A ceramic fiber preform includes a plurality of ceramic fiber plies arranged to define a wall, a void adjacent the wall, and an insert positioned within the void. The insert includes a first region having a first porosity and a second region in physical contact with the first region and having a second porosity. The first region and second region are formed from a woven ceramic material, the wall has a wall porosity, and the first porosity is less than at least one of the second porosity and the wall porosity.

A method of forming one or more high temperature co-fired ceramic articles, comprising the steps of:— a) forming a plurality of green compacts, by a process comprising dry pressing a powder comprising ceramic and organic binder to form a green compact; b) disposing a conductor or conductor precursor to at least one surface of at least one of the plurality of green compacts to form at least one patterned green compact; c) assembling the at least one patterned green compact with one or more of the plurality of green compacts or patterned green compacts or both to form a laminated assembly; d) isostatically pressing the laminated assembly to form a pressed laminated assembly; e) firing the pressed laminated assembly at a temperature sufficient to sinter the ceramic layers together.

Methods and systems are described for fabricating a component using 3D printing. A 3D printed piece is created including a body of the component, a support structure, and a first sacrificial interface region coupling the body of the component to the support structure. The body of the component is formed of a first metal or ceramic material and the first sacrificial interface region is formed at least partially of a second metal or ceramic material. The body of the component is then separated from the support structure by applying a chemical or electrochemical dissolution process to the 3D printed piece. Because the second metal or ceramic material is less resistant to the dissolution process than the first metal or ceramic material, the first sacrificial interface region at least partially dissolves, thereby separating the body of the metal component from the support structure, without dissolving the body of the component.

An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.

Methods are described to make strong, tough, and lightweight whisker-reinforced glass-ceramic composites through a self-toughening structure generated by viscous reaction sintering of a complex mixture of oxides. The invention further relates to strong, tough, and lightweight glass-ceramic composites that can be used as proppants and for other uses.

The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

A method of manufacturing a component includes forming an inner wrap about a mandrel. The inner wrap has first and second walls joined by a base portion and an outer wall. A rod is arranged at each of the first and second walls. An outer wrap is formed about the inner wrap and the rods to form a body. Features are formed in the first and second walls.

The present invention relates to a hierarchical composite structure comprising an open cell graphene foam or graphene-like foam, wherein the graphene foam or graphene-like foam is coated with a conductive nanoporous spongy structure and wherein at least 10% v/v of the hollow of the pores of the graphene foam or graphene-like foam is filled with the conductive nanoporous spongy structure. The invention also relates to a process for preparing a hierarchical composite structure wherein a conductive nanoporous spongy structure is electrodeposited so as to coat the open-cell graphene foam or graphene-like foam and to partially fill the hollow of the pores of the graphene foam or graphene-like foam.

A method for manufacturing a three-dimensional fired body includes (a) a step of producing a shaping mold using an organic material, the shaping mold having a shaping space which has the same shape as a shaped body having a hollow portion that opens to an outer surface thereof, in which a core corresponding to the hollow portion is integrated with the shaping mold; (b) a step of producing the shaped body in the shaping mold by pouring a ceramic slurry into the shaping space and solidifying the ceramic slurry; (c) a step of drying and then degreasing the shaped body, in which the shaping mold is eliminated in any one of the following stages: before drying, during drying, after drying and before degreasing, during degreasing, and after degreasing of the shaped body; and (d) a step of firing the shaped body to obtain a three-dimensional fired body.

An airfoil comprises a wall that defines a leading edge and a trailing edge and one or more cavities located within the wall along with a rib that separates the cavities. The rib or the wall comprises a first split ply that comprises a consolidated section and two or more split sections; wherein the split sections emanate from the consolidated section; and where the split sections define the wall and the cavities of the airfoil.