A compressor according to an embodiment includes: a rotational shaft provided with a compressor impeller on one end side; a rolling bearing device for rotatably supporting the rotational shaft; and a housing for housing the rolling bearing device. The rolling bearing device includes: an inner ring mounted on the rotational shaft; an outer ring supported by the housing with application of a load from the housing in an axial direction of the rotational shaft; a rolling element disposed between the inner ring and the outer ring; an elastic member disposed on an outer circumferential side of the outer ring so as to come into contact with the housing; and a sliding portion disposed on one end side of the outer ring in the axial direction so as to come into contact with the housing.

A method of sealing one or more openings provided in a wall of an aerofoil for a gas turbine engine, the aerofoil comprising at least one cavity which is at least partly filled with a vibration damping material, the method comprising steps to provide a metallic material onto the wall of the aerofoil in order to cover the opening and bond the metallic material to the wall of the aerofoil to seal the opening.

A stator assembly for a gas turbine engine includes an arcuate outer shroud, an arcuate inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat. A stator and case assembly includes a case defining a working fluid flowpath and a stator assembly positioned at the case. The stator assembly includes a plurality of stator segments arranged circumferentially about an engine axis, each stator segment including an arcuate outer shroud secured to the case, an arcuate inner shroud, and a plurality of stator vanes extending from the outer to inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat.

A stator assembly for a gas turbine engine includes an annular outer shroud, an annular inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat. A stator and case assembly for a gas turbine engine includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly located at the case. The stator assembly includes an annular outer shroud secured to the case, an annular inner shroud secured to the case and a plurality of stator vanes extending from the outer to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat.

A component is provided for a turbine engine. The component can include an airfoil defining a surface, and an energy absorbing composite positioned on the surface of the airfoil or within the airfoil. The energy absorbing composite includes a shear thickening fluid distributed through a matrix.

An e-charger includes a motor case that encases the motor and an outer housing that houses the motor case. The e-charger additionally includes a cooling system with passages cooperatively defined by the outer housing and the motor case. First and second longitudinal passages extend between the first and second ends of the motor, and a second longitudinal passage extends between the second and first ends of the motor. The end passage fluidly connects the first and second longitudinal passage. The cooling system is configured for directing flow of the coolant from the inlet, through the first longitudinal passage in a first longitudinal direction with respect to the axis, through the end passage, and back through the second longitudinal passage in a second longitudinal direction with respect to the axis.

A turbomachine blade system, in particular for a compressor or turbine stage of a gas turbine, which includes at least one blade, in particular a moving or guide blade, and at least one moving body for reducing the vibrations of this blade, at least one area of a guide for guiding the body and/or at least one area of a supporting structure for resiliently mounting the body and/or at least one area of the body being or becoming generatively manufactured together with at least one area of the blade, in particular of a vane and/or blade root and/or a shroud situated thereon.

A mechanical assembly for a vehicle (10), in particular a motor vehicle, comprises a rotating element (18), a support Got (20) for the rotating element (18), and a cover (22) attached on the support (20) for the rotating element (18). The cover (22) has at least one edge (50) attached on the support (20) for the rotating element (18) and a bottom (52) extending substantially in a plane. The N bottom (52) is at least partially covered by elastomer material (58).

A rotor blade system includes a rotor, a casing radially spaced apart from the rotor, and a plurality of blades coupled to the rotor and positioned between the rotor and the casing. The one or more of the plurality of blades have a radial length different from a remaining one or more of the plurality of blades so as to vary a tip gap between a tip of the one or more of the plurality of blades and the casing to break up a frequency content of a leakage vortex at the tip to modify natural frequencies of the plurality of blades and mode shapes to reduce or substantially eliminate flutter.

Some embodiments of the present disclosure provides a head shaking device and a fan. The head shaking device includes a fixing assembly; and a rotating assembly, which rotates relative to the fixing assembly in a reciprocating manner, wherein one of the fixing assembly and the rotating assembly includes at least one first connecting structure, the other includes at least one second connecting structure, and the first connecting structure is rotatably clamped with the second connecting structure.