This invention provides resin formulations which may be used for 3D printing and pyrolyzing to produce a ceramic matrix composite. The resin formulations contain a solid-phase filler, to provide high thermal stability and mechanical strength (e.g., fracture toughness) in the final ceramic material. The invention provides direct, free-form 3D printing of a preceramic polymer loaded with a solid-phase filler, followed by converting the preceramic polymer to a 3D-printed ceramic matrix composite with potentially complex 3D shapes or in the form of large parts. Other variations provide active solid-phase functional additives as solid-phase fillers, to perform or enhance at least one chemical, physical, mechanical, or electrical function within the ceramic structure as it is being formed as well as in the final structure. Solid-phase functional additives actively improve the final ceramic structure through one or more changes actively induced by the additives during pyrolysis or other thermal treatment.

A method of making a ceramic matrix composite (CMC) article by combining a preceramic polymer with one or more sized nanopowders and optional surfactants and/or solvents to form a mixture suitable for 3D printing, depositing the mixture on a mandrel, curing it to form a green body, and pyrolyzing the green body such that the nanocrystalline surface of the CMC article has sufficiently the same surface roughness and figure accuracy of the mandrel to enable the CMC article to be used without further polishing. The mixture can be a paste or slurry that is self supporting and exhibit pseudoplastic rheology. The preceramic polymer is preferably a precursor to SiC, and the nanopowders preferably comprise SiC. The article can be densified by using polymer infiltration pyrolysis, with or without nanoparticles. The curing and pyrolysis of the article can be performed with microwave radiation. An example structure is a gradient density lattice with a mirror surface for use in a cryogenically cooled infrared optical system such as an orbiting space telescope.

The invention relates to a method for preparing a material based on an aluminosilicate selected from barium aluminosilicate BAS, barium-strontium aluminosilicate BSAS, and strontium aluminosilicate SAS, said aluminosilicate consisting of aluminosilicate with a hexagonal structure, characterised in that it includes a single sintering step in which a mixture of powders of precursors of said aluminosilicate, including an aluminium hydroxide Al(OH).sub.3 powder, are sintered by a hot-sintering technique with a pulsed electric field SPS; whereby a material based on an aluminosilicate, said aluminosilicate consisting of an aluminosilicate with a hexagonal structure is obtained. The material based on an aluminosilicate prepared by said method can be used in a method for preparing a composite material consisting of an aluminosilicate matrix reinforced by reinforcements made of metalloid or metal oxide.

Disclosed is a synthesis method for preparing tantalum pentoxide colloid including the steps of: a. Providing a transparent solution of amorphous tantalum pentoxide, b. Subjecting the solution to solvothermal conditions in order to form tantalum pentoxide nanocrystals, c. Dispersing the tantalum pentoxide nanocrystals in a solvent so as to form a tantalum pentoxide colloid.

A refractory article is described, the refractory article including a refractory body and a refractory coating layer deposited on a surface thereof, wherein the refractory coating layer includes silica, alumina, boron oxide, and calcium oxide. The refractory article may be at least one of a melting vessel, a clarifying vessel and a molding apparatus. A composition for coating a refractory article and a method of manufacturing the refractory article are also disclosed.

A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

This invention has an object to provide a means for providing a calcium phosphate sintered body particle group that does not cause a phenomenon of bubble generation in any use mode thereof, and further has a smaller particle diameter.

There is provided a ceramic particle group containing spherical ceramic particles, which is characterized in that the ceramic particle has a particle diameter within a range of 10 nm to 700 nm, and is a calcium phosphate sintered body particle, and further the ceramic particle group contains no calcium carbonate.

Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine, an airfoil having a root and a tip, and a pin extending through the root. The root is coupled to the rotary structure and has a bulbous shape, and the airfoil is formed from a plurality of composite plies. The pin defines both a planar first surface and a planar second surface on a pin body having a generally circular cross-section. Further, the pin includes a first end and a second end that contact the rotary structure. The first and second surfaces together form a point that is oriented toward the tip of the airfoil. In one embodiment, the rotary structure is an outer rotor of an interdigitated rotor assembly and the airfoil extends radially inward.

A process for producing a process for producing a LnM.sub.2Cu.sub.3O.sub.x high-temperature superconductive powder, the process comprising: i) providing an aqueous solution of Ln, M and Cu and at least one mineral acid; ii) adding at least one sequestrating agent and, optionally, at least one dispersant to the solution to form a precipitate; iii) recovering the precipitate from the solution; and iv) heating the precipitate in a flow of oxygen to form the LnM.sub.2Cu.sub.3O.sub.x powder, wherein Ln is a rare earth element, preferably Y, Ce, Dy, Er, Gd, La, Nd, Pr, Sm, Sc, Yb, or a mixture of two or more thereof, and wherein M is selected from Ca, Sr, and Ba.

A method of making a ceramic composite component includes providing a fibrous preform or a plurality of fibers, providing a first plurality of particles, coating the first plurality of particles with a coating to produce a first plurality of coated particles, delivering the first plurality of coated particles to the fibrous preform or to an outer surface of the plurality of fibers, and converting the first plurality of coated particles into refractory compounds. The first plurality of particles or the coating comprises a refractory metal.