A damper bearing includes: a bearing portion that supports a rotary shaft; and a tubular portion located around an outer circumference of the bearing portion, the tubular portion having a predetermined radial thickness and having an outer surface attachable to a structural member, wherein the bearing portion is configured as a hydrostatic bearing that supports the rotary shaft with a predetermined bearing clearance between the hydrostatic bearing and the rotary shaft, the tubular portion includes a plurality of planar slits located between the outer surface of the tubular portion and an inner surface of the tubular portion, each planar slit having a predetermined width, extending circumferentially, and further extending through an entire axial length of the tubular portion, the planar slits are arranged circumferentially at predetermined intervals in the tubular portion, each planar slit has an open end at the outer surface of the tubular portion, extends radially from the open end, and extends circumferentially in an arc to a predetermined point in a region between the outer surface and the inner surface, and the tubular portion includes a bearing fluid supply hole formed in a region where none of the planar slits is situated, the bearing fluid supply hole extending from the outer surface of the tubular portion to the bearing portion without passing through any of the planar slits. The damper bearing thus configured can be used as a bearing for a small machine and exhibit a damper function to damp vibration transmitted from the rotary shaft of the machine.

A damper assembly includes a bearing assembly including a radially outer surface. A housing surrounds the bearing assembly and includes a radially inner surface facing the radially outer surface. The radially outer and inner surfaces define a plurality of annuli therebetween. The damper assembly further includes a plurality of fluid supplies coupled in flow communication with the plurality of annuli and configured to deliver a fluid to each annulus of the plurality of annuli. Each fluid supply of the plurality of fluid supplies independently controls the fluid within the respective annulus.

An oil supply assembly for a bearing damper of a gas turbine engine includes an oil supply tube configured to supply oil in a first direction. The assembly also includes a bearing support having a bearing damper path connecting the bearing damper to the oil supply tube and a bearing compartment path connecting a bearing compartment to the oil supply tube. The assembly also includes a check valve disposed within the bearing damper path and configured to allow fluid communication in the first direction from the oil supply tube to the bearing damper and block fluid communication in a second direction opposite the first direction.

A bearing structure of a turbocharger includes a rotor shaft, a ball bearing, and a housing. An inner ring of the ball bearing has the rotor shaft inserted therein. The oil film damper is formed between the inner ring and an outer peripheral surface of the rotor shaft. The inner ring rotates with rotation of the rotor shaft via the oil film damper. An oil discharge path for scattering oil discharged from the oil film damper radially outside, is provided at least either on one end surface of the inner ring in an axial direction or on an opposing surface opposed to the inner ring, of a collar. The oil discharge path is formed of a groove that is arranged in a manner to be gradually apart from the oil film damper in the axial direction as going radially outside.

A film damper for a gas turbine engine includes an annular inner member and an annular outer member located radially outboard of the annular inner member, the annular outer member and the annular inner member defining a damper annulus therebetween. A fluid supply passage delivers a flow of fluid into the damper annulus from the annular outer member, and a backflow prevention device is located at the fluid supply passage to prevent backflow of the flow of fluid from the damper annulus into the fluid supply passage.

An object of the present invention is to provide a bearing structure of a turbocharger that can prevent generation of unusual noise and a decrease in operation efficiency and that can reduce manufacturing costs. The bearing structure of a turbocharger to accomplish such an object, includes a rotor shaft, a ball bearing, a retainer, and a housing. The rotor shaft is provided with a turbine impeller mounted on a first end and a compressor impeller mounted on a second end.

The ball bearing includes an inner ring and an outer ring that are supported in relatively rotatable manner. The retainer holds the outer ring. Between the inner ring and an outer peripheral surface of the rotor shaft, oil in a film state is interposed to form an oil film damper.

A bearing structure of a turbocharger includes a rotor shaft, two angular ball bearings, a retainer, a housing, and an oil film damper. Each of the angular ball bearings includes an inner ring and an outer ring that are supported in relatively rotatable manner. The rotor shaft is inserted into the inner ring. The retainer holds the outer ring. The housing houses therein the rotor shaft, the angular ball bearings, and the retainer to constitute a bearing housing. The oil film damper is formed of oil in a film state and is interposed between the inner ring and an outer peripheral surface of the rotor shaft. The inner ring is configured to rotate with rotation of the rotor shaft via the oil film damper.

A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment.

A bearing assembly for a turbocharger includes a turbine wheel-side ball bearing at a first axial end of a tubular body, a compressor impeller-side ball bearing at a second axial end of the tubular body, and a bearing housing. The bearing housing includes a first opposed wall opposed to an axially outer side of an outer race of the turbine wheel-side ball bearing, and a second opposed wall opposed to an axially outer side of an outer race of the compressor impeller-side ball bearing. The outer race of the turbine wheel-side ball bearing and the outer race of the compressor impeller-side ball bearing have axially outer end surfaces which are axially outwardly displaced from respective axial end surfaces of the tubular body so that oil films are present between the respective outer races and the corresponding opposed walls.

Systems and methods are disclosed herein for bearings in a gas turbine engine. A bearing system may include a squirrel cage and a bearing support cage coupled to the squirrel cage. The bearing support cage may include an outer race and a fenestrated cone. The bearing support cage may include a support cage anti-rotation tab adjacent to the outer race. The bearing system may include a housing coupled to the squirrel cage. The housing may include a housing anti-rotation tab. The support cage anti-rotation tab and the housing anti-rotation tab may prevent the bearing system from twisting.