Abstract: An assembly can include an exhaust gas turbine housing that includes an inner wall and an outer wall that define a first exhaust gas channel and a second exhaust gas channel to a turbine wheel space where the inner wall includes an inner wall end at the turbine wheel space and the outer wall includes an outer wall end at the turbine wheel space; a first adjustable divider vane disposed adjacent to the inner wall end; a second adjustable divider vane disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle vanes that define nozzle throats that direct flow of exhaust gas from one of the exhaust gas channels to the turbine wheel space.

Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes an axially elongated ring. In the open position, the radially outer surface of the ring is spaced from a tapering inner surface of the air inlet so that air can flow in an annular passage between the tapering surface and the ring. In the closed position, the ring abuts the tapering surface to close off the annular passage, whereby the effective inlet diameter is then defined by the inner diameter of the ring at its trailing edge. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

Abstract: A turbocharger includes a variable turbine nozzle formed between first and second walls. A variable-vane assembly has a fixed nozzle ring and a plurality of circumferentially spaced vanes disposed in the nozzle and rotatably mounted on the nozzle ring such that the vanes are pivotable. The nozzle ring defines the first wall of the turbine nozzle, each vane having a first end adjacent the first wall and a second end adjacent the second wall. The second wall of the turbine nozzle is formed by a gas pressure-responsive member that is arranged to be axially movable relative to the vanes. A first stop is positioned so that the gas pressure-responsive member is urged against the first stop by a differential gas pressure exerted on the gas pressure-responsive member so that there is a non-zero first value for a clearance between the second ends of the vanes and the second wall of the turbine nozzle.

Abstract: An assembly can include an exhaust gas turbine housing that includes an inner wall and an outer wall that define a first exhaust gas channel and a second exhaust gas channel to a turbine wheel space where the inner wall includes an inner wall end at the turbine wheel space and the outer wall includes an outer wall end at the turbine wheel space; a first adjustable divider vane disposed adjacent to the inner wall end; a second adjustable divider vane disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle vanes that define nozzle throats that direct flow of exhaust gas from one of the exhaust gas channels to the turbine wheel space.

Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes an axially elongated ring. In the open position, the radially outer surface of the ring is spaced from a tapering inner surface of the air inlet so that air can flow in an annular passage between the tapering surface and the ring. In the closed position, the ring abuts the tapering surface to close off the annular passage, whereby the effective inlet diameter is then defined by the inner diameter of the ring at its trailing edge. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

Abstract: A turbocharger includes a variable turbine nozzle formed between first and second walls. A variable-vane assembly has a fixed nozzle ring and a plurality of circumferentially spaced vanes disposed in the nozzle and rotatably mounted on the nozzle ring such that the vanes are pivotable. The nozzle ring defines the first wall of the turbine nozzle, each vane having a first end adjacent the first wall and a second end adjacent the second wall. The second wall of the turbine nozzle is formed by a gas pressure-responsive member that is arranged to be axially movable relative to the vanes. A first stop is positioned so that the gas pressure-responsive member is urged against the first stop by a differential gas pressure exerted on the gas pressure-responsive member so that there is a non-zero first value for a clearance between the second ends of the vanes and the second wall of the turbine nozzle.

Abstract: An assembly includes a cast cartridge component and a curved wall where the cast cartridge includes a base plate having an opening configured for receipt of a turbine wheel, an exhaust conduit having an inlet and an outlet, a cylindrical wall, and vanes disposed between the cylindrical wall and the base plate where adjacent vanes define throats; where the curved wall includes a proximal end and a distal end, and an upper edge and a lower edge; and where joinder of the proximal end and the outlet of the exhaust conduit, joinder of the upper edge and the cylindrical wall and joinder of the lower edge and the base plate forms a volute configured to direct exhaust received via the inlet to a turbine wheel via the throats. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: An assembly for a turbocharger that includes a bearing housing with a cylindrical portion with a bore configured for receipt of a bearing, an extension that extends radially outwardly from the cylindrical portion to a base, the base configured with one or more features for securing the bearing housing to another component, a compressor fitting, a turbine fitting, and lubricant flow paths; and a fluid jacket that includes a cylindrical wall configured for placement over at least a portion of the cylindrical portion of the bearing housing where the cylindrical wall includes a recess configured to accommodate at least a portion of the extension of the bearing housing, a fluid inlet, and a fluid outlet. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A turbocharger bearing cartridge can include a bearing with an inner race, an outer race and rolling elements disposed between the inner race and the outer race; a journal bearing; and a shell that includes an interior, compressor side annular surface configured to seat the outer race of the bearing and an interior, turbine side annular surface configured to seat the journal bearing.

