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.

The present invention relates to a short carbon fiber-reinforced composite material, including a base material part and at least one sliding part contacting the base material part, in which each of the base material part and the sliding part has a plurality of short carbon fiber bundles in which at least a part thereof has been converted into SiC and a SiC matrix present among the plurality of short carbon fiber bundles, as constituent components, and the short carbon fiber bundles of the sliding part have a SiC conversion higher than that of the short carbon fiber bundles of the base material part.

An infiltratable material forms a net shape containing a porous network that can be infiltrated with a supplemental material, commonly referred to as an infiltrant, e.g., by heating the infiltrant so that it melts and wicks into the porous network of the net shape. By using additive fabrication technologies to spatially dispose an infiltrant about an infiltratable structure, a composite structure can be created that advantageously controls the amount of infiltrant applied to the infiltratable structure and the spatial distribution of the infiltrant about and/or within the infiltratable structure prior to infiltration.

A method for fabricating assemblies that includes providing a first component that further includes silicon carbide and that has an upper portion and a tapered lower portion; providing a second component that further includes silicon carbide and that has an upper portion that is adapted to receive the tapered lower portion of the first component; providing a predetermined amount of multiphase AlSi braze foil; grinding the AlSi braze foil into a powder; mixing a predetermined amount of braze paste binder with the AlSi powder to form a slurry; uniformly applying the slurry to the tapered lower portion of the first component; uniformly applying the slurry to the upper portion of the second component and inserting the tapered lower portion of the first component into the upper portion of the second component; and heating the applied slurry to a temperature of 725 C. to 1450 C. for a predetermined period of time.

A method of producing a ceramic matrix composite including a protective ceramic coating thereon comprises applying a surface slurry onto an outer surface of an impregnated fiber preform. The surface slurry includes particulate ceramic solids dispersed in a flowable preceramic polymer comprising silicon, and the impregnated fiber preform comprises a framework of ceramic fibers loaded with particulate matter. The flowable preceramic polymer is cured, thereby forming on the outer surface a composite layer comprising a cured preceramic polymer with the particulate ceramic solids dispersed therein. The cured preceramic polymer is then pyrolyzed to form a porous ceramic layer comprising silicon carbide, and the impregnated fiber preform and the porous ceramic layer are infiltrated with a molten material comprising silicon. After infiltration, the molten material is cooled to form a ceramic matrix composite body with a protective ceramic coating thereon.

The invention relates to a termination device of a tubular reactor comprising at least one separation element adapted for the separation of solid particles and gaseous effluents and at least one coupling element that is part of an end of said tubular reactor, said separation element being connected to said coupling element, characterized in that each element of the termination device is made of ceramic material. The invention also relates to a tubular reactor, having a vertical or substantially vertical axis, of a fluid catalytic cracking unit equipped with a termination device according to the invention and to a corresponding fluid catalytic cracking unit.

A ceramic centerbody (120) for an aircraft gas turbine engine. The ceramic centerbody (120) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure. The ceramic fiber and matrix are formed into a conical shape having a fore end (128) and an aft end (126). The centerbody includes a means for mechanical attachment (130) circumferentially oriented around the fore end of the centerbody. The fore end further includes additional plies oriented in a third preselected direction, thereby providing additional strength to for mechanical attachment.

There is a provided a copper-ceramic bonded body in which a copper member formed of copper or a copper alloy and a ceramic member formed of nitride ceramic are bonded to each other, in which an active element oxide layer containing an active element and oxygen is formed at bonding interfaces between the copper member and the ceramic member, and a thickness t of the active element oxide layer is in a range of 5 nm to 220 nm.

The present disclosure provides a method of manufacturing a composite sandwich panel having a core formed of a plurality of cells extending vertically between a first skin and a second skin. The method includes creating at least one first strip and a second strip from a temporary material, each strip having at least one cavity having a succession of aligned half-cells, lining the cavity of the first strip with a fibrous ply, assembling the first strip and the second strip by interlocking the cavity of the first strip with the cavity of the second strip and trapping the fibrous ply therebetween, and trimming excess temporary material of the entirety of the strips formed during the preceding assembly step so as to form a new cavity which forms a succession of aligned half-cells.

Process for the moderately refractory assembly of at least two articles made of silicon carbide-based materials by non-reactive brazing in an oxidizing atmosphere, in which the articles are placed in contact with a non-reactive brazing composition and the assembly formed by the articles and the brazing composition is heated in an oxidizing atmosphere at a brazing temperature sufficient to melt the brazing composition so as to form a moderately refractory joint, wherein the non-reactive brazing composition is a composition A composed of silica (SiO.sub.2), alumina (Al.sub.2O.sub.3) and calcium oxide (CaO), or alternatively a composition B composed of alumina (Al.sub.2O.sub.3), calcium oxide (Cao) and magnesium oxide (MgO). Brazing suspension, paste comprising a powder of said brazing composition and an organic binder. Refractory joint and assembly.