Abstract: A fiber having an environmental barrier coating is provided that includes, in one illustrative form, a Hi Nicalon preform assembled in a tooling for chemical vapor infiltration and cleaned to remove sizing char from fibers of the Hi Nicalon preform; a ytterbium doped silicon carbide coat located over the Hi Nicalon preform; a boron nitride interface coat applied over the ytterbium doped silicon carbide coat; and a silicon carbide coat applied over the boron nitride interface coat.

Abstract: An apparatus includes a composite gas turbine engine multi-airfoil blade that includes first and second circumferentially spaced adjacent composite airfoils coupled together via a common composite attachment. The common attachment does not employ a fastener. The composite multi-airfoil blade may have a unitary construction having a ceramic matrix composition.

Abstract: Ceramic matrix composite materials and processes for making said composite materials are disclosed.

Abstract: A method and apparatus for providing molten metal infiltration into a component is provided.

Abstract: A method and apparatus for providing molten metal infiltration into a component is provided.

Abstract: Ceramic matrix composite materials and a process for making said composite materials are disclosed.

Abstract: A method of producing a ceramic matrix composite component for use in a gas turbine engine comprising forming a ceramic matrix composite component, assembling the preform in a tool, loading the tool into a furnace and infiltrating the preform. Infiltrating the preform may include the methods of CVI, CVD, slurry infiltration, and melt infiltration.

Abstract: A ceramic matrix composite includes a plurality of fibers embedded in a matrix. The composition of the matrix is selected to achieve a desired relationship between the mechanical and thermal properties of the matrix and the fibers.

Abstract: A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.

Abstract: A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.

Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier.

Abstract: A method of forming a composite preform containing multiple laminates is disclosed. The method may include providing a first sublaminate comprising stacked fibers woven into a fabric; providing a second sublaminate comprising stacked fibers woven into a fabric; joining the first sublaminate and the second sublaminate forming a component comprising a region of discontinuity sandwiched between the first sublaminate and the second sublaminate; rigidizing the component; and softening the region between the first sublaminate and the second sublaminate. In illustrative embodiments, the method may include manipulating the region of discontinuity between the first sublaminate and the second sublaminate to reduce the incoherence between the sublaminates by moving fibers from the sublaminates through at least part of the region between the first sublaminate and the second sublaminate.

Abstract: A method and apparatus for providing molten metal infiltration into a component is provided.

Abstract: A high strength ceramic matrix composite and method for same is provided. A fiber preform is provided that is either self-supporting or is constrained by a tool for subsequent processing. The preform is coated with about 0.1 ?m to about 5 ?m of silicon carbide. The silicon carbide is coated with about 0.05 ?m to about 2 ?m boron nitride, carbon, or other interface layer. The interface layer is coated with at least about 0.2 ?m to about 40 ?m of silicon carbide.

Abstract: A fiber having an environmental barrier coating is provided that includes, in one illustrative form, a Hi Nicalon preform assembled in a tooling for chemical vapor infiltration and cleaned to remove sizing char from fibers of the Hi Nicalon preform; a ytterbium doped silicon carbide coat located over the Hi Nicalon preform; a boron nitride interface coat applied over the ytterbium doped silicon carbide coat; and a silicon carbide coat applied over the boron nitride interface coat.

Abstract: Creating a ceramic matrix structure may include alternating different layers of fiber fabric to achieve porosity, infiltration, and/or other objectives. Different layers of the ceramic matrix structure may be configured differently to achieve different objectives in different regions of the ceramic matrix structure. The fiber tow spacing, fiber count and/or other characteristics may be varied within individual layers and/or among different layers of the ceramic matrix structure.

Abstract: A ceramic matrix composite includes a plurality of fibers embedded in a matrix. The composition of the matrix is selected to achieve a desired relationship between the mechanical and thermal properties of the matrix and the fibers.

Abstract: Ceramic matrix composite materials and processes for making said composite materials are disclosed,

Abstract: A method of making a fiber tow coating is provided. The method includes providing a fiber tow selected from the group consisting of carbon and silicon; and applying an oxide-based fiber interface coating onto the fiber tow using directed vapor deposition or other like deposition method.

Abstract: A composite component includes a bonded portion and a component mount. The component mount is coupled to the bonded portion to move relative to the bonded portion. The bonded portion includes a fiber portion and a ceramic portion.