The cutting method of a honeycomb formed body includes an end face cutting step of cutting both end faces of the ceramic honeycomb formed body before fired, by use of blade type rough-cutting grinding wheels in which coarse abrasive grain layers are formed; a honeycomb formed body rotating step of rotating the honeycomb formed body round a rotation axis which is a central axis perpendicular to the end faces of the honeycomb formed body; and an end face finishing step of disposing two finish-polishing grinding wheels via a predetermined distance so that finishing abrasive grain layers formed in the finish-polishing grinding wheels face each other, rotating the finish-polishing grinding wheels round a rotary shaft which is a central shaft of the finish-polishing grinding wheels, and moving the honeycomb formed body to pass the honeycomb formed body between the two finish-polishing grinding wheels, thereby finish-polishing cut surfaces which are cut.

The cutting method of a honeycomb formed body includes an end face cutting step of cutting both end faces of the ceramic honeycomb formed body before fired, by use of blade type rough-cutting grinding wheels in which coarse abrasive grain layers are formed; a honeycomb formed body rotating step of rotating the honeycomb formed body round a rotation axis which is a central axis perpendicular to the end faces of the honeycomb formed body; and an end face finishing step of disposing two finish-polishing grinding wheels via a predetermined distance so that finishing abrasive grain layers formed in the finish-polishing grinding wheels face each other, rotating the finish-polishing grinding wheels round a rotary shaft which is a central shaft of the finish-polishing grinding wheels, and moving the honeycomb formed body to pass the honeycomb formed body between the two finish-polishing grinding wheels, thereby finish-polishing cut surfaces which are cut.

A ceramic fiber processing apparatus and method for processing ceramic fibers for the manufacture of ceramic matrix composites (CMCs) is provided. The apparatus includes a frame including a plurality of unidirectional ceramic fibers wound thereabout and extending across a void therein the frame to define a first planar array of ceramic fibers and a second planar array of ceramic fibers. During use, the frame is disposed in the ceramic fiber processing apparatus in a manner to enable gripping of the first planar array of ceramic fibers with a first gripper assembly and gripping of the second planar array of ceramic fibers with a second gripper assembly. A cutting mechanism provides cutting of the plurality of unidirectional ceramic fibers to separate the first planar array of ceramic fibers and the second planar array of ceramic fibers from one another.

A ceramic part and methods for making the ceramic part are disclosed. A green body or non-sintered part may be formed using a casting or molding process. The green body may not be sintered or may be partially sintered before machining one or more features into a surface of the green body. After machining, the component may be fully sintered to create a hardened ceramic component.

A ceramic part and methods for making the ceramic part are disclosed. A green body or non-sintered part may be formed using a casting or molding process. The green body may not be sintered or may be partially sintered before machining one or more features into a surface of the green body. After machining, the component may be fully sintered to create a hardened ceramic component.

A super hard polycrystalline construction comprises a body of polycrystalline super hard material, said body having an exposed working surface, a substrate attached to the body of polycrystalline super hard material along an interface and a plurality of apertures or channels. One or more of said apertures or channels extend(s) from the exposed working surface of the body into the substrate.

A super hard polycrystalline construction comprises a body of polycrystalline super hard material, said body having an exposed working surface, a substrate attached to the body of polycrystalline super hard material along an interface and a plurality of apertures or channels. One or more of said apertures or channels extend(s) from the exposed working surface of the body into the substrate.

The present invention provides a method for making a metal-ceramic laminate heat-dissipating substrate, comprising the steps of: providing a metal base layer; forming a not-yet-sintered ceramic layer on a surface of the metal base layer; and forming a metal line on a surface of the not-yet-sintered ceramic layer, and then performing a sintering process. The method of the present invention for making the metal-ceramic laminate heat-dissipating substrate has the advantages of producing heat-dissipating substrate with high bonding strength between the metal lines and the ceramic layer, and lowering the material cost of the heat-dissipating substrate.

The present invention provides a method for making a metal-ceramic laminate heat-dissipating substrate, comprising the steps of: providing a metal base layer; forming a not-yet-sintered ceramic layer on a surface of the metal base layer; and forming a metal line on a surface of the not-yet-sintered ceramic layer, and then performing a sintering process. The method of the present invention for making the metal-ceramic laminate heat-dissipating substrate has the advantages of producing heat-dissipating substrate with high bonding strength between the metal lines and the ceramic layer, and lowering the material cost of the heat-dissipating substrate.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.