A method of manufacturing a gas turbine engine component (10) and the component so formed. The method includes: stacking a plurality of CMC layers (16) along a metal core (30) to form a stack of disconnected CMC layers, wherein adjacent edge faces (46) of the layers define a surface (44); additively depositing ceramic material (14) to only selected portions of the surface (44) to bond together at least some of the layers at their respective edge faces; and selecting locations for the depositing of the ceramic material to achieve a predetermined mechanical characteristic of the resulting component.

A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration.

A ceramic matrix composite seal is disclosed. The ceramic matrix composite seal including a ceramic matrix and a number of ceramic fiber fabrics embedded in the ceramic matrix. The ceramic matrix composite seal is formed into a strip with a desired geometry such that the seal strip is configured to be assembled with a number of components to create a seal between the components.

The invention relates to a coloured zirconia ceramic dental mill blank having fluorescing properties, processes of production such a mill blank and uses thereof, in particular for producing zirconia ceramic dental restorations.

The dental mill blank having a shape allowing the dental mill blank to be attached or fixed to a machining device, the dental mill blank comprising a porous zirconia material, the porous zirconia material comprising the oxides Zr oxide calculated as ZrO.sub.2: from about 80 to about 97 wt.-%, Al oxide calculated as Al.sub.2O.sub.3: from about 0 to about 0.15 wt.-%, Y oxide calculated as Y.sub.2O.sub.3: from about 1 to about 10 wt.-%, Bi oxide calculated as Bi.sub.2O.sub.3: from about 0.01 to about 0.20 wt.-%, Tb oxide calculated as Tb.sub.2O.sub.3: from about 0.01 to about 0.8 wt.-%, and optionally one or two of the following oxides: Er oxide calculated as Er.sub.2O.sub.3: from about 0.01 to about 3.0 wt.-%, Mn oxide calculated as MnO.sub.2: from about 0.0001 to about 0.08 wt.-%, wt.-% with respect to the weight of the porous zirconia material.

The disclosure describes techniques for forming a surface layer of an article including a CMC using a cast. In some examples, the surface layer includes three-dimensional surface features, which may increase adhesion between the CMC and a coating on the CMC. In some examples, the surface layer may include excess material, with or without three-dimensional surface features, which is on the CMC. The excess material may be machined to remove some of the excess material and facilitate conforming the article to dimensional tolerances, e.g., for fitting the article to another component. The excess material may reduce a likelihood that the CMC (e.g., reinforcement material in the CMC) is damaged by the machining.

A gas plug of the present disclosure is composed of a columnar porous composite in which a plurality of silicon compound phases containing silicon carbide as a main component are connected to each other via a silicon phase having silicon as a main component. The porous composite is housed inside a tubular body made from a dense ceramic.

A method of forming a ceramic matrix composite component according to an exemplary embodiment of this disclosure, among other possible things includes laying up plies of ceramic reinforcement material with sacrificial plies to form a preform, infiltrating the preform with a ceramic matrix material, and machining away the sacrificial plies to reveal a surface profile of the ceramic matrix composite component. A preform for a ceramic matrix composite component is also disclosed.

An article includes a ceramic matrix composite wall that defines at least a side of a passage. The ceramic wall includes a ceramic matrix composite flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. The ceramic matric composite of the wall comprises woven fibers that are dispersed in a ceramic body matrix. An airfoil and a gas turbine engine are also disclosed.

A method for manufacturing an electrostatic chuck with multiple chucking electrodes made of ceramic pieces using metallic aluminum as the joining. The aluminum may be placed between two pieces and the assembly may be heated in the range of 770 C to 1200 C. The joining atmosphere may be non-oxygenated. After joining the exclusions in the electrode pattern may be machined by also machining through one of the plate layers. The machined exclusion slots may then be filled with epoxy or other material. An electrostatic chuck or other structure manufactured according to such methods.

An electrolyte sheet for solid oxide fuel cells includes a ceramic plate body containing a cubic zirconia sintered material, wherein, with the ceramic plate body being defined to have nine portions including an outer peripheral portion and a central portion, ceramic grains in each of the nine portions have a median size D.sub.50 of 1.0 μm to 4.0 μm, and a maximum median size D.sub.50 of the ceramic grains among the nine portions is 1.0 to 1.3 times a minimum median size D.sub.50 of the ceramic grains among the nine portions.