A hybrid pump includes an impeller, a magnetic drive configured to control rotation of the impeller, a drive shaft combined with the magnetic drive and a motor. The drive shaft rotates in response to rotation of an axis of the motor, the magnetic drive rotates when the drive shaft rotates, the impeller rotates in response to rotation of the magnetic drive, a drive body of the magnetic drive is formed of plastic, and the drive shaft is formed of metal.

The invention relates to a turbomachine assembly (1) comprising a fan (2) and a booster drum-type part (3), the fan (2) comprising:—blades (20) comprising an airfoil (23) and an extension (30) mounted on and attached to the trailing edge (25) of the airfoil (23),—a fan (2) disc (10) and—a series of inter-blade platforms (16), the extension (30) of each blade (20) extending beyond the downstream face (14) of the fan (2) disc (10) in the direction of the upstream edge (4) of the part (3) and covering, at least partially, the cavity (6) between the fan (2) and the part (3).

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.

A nozzle comprises a combustion chamber having a downstream end and a divergent formed of a cone-shaped wall extending between an upstream end and a downstream end. The upstream end of the divergent is connected to the downstream end of the combustion chamber by an intermediate ring having an upstream flange fixed on a fixing flange secured to the combustion chamber and a downstream flange connected to the upstream end of the divergent. The intermediate ring having an inner channel present between the upstream and downstream flanges of the intermediate ring. A material able to take heat from the ring is present in the inner channel.

An electric pump includes a pump housing, a rotor assembly, a stator assembly, an isolation sleeve, a heat dissipation plate and an electric control board. The pump housing defines a pump inner chamber; the pump inner chamber is partitioned into a first cavity and a second cavity by the isolation sleeve; the rotor assembly is disposed in the first cavity; the stator assembly and the electric control board are disposed in the second cavity; the isolation sleeve comprises a bottom portion; at least a portion of the heat dissipation plate is disposed between the electric control board and the bottom portion; at least a portion of the bottom portion and at least a portion of the heat dissipation plate are in direct contact, or are filled with thermal silicone grease or thermal silica therebetween, or are provided with a thermal patch therebetween.

A fan adapted for being disposed in an electronic device is provided. The fan includes a hub and a plurality of metal blades respectively extending from the hub. Each of the metal blades has a root portion connected to the hub and an end portion away from the hub, and a mass of the end portion is greater than a mass of the root portion, such that the metal blade is elongated while the fan is rotated.

A rotor disk assembly for a gas turbine engine includes a rotor disk with a multiple of blade slots, the rotor disk defined about an axis; a sleeve received within each of the multiple of blade slots; and a ceramic matrix composite rotor blade received within each of the multiple of sleeves.

An airfoil of a gas turbine engine includes a leading edge and an opposed trailing edge defining a chord between the leading edge and the trailing edge, wherein the chord has a chord length. A concave surface is between the leading edge and the trailing edge, which includes a first portion proximal the leading edge of the airfoil and a second portion proximal the trailing edge of the airfoil, wherein the first portion of the concave surface includes about 10% to about 50% of the chord length. An erosion-resistant ceramic, cermet or intermetallic coating is on the second portion of the concave surface, which includes a coating leading edge pattern. The first portion of the concave surface is free of the erosion-resistant coating.

Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.