High diffusion turbine wheel with hub bulb
AssigneeHoneywell International Inc.
InventorsVaclav Kares, Thomas J. Elliott
Life of this patent
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Abstract
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.
Claims12
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;
- and
- a 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;
- and
- wherein 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.
Dependencies are inferred from the claim text.