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.

The method includes forming an inner monolithic layer from crystals of beta phase stoichiometric silicon carbide on a carbon substrate in the form of a rod by chemical methylsilane vapor deposition in a sealed tubular hot-wall CVD reactor. The method further includes forming a central composite layer over the inner monolithic layer by twisting continuous beta phase stoichiometric silicon carbide fibers into tows, transporting the tows to a braiding machine, and forming a reinforcing thread framework. A pyrocarbon interface coating is built up by chemical methane vapor deposition in a sealed tubular hot-wall CVD reactor. Then, a matrix is formed by chemical methylsilane vapor deposition in the reactor. A protective outer monolithic layer is formed from crystals of beta phase stoichiometric silicon carbide over the central composite layer by chemical methylsilane vapor deposition in a CVD reactor. And then the carbon substrate is removed from the fabricated semi-finished product.

A gas turbine hot part includes: a body portion; a porous portion forming at least a part of the body portion or disposed on at least a part of the body portion and allowing a cooling gas to pass therethrough; and at least one filter disposed upstream of the porous portion in a flow direction of the cooling gas and capable of trapping foreign substances that cannot pass through the porous portion.

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

In some examples, a technique may include positioning a first part comprising a ceramic or ceramic matrix composite and a second part comprising a ceramic or a CMC adjacent to each other to define a joint region at the interface of the first part and the second part. In some examples, the joint region may be heated using at least one of a laser or a plasma arc source to heat the joint region to an elevated temperature. The first and second parts may be pressed together and cooled to join the first and second parts at the joint region. In other examples, a solid braze material including a filler material and a metal or alloy may be delivered to the joint region and locally heated to cause a constituent of the filler material and a constituent of the metal or alloy to react. When reacted, the constituents may form a solid material, which may join the first and second parts.

Disclosed is a method for making a ceramic matrix composite. A preform is subjected to one or more infiltrations with slurry comprised of a solvent, matrix binder, and particles. Removal of the solvent between infiltrations is achieved by making use of differing chemical or physical properties between the solvent and binder.

A prepreg for a ceramic matrix composite, a process for the preparation of a green body with the help of the prepreg, and a process for the preparation of the ceramic matrix composite from the green body prepared according to the present invention are provided. The inventive process comprises the following steps: a) impregnating an arrangement of ceramic fibers with a slurry, which slurry comprises the following components: (i) 10 to 40 vol.-%, based on the total volume of the slurry, of ceramic particles, (ii) an alcoholic organic solvent selected from: (ii-1) 21 to 35 wt.-%, based on the total weight of the ceramic particles in the slurry, of glycerol, (ii-2) 10 to 35 wt.-%, based on the total weight of the ceramic particles in the slurry, of an oligo or polyethylene glycol with an average molecular weight of at most 800 g/mol, (ii-3) 10 to 35 wt.-%, based on the total weight of the ceramic particles in the slurry, of at least one C2-C6 alkane diol, and (ii-4) 10 to 35 wt.-%, based on the total weight of the ceramic particles in the slurry, of a mixture of two or more components, selected from a C2-C6 alkane diol, an oligo or polyethylene glycol with an average molecular weight of at most 800 g/mol, and glycerol; and (iii) water; b) reducing the water content in the slurry in the impregnated fiber arrangement to obtain a prepreg for a ceramic matrix composite; c) providing a shaped composite material from one or more prepregs obtained according to step b); d) consolidating the shaped composite material by reducing the water content and the content of alcoholic organic solvent so that a green body is obtained.

A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.

A method for forming a passage in a ceramic matrix composite component includes forming a core for a ceramic matrix composite component; embedding a hollow member into the core at a desired location for a passage in the ceramic matrix composite component; wrapping the core with a ceramic material; and inserting a rod through the hollow member and into the core.

A method for forming a ceramic matrix composite article includes laying up a first group of plies; laying up a second group of plies, the first and second groups of plies being adjacent to each other; compacting the first group of plies and the second group of plies in the same processing step; and performing a first infiltration process on the first group of plies. The method also includes performing a second infiltration process on the second group of plies, the first infiltration process being one of a melt infiltration process or a chemical vapor infiltration process, and the second infiltration process being the other of the melt infiltration process or the chemical vapor infiltration process.