A method and apparatus for fabricating a short length carbon fiber preform with a through thickness reinforcement is disclosed herein. The starting media for fabricating a net shape (e.g., annular disc) may meet specific requirements including a sufficient fiber volume and a binding mechanism compatible with the needle-punching process.

A part made from a composite material having a ceramic matrix and including a protection device, the protection including a coating layer having a gradual composition. The gradual-composition coating layer includes at least one silicon phase and one aluminium phase, the proportions of which change according to the height in the layer, with a first height in the gradual-composition coating layer corresponding to a silicon-free composition, and a second height corresponding to an aluminium-free composition. A method for producing such a protection, and to a device for carrying out the method, are disclosed.

A part made from a composite material having a ceramic matrix and including a protection device, the protection including a coating layer having a gradual composition. The gradual-composition coating layer includes at least one silicon phase and one aluminium phase, the proportions of which change according to the height in the layer, with a first height in the gradual-composition coating layer corresponding to a silicon-free composition, and a second height corresponding to an aluminium-free composition. A method for producing such a protection, and to a device for carrying out the method, are disclosed.

A thin-film thermocouple for measuring the temperature of a ceramic matrix composite (CMC) component comprises a first thermocouple leg and a second thermocouple leg deposited on a surface of a CMC component, where each of the first and second thermocouple legs has a length extending from a reference end to a working end thereof. The working ends of the first and second thermocouple legs are joined at a junction region on the surface. At least one of the first thermocouple leg and the second thermocouple leg comprises silicon carbide.

A thin-film thermocouple for measuring the temperature of a ceramic matrix composite (CMC) component comprises a first thermocouple leg and a second thermocouple leg deposited on a surface of a CMC component, where each of the first and second thermocouple legs has a length extending from a reference end to a working end thereof. The working ends of the first and second thermocouple legs are joined at a junction region on the surface. At least one of the first thermocouple leg and the second thermocouple leg comprises silicon carbide.

A ceramic component is generally provided that includes a silicon-based layer comprising a silicon-containing material (e.g., a silicon metal and/or a silicide) and about 0.001% to about 85% of an In-containing compound. For example, the silicon-based layer can be a bond coating directly on the surface of the substrate. Alternatively or additionally, the silicon-based layer can be an outer layer defining a surface of the substrate, with an environmental barrier coating on the surface of the substrate. Gas turbine engines are also generally provided that include such a ceramic component.

A compound is provided that has the formula: Ln.sub.4-x-zB.sub.xD.sub.zM.sub.2-n-yA.sub.nB.sub.yO.sub.9, where Ln comprises La, Ce, Pr, Nd, Pm, Sm, or a mixture thereof; x is 0 to about 2; D is La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, or a mixture thereof, where: D is not equal to Ln; if D is La, Ce, Pr, Nd, Pm, Sm, or a mixture thereof, then z is 0 to less than 4; if D is Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, or a mixture thereof, then z is 0 to about 2; M comprises Ga, Al, or a combination thereof; A comprises Fe, In, or a combination thereof; n is 0 to about 1; y is 0 to about 1; and x+y is greater than 0. In one embodiment, a composition is generally provided that includes a silicon-containing material and such a boron-doped refractory compound.

A nanoheterostructure includes a first inorganic component and a second inorganic component one of which is a matrix, and the other of which is three-dimensionally and periodically arranged in the matrix, and has a three-dimensional periodic structure whose average value of one unit length of a repeated structure is 1 nm to 100 nm.

A nanoheterostructure includes a first inorganic component and a second inorganic component one of which is a matrix, and the other of which is three-dimensionally and periodically arranged in the matrix, and has a three-dimensional periodic structure whose average value of one unit length of a repeated structure is 1 nm to 100 nm.

A process of producing a ceramic matrix composite turbine bucket, an insert for a ceramic matrix composite turbine bucket, and a ceramic matrix composite turbine bucket are disclosed. The process includes providing a bucket preform having a dovetail cavity, the dovetail cavity being enclosed within a dovetail shank of the bucket preform, positioning an insert within the dovetail cavity, then forming the ceramic matrix composite turbine bucket in a furnace. The insert includes a geometry configured to be fit within a dovetail cavity of the ceramic matrix composite turbine bucket, a bucket preform, or both. The insert is foam material or a plurality of ceramic matrix composite plies. The ceramic matrix composite turbine bucket includes a dovetail shank and a dovetail cavity enclosed within the dovetail shank. The dovetail cavity is arranged and disposed for receiving an insert.