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 method for producing a gas-tight metal-ceramic join is disclosed. In an embodiment a method includes providing at least one ceramic main body having a first end face and a second end face, applying a metallization to at least a partial region of the end faces of the main body, applying a nickel layer to the metallized partial region of the end faces, applying a brazing paste to the metallized partial region of the first end face and/or the second end face of the main body, drying the brazing paste, and firing the brazing paste.

A ceramic circuit substrate and power module with excellent heat cycle resistance characteristics, which is formed by bonding a ceramic substrate and a copper plate via a brazing material including Ag, Cu, and an active metal, wherein the bond void fraction is no greater than 1.0% and the diffusion distance of the Ag, which is a brazing material component, is 5-20 m. Also, a method for manufacturing a ceramic circuit substrate characterized in that the heating time in a temperature range 400-700 C. in a process for raising the temperature to a bonding temperature is 5-30 minutes and bonding is performed by maintaining the bonding temperature at 720-800 C. for 5-30 minutes.

A method for producing a ceramic-aluminum bonded body obtained by bonding a ceramic member and an aluminum member, the aluminum member before bonding being composed of aluminum having a purity of 99.0 mass % or higher and 99.9 mass % or lower, includes a heat treatment step of subjecting the aluminum member to a heat treatment in a range of 400 C. or higher and lower than a solidus temperature, and a bonding step of bonding the aluminum member after the heat treatment step and the ceramic member via a brazing filler material including Si.

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 multilayer component and a mathod for producing a multilayer component are disclosed. In an embodiment a multilayer component includes a ceramic main element and at least one metal structure, wherein the metal structure is cosintered and wherein main element is a varistor ceramic having 90 mol % of ZnO, from 0.5 to 5 mol % of Sb.sub.2O.sub.3, from 0.05 to 2 mol % of Co.sub.3O.sub.4, Mn.sub.2O.sub.3, SiO.sub.2 and/or Cr.sub.2O.sub.3, and <0.1 mol % of B.sub.2O.sub.3, Al.sub.2O.sub.3 and/or NiO.

A method for the joining of ceramic pieces with a hermetically sealed joint comprising brazing a layer of joining material between the two pieces. The wetting and flow of the joining material is controlled by the selection of the joining material, the joining temperature, the joining atmosphere, and other factors. The ceramic pieces may be on a non-diffusable type, such as aluminum nitride, alumina, beryllium oxide, and zirconia, and the pieces may be brazed with an aluminum alloy under controlled atmosphere. The joint material is adapted to later withstand both the environments within a process chamber during substrate processing, and the oxygenated atmosphere which may be seen within the shaft of a heater or electrostatic chuck.

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 joined body according to the invention is a ceramic/aluminum joined body including: a ceramic member; and an aluminum member made of aluminum or an aluminum alloy, in which the ceramic member and the aluminum member are joined to each other, the ceramic member is formed of silicon nitride containing magnesium, and a joining layer in which magnesium is contained in an aluminum-silicon-oxygen-nitrogen compound is formed at a joining interface between the ceramic member and the aluminum member.

In a ceramic/aluminum bonded body according to the present invention, a ceramic member and an aluminum member formed of aluminum or an aluminum alloy are bonded to each other, the ceramic member has a ceramic main body formed of silicon nitride, and an aluminum nitride layer or an aluminum oxide layer formed on the surface of the ceramic main body to which the aluminum member is bonded, the ceramic member and the aluminum member are bonded to each other through the aluminum nitride layer or the aluminum oxide layer, the ceramic main body is provided with silicon nitride phases and a glass phase formed between the silicon nitride phases, Al is present in a portion of the glass phase of the ceramic main body at an interface with the aluminum nitride layer or aluminum oxide layer.