Assemblies are provided for an aircraft with a gas turbine engine. One assembly includes a body such as an inlet nose lip of a nacelle for the gas turbine engine. This assembly also includes a thermal management system that includes a duct, a regulator and a flow restrictor. The thermal management system is configured to direct a flow of bleed gas through the duct from the gas turbine engine to the body for substantially preventing ice buildup on the body. The regulator is configured to affect the flow of bleed gas downstream of the regulator. The flow restrictor is configured to selectively restrict the flow of bleed gas through the duct when a temperature of the flow of bleed gas is greater than a threshold temperature.

A method for manufacturing impellers is described. The method provides for manufacturing a plurality of tubular components, each tubular component forming an inner passage, which is shaped as one of the flow passages of the final impeller. The tubular components are assembled together forming a semi-finished impeller. The semi-finished impeller is provided with annular cavities extending around the rotation axis of the impeller and gaps between adjacent tubular components. The gaps and cavities are filled with metal powder and the semi-finished impeller is subject to hot isostatic pressing, to densify the metal powder and form a monolithic final impeller.

Various pumps capable of preventing distortion are disclosed. A casing of the pump comprises a metal member configured to have at least two sub metal members and a body. Here, the sub metal members are included in the body, and the body is formed of plastic.

The impeller (1) includes a main plate (3) formed from a metal plate; and vanes (5) each formed from a metal plate. Each of the vanes (5) has a three-dimensional portion (5A) having a surface inclined with respect to a rotation axis (CA) of the impeller (1) and a two-dimensional portion (5B) having a surface parallel to the rotation axis (CA) of the impeller (1), and the two-dimensional portion (5B) is fixed to the main plate (3) by a first weld (10) formed by projection welding.

A The 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.

A rolling bearing includes an inner ring, an outer ring, rolling elements, and a retainer that holds the rolling elements. The retainer includes a metal portion and a sliding resin portion The metal portion has communication holes each having a plurality of openings on the surface of the metal portion, and the sliding resin portion is disposed in the communication holes.

A method for manufacturing a stage of a steam turbine comprising the steps of milling a block of material to define a sector having a plurality of blades, each blade having an external surface; machining an opening in the external surface of at least one of the blades; machining a cavity in fluid communication with the opening; the step of machining the cavity being performed by wire electric discharge machining.

A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate.

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.

An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.