A method for forming a ceramic matrix composite component includes forming a fibrous preform of the component with a plurality of fiber layers and a fill region disposed between one or more of the plurality of fiber layers. Ceramic particles are provided in the fill region, which is densified using chemical vapor infiltration.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.

An airfoil assembly includes first and second fiber-reinforced composite airfoil rings each having inner and outer platform sections. A sealing shelf extends from a suction side wall of one of the first and second fiber-reinforced composite airfoil rings, and towards the pressure side wall of the other of the rings. A first seal is captured radially inwardly of the sealing shelves on outer platforms of each of the first and second fiber-reinforced composite airfoil rings. A second seal is captured inward of the sealing shelves on the inner platforms of each of the first and second fiber-reinforced composite rings to provide a seal between the respective first and second fiber-reinforced composite airfoil rings, and a captured internal component. A gas turbine engine is also disclosed.

A turbine assembly for use with a gas turbine engine includes a bladed wheel assembly and a vane assembly. The bladed wheel assembly is adapted to interact with gases flowing through a gas path of the gas turbine engine. The vane assembly is located upstream of the bladed wheel assembly and adapted to direct the gases at the bladed wheel assembly.

A vane arc segment includes an airfoil piece that defines first and second platforms and a airfoil section that extends between the first and second platforms. The airfoil section has a trailing edge, a leading edge, a pressure side, and a suction side. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Each radial flange extends continuously and includes a first leg portion that extends adjacent the trailing edge, a second leg portion that extends from the first leg portion and curves around the suction side, and a third leg portion that extends from the second leg portion toward the forward side.

An airfoil for a gas turbine engine includes a fiber-reinforced laminate composite airfoil fairing that defines a platform that has first and second radial sides, an airfoil section that extends off of the first radial side, and a branched flange that extends off of the second radial side. The branched flange includes a trunk that radially extends off of the second radial side and at least one branch that extends off of the trunk.

A method for manufacturing a metal bladed wheel of a turbomachine reinforced by an insert made of metal matrix composite material, includes winding the ceramic fibers around a mandrel in order to form the insert, the ceramic fibers being surrounded by a material constituting the matrix; and spark plasma sintering the insert with a powder of metal constituting the bladed wheel to be manufactured.

A coated component, along with methods of its formation, are provided. The coated component may include a ceramic matrix composite substrate comprising silicon carbide and having a surface, a bond coat on the surface of the substrate, and an environmental barrier coating on the bond coat. The bond coat includes a plurality of discrete particles dispersed within a matrix phase, with the matrix phase formed from mullite and defining 60% to 98% by volume of the bond coat. The plurality of discrete particles include an oxygen getter and has 50% of its volume or greater formed from particles having an average size of 10 μm to 100 μm.

A gas turbine engine includes a turbine section disposed about an engine axis. The turbine section includes inner and outer diameter ceramic support rings that define a gaspath there between. Each of the inner and outer diameter ceramic support rings is monolithic and continuous. Ceramic vane arc segments are disposed in the gaspath and supported by the inner and outer diameter ceramic support rings. Each of the ceramic vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter ceramic support ring with the ceramic vane arc segments to retain the ceramic vane arc segments between the inner and outer diameter ceramic support rings.

Disclosed is a coated composite comprising a seal coat disposed on a composite material wherein the seal coat comprises protective particles and a matrix.