This composite-material blade formed by using a fiber-reinforced resin containing a resin and reinforcing fibers is provided with: a base material part provided on the inner surface of the composite-material blade; and a first cover part for covering the outer surface of the base material part. The base material part is formed by using a carbon fiber-reinforced resin containing a first resin and carbon fibers. The first cover part is formed from an elastic polymer fiber-reinforced resin containing a second resin and elastic polymer fibers, and has more resistance to impact than the base material part.

A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness. The fusible mount is arranged to break when a predetermined load is applied. The rigid electrical raft may be attached to a fan case of the engine, and the predetermined load may be that which results from a fan blade being released from the hub. This ensures that the rigid electrical raft is protected from the load.

An inlet for an aircraft nacelle may comprise a nanoreinforced polyimide composite lip skin. The nanomaterials may increase thermal conductivity and decrease microcracking in the lip skin. A lip skin for an inlet with an electric heater may comprise a surface layer, an outer composite skin, an electric heater, an inner composite skin, and a thermal barrier coating. A lip skin for an inlet with a pneumatic deicing system may comprise a surface layer, a composite skin, and a thermal barrier coating.

A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing ling edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.

A turbofan having a dilution rate of at least 10 and including a fan having a disc provided with blades at the periphery thereof, a distance between the head of the blades and the housing of the fan being less than or equal to ten millimeters; a primary flow space and secondary flow space that are concentric; a turbine, housed in the primary flow space and in fluid communication with the fan; and a reduction mechanism coupling the turbine and the fan.

The coupling can have a female member configured to rotate around an axis, defining an axial recess, and having a plurality of connections circumferentially arranged along a radially inner face; a male member extending inside the axial recess concentrically to the female member and having a plurality of connections circumferentially arranged along a radially outer face; and a plurality of circumferentially arranged links, each link having an inner end engaged with a corresponding one of the male member connections, and an outer end engaged with a corresponding female member connection, the links being slanted off the radial orientation, with the inner end being circumferentially offset from the outer end, the links subjected to compression when transmitting torque between the female member and male member.

A hybrid vane for a gas turbine engine. The hybrid vane comprises an airfoil having an inner core composed of a fiber-reinforced thermoplastic composite. A longitudinal axis of the hybrid vane extends between a vane root and a vane tip. The hybrid vane further comprises a metallic outer layer at least partially covering the inner core.

The coupling can have a female member configured to rotate around an axis, defining an axial recess, and having a plurality of connections circumferentially arranged along a radially inner face; a male member extending inside the axial recess concentrically to the female member and having a plurality of connections circumferentially arranged along a radially outer face; and a plurality of circumferentially arranged links, each link having an inner end engaged with a corresponding one of the male member connections, and an outer end engaged with a corresponding female member connection, the links being slanted off the radial orientation, with the inner end being circumferentially offset from the outer end, the links subjected to compression when transmitting torque between the female member and male member.

The present disclosure relates to a method of manufacturing an aerofoil structure for a gas turbine engine, wherein the aerofoil structure includes a root configured to be received in a rotor disc of the gas turbine engine, the method including: providing a pre-moulded polymer insert; adding the polymer insert into a mould for forming the aerofoil structure; adding a composite constituent into the mould; and heating the composite constituent in the mould to bond the polymer insert to the composite constituent, the polymer insert being provided at a shoulder of the aerofoil structure root. The composite constituent is pre-impregnated with a resin and heating the composite constituent in the mould thermosets the resin. Heating the composite constituent in the mould to bond the polymer insert to the composite constituent forms an intermediate part and the method further comprises machining the intermediate part to remove excess material and form the aerofoil structure.