A support assembly for a load-bearing unit, a gas turbine engine including the support assembly, and a method of operation of the support assembly are provided. The support assembly includes a support element, a damper, and a variable stiffness member. The support element supports the load-bearing unit. The damper supports the support element and is configured to provide dampening of the load-bearing unit. The variable stiffness member is positioned between the damper and the load-bearing unit. The variable stiffness member is configured to provide a serial dampening of the load-bearing unit with the damper. The variable stiffness member includes a shape memory alloy.

The disclosure relates to an anti-cavitation device for impeding gas intrusion into oil dampers that support bearings and a rotating shaft. The oil film damper includes an annulus and a pair of piston rings between a structural support and the bearing housing. The piston rings define the axial boundaries of the oil filled annulus. An oil inlet between the pair of piston rings is in communication with a source of pressurized oil. An oil seal is axially spaced from each piston ring defining an annular oil filled reservoir external to each piston ring. The oil seal acts as a one way check valve to impede gas incursion into the oil reservoir and oil filled annulus.

Aspects of the disclosure are directed to an engine oil damper comprising: a bearing support, and a housing radially outward from the bearing support and co-axial with the bearing support, where at least one oil flow restrictor is formed with respect to at least one of the bearing support and the housing, where the at least one oil flow restrictor is configured to at least partially interrupt a flow of oil in an annulus radially defined between the bearing support and the housing.

A bearing assembly for a rotatable shaft, the bearing assembly comprising: a bearing housing; a bearing located within the bearing housing having an axis of rotation and arranged to receive a rotatable shaft; a first spring bar that couples the bearing to the bearing housing, the first spring bar being configured to tune vibrations of the rotatable shaft; and a first piezoelectric actuator disposed between the bearing housing and the first spring bar, the first piezoelectric actuator being configured to extend in a first direction, wherein extension of the piezoelectric actuator in the first direction displaces the first spring bar relative to the bearing housing.

The present invention provides a turbocharger including: a rotating shaft; a turbine wheel; a compressor wheel; a rolling bearing including an inner race fixed to an outer circumferential surface of the rotating shaft, an outer race surrounding the inner race from the outside in a radial direction, and rolling bodies arranged between the inner and outer races and that supports the rotating shaft to be rotatable about an axis; a housing that covers the rolling bearing from an outer circumferential side via a gap between the housing and an outer circumferential surface of the rolling bearing; and a lubricant supply line configured to supply a lubricant into the housing. The turbocharger includes an operating state detection unit that detects an operating state of the turbocharger and a lubricant regulating unit configured to regulate the flow rate of the lubricant flowing through the lubricant supply line depending on the operating state.

In a bearing device, a squeeze film damper includes an annular mass member disposed in a floating state between an outer periphery of an outer race and an inner periphery of a bearing retaining member, a first squeeze film damper part formed between the outer periphery of the outer race and an inner periphery of the annular mass member, and a second squeeze film damper part formed between an outer periphery of the annular mass member and the inner periphery of the bearing retaining member. Therefore, due to the floatingly supported annular mass member being eccentric with the opposite phase to a rotating shaft, which is eccentric and undergoes centrifugal whirling, an inertial force acting on the annular mass member counteracts the centrifugal force acting on the rotating shaft, thus enabling a damping effect to be exhibited.

A fluid damping structure is provided that includes a damper ring. The damper ring includes an annular body a plurality of fluid check valves, and at least one fluid stop. The annular body extends circumferentially around an axial centerline, and is defined by a first end surface, a second end surface, an outer radial surface, and an inner radial surface. The outer radial surface and the inner radial surface extend axially from the first end surface toward the second end surface. The body includes one or more check valve passages. Each check valve passage extends axially from an open end disposed at the first end surface inwardly toward the second end surface, and is disposed between the inner radial surface and the outer radial surface. An inlet aperture extends between each check valve passage and the outer radial surface, and an outlet aperture extends between each check valve passage and the inner radial surface. Each fluid check valve is disposed in a check valve passage. The at least one fluid stop is configured to prevent fluid exit from the open end of each check valve passage.

A seal assembly for a bearing compartment of a gas turbine engine includes a seal carrier, a seal element, a seal plate, and a trough. At least a portion of the seal element is within the seal carrier. The seal plate is in contact with the seal element and is configured to rotate relative to the seal element. The trough extends around the seal plate and comprises an annular channel positioned to capture oil slung from the seal plate.

The present invention provides a vehicle air compressor including a shaft provided with an impeller disposed at one side thereof and a runner disposed at the other side thereof, a motor configured to rotate the shaft, a trust bearing which supports the shaft in a longitudinal direction of the shaft and of which a surface is disposed adjacent to a surface of the runner, wherein a cooling hole for cooling air between the trust bearing and the runner is disposed in the trust bearing.

A bearing compartment for a gas turbine engine includes an engine static structure. A rotating structure is configured to rotate about an axis relative to the engine static structure. A bearing supports the rotating structure. A centering spring has first and second rings interconnected by axially extending circumferentially spaced beams. An aperture is provided between an adjacent pair of the beams. The first ring is mounted to the engine static structure. The bearing is mounted to the second ring. The first ring includes multiple circumferentially spaced lugs. Each of the lugs axially extend into a corresponding one of the apertures. The lugs include a support surface that engages the engine static structure.