Abstract: A gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.

Abstract: A method of producing an enhanced ceramic matrix composite includes applying a tackifier compound to a fiber preform. The tackifier compound includes inorganic filler particles. The method further includes modifying the tackifier compound such that the inorganic filler particles remain interspersed throughout the fiber preform, and occupy pores of fiber preform.

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 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 ceramic matrix composite having improved operating characteristics includes a barrier layer.

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 producing an enhanced ceramic matrix composite includes applying a tackifier compound to a fiber preform. The tackifier compound includes inorganic filler particles. The method further includes modifying the tackifier compound such that the inorganic filler particles remain interspersed throughout the fiber preform, and occupy pores of fiber preform.

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 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 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 gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.

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

Abstract: A ceramic matrix composite seal is disclosed. The ceramic matrix composite seal including a ceramic matrix and a number of ceramic fiber fabrics embedded in the ceramic matrix. The ceramic matrix composite seal is formed into a strip with a desired geometry such that the seal strip is configured to be assembled with a number of components to create a seal between the components.

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

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