A gyroscopic roll stabilizer comprises a gimbal having a support frame and enclosure configured to maintain a below-ambient pressure, a flywheel assembly including a flywheel and flywheel shaft, one or more bearings for rotatably mounting the flywheel inside the enclosure, a motor for rotating the flywheel, and bearing cooling system for cooling the bearings supporting the flywheel. For smaller units, the bearing cooling system is effective to enable a flywheel with a moment of inertia less than 11.7 kg.m.sup.2 (40000 lbm in.sup.2) to be accelerated at a rate of 5 rpm/s or greater. For larger units, the bearing cooling system is effective to enable a flywheel with a moment of inertia greater than 11.7 kg.m.sup.2 (40000 lbm in.sup.2) to be accelerated at a rate of 2.5 rpm/s or greater.

An arrangement for cooling a spindle bearing or bearings of an abrading apparatus with rotating abrading members is disclosed. This is premised on arranging in a housing of the abrading apparatus conduits which extend from a spindle bearing chamber wall of the housing to an inner suction chamber wall of the housing. Via such conduits, hot air may be expelled from a spindle bearing chamber of the housing as an overpressure in front of a protruding balancer element of a rotating shaft balancer is discharged from the spindle bearing chamber via a conduit into a suction chamber. Cool air may be conveyed from a suction chamber into the spindle bearing chamber as an underpressure behind the protruding balancer element draws in air from the suction chamber via the conduit to the spindle bearing chamber.

A housing for a bearing cavity in a gas turbine engine is disclosed. The housing comprise features that mitigate heat transfer from a heat source in the gas turbine engine to the nearby bearing cavity to prevent exposing the oil in the bearing cavity to excessively high temperatures. The housing comprises an annular flange that defines one or more barriers to heat transfer from the heat source to the bearing cavity.

An air starter for starting a turbine engine that includes a housing, a turbine member, a drive shaft, and at least one bearing assembly. The housing can define an interior where the turbine member rotatably couples to the drive shaft, where the drive shaft or turbine member are rotatably supported by the least one bearing assembly. A scoop wheel located in the interior of the housing provides lubrication to the at least one bearing assembly.

A gyroscopic roll stabilizer comprises a gimbal having a support frame and enclosure configured to maintain a below-ambient pressure, a flywheel assembly including a flywheel and flywheel shaft, one or more bearings for rotatably mounting the flywheel inside the enclosure, a motor for rotating the flywheel, and bearing cooling system for cooling the bearings supporting the flywheel. The bearing cooling system enables heat generated by the bearings to be transferred through the flywheel shaft to a heat sink disposed within a cavity in the end of the flywheel shaft, or to a liquid coolant circulating within the cavity.

A motion guide apparatus cooling nozzle is provided which can gas-cool a motion guide apparatus. Cooling nozzles 1a and 1b of the present invention are mounted on a block 4 of the motion guide apparatus to cool at least one of a guide rail 2 and a block 4 that is assembled to the guide rail 2 via a rolling element 6 in such a manner as to be movable relatively. The cooling nozzles la and 1b include an inner passage 18 into which gas is introduced, an opening 12a configured to emit a gas flow introduced into the inner passage 18, a deflection surface 22a that is provided adjacently to the opening 12a to bend the gas flow emitted from the opening 12a, and a guiding surface 32a configured to attract gas outside the cooling nozzles 1a and 1b.

A clutch mechanism designed to be installed between an engine and a motor vehicle transmission, wherein the clutch mechanism includes at least one cooling duct arranged to make a cooling fluid circulate toward the clutch, wherein each cooling duct includes an axially extending part and at least one radially extending part, the axially extending part of each cooling duct is situated radially between a transmission shaft and an interior face of the clutch support, and at least one radially extending part of each cooling duct is situated axially between the support bearing and the output hub.

A gyroscopic roll stabilizer includes an enclosure, a flywheel assembly, a bearing, a motor, and a bearing cooling circuit. The enclosure is mounted to a gimbal for rotation about a gimbal axis and configured to maintain a below-ambient pressure. The flywheel assembly includes a flywheel and flywheel shaft. The bearing rotatably mounts the flywheel assembly inside the enclosure for rotation about a flywheel axis. The bearing has an inner race and an outer race. The inner race is affixed to the flywheel shaft, and the outer race is held rotationally fixed relative to the enclosure. The motor is operative to rotate the flywheel assembly. The bearing cooling circuit is configured to transfer heat away from the bearing by recirculating cooling fluid along a closed fluid pathway. The gyroscopic roll stabilizer is configured to transfer heat away from the inner and/or outer race of the bearing to the cooling fluid.

A cooling system for a shafting and a control method therefor, and a wind turbine are provided. The cooling system includes a cold air supply unit and a rotating-shaft air blow box. The rotating-shaft air blow box is mounted on an inner surface of the stationary shaft and in the shape of a circular ring-shaped box, multiple first air blow openings are uniformly distributed in a surface, facing the rotating shaft, of the rotating-shaft air blow box in a circumferential direction, to blow cold air from the cold air supply unit to the rotating shaft. Each first air blow opening is in the shape of a slit to form a jet.

An oil chamber wall arrangement is described as comprising: a chamber wall surrounding a rotor; a plurality of apertures defining through-holes for a flow of oil through the chamber wall, the apertures being defined by a pair of axially separated opposing walls and a pair of circumferentially opposing walls wherein the circumferentially opposing walls are separated by a midline which is radial to the rotational axis of the rotor and at least one of the pair of circumferentially opposing walls is not parallel to the radial midline.