The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion.

The present invention relates to a silica glass member including: a main body including a silica glass and having a bonding part for bonding to another member; and a bonding film which is provided on the bonding part, has a thickness of 0.2 m to 10 m, and includes Au and a glass formed through melting of glass frit, in which the bonding film is produced from Au powder having an average particle diameter of 3 m or less and glass frit having a softening point of 850 C. or lower, a process for producing a silica glass member, and a process for bonding a ceramic and a silica glass.

A pre-stressed curved plate comprising a curved plate having at least one concave surface, the curved plate being enveloped and adhesively bonded with tensioned reinforcing fibers, whereby the reinforcing fibers are first wound around the plate under tension being spaced apart from the concave surface and subsequently subjected to pressure to stretch and bond the reinforcing fibers to the surfaces of the plate, where upon bonding, the tensile strain of the fiber introduces stress in the plate.

A method for the joining of ceramic pieces with a hermetically sealed joint comprising brazing a continuous 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 time at temperature, the joining atmosphere, and other factors. The ceramic pieces may be aluminum nitride 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 pre-stressed curved plate comprising a curved plate having at least one concave surface, the curved plate being enveloped and adhesively bonded with tensioned reinforcing fibers, whereby the reinforcing fibers are first wound around the plate under tension being spaced apart from the concave surface and subsequently subjected to pressure to stretch and bond the reinforcing fibers to the surfaces of the plate, where upon bonding, the tensile strain of the fiber introduces stress in the plate.

A part made of a ceramic material, including a portion forming a base and a portion forming a wall, wherein the base consists of a low-porosity ceramic material and the wall is obtained by powder sintering and includes an envelope and a core, the core being within the envelope, the porosity of the core being higher than that of the base and increasing the further it is from the base.

A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.

Provided is a slider having appearance or texture which cannot be obtained with a slider body made of metal or synthetic resin in the related art and further having properties superior than those of sliders in the related art. A slider of an embodiment of the invention includes a slider body formed by sintered bodies containing zirconium oxide as a main component and a tab held by a tab attaching portion of the slider body.

A polycrystalline CaF.sub.2 member includes a combined assembly of a plurality of polycrystalline bodies made from CaF.sub.2 that are pressure bonded together.

A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.