Turbine assembly with semi-divided nozzle and half-collar piston
View Patent ↗A turbine assembly for a turbocharger includes a variable nozzle formed by a sliding half-collar piston. A first-stage nozzle has a plurality of first vanes supported by a first nozzle ring and extending axially therefrom. A second-stage nozzle has a second nozzle ring connected to the ends of the first vanes, and a plurality of second vanes extending axially therefrom. The piston regulates flow through the second-stage nozzle, while the first-stage nozzle remains open when the piston is fully closed. The second nozzle ring at least partially divides the first vanes from the second vanes. The half-collar piston includes recesses that receive the second vanes and only partially surround the girth of each second vane.
1. A turbine assembly for a turbocharger, comprising:
a turbine housing defining a bore extending along an axial direction and defining a chamber surrounding the bore for receiving exhaust gas, the chamber being open to the bore at a radially inner side of the chamber;
a first-stage nozzle comprising a first nozzle ring mounted in the turbine housing and a plurality of circumferentially spaced first vanes each having a first end connected to the first nozzle ring and each extending generally parallel to the axial direction from the first end to an opposite second end;
a second-stage nozzle comprising a second nozzle ring connected to the second ends of the first vanes and a plurality of circumferentially spaced second vanes each having a first end connected to the second nozzle ring and each extending generally parallel to the axial direction from the first end to an opposite second end, wherein the second nozzle ring divides only part of the second end of each first vane from part of the first end of each second vane; and
a tubular piston disposed in the bore of the turbine housing, the piston being axially slidable relative to the turbine housing along the radially inner side of the chamber such that the piston blocks a variable portion of an axial length of the second-stage nozzle depending on axial position of the piston, the piston in a closed position thereof substantially closing the second-stage nozzle while the first-stage nozzle remains open such that exhaust gas flows to the turbine wheel via the first-stage nozzle, the piston in non-closed positions permitting flow through the second-stage nozzle.
2. The turbine assembly of claim 1 , wherein the second vanes differ in configuration from the first vanes.
3. The turbine assembly of claim 1 , wherein the piston has a radially outer surface in which recesses are formed for respectively receiving the second vanes with a radially inwardly facing surface of each second vane confronting a radially outwardly facing wall of each respective recess.
4. The turbine assembly of claim 3 , wherein the recesses in the piston surround only a fractional part of a girth of each second vane.
5. The turbine assembly of claim 4 , wherein the recesses surround less than about three-quarters of the girth of each second vane.
6. The turbine assembly of claim 3 , wherein the second end of each second vane comprises a free end, and wherein the second ends of the second vanes abut or nearly abut a wall of the piston in the closed position of the piston.
7. The turbine assembly of claim 1 , wherein the second end of each second vane comprises a free end axially spaced from the downstream wall, and wherein the second ends of the second vanes abut or nearly abut a wall of the piston in the closed position of the piston.
8. The turbine assembly of claim 1 , wherein the second nozzle ring divides a leading edge region of the second end of each first vane from a leading edge region of the first end of each second vane, and wherein trailing edge regions of the first and second vanes are not divided by the second nozzle ring.
9. The turbine assembly of claim 1 , wherein the piston has a radially outer surface in which recesses are formed for respectively receiving the second vanes with a radially inwardly facing surface of each second vane confronting a radially outwardly facing wall of each respective recess.
10. The turbine assembly of claim 9 , wherein the piston includes an end surface facing generally axially toward the second nozzle ring and having recesses for receiving portions of the second nozzle ring.
11. The turbine assembly of claim 9 , wherein the recesses in the piston surround only a fractional part of a girth of each second vane.
12. The turbine assembly of claim 11 , wherein the recesses surround less than about three-quarters of the girth of each second vane.
13. The turbine assembly of claim 9 , wherein the second end of each second vane comprises
a free end axially spaced from the downstream wall, and wherein the second ends of the second vanes abut a wall of the piston in the closed position of the piston.
14. The turbine assembly of claim 1 , wherein the second vanes engage the piston in a manner substantially preventing rotation of the piston about an axis thereof.