An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.

A breathing assistance apparatus has a pressurised gases source featuring a lightweight impeller with a plastic shaft. The impeller is shroudless. The plastic shaft is supported within the stator by a bearing structure. The resilient motor mount couples the stator and the housing and provides compliance and/or damping for the motor.

A process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.

A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

A submersible pump assembly includes an electric motor (1) and a centrifugal pump, which is driven by the electric motor (1). A rotor (4) formed of plastic or composite material which is manufactured in the extrusion or pultrusion method.

A water pump with an impeller driven by an electrical machine comprising a housing cap and a volute with an inlet) and an outlet and a boot hosting a stator and a rotor of the electrical machine, wherein the rotor is mounted on a fixed shaft in the water pump having a bushing rotatable mounted on the shaft.

A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abrasive filler between about 50%-75% by volume of the abrasive coating.

A centrifugal compressor (P) is provided with: a casing (10) which forms an impeller inlet flow path (11), an impeller flow path (12), an impeller outlet flow path (13), and a scroll (14); and an impeller (3) which is arranged in the impeller flow path (11), wherein the casing (10) is provided with a casing body (15) and a heat conduction inhibiting part (16) which is disposed to heat conduction paths to the impeller inlet flow path (11) from at least the impeller outlet flow path (13) and the scroll (14) so as to inhibit heat conduction to the impeller inlet flow path (11) from at least the impeller outlet flow path (13) and the scroll (14).

A polymer airfoil assembly is disclosed and includes at least one cooling passage for circulating coolant to remove heat from the polymer airfoil portion.

A vane for a turbine engine includes a body in the form of an aerodynamic profile formed by a shell produced from a composite material formed from a three-dimensional textile of reinforcement fibres consolidated by a hardened resin. The shell forms a pressure surface and a suction surface of the vane connected to each other while forming on one side a leading edge and on the opposite side a trailing edge of the vane, and a core including a core body surrounded by the shell. The core is produced from non-porous plastics material, and the core body is in the form of an aerodynamic profile and delimits at least one closed cavity of the core.