Abstract: An assembly can include a compressor backplate; a bearing boss that extends axially from the compressor backplate and that includes an outer surface and male coupling features disposed along the outer surface; and a casing that includes a compressor end, a bearing boss opening at the compressor end, a turbine end, an inner surface located between the compressor end and the turbine end and female coupling features disposed along a portion of the inner surface, the male coupling features and the female coupling features configured to couple the bearing boss to the casing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: An assembly can include a compressor backplate; a bearing boss that extends axially from the compressor backplate and that includes an outer surface and male coupling features disposed along the outer surface; and a casing that includes a compressor end, a bearing boss opening at the compressor end, a turbine end, an inner surface located between the compressor end and the turbine end and female coupling features disposed along a portion of the inner surface, the male coupling features and the female coupling features configured to couple the bearing boss to the casing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A vane for a turbine assembly of a turbocharger includes an airfoil that has a pair of flow surfaces disposed between a hub end and a shroud end and a leading edge and a trailing edge where the airfoil further includes a non-zero sweep angle, a non-zero lean angle, a non-zero twist angle or any two or more combinations thereof. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

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 vane for a turbine assembly of a turbocharger includes an airfoil that has a pair of flow surfaces disposed between a hub end and a shroud end and a leading edge and a trailing edge where the airfoil further includes a non-zero sweep angle, a non-zero lean angle, a non-zero twist angle or any two or more combinations thereof. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

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 wastegate valve and associated method for controlling a flow of gas, such as a flow of exhaust gas from an exhaust inlet of a turbocharger, are provided. The wastegate valve includes multiple bypass ports that are selectively opened and closed by poppets, which are controlled by a linkage. The poppets are configured so that the pressure of the gas in the exhaust inlet biases one of the poppets to the open position and one of the poppets to the closed position. Thus, the forces resulting from the pressure of the gas on the poppets are offset, thereby reducing the force required for adjusting or maintaining the position of the linkage and the poppets.

Abstract: A turbocharger with variable geometry turbine inlet nozzle employs a rotating unison ring for actuation of multiple vanes. A crank arm engages a slot in the unison ring to convert linear actuator motion into rotation of the unison ring. A crank pin having a rectangular tongue adapted to be received in the slot and a circular body received in an aperture in the crank arm reduces contact stresses between the crank tongue and unison ring slot. The crank pin is retained in the crank arm by the unison ring and center housing flange of the turbocharger.

Abstract: A turbocharger with variable geometry turbine inlet nozzle employs a rotating unison ring for actuation of multiple vanes. A crank arm engages a slot in the unison ring to convert linear actuator motion into rotation of the unison ring. A crank pin having a rectangular tongue adapted to be received in the slot and a circular body received in an aperture in the crank arm reduces contact stresses between the crank tongue and unison ring slot. The crank pin is retained in the crank arm by the unison ring and center housing flange of the turbocharger.