A cermet and/or ceramic multi-coloured article, and in particular a bezel (1) of a timepiece, produced by a method for compressing at least two materials (2, 3) of distinct colours, the article including a relief decoration (8) of a different colour from the rest of the article, the decoration (8) being produced by laser ablation on one of the materials (3) after compression of the two materials (2, 3).

A honeycomb body having a cutout, an assembly including the honeycomb body, and a method of manufacturing. The method includes forming the honeycomb body having a matrix of intersecting walls that define a plurality of cells and channels extending longitudinally through the honeycomb body. A subset of the channels are plugged to create a plurality of plugged cells in a reinforcement region of the honeycomb body. Material is removed from the honeycomb body within the reinforcement region in accordance with a peripheral shape that passes through the plugged cells to form a cutout that extends an axial depth into the honeycomb body.

A sump for a toilet includes a first end of the sump, defined by a first boundary, and a second end of the sump, defined by a second boundary. The sump includes a channel running from the first end of the sump to the second end of the sump defined by a sump surface. The first end of the sump is configured to receive liquid and the second end of the sump is configured to supply liquid. The sump has a sump can-cut diameter corresponding to a diameter of the channel at the first end of the sump, a sump side radius extending from a center of the channel to an inner surface of the channel, and a sump depth corresponding to a largest vertical distance within the channel. The sump may be drain cast using a single continuous pathway.

A bottom face processing method of a pillar-shaped honeycomb structure including steps of: preparing a pillar-shaped honeycomb structure including a plurality of first cells which extend in parallel with each other from a first bottom face to a second bottom face, and each of which is opened in the first bottom face and has a protruding plugged portion in the second bottom face, and a plurality of second cells each of which is adjacent to at least one of the first cells with a partition wall interposed therebetween, which extend in parallel with each other from the first bottom face to the second bottom face, and each of which has a protruding plugged portion in the first bottom face, and is opened in the second bottom face; and removing the protruding portion from the plugged portion of each of the first cells and the second cells of the pillar-shaped honeycomb structure.

A bottom face processing method of a pillar-shaped honeycomb structure including steps of: preparing a pillar-shaped honeycomb structure including a plurality of first cells which extend in parallel with each other from a first bottom face to a second bottom face, and each of which is opened in the first bottom face and has a protruding plugged portion in the second bottom face, and a plurality of second cells each of which is adjacent to at least one of the first cells with a partition wall interposed therebetween, which extend in parallel with each other from the first bottom face to the second bottom face, and each of which has a protruding plugged portion in the first bottom face, and is opened in the second bottom face; and removing the protruding portion from the plugged portion of each of the first cells and the second cells of the pillar-shaped honeycomb structure.

An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.

A method of providing datum features on a ceramic article including the steps of providing a ceramic member having a plurality of substantially parallel holes extending into the ceramic member. Providing a plurality of tubular mounts, the cross-sectional area of each tubular mount being less than the cross-sectional area of the corresponding hole. Applying adhesive to the exterior surface of each one of the tubular mounts and inserting an adhesive covered tubular mount into each one of the holes. Providing a fixture member having a plurality of substantially parallel projections extending from predetermined positions. Positioning the ceramic member on the fixture member such that each projection locates in one of the tubular mounts and fixes the tubular mounts at the predetermined positions. The ceramic article may be removed from the fixture member or located in a machine tool using the fixture member and machining the ceramic article.

A method of providing datum features on a ceramic article including the steps of providing a ceramic member having a plurality of substantially parallel holes extending into the ceramic member. Providing a plurality of tubular mounts, the cross-sectional area of each tubular mount being less than the cross-sectional area of the corresponding hole. Applying adhesive to the exterior surface of each one of the tubular mounts and inserting an adhesive covered tubular mount into each one of the holes. Providing a fixture member having a plurality of substantially parallel projections extending from predetermined positions. Positioning the ceramic member on the fixture member such that each projection locates in one of the tubular mounts and fixes the tubular mounts at the predetermined positions. The ceramic article may be removed from the fixture member or located in a machine tool using the fixture member and machining the ceramic article.

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.