles, a binder, and a species. The binder may be dispersed among the plurality of tungsten carbide particles. The species may be dispersed in the compact, wherein the binder has a melting point from about 600° C. to about 1350° C. at ambient pressure. A superabrasive compact may include a diamond table and a substrate. The diamond table may be attached to the substrate. The substrate may have a binder. The melting point of the binder is from about 600° C. to about 1350° C. at high pressure from about 30 kbar to about 100 kbar.

A method of manufacturing a gas turbine engine component (10) and the component so formed. The method includes: stacking a plurality of CMC layers (16) along a metal core (30) to form a stack of disconnected CMC layers, wherein adjacent edge faces (46) of the layers define a surface (44); additively depositing ceramic material (14) to only selected portions of the surface (44) to bond together at least some of the layers at their respective edge faces; and selecting locations for the depositing of the ceramic material to achieve a predetermined mechanical characteristic of the resulting component.

A ceramic matrix composite article, method for forming the article, and perforated ply which may be incorporated therein are disclosed. The article includes at least one shell ply forming an exterior wall having first and second portions and defining a plenum. An annular brace formed of at least one structural support ply is disposed within the plenum, including a first integral portion integral with and part of the first portion of the exterior wall, a first curved portion extending from the first integral portion and curving across the article plenum to the second portion of the exterior wall, a second integral portion integral with and part of the second portion of the exterior wall, a second curved portion extending from the second integral portion and curving across the article plenum to the first curved portion, and an overlap in which the first and second curved portions are integral.

A gas turbine seal assembly includes a gas turbine component and a gas turbine seal component contacting the gas turbine component to form a seal between the two components. The gas turbine seal component includes ceramic matrix composite plies bonded together to form the ceramic matrix composite component. A bond-inhibiting coating on a non-bonding portion of a first surface of one of the ceramic matrix composite plies prevents bonding between the non-bonding portion of the first surface and a second surface of a neighboring ceramic matrix composite ply. At least one bonding portion of the first surface lacking the bond-inhibiting coating is bonded to the second surface. A method of forming a ceramic matrix composite component includes selectively applying a bond-inhibiting coating to a non-bonding portion of a first surface of a ceramic matrix composite ply and bonding the ceramic matrix composite plies together.