A method of repairing a nonconforming article includes applying a machinable coating to an article with a nonconformance. The article includes a preform at least partially infiltrated with a matrix material, to form a repaired article. The method also includes machining the machinable coating and completing infiltration of the repaired article with the matrix material. A method of repairing an article is also disclosed.

In one example, a method including depositing an antioxidant material on a first surface region of a carbon-carbon composite substrate via a print head of a three-dimensional printing device to form a first layer of the antioxidant material on the first surface region of the substrate, and depositing the antioxidant material on a second surface region of the substrate via the print head of the three-dimensional printing device to form a second layer of the antioxidant material on the second surface region. The method may be, for example, a method for forming a carbon-carbon composite component including an antioxidant coating, the antioxidant coating including the first layer and second layer of the antioxidant material.

The present invention relates to a method of manufacturing a ceramic article (3) from a metal or metal matrix composite preform (1) provided by 3D-printing or by 3D-weaving. The preform (1) is placed in a heating chamber (2), and a predetermined time-temperature profile is applied in order to controllably react the preform (1) with a gas introduced into the heating chamber (2). The metal, the gas and the time-temperature profile are chosen so as to induce a metal-gas reaction resulting in at least a part of the preform (1) transforming into a ceramic. Preferred embodiments of the invention comprises a first oxidation stage involving a metal-gas reaction in order to form a supporting oxide layer (5) at the surface of the metal, followed by a second stage in which the heating chamber (2) is heated to a temperature above the melting point of the metal to increase the kinetics of the chemical reaction. The invention also relates to a number of advantageous uses of a ceramic article manufactured as described.

Brake disks with integrated heat sink are provided. Brake disk includes a fiber-reinforced composite material and an encapsulated heat sink material impregnated into the fiber-reinforced composite material. The encapsulated heat sink material comprises a heat sink material encapsulated within a silicon-containing encapsulation layer. Methods for manufacturing the brake disk with integrated heat sink and methods for producing the encapsulated heat sink material are also provided.

The present disclosure provides a method of manufacturing a composite sandwich panel having a core formed of a plurality of cells extending vertically between a first skin and a second skin. The method includes creating at least one first strip and a second strip from a temporary material, each strip having at least one cavity having a succession of aligned half-cells, lining the cavity of the first strip with a fibrous ply, assembling the first strip and the second strip by interlocking the cavity of the first strip with the cavity of the second strip and trapping the fibrous ply therebetween, and trimming excess temporary material of the entirety of the strips formed during the preceding assembly step so as to form a new cavity which forms a succession of aligned half-cells.

An aerospace mirror having a reaction bonded (RB) silicon carbide (SiC) mirror substrate, and a SiC cladding on the RB SiC mirror substrate forming an optical surface on a front side of the aerospace mirror. A method for manufacturing an aerospace mirror comprising obtaining a green mirror preform comprising porous carbon, silicon carbide (SiC), or both, the green mirror preform defining a front side of the aerospace mirror and a back side of the aerospace mirror opposite the front side; removing material from the green mirror preform to form support ribs on the back side; infiltrating the green mirror preform with silicon to create a reaction bonded (RB) SiC mirror substrate from the green mirror preform; forming a mounting interface surface on the back side of the aerospace mirror from the RB SiC mirror substrate, and forming a reflector surface of the RB SiC mirror substrate on the front side of the aerospace mirror. Additionally, the method can comprise cladding the reflector surface of the RB SiC mirror substrate with SiC to form an optical surface of the aerospace mirror.

A mortar composition, in particular for preparing a viscoelastic structure and/or a fire barrier, including: a) 15-50 wt.-% of a hydraulic binder, b) 5-35 wt.-% of lightweight aggregates, c) 5-25 wt. % of further aggregates which have a particle density that is higher than the particle density of the lightweight aggregates, and d) 10-50 wt.-% of a polymer.

Coating systems are provided for positioning on a surface of a substrate, along with the resulting coated components and methods of their formation. The coating system may include a layer having a compound of the formula: A.sub.1bB.sub.bZ.sub.1dD.sub.dMO.sub.6 where: A is Al, Ga, In, Sc, Y, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Fe, Cr, Co, Mn, Bi, or a mixture thereof; b is 0 to about 0.5; Z is Hf, Ti, or a mixture thereof; D is Zr, Ce, Ge, Si, or a mixture thereof; d is 0 to about 0.5; and M is Ta, Nb, or a mixture thereof.

Some examples include a turbine component comprising: a ceramic composite (CMC) having a matrix; and a watertight coating chemically miscible and/or mutually soluble with/in the CMC because particles and/or fibers which are composed of an identical or chemically matching, but at least chemically compatible. At least part of the watertight coating is incorporated in the matrix of the CMC, the matching and compatible material comprising at least one of: aluminum oxide, yttrium aluminum garnet (YAG), and yttrium-stabilized zirconium oxide (YSZ).

A method for forming an oxidation protection system on a composite structure may comprise: applying a ceramic layer slurry to the composite structure, wherein the ceramic layer slurry comprises aluminum and silicon in a solvent or carrier fluid; and heating the composite structure in an environment comprising nitrogen gas and oxygen gas to form a ceramic layer on the composite structure, wherein the ceramic layer comprises aluminum nitride and alumina.