Abstract: A bypass valve assembly for a turbocharger includes a bypass valve having a valve stem rotatable about a valve stem axis for opening and closing the valve. The end of a first crank of an articulated two-bar linkage is connected to the valve stem. The end of a second crank of the linkage is connected to a cam follower engaged with a guide cam. An actuator provides motive force to the cam follower to proceed along the guide cam, which is configured to advance the cam follower along a guide path that is non-linear and non-circular arc, causing the two-bar linkage to rotate the valve stem. Valve stem angular displacement versus actuator stroke can be altered by modification of the shape of the guide path.

Abstract: A turbine housing assembly seal can include a cylindrical portion that defines an opening having an axis where the cylindrical portion is disposed at a cylinder radius from the axis; a lower edge disposed at a lower edge radius that exceeds the cylinder radius; an sloped annular portion that extends radially inwardly from the lower edge; a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion; an upper bend that extends from an upper axial position of the cylindrical portion; and an upper edge that extends radially outwardly from the upper bend to an upper edge radius that exceeds the cylinder radius and that is less than the lower edge radius.

Abstract: A turbocharger having a variable-nozzle turbine formed by pivotable vanes supported by a nozzle ring includes a locator that is radially elastically deformable and is disposed between a radially outwardly facing surface of the center housing and an opposing surface of the nozzle ring for radially locating the nozzle ring relative to the center housing. At least one vent is defined in either a radially outermost surface of the locator or the surface of the nozzle ring to allow pressure communication between spaces on axially opposite sides of the locator.

Abstract: A turbocharger having a variable-nozzle turbine formed by pivotable vanes supported by a nozzle ring includes a locator that is radially elastically deformable and is disposed between a radially outwardly facing surface of the center housing and an opposing surface of the nozzle ring for radially locating the nozzle ring relative to the center housing. At least one vent is defined in either a radially outermost surface of the locator or the surface of the nozzle ring to allow pressure communication between spaces on axially opposite sides of the locator.

Abstract: A variable-nozzle turbocharger includes a variable vane mechanism that has an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into a bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, and a plurality of two-piece self-centering spacer assemblies connected between the nozzle portion of the insert and the nozzle ring. Each spacer assembly comprises a tubular sleeve and a separate pin that passes through the through-passage of the sleeve, end portions of the pin being secured respectively to the nozzle ring and the nozzle portion. One end of each sleeve has a conical surface and engages in a corresponding conical countersink in the adjacent face of the nozzle ring or nozzle portion.

Abstract: An assembly can include a turbine wheel; a turbine housing that includes a lower turbine housing surface that extends from an exhaust volute to a cylindrical surface that defines an upper portion of a turbine wheel space; a shroud component that includes a contoured surface disposed between an inner end of an upper shroud component surface and an inner end of a lower shroud component surface where the contoured surface defines a lower portion of a turbine wheel space; and a seal mechanism where the turbine housing and the shroud component form an axial gap between a lower axial position of the cylindrical surface and an upper axial position of the contoured surface where the axial gap is axially positioned between an axial position of an inducer portion of the turbine wheel and an axial position of an exducer portion of the turbine wheel.

Abstract: A turbine assembly for a turbocharger can include a C-shaped seal that includes an inner diameter, an outer diameter, an axis aligned parallel to a rotational axis of a turbine wheel, a lower lip that contacts a lower axial face of an outer surface of a shroud component along an annular portion of the shroud component, an upper lip that contacts a lower axial face of an inner surface of a turbine housing, and a wall portion that extends between the lower lip and the upper lip. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A compressor housing assembly for a turbocharger can include a compressor housing shell that includes an axis for alignment with a rotational axis of a compressor wheel, a wall that includes features defined in part by radii with respect to the axis, and an edge that defines in part an inlet opening of a shroud port; and an insert that includes a shroud section and a noise suppressor section that define a recirculation port where the insert is axially located by the wall of the compressor housing shell, where an internal recirculation passage is defined in part by the insert and the wall, and where an edge of the shroud section (e.g., a lowermost edge) defines in part the inlet opening of the shroud port.

Abstract: An assembly can include a turbine wheel; a turbine housing that includes a lower turbine housing surface that extends from an exhaust volute to a cylindrical surface that defines an upper portion of a turbine wheel space; a shroud component that includes a contoured surface disposed between an inner end of an upper shroud component surface and an inner end of a lower shroud component surface where the contoured surface defines a lower portion of a turbine wheel space; and a seal mechanism where the turbine housing and the shroud component form an axial gap between a lower axial position of the cylindrical surface and an upper axial position of the contoured surface where the axial gap is axially positioned between an axial position of an inducer portion of the turbine wheel and an axial position of an exducer portion of the turbine wheel.

Abstract: A turbine housing assembly seal can include a cylindrical portion that defines an opening having an axis where the cylindrical portion is disposed at a cylinder radius from the axis; a lower edge disposed at a lower edge radius that exceeds the cylinder radius; an sloped annular portion that extends radially inwardly from the lower edge; a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion; an upper bend that extends from an upper axial position of the cylindrical portion; and an upper edge that extends radially outwardly from the upper bend to an upper edge radius that exceeds the cylinder radius and that is less than the lower edge radius.

Abstract: A variable-nozzle turbocharger includes a variable vane mechanism that has an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into a bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, and a plurality of two-piece self-centering spacer assemblies connected between the nozzle portion of the insert and the nozzle ring. Each spacer assembly comprises a tubular sleeve and a separate pin that passes through the through-passage of the sleeve, end portions of the pin being secured respectively to the nozzle ring and the nozzle portion. One end of each sleeve has a conical surface and engages in a corresponding conical countersink in the adjacent face of the nozzle ring or nozzle portion.

Abstract: A compressor housing assembly for a turbocharger can include a compressor housing shell that includes an axis for alignment with a rotational axis of a compressor wheel, a wall that includes features defined in part by radii with respect to the axis, and an edge that defines in part an inlet opening of a shroud port; and an insert that includes a shroud section and a noise suppressor section that define a recirculation port where the insert is axially located by the wall of the compressor housing shell, where an internal recirculation passage is defined in part by the insert and the wall, and where an edge of the shroud section (e.g., a lowermost edge) defines in part the inlet opening of the shroud port. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A turbine assembly for a turbocharger can include a C-shaped seal that includes an inner diameter, an outer diameter, an axis aligned parallel to a rotational axis of a turbine wheel, a lower lip that contacts a lower axial face of an outer surface of a shroud component along an annular portion of the shroud component, an upper lip that contacts a lower axial face of an inner surface of a turbine housing, and a wall portion that extends between the lower lip and the upper lip. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.