An airfoil includes a ceramic matrix composite airfoil core that defines an airfoil portion and a root portion. The ceramic matrix composite airfoil core is subject to core thermal growth. A platform includes a ceramic matrix composite that wraps around the root portion. The platform is subject to platform thermal growth. A buffer layer is located between the root portion and the platform. The buffer layer absorbs a mismatch between the core thermal growth and the platform thermal growth.

An airfoil includes a ceramic matrix composite airfoil core that defines an airfoil portion and a root portion. The ceramic matrix composite airfoil core is subject to core thermal growth. A platform includes a ceramic matrix composite that wraps around the root portion. The platform is subject to platform thermal growth. A buffer layer is located between the root portion and the platform. The buffer layer absorbs a mismatch between the core thermal growth and the platform thermal growth.

A ceramic substrate includes a substrate main body, and a conductor layer provided inside of the substrate main body. The substrate main body includes an insulator layer that is ceramics composed of aluminum oxide, and a composite oxide layer of aluminum and silicon, the composite oxide layer being formed between the insulator layer and the conductor layer.

A method of making a scintillator material includes forming a dried ceramic composition into a ceramic body with a garnet crystal formula (Gd.sub.3-x-zY.sub.x)Ce.sub.z(Ga.sub.5-yAl.sub.y)O.sub.12, where x is about 0 to about 2, y is about 0 to about 5, and z is about 0.001 to about 1.0. The ceramic body is sintered to form a sintered ceramic body. The sintered ceramic body is surrounded by a powder mixture that includes a garnet powder. The density of the sintered ceramic body is increased by applying an increased temperature and isostatic pressure to form the scintillator material.

A coating fabrication method includes providing engineered granules and thermally consolidating the engineered granules on a substrate to form a silicate-resistant barrier coating. Each of the engineered granules is an aggregate of at least one refractory matrix region and at least one calcium aluminosilicate additive region (CAS additive region) attached with the at least one refractory matrix region. In the thermal consolidation, the refractory matrix region from the engineered granules form grains of a refractory matrix of the silicate-resistant barrier coating and the CAS additive region from the engineered granules form CAS additives that are dispersed in grain boundaries between the grains.

A method of protecting a carbon-containing composite material part against oxidation, includes applying a first coating composition in the form of an aqueous suspension on an outside surface of the part, the first coating composition including a metallic phosphate; a powder of an ingredient comprising titanium; and a powder of B.sub.4C; subjecting the applied first coating composition to heat treatment in order to obtain a first coating on the outside surface of the part; applying a second coating composition on the first coating composition, the second coating composition including an aqueous suspension of colloidal silica; a powder of borosilicate glass; and a powder of TiB.sub.2; and subjecting the applied second coating composition to second heat treatment in order to obtain a second coating on the first coating.

A method of protecting a carbon-containing composite material part against oxidation, includes applying a first coating composition in the form of an aqueous suspension on an outside surface of the part, the first coating composition including a metallic phosphate; a powder of an ingredient comprising titanium; and a powder of B.sub.4C; subjecting the applied first coating composition to heat treatment in order to obtain a first coating on the outside surface of the part; applying a second coating composition on the first coating composition, the second coating composition including an aqueous suspension of colloidal silica; a powder of borosilicate glass; and a powder of TiB.sub.2; and subjecting the applied second coating composition to second heat treatment in order to obtain a second coating on the first coating.

There is provided a group III nitride laminate, including: a substrate comprised of silicon carbide; a first layer comprised of aluminum nitride and formed on the substrate; a second layer comprised of gallium nitride and formed on the first layer; and a third layer formed on the second layer and comprised of group III nitride having an electron affinity lower than that of the gallium nitride which is comprised in the second layer, the second layer having a thickness of less than 500 nm, the second layer containing iron at a concentration of less than 1-10.sup.17/cm.sup.3, and the second layer containing carbon at a concentration of less than 110.sup.17/cm.sup.3.

A method of applying a circumferential coating material on a circumferential surface of a ceramic honeycomb structure to form a circumferential coat layer. The method includes vertically aligning the longitudinal axis of the ceramic honeycomb structure, rotating the ceramic honeycomb structure around the vertically-aligned longitudinal axis, and applying the circumferential coating material on the circumferential surface of the rotating honeycomb structure at a discharge speed of 50 to 120 mm/s, calculated by
Discharge speed V [mm/s]=Supplied amount q [g/s] of circumferential coating material(Density [g/mm.sup.3] of circumferential coating materialArea S [mm.sup.2] of discharge opening).

The invention relates to a method for producing a friction lining material as well as a friction lining material having a porous body, whose pores are filled with a filling material, said porous body being formed on the basis of petroleum coke.