Granted Patent B2

US 9,429,162 · App. 13/757,145 · Granted Aug 30, 2016

Abstract

Claims (20)

1. An axial turbine for an exhaust-gas-driven turbocharger, the turbine having no inlet stator, and comprising:

an axial turbine wheel comprising a hub and a plurality of blades extending generally radially outward from the hub, and a turbine housing assembly that houses the turbine wheel;

the turbine housing assembly comprising a sector-divided turbine housing and a separately formed heat shroud, the sector-divided turbine housing defining a plurality of separate exhaust gas inlets into the turbine housing, each exhaust gas inlet for receiving a separate exhaust gas stream from an internal combustion engine, the sector-divided turbine housing further defining a plurality of separate angular sector passageways each of which occupies a fractional part of a circumference surrounding the turbine wheel, the angular sector passageways succeeding one another in a circumferential direction, each angular sector passageway being supplied with exhaust gas by a respective one of the plurality of exhaust gas inlets, each angular sector passageway being characterized by a convergent cross-section that spirals inward and converges to accelerate the exhaust gas;

the turbine housing assembly defining a separate sector outlet for each angular sector passageway through which the respective exhaust gas stream is fed into an inlet side of the turbine wheel generally in an axial direction of the turbine wheel, wherein the sector outlets are formed at least in part by the heat shroud.

2. The axial turbine of claim 1 , wherein the heat shroud has a radial flange portion and, connected to the radial flange portion, a plurality of dividing walls that extend radially inwardly and circumferentially in a spiral fashion so as to divide the separate sector outlets from one another.

3. The axial turbine of claim 2 , wherein the heat shroud has a tapering portion that extends axially from the radial flange portion and decreases in radius toward the inlet side of the turbine wheel to form a radially inner boundary of an axial inlet to the turbine wheel.

4. The axial turbine of claim 1 , wherein an outer diameter of the turbine wheel, as defined by radially outer tips of the blades, is generally constant from the inlet side to an outlet side of the turbine wheel.

5. The axial turbine of claim 1 , wherein there are two said exhaust gas inlets and two said angular sector passageways, each of the angular sector passageways occupying substantially 180 degrees along the circumference.

6. A turbocharger, comprising:

an axial turbine, the axial turbine having no inlet stator, and comprising:

an axial turbine wheel comprising a hub and a plurality of blades extending generally radially outward from the hub, and a turbine housing assembly that houses the turbine wheel;

the turbine housing assembly comprising a sector-divided turbine housing and a separately formed heat shroud, the sector-divided turbine housing defining a plurality of separate exhaust gas inlets into the turbine housing, each exhaust gas inlet for receiving a separate exhaust gas stream from an internal combustion engine, the sector-divided turbine housing further defining a plurality of separate angular sector passageways each of which occupies a fractional part of a circumference surrounding the turbine wheel, the angular sector passageways succeeding one another in a circumferential direction, each angular sector passageway being supplied with exhaust gas by a respective one of the plurality of exhaust gas inlets, each angular sector passageway being characterized by a convergent cross-section that spirals inward and converges to accelerate the exhaust gas;

the turbine housing assembly defining a separate sector outlet for each angular sector passageway through which the respective exhaust gas stream is fed into an inlet side of the turbine wheel generally in an axial direction of the turbine wheel, wherein the sector outlets are formed at least in part by the heat shroud;

a compressor comprising a compressor wheel mounted in a compressor housing, the compressor housing defining a compressor discharge volute receiving pressurized air from the compressor wheel;

a shaft having one end affixed to the compressor wheel and an opposite end affixed to the turbine wheel; and

a center housing assembly connected between the turbine housing assembly and the compressor housing, the center housing assembly containing bearings for the shaft.

7. The turbocharger of claim 6 , wherein the heat shroud has a radial flange portion and, connected to the radial flange portion, a plurality of dividing walls that extend radially inwardly and circumferentially in a spiral fashion so as to divide the separate sector outlets from one another.

8. The turbocharger of claim 7 , wherein the heat shroud has a tapering portion that extends axially from the radial flange portion and decreases in radius toward the inlet side of the turbine wheel to form a radially inner boundary of an axial inlet to the turbine wheel.

9. The turbocharger of claim 6 , wherein an outer diameter of the turbine wheel, as defined by radially outer tips of the blades, is generally constant from the inlet side to an outlet side of the turbine wheel.

10. The turbocharger of claim 6 , wherein there are two said exhaust gas inlets and two said angular sector passageways, each of the angular sector passageways occupying substantially 180 degrees along the circumference.

Assignments (7)