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 laminated glazing having a first ply connected to a second ply by a polymeric interlayer; and a solar control coating located on at least one of the major surfaces thereof, the solar control coating including: a first phase adjustment layer; a first metallic layer located over the first phase adjustment layer; a first primer layer located over the first metallic layer; a second phase adjustment layer located over the first primer layer; a second metallic layer located over the second phase adjustment layer; a second primer layer located over the second metallic layer; a third phase adjustment layer located over the second primer layer; a third metallic layer located over the third phase adjustment layer; a third primer layer located over the third metallic layer; a fourth phase adjustment layer located over the third primer layer; and a protective layer located over the fourth phase adjustment layer.

One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

A wavelength conversion member complex includes a wavelength conversion member, a joining material, and a heat dissipation member. The wavelength conversion member includes a support and a phosphor member. The support defines a through-hole extending from an upper surface to a lower surface. The support has a concave portion on the lower surface around the through-hole. The concave portion is spaced apart from the through-hole. The phosphor member is disposed in the through-hole and includes a phosphor. The lower surface of the phosphor member is continuous with the lower surface of the support. The joining material is disposed in the concave portion, and has a lower surface that is flush with the lower surface of the support. The heat dissipation member is disposed under the joining material and the phosphor member, and has an upper surface in contact with the lower surface of the joining material.

An apparatus and method of manufacturing a porous ceramic segmented honeycomb body (340,340) comprising axial channels (216) extending from a first end face (220) to a second end face (224). A plurality of porous ceramic honeycomb segments (204) is moved axially past respective apertures (110) of an adhesive applying device (100). Adhesive (118) is applied through openings (126) in the adhesive applying device (100) onto peripheral axial surfaces of each porous ceramic honeycomb segment (204). The plurality of porous ceramic honeycomb segments (204) enters a wide opening (318) of a tapered chamber (314) and exits a narrow opening (322) of the tapered chamber (314); a tapered wall (326) from the wide opening (318) to the narrow opening (322) presses the plurality of porous ceramic honeycomb segments (204) together forming the porous ceramic segmented honeycomb body (340,340). The adhesive (118) on the peripheral axial surfaces between respective porous ceramic honeycomb segments (204) is distributed by the pressing.

Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming thereupon another segment comprising a CMC, which may be another matrix portion including a silicon carbide and a silicon phase dispersed within therewithin. Also provided is a gas turbine component with a CMC segment including a matrix portion including a silicon carbide and a silicon phase dispersed therewithin, a sealing layer including silicon carbide enclosing the first segment, and a second segment on the sealing layer, wherein the second segment includes a melt-infiltrated CMC having a matrix portion including a silicon carbide and a silicon phase dispersed therewithin.

Disclosed is a gas turbine engine component, and a method for forming the component. The component includes a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion.

This patent document relates to systems, structures, devices, and fabrication processes for ceramic matrix composites suitable for use in a nuclear reactor environment and other applications requiring materials that can withstand high temperatures and/or highly corrosive environments. In one exemplary aspect, a method of joining and sealing ceramic structures is disclosed. The method comprises forming a joint of a ceramic structure and an end plug using a sealing material, wherein the end plug has a hole that goes through a top surface and a bottom surface of the end plug; filling the ceramic structure with a desired gas composition through the hole; heating a material into a molten form using a heat source; and directing the material into the hole, wherein the material solidifies to seal the end plug.

The present disclosure relates to a multilayer ceramic substrate preparation method. The multilayer ceramic substrate preparation method according to the present disclosure includes firing a plurality of ceramic green sheets, to create a plurality of ceramic thin films; forming a via hall in each of the plurality of ceramic thin films; filling the via hall of the plurality of ceramic thin films with conductive paste, and heat treating the via hall filled with the conductive paste, to form a via electrode; printing a pattern on a cross section of each of the plurality of ceramic thin films, and heat treating the printed pattern, to form an inner electrode; applying a bonding agent on the cross section of each of the ceramic thin films excluding an uppermost ceramic thin film of the plurality of ceramic thin films; aligning and laminating each of the plurality of ceramic thin films such that each of the plurality of ceramic thin films is electrically connected through the via electrode and the inner electrode; and firing or heat treating the laminated plurality of ceramic thin films.

A method of making a stoichiometric monazite (LaPO.sub.4) composition or a mixture of LaPO.sub.4 and LaP.sub.3O.sub.9 composition, as defined herein. Also disclosed is a method of joining or sealing materials with the compositions, as defined herein.