Granted Patent B2

US 8,113,770 · App. 12/364,715 · Granted Feb 14, 2012

Abstract

Claims (22)

1. A turbine assembly for an exhaust gas-driven turbocharger having a variable nozzle, comprising:

a turbine housing defining at least part of a generally annular chamber extending circumferentially about a longitudinal axis of the turbine housing, the turbine housing defining a bore extending along the longitudinal axis;

a turbine wheel disposed in the turbine housing;

a nozzle passage leading from the chamber radially inwardly into the turbine wheel, the nozzle passage being defined between two walls spaced apart in a longitudinal direction; and

a variable nozzle assembly comprising:

a stator that is fixed in a rotational sense with respect to the turbine housing and that defines a plurality of circumferentially spaced fixed vanes extending into the nozzle passage, the stator defining a bypass opening that is exposed to exhaust gas within the chamber; and

a rotor that is rotational with respect to the turbine housing about the longitudinal axis, the rotor defining a bypass channel having an inlet and an outlet, the outlet being in fluid communication with the bore at a position spaced downstream from the nozzle passage with respect to flow of exhaust gas through the bore, and wherein the rotor is rotatable between a closed position in which the inlet is closed by the stator and an open position in which the inlet is aligned with the bypass opening in the stator such that exhaust gas flows from the chamber through the bypass opening and through the bypass channel into the bore, bypassing the turbine wheel.

2. The turbine assembly of claim 1 , wherein the stator includes a tubular portion that extends circumferentially about the longitudinal axis and defines a plurality of circumferentially spaced bypass openings, and the rotor includes a tubular portion that extends circumferentially about the longitudinal axis and defines a plurality of circumferentially spaced bypass channels that are closed by the stator when the rotor is in the closed position and that are respectively aligned with the bypass openings when the rotor is in the open position.

3. The turbine assembly of claim 2 , wherein the rotor defines a plurality of circumferentially spaced movable vanes each of which overlaps in a circumferential direction with a respective one of the fixed vanes to form a composite vane having a leading-edge portion defined by the fixed vane and a trailing-edge portion defined by the movable vane.

4. The turbine assembly of claim 3 , wherein the movable vanes have a maximum degree of overlap with the fixed vanes in the open position of the rotor, and have a minimum degree of overlap with the fixed vanes in the closed position of the rotor.

5. The turbine assembly of claim 3 , further comprising a stop for limiting rotation of the rotor between predetermined closed and open positions.

6. The turbine assembly of claim 5 , wherein the stop comprises a projection from one of the rotor and stator that is disposed in an opening defined in the other of the rotor and stator, the projection abutting one end of the opening to define the open position of the rotor and abutting an opposite end of the opening to define the closed position of the rotor.

7. The turbine assembly of claim 1 , wherein the stator includes an integral locating projection that engages a receptacle defined in the turbine housing so as to place the stator in a predetermined rotational orientation with respect to the turbine housing.

8. The turbine assembly of claim 1 , further comprising an actuator linkage coupled with the rotor for imparting rotational movement to the rotor.

9. The turbine assembly of claim 8 , wherein the actuator linkage includes a rotary member that extends generally radially inwardly through a wall of the turbine housing and is rotational about a generally radial axis, and an arm that has one end attached to the rotary member and an opposite end engaged with the rotor, such that rotation of the rotary member about the generally radial axis causes the arm to pivot and impart rotational movement to the rotor.

10. The turbine assembly of claim 2 , wherein the tubular portion of the rotor has a radially outer surface and a radially inner surface, and the tubular portion of the stator has a radially inner surface that contacts the radially outer surface of the tubular portion of the rotor and forms a bearing surface for the rotor.

11. The turbine assembly of claim 10 , wherein the tubular portion of the stator includes a generally conical portion at an upstream end of the stator and a generally cylindrical portion at a downstream end of the stator, and the tubular portion of the rotor correspondingly includes a generally conical portion at an upstream end of the rotor and a generally cylindrical portion at a downstream end of the rotor, and wherein the bypass openings are defined in the conical portion of the stator and the inlets of the bypass channels are defined in the conical portion of the rotor.

12. The turbine assembly of claim 10 , wherein an upstream portion of each bypass opening extends in a direction having a circumferential component.

13. The turbine assembly of claim 10 , wherein the outlets of the bypass channels are defined in an end surface of the rotor that extends between the radially outer and inner surfaces at the downstream end of the rotor.

14. The turbine assembly of claim 13 , wherein the bypass channels in the rotor are configured to discharge exhaust gas from the outlets of the bypass channels into the bore in the turbine housing in a generally axial direction.

15. The turbine assembly of claim 1 , wherein the stator has a radially outer surface that defines part of the generally annular chamber, the turbine housing defining the remainder of the generally annular chamber.

16. The turbine assembly of claim 15 , wherein one of the walls defining the nozzle passage is constituted entirely by the stator and the rotor.

Assignments (6)