A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.

A turbocharger includes a compressor housing, turbine housing, and center housing between the compressor and turbine housings. A turbine wheel is disposed in the turbine housing on a turbine shaft. A compressor wheel having a shank is disposed in the compressor housing on the turbine shaft. The shank has outer and reduced portions. The reduced portion has a smaller diameter than the outer portion. A backplate is mounted to the compressor housing adjacent the compressor wheel and defines a stepped cylindrical bore with a maximum diameter portion and a minimum diameter portion having a smaller diameter than the maximum portion. The outer portion is disposed in the maximum portion. The reduced portion is disposed in the minimum portion. The outer diameter of the shank is greater than or equal to the minimum diameter of the backplate, and the stepped cylindrical bore and the shank define a variable width gap.

A seal assembly is disclosed for sealing a higher pressure fluid cavity from a lower pressure fluid cavity. The seal assembly comprises a ceramic seal runner and a mounting assembly. The ceramic seal runner extends around an axial portion of a shaft. The mounting assembly is affixed to and carries the seal runner in axial and radial alignment with the shaft. The mounting assembly comprises an annular base member, a plurality of flexible members, and an annular sleeve member. The plurality of flexible members are circumferentially spaced about the base member and each extend radially outward from one end affixed to the base member in a direction opposite the direction of rotation of the shaft to a distal end. The annular sleeve member is positioned to engage the distal ends of the flexible members and a radially inner surface of the seal runner.

A seal structure for a turbocharger, including: a seal ring; a seal groove in which the seal ring is disposed; and a treated portion, which is formed at least at a part of one or both of the seal ring and the seal groove, and is subjected to surface treatment for anti-oxidation.

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.

A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.

An annular stator seal support extends radially between a radial inner support side and a radial outer support side. A secondary seal includes a first radially extending secondary seal sidewall surface, a second radially extending secondary seal sidewall surface and a third radially extending secondary seal sidewall surface. An annular stator sleeve support includes a channel radially distal the radial inner support side, the channel includes a first radially extending channel sidewall and a second radially extending channel sidewall located axially forward of the first radially extending channel sidewall, and a third radially extending channel sidewall located axially behind the first radially extending channel sidewall. The first radially extending seal sidewall surface contacts the first radially extending channel sidewall, and the second radially extending channel sidewall is axially spaced from the second radially extending secondary seal sidewall surface.

A seal system has: a first member; a seal carried by the first member and having a seal face; and a second member rotatable relative to the first member about an axis. The second member has: a seat, the seat having a seat face in sliding sealing engagement with the seal face; and a circumferential array of passageway legs. The second member further has an annular channel axially spaced from the seat face, the passageway legs connected to the annular channel.

An assembly for a turbine engine includes a case, a guide vane arrangement and a flexible seal ring. The case extends circumferentially around an axis, and includes a first seal land. The guide vane arrangement is located radially within the case, and includes a second seal land. The seal ring at least partially seals a gap between the first seal land and the second seal land. The seal ring includes a first leg and a second leg that is connected to the first leg at a corner of the seal ring. The first leg is axially engaged with the first seal land. The second leg is axially engaged with the second seal land.

A control valve composed of sectors of stationary blades, which are externally connected to a stator, includes an inner platform divided into an outer portion formed of sectors and associated, by radial slide connections, with an inner portion in the form of a ring which is continuous over a circumference, which carries an abradable seal. Springs ensure the radial position of the crown, and the concentricity thereof to the rest of the machine. The diameter of the crown is essentially determined by the temperature of the gases which pass in front of it. The independence of the radial thermal deformations is ensured by slides composed of sliding sleeves.