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 that has a plurality of turbine vanes. Each of the turbine vanes includes inner and outer platforms and an airfoil section that extends there between. The airfoil section is hollow and rib-less and has a first end at the outer platform and a second end at the inner platform. The airfoil section is tangentially bowed from the first end to the second end with a radius of curvature that is from 17 centimeters to 130 centimeters.

A gas turbine engine includes a turbine section that has a plurality of turbine vanes. Each of the turbine vanes includes inner and outer platforms and an airfoil section that extends there between. The airfoil section is hollow and rib-less and has a first end at the outer platform and a second end at the inner platform. The airfoil section is tangentially bowed from the first end to the second end with a radius of curvature that is from 17 centimeters to 130 centimeters.

The present invention relates to a blade comprising: - a structure made of composite material; - a blade root attachment part comprising a wall delimiting a cavity, a first opening formed in the wall and a second opening located under the blade root portion, the structure made of composite material extending through the first opening; - two locking parts configured to axially abut against a shoulder of the attachment part and to bear against the blade root portion; and - a cover for compressing the blade root portion against the locking parts.

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

An assembly for a gas turbine engine according to an example of the present disclosure includes at least one platform having a main body extending between a first mate face and a second mate face to establish a gas path surface. The main body has an internal passage extending circumferentially between a first opening along the first mate face and a second opening along the second mate face relative to an assembly axis. A perimeter of the first mate face establishes a first area, a perimeter of the second opening establishes a second area, and the second area is greater than the first area. An airfoil section extends radially from the at least one platform.

In one aspect, an article comprises a substrate that comprises a ceramic matrix composite; and a metal oxide layer disposed on the substrate; where the metal oxide layer has a marking etched into the metal oxide via laser ablation. The markings include alphabets, numbers, symbols, bar codes, matrix bar codes, quick response codes, or a combination thereof. Disclosed herein too is a method comprising disposing upon a ceramic matrix composite a metal oxide layer; and laser ablating the metal oxide layer to etch the metal oxide layer. The etchings produce markings that comprise alphabets, numbers, symbols, bar codes, matrix bar codes, quick response codes, or a combination thereof.

A method for processing a component is provided and includes masking a first portion of the component with a maskant. The maskant includes a slurry having a plurality of particles in a fluid carrier. The plurality of particles comprises at least one of silicon, carbon, one or more rare earth disilicates, monosilicates or oxides, and combinations thereof. The method includes depositing a silicon-based coating on a second portion of the component via a chemical vapor deposition process and removing the maskant and any overlying silicon-based coating from the first portion of the component.

A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.