A combination of a component and a composite, the composite having a) a PMC layer, and b) a tile layer comprising a plurality of Ox/Ox CMC tiles, each tile having: i) a central portion, ii) an outer portion and iii) one or more overlap joints formed by the overlapping of the outer portions of adjoining tiles so that hot gases entering a smooth top surface of the tile layer between abutting outer and central periphery segments must travel laterally between the overlapping outer portions of adjoining tiles to reach a top surface of the PMC layer. A method of heat shielding a component with a heat shielding composite comprising a) providing the composite and b) applying the composite to a surface of the component.

A nuclear reactor fuel rod is a fuel rod for a light-water reactor. The nuclear reactor fuel rod includes a fuel cladding tube and an end plug, both of which are formed of a silicon carbide material. A bonding portion between the fuel cladding tube and the end plug is formed by brazing with a predetermined metal bonding material interposed, and/or by diffusion bonding. The predetermined metal bonding material has a solidus temperature of 1200 C. or higher. An outer surface of the bonding portion, and a portion of an outer surface of the fuel cladding tube and the end plug, which is adjacent to the outer surface of the bonding portion are covered by bonding-portion coating formed of a predetermined coating metal. The predetermined metal bonding material and the predetermined coating metal have an average linear expansion coefficient which is less than 10 ppm/K.

CMC articles and methods for forming CMC articles are provided. In one example aspect, a method for forming a CMC article includes forming a CMC preform defining a first section and a second section. The first section has one or more plies that include sacrificial fibers. The second section of the CMC preform does not include sacrificial fibers. The first and second sections can be laid up to form the CMC prior to thermally processing, e.g., consolidation, firing, and infiltration. When the CMC preform is fired or burned out, the sacrificial fibers are removed or decomposed resulting in formation of channels within the first section of the pyrolyzed CMC preform. The channels are used as gas transport paths during chemical vapor infiltration to facilitate infiltration of a gaseous infiltrant into the fired CMC preform. The channels are then backfilled with a liquid infiltrant during a melt infiltration process.

The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.

A blade outer air seal includes a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall is axially spaced from a second wall. The first and second walls extend from the base portion. An outer wall joins the first and second walls. The outer wall has a first edge and a second edge. Each of the edges have a first portion and a second portion arranged at a first angle relative to the first portion.

A turbine engine component may comprise a Ceramic Matrix Composite (CMC) structure including a plurality of nominally dense plies, wherein each of the plurality of the nominally dense plies are bonded by at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS), or a localized heating at a bonding interface. The turbine engine component may include an airfoil extending between a first platform and a second platform, wherein the airfoil, the first platform, and the second platform define the CMC structure.

A blade outer air seal includes a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall is axially spaced from a second wall. The first and second walls extend from the base portion to an outer wall. A rib extends from the base portion to the outer wall and spaced axially between the first and second walls.

A ceramic matrix composite article includes a chemical vapor infiltration ceramic matrix composite base portion including ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon. The ceramic matrix composite article further includes a melt infiltration ceramic matrix composite covering portion including a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion.

A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.