Axial turbine with radial vnt vanes

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.

Description

[0001]The present invention relates generally to turbochargers and, more particularly, to an axial turbine having radial variable nozzle turbine vanes.BACKGROUND OF THE INVENTION[0002]With reference to FIG. 1, a typical turbocharger 101 having a radial turbine includes a turbocharger housing and a rotor configured to rotate within the turbocharger housing along an axis of rotor rotation 103 on thrust bearings and two sets of journal bearings (one for each respective rotor wheel), or alternatively, other similarly supportive bearings. The turbocharger housing includes a turbine housing 105, a compressor housing 107, and a bearing housing 109 (i.e., a center housing that contains the bearings) that connects the turbine housing to the compressor housing. The rotor includes a turbine wheel 111 located substantially within the turbine housing, a compressor wheel 113 located substantially within the compressor housing, and a shaft 115 extending along the axis of rotor rotation, through th...

AI Technical Summary

Benefits of technology

The present invention is a cost-effective turbocharger turbine that has low moment of inertia and small size, making it highly efficient at both lower and higher expansion ratios. It also has minimal changes in static loads and can extract a significant amount of energy from high-speed exhaust gas without impacting the static pressure. The turbine wheel does not require extremely tight manufacturing tolerances or small blade sizes, even when the wheel is manufactured in relatively small sizes. The vanes positioned in the turbine inlet minimize the effect on the static pressure transition into dynamic pressure, particularly when the vanes are in a substantially or fully open configuration.

Problems solved by technology

While conventional axial turbines generally offer a lower inertia, albeit with some loss of efficiency and performance, they suffer from an inability to be efficiently manufactured in the small sizes usable with many modern internal combustion engines.

This is, e.g., due to the exceptionally tight tolerances that would be required, due to aerodynamic limitations, and / or due to dimensional limitations on creating small cast parts.

Axial turbines also lack the ability to perform well at higher expansion ratios, such as are typically needed due to the pulsing nature of the exhaust of an internal combustion engine.

Furthermore, conventional axial turbines have a significant change in static pressure across the blades, causing significant thrust loads on the thrust bearings of the rotor, and potentially causing blowby.

Nevertheless, the axial loads from the turbines and compressors do not vary evenly with one another and may be at significantly different levels, so the thrust bearings must be designed for the largest load condition that may occur during turbocharger use.

Bearings configured to support high axial loads waste more energy than comparable low-load bearings, and thus turbochargers that must support higher axial loads lose more energy to their bearings.

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