Abstract: A turbine of a turbocharger includes a floating insert which defines a nozzle for passing a fluid and which is supported axially slidable with respect to a housing by a sliding support. Furthermore, the turbine comprises a sealing member for preventing a flow of fluid between the floating insert and the housing. The sealing member is axially expandable and has a fixed end attached to the turbine housing and an opposite movable end attached to the floating insert.

Abstract: An exemplary bearing and locating pin system for a turbocharger includes a locating pin including a shaft, a head and an aperture and a bearing having a central axis and including an internal bore to receive a shaft extending between a compressor wheel and a turbine wheel, the internal bore including a plurality of axial grooves, the bearing including a locating pin aperture substantially equidistant from axial ends of the bearing for engaging the locating pin to prevent rotation of the bearing within a bearing case bore, the bearing further including a plurality of lubricant inlets, each inlet extending between an outer surface of the bearing and one of the axial grooves at an angle non-orthogonal to the central axis. Other exemplary technologies are also disclosed.

Abstract: An exemplary bearing assembly for a turbocharger includes a center housing with a bearing bore having a bearing bore turbine end radius and an inlet for lubricant and a unitary bearing disposed in the bearing bore and forming an outer lubricant film between the bearing and the bearing bore wherein the bearing includes a central axis, an internal bore to receive a shaft extending between a compressor end and a turbine end of the bearing and forming an inner lubricant film between the internal bore and the shaft, a locating mechanism between axial ends of the bearing to prevent rotation and translation of the bearing within the bearing bore and a turbine end protrusion wherein the protrusion comprises a radius that exceeds the bearing bore turbine end radius to thereby deflect lubricant from the outer lubricant film layer radially outward. Other exemplary technologies are also disclosed.

Abstract: A turbine of a turbocharger comprises a floating insert which defines a nozzle for passing a fluid and which is supported axially slidable with respect to a housing by a sliding support means. Furthermore, the turbine comprises a sealing means for preventing a flow of said fluid between said floating insert and said housing.

Abstract: An exemplary bearing assembly for a turbocharger includes a center housing with a bearing bore having a bearing bore turbine end radius and an inlet for lubricant and a unitary bearing disposed in the bearing bore and forming an outer lubricant film between the bearing and the bearing bore wherein the bearing includes a central axis, an internal bore to receive a shaft extending between a compressor end and a turbine end of the bearing and forming an inner lubricant film between the internal bore and the shaft, a locating mechanism between axial ends of the bearing to prevent rotation and translation of the bearing within the bearing bore and a turbine end protrusion wherein the protrusion comprises a radius that exceeds the bearing bore turbine end radius to thereby deflect lubricant from the outer lubricant film layer radially outward. Other exemplary technologies are also disclosed.

Abstract: An exemplary bearing and locating pin system for a turbocharger includes a locating pin including a shaft, a head and an aperture and a bearing having a central axis and including an internal bore to receive a shaft extending between a compressor wheel and a turbine wheel, the internal bore including a plurality of axial grooves, the bearing including a locating pin aperture substantially equidistant from axial ends of the bearing for engaging the locating pin to prevent rotation of the bearing within a bearing case bore, the bearing further including a plurality of lubricant inlets, each inlet extending between an outer surface of the bearing and one of the axial grooves at an angle non-orthogonal to the central axis. Other exemplary technologies are also disclosed.