A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal plate includes a cooling passageway having a circumferentially-extending section radially aligned with the contact area.

Embodiments disclosed herein are directed to tilting pad bearing assemblies, bearing apparatuses including the tilting pad bearing assemblies, and methods of using the bearing apparatuses. The tilting pad bearing assemblies disclosed herein include a plurality of tilting pads. At least some of the superhard tables exhibit a thickness that is at least about 0.120 inch and/or at least two layers having different wear and/or thermal characteristics.

Embodiments disclosed herein are directed to tilting pad bearing assemblies, bearing apparatuses including the tilting pad bearing assemblies, and methods of using the bearing apparatuses. The tilting pad bearing assemblies disclosed herein include a plurality of tilting pads. At least some of the superhard tables exhibit a thickness that is at least about 0.120 inch and/or at least two layers having different wear and/or thermal characteristics.

A device for lubricating and cooling a turbomachine rolling bearing is at least partially annular. The device comprises a first duct and a second duct inclined with respect to the first duct. The first duct is configured to be in thermal contact with an outer ring of the rolling bearing that at least partially surrounds same. The second duct is fluidically connected to the first duct. The first duct is configured to circulate the lubricant for cooling the outer ring, towards a discharge outlet of the lubricant. The second duct is configured to eject the lubricant through a lubrication outlet towards the rolling bearing.

The invention relates to a control system for reducing rotor vibrations, in particular the variability thereof, in shafting, in particular turbine shafting, in which the temperature of the bearing (6) of the shaft is measured and the oil (8) supplied to the bearing is adjusted to a temperature as is assigned as the output variable in an allocation for minimised rotor vibrations with the measured temperature of the bearing as the input variable. The allocation can, for example, be provided by an initial measurement of the rotor vibrations or by a self-learning system. According to the invention, the variability of the rotor vibrations is restricted.

A dental handpiece (1) having a drive (3) of a tool (4), which drive is located in a head housing (2), has at least one media-conducting line arranged in the head housing, which media-conducting line has an outlet opening to the tool, and a tool receptacle (16) arranged in a drive chamber, which tool receptacle is rotatably supported by means of a rolling bearing (11) in a support (14) of the head housing (2) on a side of the drive chamber facing the tool. The rolling bearing has an outer race (13), which is supported against the head housing (2) radially in the support (14) in the area of a raceway (22) and which has a sub-area (21), the outside diameter D2 of which is reduced compared to the outside diameter D1 in the area of the raceway (22). The head housing has a housing projection (23), which extends into the area of the reduced outside diameter D2, and the media-conducting line (17) runs at least partially through said housing projection (23).

A thermal management structure may include a body and a pad. The body extends between a first outer surface and a second outer surface. The pad moves relative to the body. A thermal management channel extends within a portion of the body and extends within a portion of the pad. The thermal management channel directs fluid to one or more locations within the body and to one or more locations within the pad.

Various methods and systems are provided for a radial turbocharger. In one example, the turbocharger comprises a turbine case housing a turbine wheel and a compressor case housing a compressor wheel, the turbine case including a vaneless turbine nozzle integrated into the turbine case, a bearing case surrounding a shaft connecting the turbine wheel to the compressor wheel and arranged between the turbine case and compressor case, a plurality of long bolts arranged around a circumference of the turbine case, and a plurality of slots arranged around a circumference of the turbine case, a slot length of each slot extending in a radial direction and adapted to receive a dowel pin having a diameter smaller than the slot length, where each dowel pin, via a corresponding slot, couples the bearing case to the turbine case.

Embodiments of the present invention provide a magnetic bearing system comprising an axial bearing rotating flywheel arranged so as to magnetically interact with at least one fixed axial stop. The system includes a cooling fluid path configured so as to send the flow to the flywheel in a direction of flow being in a substantially radial plane relative to the axis of rotation of the flywheel.

There is prepared a formed body constituted of steel and having an outer circumferential surface having an annular groove having a bottom surface to serve as a raceway surface of the bearing ring. In the step of forming a heated region, the formed body is induction heated to form a heated region including the bottom surface of the groove and heated to a temperature of at least an A.sub.1 point. In the cooling step, the whole of the heated region is simultaneously cooled to a temperature of not more than an M.sub.s point. The step of retaining the formed body in a state in which heating is stopped is performed after the step of forming a heated region before the step of cooling. In the step of retaining, dispersion in temperature in the heated region in the circumferential direction is suppressed to not more than 20 C.