Variable-geometry turbocharger with asymmetric divided volute for engine exhaust gas pulse optimization
View Patent ↗A turbine assembly for a variable-geometry turbocharger includes a turbine housing defining a divided volute having first and second scrolls, wherein the first scroll has a substantially smaller volume than the second scroll. The first scroll feeds exhaust gas to a first portion of a turbine wheel upstream of the throat of the wheel, while the second scroll feeds gas to a second portion of the wheel at least part of which is downstream of the throat. Flow from the second scroll is regulated by a sliding piston. The first scroll can be optimized for low-flow conditions such that the turbocharger can operate effectively like a small fixed-geometry turbocharger when the piston is closed. The turbine housing defines an inlet that is divided by a dividing wall into two portions respectively feeding gas to the two scrolls, a leading edge of the dividing wall being downstream of the inlet mouth.
1. A turbine assembly of a turbocharger for use with an internal combustion engine having two banks of engine cylinders, each bank having multiple engine cylinders exhausting exhaust gas into an exhaust gas discharge line separate from the exhaust gas discharge line for the other bank, the turbine assembly comprising:
a turbine housing having a bore extending in an axial direction and having a twin scroll surrounding the bore for receiving exhaust gas from the exhaust gas discharge lines of the engine, the twin scroll defining a first scroll and a second scroll that is substantially divided and separated from the first scroll, the first scroll located upstream of the second scroll with respect to an axial flow direction along which exhaust gas flows through the bore of the turbine housing;
a turbine wheel rotatably mounted in the bore, the turbine wheel comprising a hub and a plurality of circumferentially spaced blades joined to the hub and extending generally radially outwardly therefrom and terminating in blade tips, the blades defining blade passages therebetween, each blade passage having a throat at which a flow area of the blade passage is a minimum, a radial-axial projection of the blade tips defining a contour having a first portion located axially upstream of the throat and a second portion located axially downstream of the first portion, at least part of the second portion being located axially downstream of the throat;
an exhaust gas inlet defined by the turbine housing for admitting exhaust gas into the first and second scrolls, the exhaust gas inlet being configured to place both the first and second scrolls in fluid communication with both exhaust gas discharge lines from the engine;
the first scroll having an outlet portion configured to direct exhaust gas substantially only to the first portion of the contour; and
the second scroll having an outlet portion configured to direct exhaust gas substantially only to the second portion of the contour.
2. The turbine assembly of claim 1 , wherein the first portion of the contour has an axial B-width, and the outlet portion of the first scroll that directs exhaust gas to the turbine wheel has an axial width substantially equal to the B-width.
3. The turbine assembly of claim 1 , wherein the first scroll is free of guide vanes.
4. The turbine assembly of claim 1 , wherein the first scroll is substantially smaller in volume than the second scroll.
5. The turbine assembly of claim 4 , wherein the first scroll has a volume less than half that of the second scroll.
6. The turbine assembly of claim 1 , further comprising a variable-geometry mechanism structured and arranged to regulate a flow area leading from the second scroll into the turbine wheel.
7. The turbine assembly of claim 6 , wherein the variable-geometry mechanism is operable to substantially prevent any flow from the second scroll to the turbine wheel under operating conditions in which use of the first scroll alone is adequate.
8. The turbine assembly of claim 6 , wherein the variable-geometry mechanism comprises a tubular piston disposed in the bore of the turbine housing so as to be axially slidable therein, the turbine housing including a dividing wall separating the portions of the first and second scrolls that direct exhaust gas into the turbine wheel, and the piston being ridable between a closed position having an upstream end of the piston proximate the dividing wall so as to substantially close the outlet portion of the second scroll, and an open position having the upstream end of the piston spaced from the dividing wall such that substantially a full axial width of the outlet portion of the second scroll is uncovered by the piston.
9. The turbine assembly of claim 8 , further comprising a plurality of circumferentially spaced vanes disposed proximate the outlet portion of the second scroll for guiding exhaust gas into the turbine wheel.
10. The turbine assembly of claim 9 , the piston and vanes at least partially overlapping in a radial direction, the piston including recesses for receiving at least portions of the vanes.
11. The turbine assembly of claim 8 , wherein the contour includes a concave portion that is concave in a radially outward direction, and the piston has a radially inner surface a portion of which in radial-axial projection is convex in a radially inward direction and which is substantially complementary in shape to the concave portion of the contour.
12. The turbine assembly of claim 1 , wherein the turbine housing defines an inlet for receiving exhaust gas from the exhaust gas discharge lines of the engine and directing the exhaust gas along a flow direction into the first and second scrolls, the inlet having a dividing wall that divides a lengthwise portion of the inlet into first and second portions, the dividing wall having a leading edge spaced in the flow direction from a mouth of the inlet.