The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded,—the fibrous reinforcement comprising a first portion forming the leading edge and a second portion forming all or part of the trailing edge,—the strands of the fibrous reinforcement comprising first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.

A method of repairing a tip of an airfoil can comprise: removing a coating from the tip of the airfoil; preparing a repair area for bonding, the repair area including the tip and a portion of a concave side of the airfoil; applying an epoxy film and an abrasive component to the repair area; and bonding the epoxy film and the abrasive component to the repair area.

The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

An airfoil includes an airfoil section that has an airfoil wall that circumscribes an internal airfoil cavity and defines leading and trailing ends and pressure and suction sides. The airfoil wall is formed of a ceramic matrix composite (CMC) laminate comprised of fiber plies disposed in a ceramic matrix. The fiber plies include a skin fiber ply that defines an exterior of the airfoil section and at least one inner fiber ply that lines the skin fiber ply. At least one inner fiber ply locally terminates at one of the leading end or the trailing end such that the airfoil wall has fewer of the fiber plies in the leading end or the trailing end than in each of the pressure side and the suction side.

A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

A ducted fan turbine engine with a nacelle and a duct for a secondary flow. The nacelle comprises a fixed structure. A mobile cowl is able to move between a forward position and a backward position to define an opening between the duct and the outside. A plurality of rollers are mounted to freely rotate on the mobile cowl. For each roller there is a flexible screen with a first edge fixed to the roller and a second edge, in which the screen is able to adopt a furled position, wound around the roller, or a deployed position deployed across the duct. A deployment mechanism is arranged to move each second edge to move the screen from the furled position to the deployed position. A furling mechanism is arranged to drive each roller in rotation to move the associated screen from the deployed position to the furled position.

A blade including at least one web and a vane having a leading edge and a trailing edge, wherein, for at least one aerofoil of the vane in the vicinity of the web, a maximum sweep angle associated with a position along a chord of the aerofoil extending from the leading edge to the trailing edge of the vane corresponding to a relative chord length of at least 50%.

A manufacturing process of a fibrous preform for a composite material includes creating a fibrous texture by three-dimensional or multilayer weaving between a plurality of weft layers and warp layers, the fibrous texture including an extra-thick portion having a sacrificial portion and a useful portion adjacent to the sacrificial portion in the warp direction, the sacrificial portion, placing the fibrous texture in a forming toolset, shaping the fibrous texture so as to obtain a fibrous preform having a sacrificial portion and an adjacent useful portion, removing the sacrificial portion from the fibrous preform. When weaving the fibrous blank, one or more expansion elements are inserted into the weft layers located at the core of the sacrificial portion of the fibrous texture. Each expansion element has a cross-section greater than the cross-section or count of the weft threads or strands present in the useful portion.

The present invention includes an apparatus for protecting an aerodynamic surface from erosion including a screen capable of being applied to a leading edge of the aerodynamic surface; and an erosion protection coating applied to the screen before or after the screen is applied to the leading edge, wherein the erosion protection coating protects the aerodynamic surface from erosion.

The present disclosure relates to a variable stator vane and a method of fabricating the variable stator vane of a gas turbine engine. The method includes providing at least one fibre sheet. The method further includes rolling the at least one fibre sheet around a mandrel to form a spindle section of the variable stator vane. An excess of material of the at least one fibre sheet remains after forming the spindle section. The method further includes using the excess of material of the at least one fibre sheet to form the at least one aerofoil section of the variable stator vane.