Abstract: A turbocharger is provided including a turbine housing having a gas inlet passage. A turbine wheel having a plurality of blades is arranged within the turbine housing. A nozzle ring is disposed around the turbine wheel and includes a plurality of vanes with flow channels being defined between the vanes that are in fluid communication the gas inlet passage and with the turbine wheel. A shroud is arranged in surrounding relation to at least a portion of the turbine wheel and in spaced relation from the turbine housing. The shroud is integrally formed with the nozzle ring such that the plurality of vanes extend away from the shroud.

Abstract: A turbine assembly includes a turbine housing and a turbine wheel disposed within the turbine housing. The turbine wheel includes a rotational axis and a plurality of blades. The turbine assembly includes a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction. The turbine shroud is separate from the turbine housing. The turbine shroud includes an annular portion extending generally in an axial direction with respect to the rotational axis and a plate portion intersecting the annular portion to form a convex curved surface. At least a portion of the blades is disposed in at least a portion of the annular portion. Each blade includes a leading edge and a tip portion. Each leading edge is angled with respect to the rotational axis, and each tip portion forms a concave portion that curves around the curved surface of the turbine shroud.

Abstract: A turbocharger including a turbine housing including a gas inlet passage and a turbine wheel arranged in the turbine housing. A bearing housing is connected to the turbine housing. A nozzle ring is disposed around the turbine wheel and a shroud is arranged in surrounding relation to at least a portion of the turbine wheel. The shroud is connected to the nozzle ring and the nozzle ring and shroud are connected to a heat shield. The heat shield is secured to the bearing housing by a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing. The first passages and second passages are symmetrically arranged in a circular pattern about a rotational axis of the turbine.

Abstract: A turbocharger is provided that includes a turbine housing including a gas inlet passage. A turbine wheel has a plurality of blades and is arranged in the turbine housing. A bearing housing is connected to the turbine housing. A shaft is rotatably supported in the bearing housing and connected to the turbine wheel. A shroud is arranged in surrounding relation to at least a portion of the turbine wheel, the shroud being arranged in spaced relation from and not in contact with the turbine housing. A fastening system secures the shroud relative to the bearing housing. The fastening system is configured to fracture when a force is exerted on the shroud corresponding to at least a portion of the turbine wheel contacting the shroud.

Abstract: A turbocharger is provided that includes a turbine housing including a gas inlet passage. A turbine wheel has a plurality of blades and is arranged in the turbine housing. A bearing housing is connected to the turbine housing. A shaft is rotatably supported in the bearing housing and connected to the turbine wheel. A shroud is arranged in surrounding relation to at least a portion of the turbine wheel, the shroud being arranged in spaced relation from and not in contact with the turbine housing. A fastening system secures the shroud relative to the bearing housing. The fastening system is configured to fracture when a force is exerted on the shroud corresponding to at least a portion of the turbine wheel contacting the shroud.

Abstract: A turbine assembly includes a turbine housing and a turbine wheel disposed within the turbine housing. The turbine wheel includes a rotational axis and a plurality of blades. The turbine assembly includes a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction. The turbine shroud is separate from the turbine housing. The turbine shroud includes an annular portion extending generally in an axial direction with respect to the rotational axis and a plate portion intersecting the annular portion to form a convex curved surface. At least a portion of the blades is disposed in at least a portion of the annular portion. Each blade includes a leading edge and a tip portion. Each leading edge is angled with respect to the rotational axis, and each tip portion forms a concave portion that curves around the curved surface of the turbine shroud.

Abstract: A turbocharger is provided including a turbine housing having a gas inlet passage. A turbine wheel having a plurality of blades is arranged within the turbine housing. A nozzle ring is disposed around the turbine wheel and includes a plurality of vanes with flow channels being defined between the vanes that are in fluid communication the gas inlet passage and with the turbine wheel. A shroud is arranged in surrounding relation to at least a portion of the turbine wheel and in spaced relation from the turbine housing. The shroud is integrally formed with the nozzle ring such that the plurality of vanes extend away from the shroud.

Abstract: A wheel of a turbocharger includes a first end opposite a second end and a rotational axis extending between the first end and the second end. The wheel also includes a back wall located at the second end and a balance groove formed in the back wall. The balance groove has a plurality of side walls and a bottom surface. The side walls and the bottom surface of the balance groove are milled surfaces.

Abstract: A turbocharger including a turbine housing including a gas inlet passage and a turbine wheel arranged in the turbine housing. A bearing housing is connected to the turbine housing. A nozzle ring is disposed around the turbine wheel and a shroud is arranged in surrounding relation to at least a portion of the turbine wheel. The shroud is connected to the nozzle ring and the nozzle ring and shroud are connected to a heat shield. The heat shield is secured to the bearing housing by a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing. The first passages and second passages are symmetrically arranged in a circular pattern about a rotational axis of the turbine.