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 joined structure includes a joint section in which a plurality of tubular bodies formed of a ceramic-based composite material are joined to each other such that end surfaces of the tubular bodies abut each other via an intermediate material. The joint section is configured such that each of the end surfaces of the joined tubular bodies is inclined from one of an inner surface and an outer surface of the tubular body toward the other.

A reinforced oxide-oxide CMC component for a gas turbine engine includes a composite body and a structural element embedded in the composite body, where the composite body comprises a 2D oxide-oxide composite and the structural element comprises a 3D oxide-oxide composite. The 2D oxide-oxide composite includes 2D woven or nonwoven oxide fibers in a first oxide matrix, and the 3D oxide-oxide composite includes 3D woven oxide fibers in a second oxide matrix. The first oxide matrix and the second oxide matrix may comprise the same or a different oxide.

A spar cap for a rotor blade of a wind power installation, having a longitudinal extent from a first end to a second end, a transverse extent orthogonal to the longitudinal extent, and a thickness orthogonal to the longitudinal extent and to the transverse extent. A method for producing a spar cap as mentioned at the outset. The spar cap has a longitudinal extent from a first end to a second end, a transverse extent orthogonal to the longitudinal extent, and a thickness orthogonal to the longitudinal extent and to the transverse extent, at least two tiers of a first fiber composite material, and at least one tier of a second fiber composite material, wherein the first fiber composite material has a matrix material and/or fibers which is/are different from that/those of the second fiber composite material, the second fiber composite material is disposed in a portion adjacent to the second end, in the direction of the thickness between the at least two tiers of the first fiber composite material, and the at least one tier of the second fiber composite material terminates ahead of the second end.

A method of creating a tackified prepreg, includes steps of providing a fiber weave having unidirectional fibers and woven sections spaced apart from one another to provide unidirectional fiber sections, applying a tackifier to the fiber weave, arranging layers of the fiber weave onto one another to provide a stack, and wrapping the stack around a form to provide an article having a desired shape.

A braze alloy for joining or repairing ceramic matrix composite (CMC) components comprises a braze composition including silicon at a concentration from about 48 at. % to about 66 at. %, titanium at a concentration from about 1 at. % to about 35 at. %, and an additional element selected from aluminum, cobalt, vanadium, nickel, and chromium. The braze composition comprises a melting temperature of less than 1300 C.

A method for repairing a target member including a ceramic matrix composite reinforced by ceramic fiber includes: a removal step of removing at least a part of a surface of the target member; an arrangement step of arranging a green body for repair which includes the ceramic fiber on a portion where the surface is removed in the removal step; an impregnation step of impregnating at least the portion of the target member where the green body for repair is disposed with slurry; and a sintering step of sintering the target member on which the green body for repair is disposed, after the impregnation step.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A brake disc manufactured by a method of manufacturing a brake disc according to the present invention includes a carbon fiber Cf, silicon Si, silicon carbide Sic, and a silicon-copper alloy Si.sub.xCu.sub.y. The carbon fiber Cf, silicon Si, carbon C, and silicon carbide SiC make a disc light and provide high thermal shock resistance, anti-oxidation, wear resistance, strength, and friction coefficient. The copper Cu and silicon-copper alloy Si.sub.xCu.sub.y increase heat capacity at constant volume of a disc, so a large increase in temperature of the disc is prevented and a changing range of the friction coefficient is reduced in braking. Accordingly, the brake disc according to the present invention has all of the advantage of a brake disc made of a carbon fiber-reinforced ceramic composites without thermal deformation and deterioration of a pad, a hat part, and a caliper.

A blade for a gas turbine engine includes composite layers that include a uni-directional layer and a fabric compliant wedge layer that are arranged adjacent to the uni-directional layer. The fabric compliant wedge layer has a reduced compressive Young's modulus compared to the uni-directional layer.