Abstract: Provided is a radial diffuser that includes a housing, a plurality of diffuser vanes, and a plurality of deswirl vanes and at least one vane extension providing a service routing. Each of the vane extensions is disposed after a radial section and may extend into or through a transition and into the deswirl cascade. At least a portion of the vane extensions include a service passage extending therethrough. Each service passage is configured to allow a service conduit to extend therethrough without adversely crossing either a diffusion flow passage or a transition flow passage.

Abstract: A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.

Abstract: A turbocharger is disclosed for use with an engine system. The turbocharger may have a housing at least partially defining a compressor shroud and a turbine shroud. The turbine shroud may form a first volute and a second volute, each having an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction, and an axial channel disposed downstream of the inlet. The turbocharger may also have a turbine wheel disposed within the turbine shroud and configured to receive exhaust from the axial channels of the first and second volutes, a compressor wheel disposed within the compressor shroud, and a shaft connecting the turbine wheel to the compressor wheel. The turbocharger may further have a nozzle ring in fluid communication with the axial channels of the first and second volutes at a location upstream of the turbine wheel.

Abstract: A turbocharger is disclosed for use with an engine. The turbocharger may include a housing at least partially defining a compressor shroud and a turbine shroud, a turbine wheel disposed within the turbine shroud, a compressor wheel disposed within the compressor shroud, and a shaft connecting the turbine wheel to the compressor wheel. The turbocharger may also include an annular recirculation passage extending between an inlet located radially outward of the compressor wheel and an outlet located upstream of the compressor wheel, and a generally ring-shaped hub at least partially forming the recirculation passage. The hub may have an outer surface. The turbocharger may further include a plurality of first vanes disposed circumferentially around the outer surface, and a plurality of second vanes disposed circumferentially around the outer surface. The second vanes may be shorter than the first vanes.

Abstract: A turbocharger is disclosed for use with an engine. The turbocharger may include a housing at least partially defining a compressor shroud and a turbine shroud. The turbine shroud may form a volute having an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction. The volute may also include an axial channel disposed downstream of the inlet. The turbocharger may also include a turbine wheel disposed within the turbine shroud that may be configured to receive exhaust from the axial channel. The turbocharger may also include a compressor wheel disposed within the compressor shroud, and a shaft connecting the turbine wheel to the compressor wheel. The turbocharger may also include a nozzle ring disposed within the axial channel at a location upstream of the turbine wheel.

Abstract: A turbocharger is disclosed for use with an engine. The turbocharger may include a housing at least partially defining a compressor shroud and a turbine shroud. The turbocharger may also include a compressor wheel disposed within the compressor shroud, a shaft connected to the compressor wheel, and a turbine wheel disposed within the turbine shroud and connected to an end of the shaft opposite the compressor wheel. The turbine wheel may have a generally annular hub, and a plurality of blades disposed radially around the hub. Each of the plurality of blades may include an airfoil having a hub face connected to the hub, a shroud face opposite the hub face and oriented towards the turbine shroud, a trailing edge, and a leading edge opposite the trailing edge. The leading edge may be substantially straight or substantially concave in a meridional plane. An angle between a base of the hub and the leading edge may be about 25-55 degrees.

Abstract: A turbocharger is disclosed for use with an engine system. The turbocharger may have a housing at least partially defining a compressor shroud and a turbine shroud. The turbine shroud may form a first volute and a second volute, each having an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction, and an axial channel disposed downstream of the inlet. The turbocharger may also have a turbine wheel disposed within the turbine shroud and configured to receive exhaust from the axial channels of the first and second volutes, a compressor wheel disposed within the compressor shroud, and a shaft connecting the turbine wheel to the compressor wheel. The turbocharger may further have a nozzle ring in fluid communication with the axial channels of the first and second volutes at a location upstream of the turbine wheel.

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: A turbocharger is disclosed for use with an engine. The turbocharger may include a housing at least partially defining a compressor shroud and a turbine shroud. The turbine shroud may form a volute having an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction. The volute may also include an axial channel disposed downstream of the inlet. The turbocharger may also include a turbine wheel disposed within the turbine shroud that may be configured to receive exhaust from the axial channel. The turbocharger may also include a compressor wheel disposed within the compressor shroud, and a shaft connecting the turbine wheel to the compressor wheel. The turbocharger may also include a nozzle ring disposed within the axial channel at a location upstream of the turbine wheel.

Abstract: A diffuser is disclosed for use with a compressor. The compressor diffuser may have a ring-shaped generally flat plate, a plurality of first vanes disposed radially around an upper surface of the plate, and a plurality of second vanes shorter than the first vanes. Each of the second vanes may be connected to the plate between adjacent first vanes. The first and second vanes may each have a high-pressure side and an opposing low-pressure side, and each may tilt towards one of its corresponding high- and low-pressure sides at a lean angle that changes along its meridional length.

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.