A turbine blade having an airfoil portion includes a first ceramic matrix composite (CMC) component having a first outer surface and a second ceramic matrix composite (CMC) component having a second outer surface. The second CMC component is positioned adjacent the first CMC component such that the first outer surface and the second outer surface align with one another and at least partially define the airfoil portion. A ceramic bead is at least partially formed at an interface between the first CMC component and the second CMC component. The formation of the bead melts a portion of the first CMC component and the second CMC component, such that the ceramic bead, the first CMC component, and the second CMC component become a single contiguous component and the bead fixedly attaches the first CMC component and the second CMC component. The bead includes a bead outer surface that extends outward beyond the first outer surface and the second outer surface and an overlayer is deposited onto the airfoil portion, the overlayer bonded to the first outer surface, the second outer surface, and the bead outer surface.

A void filler material includes a ceramic rod and a fibrous overwrap. The void filler material may be used in a ceramic matrix composite. The method of making the ceramic matrix composite includes inserting the void filler material in voids of a preform and depositing a ceramic matrix on the preform and the void filler material using chemical vapor infiltration.

A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.

Provided is a nuclear fuel pellet having excellent impact resistance, the pellet being prepared with UO.sub.2 powder and having a cylindrical shape with a height of 9 to 13 mm and a horizontal cross-section diameter of 8 to 8.5 mm, and including: at each of a top surface and a bottom surface thereof, a dish configured as a spherical groove shape having a predetermined curvature and a groove diameter of 4.8 to 5.2 mm on a center; a shoulder configured as an annular plane along a rim of the dish; and a chamfer configured as a shape in which a corner is chamfered along a rim of the shoulder, wherein a width of the shoulder is 0.20 mm to 0.80 mm, and an angle between the chamfer and a horizontal plane is a 14-degree angle to 18-degree angle.

A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.

Disclosed are embodiments of materials for microstrip and substrate integrated waveguide circulators/isolators which can be integrated with a substrate. This composite structure can serve as a platform for other components, allowing for improved miniaturization of components. In particular, a sintering aid can be used to improve the fit between a ferrite material and a dielectric material, improving performance.

In some examples, techniques of repairing and/or reinforcing oxide-oxide ceramic matrix composite (CMC) materials using a metallic material. In one example, a method including applying a metallic material at an edge of an oxide-oxide CMC substrate; and heating the metallic material to diffuse the metal material into the oxide-oxide CMC substrate at the edge. In another example, a method including applying a metallic material onto a damaged area of the oxide-oxide CMC; applying a reinforcing phase material onto the damaged area of the oxide-oxide CMC; and heating the metallic material to diffuse the metallic material into the oxide-oxide CMC and attach the reinforcing phase material to the damaged area of the oxide-oxide CMC.

A method for modifying a composite component may include positioning a barrier segment between an infiltrated segment of the composite component and a green segment to form an assembly; and initiating an infiltration process. The barrier segment may have a barrier segment permeability that is lower than a permeability of the infiltrated segment, a permeability of the green segment, or both. A composite component may include an infiltrated segment infiltrated with a molten material during a prior infiltration process; a green segment that is uninfiltrated; and a barrier segment having a microstructure different from the infiltrated segment, the green segment, or both. The microstructure of the barrier segment may be configured to slow a flow of material between the infiltrated segment and the green segment during a subsequent infiltration process.

This invention relates to a product and a method of preparing ceramic and/or ceramic hybrid materials through the construction of a printed die. The printed die being made by three dimensional printing or additive manufacturing processes possesses both an external geometry and an internal geometry.