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 thin-film thermocouple for measuring the temperature of a ceramic matrix composite (CMC) component includes 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 includes 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 matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.

A ceramic matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.

According to a method set forth herein a plurality of preform plies having first and second preform plies can be associated together to define a preform. The preform can be subject to chemical vapor infiltration (CVI) processing to define a ceramic matrix composite (CMC) structure.

According to a method set forth herein a plurality of preform plies having first and second preform plies can be associated together to define a preform. The preform can be subject to chemical vapor infiltration (CVI) processing to define a ceramic matrix composite (CMC) structure.

A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.

A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.

Various methods and assemblies are provided for producing composite components having formed in features. For example, a method may comprise depositing a composite material on a base tool; bringing a feature forming tool into contact with the composite material; and processing the composite material with the feature forming tool in contact with the composite material. The processed composite material forms a green state composite component. The feature forming tool comprises a sheet having one or more elements for interacting with one or more elements of the base tool to form one or more features of the composite component. In some embodiments, the method also may comprise sealing a bag around the feature forming tool and the composite material after bringing the tool into contact with the composite material and removing the bag and the feature forming tool from the green state composite component after processing.