A bearing for holding a rotary conversion tool (10, 11) that includes two end rolling bearing devices (26, 28), at least one intermediate rolling bearing device (27) interposed between the end rolling bearing devices (26, 28), the end and intermediate rolling bearing devices (26, 27, 28) being intended to engage with an end (10a, 10b, 11a, 11b) of the rotary tool (10, 11), and at least one mechanical actuator (32, 33) configured to exert a radial preload force (Fo, Fo′) at the intermediate rolling bearing device (27).

A bearing for holding a rotary conversion tool (10, 11) that includes two end rolling bearing devices (26, 28), at least one intermediate rolling bearing device (27) interposed between the end rolling bearing devices (26, 28), the end and intermediate rolling bearing devices (26, 27, 28) being intended to engage with an end (10a, 10b, 11a, 11b) of the rotary tool (10, 11), and at least one mechanical actuator (32, 33) configured to exert a radial preload force (Fo, Fo′) at the intermediate rolling bearing device (27).

A bearing assembly includes at least two bearings each having an inner ring and outer ring, the inner rings being mounted on a shaft, and a balancing piston being disposed between the two bearings. The balancing piston includes a first part and a second part, the first and second parts each contacting the outer rings of the two bearings in an axial direction. The balancing piston further includes an inlet for directing a pressure fluid between the first and second parts to provide pressure to the first and second parts such that the balancing piston adjusts or exerts axial force on at least one of the two bearings. The balancing piston includes an outlet for directing the pressure fluid to lubricate at least one of the two bearings. Also, the outer diameter of the balancing piston is greater than the outer diameter of the outer rings of the two bearings.

A drive train for an electric machine is provided. The drive train includes a shaft. The shaft has a front end and a rear end and which is supported in a housing via a front bearing and a rear bearing, wherein the front bearing including a front bearing outer ring and a front bearing inner ring, and the rear bearing including a rear bearing outer ring and a rear bearing inner ring). The drive train includes a first cover mounted to the housing and being configured to seal a rear side of the front bearing, wherein the first cover is mounted to the housing by an auxiliary support which connects the first cover to the housing, a second cover mounted to the housing and being configured to seal a front side of the rear bearing, a third cover mounted to the housing and being configured to seal the rear bearing.

A method of operating a gas turbine engine of a multi-engine aircraft is disclosed, where the gas turbine engine has an engine shaft mounted for rotation in a bearing of a bearing assembly. The method comprises limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.

A method of operating a gas turbine engine of a multi-engine aircraft is disclosed, where the gas turbine engine has an engine shaft mounted for rotation in a bearing of a bearing assembly. The method comprises limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.

An electromechanical servo steering system with an electric servomotor having a motor shaft that drives a shaft which cogs with a helical gear. The shaft is arranged in a transmission housing and is mounted rotatably about an axis of rotation at its end near the motor in a bearing arrangement and is mounted pivotably in the transmission housing about a pivot axis which lies transverse to the axis of rotation. At least one spring element is provided which axial pretensions a bearing element that is pivotably movable with the shaft about the pivot axis, of the bearing arrangement in a spring-elastic manner against a bearing element that is arranged in a stationary manner in the transmission housing, of the bearing arrangement, wherein precisely two spring elements are provided which are arranged oppositely in the circumferential direction of the bearing arrangement.

An active wheel suspension element has a ball screw drive having a screw drive with a threaded spindle and a spindle nut which is mounted in a housing via an axial bearing. The axial bearing is formed as a rolling bearing, whose rolling element rolls directly on the spindle nut.

A method of operating a gas turbine engine of a multi-engine aircraft is disclosed, where the gas turbine engine has an engine shaft mounted for rotation in a bearing of a bearing assembly. The method comprises limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.

A method of operating a gas turbine engine of a multi-engine aircraft is disclosed, where the gas turbine engine has an engine shaft mounted for rotation in a bearing of a bearing assembly. The method comprises limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.