An airfoil includes an airfoil body that has a trailing edge region. The trailing edge region includes first and second monolithic ceramic exterior walls, a flow discharge passage between the first and second monolithic ceramic exterior walls, a ceramic matrix composite (CMC) liner at least a portion of which is disposed in the flow discharge passage between the first and second monolithic ceramic exterior walls, and an array of pedestals disposed in the flow discharge passage. Each of the flow guides bridges the CMC liner and at least one of the first and second monolithic ceramic exterior walls.

A ceramic matrix composite gas turbine blade comprising a root portion coupled to a disk, said root portion having a neck; a platform region is disposed along an upper portion of the neck; an airfoil is located opposite the neck relative to the platform and extends outwardly from the platform; and a limiting section fuse formed in the blade proximate the neck.

The invention relates to a method for manufacturing a turbine engine blade from a preform (10) of composite material polymerised in a mould comprising a lower part (16) and an upper part, comprising at least one closure step, during which the upper part of said mould is placed on the lower part (16) of the mould containing the preform (10). The method comprises, prior to said closure step, at least one sub-step of inserting a position marker (28) into the preform (10), at least one sub-step of compacting the preform using an insert (34) intended to be received in the upper part of the mould (18), and at least one sub-step of checking the position of the marker (28) relative to a reference mark (30) of said insert (34).

The disclosure describes techniques for infiltrating a CMC substrate with a first slurry to at least partially fill at least some inner spaces of the CMC substrate, where the first slurry comprises first solid particles, drying the first slurry to form an infiltrated CMC including the first solid particles, depositing a second slurry including a carrier material and second solid particles on a surface of the infiltrated CMC, where the second solid particles comprise a plurality of fine ceramic particles, a plurality of coarse ceramic particles, and a plurality of diamond particles, drying the second slurry to form an article having an outer surface layer comprising the second solid particles on the infiltrated CMC, and infiltrating the article with a molten infiltrant to form a composite article.

An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.

The invention relates to sheath for a blade that has a uniform assembly direction over the radial height of the sheath whether the blade has a straight or curved trajectory. This is achieved by the a sheath formed around the edge, having a first inner surface wherein a first tangential vector projected tangentially to the first inner surface in a direction away from the head portion in an longitudinal plain forms a first angle with the rotational axis that does not vary over the radial height of the sheath while a second tangential vector projected tangentially from any point of the second inner surface of the sheath in a direction towards the head portion intersects the first tangential vector.

A component of a gas turbine engine comprises a substrate, a corrosion resistant top layer, and an intermediate corrodible layer disposed between the corrosion resistant top layer and the substrate. When corroding, the intermediate layer has a color contrasting with a color of the top layer. A method of detecting a crack when it penetrated the top layer in a component of a gas turbine engine having a corrosion resistant top layer and an intermediate corrodible layer comprises, in sequence, observing that at least one area of the component has a color contrasting with that of the top layer; determining that the color of the at least one area is a result of corrosion of the intermediate corrodible layer; and determining that the top layer has a crack as a result of determining corrosion of the intermediate layer. A method of facilitating crack detection in a component is also presented.

A vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the flange. There is a conformal thermal insulation blanket disposed on the flange.

A thermal boundary protection system including one or more carbon nanotubes for increased durability is disclosed. The thermal boundary protection system may include a bond coat applied on an outer surface of a base material, a thermal barrier coating applied on an outer surface of the bond coat, and a plurality of carbon nanotubes extending from the bond coat at least partially into the thermal barrier coating.

A method may include oxidizing a surface of a silicon-containing substrate to form a layer including silica on the surface of the silicon-containing substrate. The method also may include depositing, from a slurry including at least one rare earth oxide, a layer including the at least one rare earth oxide on the layer including silicon. The method additionally may include heating at least the layer including silica and the layer including the at least one rare earth oxide to cause the silica and the at least one rare earth oxide to react and form a layer including at least one rare earth silicate.