Provided is a steam valve including a valve seat, a valve disc capable of contacting the valve seat, a valve rod connected or linked to the valve disc, a bush that slidably supports the valve rod, and an actuator that moves the valve disc via the valve rod, in which the valve rod has thereon a plurality of groves depressed to an inner side in a diametrical direction of the valve rod and a plurality of projections formed between the plurality of grooves, and each of the plurality of projections in an axial cross section of the valve rod is shaped so as to have one tip point.

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 couples to the drive shaft that is rotatably supported by the least one bearing assembly. A lubricant passageway can provide lubrication to the at least one bearing assembly.

A journal bearing comprising a first component and a second component, the first and second components being arranged to rotate relative to one another in normal use. The first component comprises a first body, a first layer forming a functional surface facing the second component, and a first subsurface layer between the body and the layer. The first subsurface layer is formed of a material having a first coefficient of thermal expansion in the radial direction, and the first body is formed of a material having a second coefficient of thermal expansion in the radial direction. The first coefficient of thermal expansion is lower than the second coefficient of thermal expansion.

Rolling bearing with three contact points, wherein the inner raceway, the third contact point being located in a sector of the outer raceway delimited by a proximal end of the outer raceway on the one hand, and by the rolling plane on the other hand, characterized in that the outer ring comprises a drain provided in the outer raceway, and opening from an outer surface of the outer ring, said drain opening eccentrically on the outer raceway with respect to the rolling plane, in a sector of the outer raceway delimited by the rolling plane on the one hand, and a distal end of the outer raceway on the other hand, the drain and the third contact point being disjoint.

A carrier assembly has a pair of axially spaced-apart plates defining an axial gap therebetween. The plates have a plurality of planetary bores on a plurality of planetary axes. A plurality of planetary gear mount assemblies are disposed on the planetary axes and mounted within the planetary bores of the gear carrier. Each assembly comprises a journal bearing shaft having a pair of compliance grooves extending axially from opposed axial ends of the shaft. An inner cylindrical surface of each compliance groove defines a shaft mounting surface. A pair of collars is provided to assemble each journal bearing shaft to the carrier. Each collar has a mounting socket mating the shaft mounting surface and an external collar surface matching the planetary bore diameter.

A rotor journal support system (10) configured to allow for a bearing shoe (16) to properly align to the rotor (14) while keeping the bearing shoe (16) constrained during handling, installation, and operation limit is disclosed. The rotor journal support system (10) may be configured to enable limited movement of a bearing shoe (16) such that when the rotor journal (14) is installed, the bearing shoe (16) is properly aligned with the rotor journal (14), thereby requiring less torque to turn the rotor journal (14) from a stop than when the bearing shoe (16) is misaligned. The rotor journal support system (10) may include bearing shoe supports (88) extending radially outward from the bearing shoe (16). The bearing shoe support (88) may include an outer bearing surface (100) having at least a partial spherical shape configured to bear against the aligning ring (24). In this position, the bearing shoe support (88) enables the bearing shoe (16) to be moved in any direction other than circumferentially and radially outward.

A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a planet gear carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. Each planet gear is rotatably mounted in the planet gear carrier. The planet gear carrier comprises a plurality of axles arranged parallel to the axis of the gearbox. The axially spaced ends of each axle are secured to the planet gear carrier. Each planet gear is rotatably mounted on a corresponding one of the axles by a bearing arrangement. Each bearing arrangement comprises a journal bearing and a rolling element bearing and each planet gear is rotatably mounted on a journal bearing and each journal bearing is rotatably mounted on an axle by at least one rolling element bearing.

A system includes a gas delivery disk coupled to a second shaft, wherein the second shaft and the gas delivery disk are disposed about an axis. The gas delivery disk includes an inner axial opening configured to facilitate a first axial flow through a first passage within the second shaft, a duct configured to supply a bearing flow in a radial direction toward the axis, and a bearing face disposed within the first passage and radially interior to the inner axial opening. The bearing face is configured to receive the bearing flow, and the bearing face is configured to form a gas bearing between the bearing face and a first shaft disposed about the axis.

A bearing configured to actively damp vibration of a shaft in a turbine. In one implementation, the bearing can include actuating members that move in a manner that changes properties of fluid, typically a thin film of lubricant, disposed in the bearing to facilitate rotation of the shaft. These changes effectively manipulate the stiffness and damping of the thin film according to a time periodicity that matches a parametric anti-resonance of the bearing. In turn, the resulting interaction of vibrating modes is favorable to damp vibration amplitudes at critical speeds.

A bearing assembly for a turbine engine includes a first gas bearing configured to receive a load from a rotating shaft of the turbine engine, a transmission disk configured to receive the load from the first gas bearing, and a damping member coupled to a casing of a combustor section of the turbine engine. The transmission disk includes a gas delivery disk, which includes an axial opening configured to facilitate an axial flow through the gas delivery disk and a duct configured to facilitate a radial flow through the gas delivery disk to form the first gas bearing. The damping member is configured to receive the load from the transmission disk.