As a sintered body for a radiation shielding material, which can effectively shield mainly low-energy-level neutrons, that is, thermal neutrons and lower, slow neutrons, and has excellent physical properties such as bending strength and Vickers hardness, leading to high machining strength, a sintered body for a radiation shielding material comprising LiF ranging between 99 wt. % to 5 wt. %, and one or more fluorides selected from among MgF.sub.2, CaF.sub.2, AlF.sub.3, KF, NaF, and/or YF.sub.3 ranging between 1 wt. % to 95 wt. %, having physical properties of a relative density of 92% or more, a bending strength of 50 MPa or more, and a Vickers hardness of 100 or more, is provided.

A method of fabricating a brake component made from a ceramic matrix composite is disclosed. In various embodiments, the method includes infiltrating a carbon fabric with a slurry containing a ceramic powder and a sintering aid; laying up the carbon fabric in a desired geometry to form a raw component; warm pressing the raw component to form a green component; and sintering the green component via a spark plasma sintering process to form a sintered component.

Provided is a method for manufacturing a composite body, the method including: a nitriding step of firing a boron carbide powder in a nitrogen atmosphere to obtain a fired product containing boron carbonitride; a sintering step of molding and heating a blend containing the fired product and a sintering aid to obtain a boron nitride sintered body including boron nitride particles and pores; and an impregnating step of impregnating the boron nitride sintered body with a resin composition, the composite body having the boron nitride sintered body and a resin filled in at least some of the pores of the boron nitride sintered body.

A method for forming a ceramic matrix composite (CMC) component with an internal cooling channel includes partially densifying a first fiber preform to form a portion of a final ceramic matrix volume, machining a first channel into a surface of the partially densified first fiber preform, covering the first channel with a fibrous member to form a near net shape fiber preform with an internal passage formed by the first channel and the fibrous member, and densifying the near net shape fiber preform.

Disclosed are a multi-layer composite ceramic plate and a manufacturing method thereof. The composite ceramic plate includes at least one basic sandwich structure. The manufacturing method includes: preparing a sheet-like green body with ceramic powders; pre-sintering the green body at a pre-sintering temperature lower than the sintering temperature to obtain a pre-sintered ceramic member with certain strength; forming a metal electrode layer on an upper surface of the pre-sintered ceramic member; placing the pre-sintered ceramic member in a mold, with the upper surface coated with the metal electrode layer facing upwards; providing a ceramic precursor layer on the upper surface of the pre-sintered ceramic member; carrying out hot-pressing sintering in the axial direction of the pre-sintered ceramic member at the sintering temperature to form an integral structure, wherein by the hot-pressing sintering, a second ceramic layer is formed by the pre-sintered ceramic member, a first ceramic layer is formed by the ceramic precursor layer, and the metal electrode layer is located between the first ceramic layer and the second ceramic layer to from a basic sandwich structure together with the first ceramic layer and the second ceramic layer.

A method for making ceramic fixed partial dentures comprising separating the as-sintered partial denture structure, rejoining the retainers and pontic with glass, which forms a strong joint between the retainers and pontic after sintering. This method may produce ceramic long-span fixed partial dentures with a better fit.

A polycrystalline ceramic solid and a method for producing a polycrystalline ceramic solid are disclosed. In an embodiment a polycrystalline ceramic solid includes a main phase with a composition of the general formula: (1-y)Pb.sub.a(Mg.sub.bNb.sub.c)O.sub.3-e+yPb.sub.aTi.sub.dO.sub.3 with 0.055≤y≤0.065, 0.95≤a≤1.02, 0.29≤b≤0.36, 0.63≤c≤0.69, 0.9≤d≤1.1, and 0≤e≤0.1, and optionally one or more secondary phases, wherein, in each section through the solid, a proportion of the secondary phases relative to any given cross-sectional area through the solid is less than or equal to 0.5 percent, or wherein the solid is free of the secondary phases.

A porous ceramic structure includes one sheet, and a plurality of porous ceramic particles bonded on the sheet. A gap d formed between adjacent ones of the porous ceramic particles is 10˜80 μm.

A method of forming a component for a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes preforming the aerodynamic component into an initial desired shape using the CMCs, executing partial densification of the CMCs, repeating the preforming operations and the executing of the partial densification until a final desired shape of the aerodynamic component is achieved, machining or cutting the CMCs during one or more of the preforming operations and the executing of the partial densification to remove defects from the CMCs and executing a full densification of the CMCs.

A method of manufacturing a chamber component for a processing chamber comprises forming a green body using a Y.sub.2O.sub.3—ZrO.sub.2 powder consisting essentially of 55-65 mol % Y.sub.2O.sub.3 and 35-45 mol % ZrO.sub.2; and sintering the green body to produce a sintered ceramic body consisting essentially of one or more phase of Y.sub.2O.sub.3—ZrO.sub.2, the sintered ceramic body consisting essentially of 55-65 mol % Y.sub.2O.sub.3 and 35-45 mol % ZrO.sub.2.