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A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumfer

A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.

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1. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising: a housing including a turbine housing; anda rotor configured to rotate within the hou

1. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising: a housing including a turbine housing; anda rotor configured to rotate within the housing along an axis of rotor rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotor rotation and connecting the turbine wheel to the compressor wheel;wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotor rotation when the turbocharger receives the exhaust gas stream from the engine, the blades each having an axially upstream blade leading edge, an axially downstream blade trailing edge, a hub end, and a tip end opposite the hub end;wherein the compressor wheel is configured to compress the input air into the pressurized air stream when the rotor is driven in rotation around the axis of rotor rotation by the turbine wheel;wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway that turns in an axial direction; andwherein the turbine wheel hub is radially larger at the blade leading edges than it is at the blade trailing edges, and wherein the turbine wheel hub is radially larger at an intermediate axial location between the blade leading edges and the blade trailing edges than it is at either the leading edges or the trailing edges. 2. The turbocharger of claim 1, wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway characterized by a primary-scroll inlet port characterized by a centroid that is radially external to the axially upstream ends of the blades. 3. The turbocharger of claim 2, wherein: the trailing edge being characterized by a radius at the hub end and a radius of the tip end; andthe radius at the hub end of the turbine wheel trailing edge is no more than 60% of the radius of the tip end of the turbine wheel trailing edge. 4. The turbocharger of claim 3, wherein the turbine blades are each characterized by a blade turning angle at the hub that is greater than or equal to 45 degrees. 5. The turbocharger of claim 4, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 6. The turbocharger of claim 3, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 7. The turbocharger of claim 1, wherein: the turbine housing forms an inwardly spiraling turbine primary-scroll passageway; andwherein the turbine is configured to limit the static pressure upstream of the wheel near the wheel hub to a value that is not greater than 120% of the turbine outlet static pressure for at least some operating conditions of the range of standard operating conditions. 8. The turbocharger of claim 7, wherein: the trailing edge being characterized by a radius at the hub end and a radius of the tip end; andthe radius at the hub end of the turbine wheel trailing edge is no more than 60% of the radius of the tip end of the turbine wheel trailing edge. 9. The turbocharger of claim 8, wherein the turbine blades are each characterized by a blade turning angle at the hub that is greater than or equal to 45 degrees. 10. The turbocharger of claim 9, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 11. The turbocharger of claim 8, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 12. The turbocharger of claim 1, wherein: the trailing edge being characterized by a radius at the hub end and a radius of the tip end; andthe radius at the hub end of the turbine wheel trailing edge is no more than 60% of the radius of the tip end of the turbine wheel trailing edge.