Abstract: An assembly includes a cast cartridge component that includes a base plate having an opening configured for receipt of a turbine wheel, a cylindrical wall that comprises a shroud portion, one or more supports disposed between the cylindrical wall and the base plate, an exhaust conduit that has an inlet, an outlet and a wastegate opening positioned intermediate the inlet and the outlet, and a substantially planar surface integral to the exhaust conduit, the wastegate opening located on the planar surface; and a wastegate outlet component that includes a cylindrical portion that extends between and defines an inlet and an outlet, and a cover portion configured to cover the substantially planar surface of the cast cartridge component to form a wastegate chamber where one or more openings provide for flow of exhaust from the wastegate chamber to the cylindrical portion. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) grooves extending substantially transverse to a general flow direction of the flow through the nozzle, and there are clearances between the ends of the vanes and the adjacent faces. Leakage flow through the clearance between the end of each vane and the adjacent face having the grooves must proceed across the grooves, and thus a labyrinthine flow passage is presented to the leakage flow. The labyrinthine passage has a greater resistance to flow than would be the case without the grooves. Accordingly, leakage flow is reduced, which is beneficial to turbine efficiency.

Abstract: A variable-nozzle assembly for a turbocharger includes a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. A unison ring engages vane arms that are affixed to axles of the vanes, such that rotation of the unison ring causes the vanes to pivot between a closed position and an open position. The vanes have proximal ends that are adjacent a face of the nozzle ring. A vane sealing member is supported on the nozzle ring and has a portion disposed between the proximal ends of the vanes and the face of the nozzle ring. The unison ring includes cams that engage cam followers. Rotational movement of the unison ring causes the cam followers to be moved axially and thereby urge the vane sealing member against the proximal ends of the vanes.

Abstract: An exemplary multi-piece bearing for a turbocharger includes a cylindrical piece that has a coefficient of thermal expansion, opposing ends and an outer surface and an inner surface that extend between the opposing ends where the outer surface includes one or more lubricant openings; an end piece that has a different coefficient of thermal expansion and a face where the face includes one or more lubricant openings; and lubricant passages formed by the cylindrical piece and the end piece for passage of lubricant between the one or more lubricant openings of the outer surface of the cylindrical piece and the one or more lubricant openings of the face of the end piece. As described herein, such an exemplary multi-piece bearing can, upon selection of coefficients of thermal expansion, help maintain axial clearances between various components during operation of a turbocharger. Other exemplary bearings, arrangements and methods are also disclosed.

Abstract: A variable-nozzle turbocharger includes a turbine housing and a center housing, and a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes are rotatably adjustable for regulating exhaust gas flow to the turbine wheel. An elastically deformable member is disposed between a radially inwardly facing surface of the nozzle ring and a radially outwardly facing surface of the center housing, the elastically deformable member having a radially inner surface contacting the radially outwardly facing surface of the center housing and having a radially outer surface contacting the radially inwardly facing surface of the nozzle ring so as to radially center the nozzle ring relative to the center housing.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) grooves extending substantially transverse to a general flow direction of the flow through the nozzle, and there are clearances between the ends of the vanes and the adjacent faces. Leakage flow through the clearance between the end of each vane and the adjacent face having the grooves must proceed across the grooves, and thus a labyrinthine flow passage is presented to the leakage flow. The labyrinthine passage has a greater resistance to flow than would be the case without the grooves. Accordingly, leakage flow is reduced, which is beneficial to turbine efficiency.

Abstract: A variable-nozzle assembly for a turbocharger includes a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. A unison ring engages vane arms that are affixed to axles of the vanes, such that rotation of the unison ring causes the vanes to pivot between a closed position and an open position. The vanes have proximal ends that are adjacent a face of the nozzle ring. A vane sealing member is supported on the nozzle ring and has a portion disposed between the proximal ends of the vanes and the face of the nozzle ring. The unison ring includes cams that engage cam followers. Rotational movement of the unison ring causes the cam followers to be moved axially and thereby urge the vane sealing member against the proximal ends of the vanes.

Abstract: A turbocharger bearing cartridge can include a bearing with an inner race, an outer race and rolling elements disposed between the inner race and the outer race; a journal bearing; and a shell that includes an interior, compressor side annular surface configured to seat the outer race of the bearing and an interior, turbine side annular surface configured to seat the journal bearing. Such a cartridge can optionally include an anti-rotation feature to limit rotation of the shell in a bore of a housing of a turbocharger and can optionally be configured to float in a bore of a housing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: An exemplary bearing for a turbocharger includes one or more thrust pads where each thrust pad includes a portion of a conical well; and a through-bore that includes lubricant channels, each channel configured to direct lubricant from the bore to a corresponding conical well of a thrust pad. 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. Said floating insert is axially supported by said guiding means formed by a portion of a center housing.

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.