A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

A cathode having a tandem electrocatalyst structure is provided. The cathode includes a plurality of wires spaced apart from each other, a layer formed on a surface of each of the plurality of wires, and a plurality of nanoparticles disposed on the layer. Each of the plurality of wires includes a first perovskite material or a metal. The layer includes a second perovskite material. Each of the nanoparticles includes a metal oxide.

A process for the preparation of non-fibrous alkaline titanates comprising the steps of: melting alkaline titanate in a furnace at a temperature ranging from 1300° C. to 1500° C. to form a molten product; cooling said molten product by placing it in contact with a material having a temperature equal to or lower than 15° C.

The gas turbine combustor liner can delimit a combustion chamber, and have at least one monolithic ceramic block having a first face exposed to the combustion chamber and a second face opposite the first face, and a 3D fabric of ceramic fibers partially embedded inside the monolithic ceramic block, and partially extending outside the second face of the monolithic ceramic block, away from the combustion chamber.

A honeycomb body made of a composite material for fire-resistant lightweight structures including honeycomb cells having a cross section is provided. The cell walls of the honeycomb cells are produced from a composite material. The composite material has at least one carrier, for example a woven fabric or a laid fabric made of fibers, and a matrix into which the carrier is embedded. The matrix includes a silicon-based ceramic material, of which the proportion by mass in the matrix along the cell walls is at least 30 wt. %. A method for producing such a ceramic honeycomb body and a honeycomb tube as an intermediate product for the same are also provided. A flat semi-finished product as a curable intermediate product for the production of fire-resistant fiber composite lightweight structures, which has a matrix mixture including dispersed silicon particles, is also provided.

Disclosed herein is a chemical vapor infiltration method including flowing ceramic precursors through a preform and depositing a matrix material on the preform at a first gas infiltration pressure, increasing the gas filtration pressure to a second gas infiltration pressure, and lowering the gas infiltration pressure to a third gas infiltration pressure which is intermediate to the first and second gas infiltration pressures.

Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.

A method of making a ceramic matrix composite is disclosed. According to the method, a first preform comprising fibers is formed, and a second preform including a helical surface portion is inserted into the first preform. The first preform with the inserted second preform is infiltrated with a matrix material comprising a ceramic to form the ceramic matrix composite. A ceramic matrix composite is also disclosed. The ceramic matrix composite includes a first portion including a matrix comprising a ceramic, and a reinforcement including fibers derived from the first preform in the matrix. A second portion including a helical surface portion interface with the first portion is disposed within the first portion.

An apparatus contains at least one pressure-rated apparatus shell and at least one modular framework system containing ceramic fiber composite materials and arranged within the apparatus shell. A modular lining apparatus includes the modular framework system and. refractory bricks. The apparatus can be used for high-temperature reactors, especially electrically heated high-temperature reactors.

Disclosed is a preform for a ceramic matrix composite including direct channels extending from an exterior surface of the preform to an interior space of the preform wherein the direct channels are free of char.