A selective laser sintering system includes a leveling roller having a first orientation. The leveling roller is configured to roll over a first feed bin. The build chamber is configured to receive, from the first feed bin and by the leveling roller, a transfer of a portion of matrix material. The selective laser sintering system is configured to transfer the portion to the build chamber in a number of orientations.

A combination of a component and a composite, the composite having a) a PMC layer, and b) a tile layer comprising a plurality of Ox/Ox CMC tiles, each tile having: i) a central portion, ii) an outer portion and iii) one or more overlap joints formed by the overlapping of the outer portions of adjoining tiles so that hot gases entering a smooth top surface of the tile layer between abutting outer and central periphery segments must travel laterally between the overlapping outer portions of adjoining tiles to reach a top surface of the PMC layer. A method of heat shielding a component with a heat shielding composite comprising a) providing the composite and b) applying the composite to a surface of the component.

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.

A preform for a carbon-carbon composite including a plurality of fibrous layers stacked and needled-punched together to form the preform in the shape of an annulus having an inner radial section and an outer radial section. Each fibrous layer includes a respective plurality of fabric segments comprising at least one of carbon fibers or carbon-precursor fibers. At least one fibrous layer includes a first fabric segment forming at least a portion the inner radial section, the first fabric segment defining a first segment bisector and a first fiber orientation angle, and a second fabric segment forming at least a portion the outer radial section, the second fabric segment defining a second segment bisector and a second fiber orientation angle, where the first and second segment bisectors are radially aligned and the first fiber orientation angle is different than the second fiber orientation angle.

A combination of a component and a composite, the composite having a) a PMC layer, and b) a tile layer comprising a plurality of Ox/Ox CMC tiles, each tile having: i) a central portion, ii) an outer portion and iii) one or more overlap joints formed by the overlapping of the outer portions of adjoining tiles so that hot gases entering a smooth top surface of the tile layer between abutting outer and central periphery segments must travel laterally between the overlapping outer portions of adjoining tiles to reach a top surface of the PMC layer. A method of heat shielding a component with a heat shielding composite comprising a) providing the composite and b) applying the composite to a surface of the component.

Various embodiments include a metal-repaired ceramic matrix composite (CMC) article, and a method of repairing a CMC article having a defect. Particular embodiments include a method including: removing a defect-containing portion of the CMC article; forming at least one opening in a remaining portion of the CMC article; preparing a metal repair preform for replacing at least the removed portion of the CMC article, wherein a portion of the metal repair preform complements the at least one opening; and attaching the metal repair preform to the remaining portion of the CMC article.

The present invention concerns a shaped composite material and a method for producing it. More specifically, the invention concerns a disc for a disc brake made from ceramic composite materials, usually known as CMC, i.e. Carbon Material Ceramic or CCM, i.e. Carbon Ceramic Material. These materials consist of carbon matrices containing carbon fibres usually infiltrated with silicon and a product of reaction between C and Si, silicon carbide (SiC). More specifically, the invention concerns a shaped composite material comprising a inner layer (3; 103) of CCM C/SiC/Si material comprising disorderly short filaments consisting mainly of carbon and respective outer layers (2, 2; 102, 102) of C/SiC/Si material and having an orderly fabric structure of mainly carbon fibres.

A turbine component assembly is disclosed, including a first component, a second component, and an interface shield. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The interface shield is disposed on a contact region of the first component, and directly contacts the second component.

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 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.