Variable geometry turbine

• US 20050260067A1
• Filed: 04/08/2005
• Published: 11/24/2005
• Est. Priority Date: 04/08/2004
• Status: Active Grant

• Current Assignee: Holset Engineering Co Ltd. (Cummins Incorporated)
• Original Assignee: Holset Engineering Co Ltd. (Cummins Incorporated)
• Inventors: Parker, John Frederick, Garrett, Stephen Edward
• Granted Patent: US 7,628,580 B2
• Time in Patent Office: Days
• US Class Current: 415/160
• CPC Class Codes: F01D 17/165 for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F02C 6/12 Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: F05D 2250/324 divergent
• CPC Class Codes: F05D 2250/52 Outlet

Abstract

A variable geometry turbine comprises a turbine housing defining a turbine chamber within which a turbine wheel is mounted for rotation about a turbine axis. The turbine chamber has a radially extending annular inlet defined between facing annular side walls of the turbine housing, the annular inlet having an axial width defined between the annular side walls. An annular array of swing vanes is mounted within the inlet, each vane having an axial length extending across the inlet between chordal vane edges lying adjacent respective annular side walls of the inlet, and a chordal length defined between leading and trailing vane edges extending across the inlet. Means are provided for pivoting each vane about a respective pivot axis extending across the inlet to adjust the effective cross-section area of the annular inlet. Each vane is pivotable between a first position in which the area of the inlet is a minimum and a second position in which the area of the inlet is a maximum. At least one of said annular side walls is configured so that clearance between the side wall and at least a portion of the adjacent chordal edge of each vane varies in a predetermined manner as the vane moves between positions intermediate the first and second vane positions.

Claims

1. A variable geometry turbine comprising:

a turbine housing defining a turbine chamber within which a turbine wheel is mounted for rotation about a turbine axis;

the turbine chamber having a radially extending annular inlet defined between facing annular side walls of the turbine housing, the annular inlet having an axial width defined between said annular side walls;

an annular array of swing vanes mounted within the inlet, each vane having an axial length extending across the inlet between chordal vane edges lying adjacent respective annular side walls of the annular inlet, and a chordal length defined between leading and trailing vane edges extending across the inlet upstream and downstream respectively having regard to direction of flow through the turbine;

means for pivoting each vane about a respective pivot axis extending across the inlet to adjust the effective cross-section area of the annular inlet, each vane being pivotable between a first position in which the area of the inlet is a minimum and a second position in which the area of the inlet is a maximum;

wherein at least one of said annular side walls is configured so that clearance between said side wall and at least a portion of the adjacent chordal edge of each vane varies in a predetermined manner as the vane moves between positions intermediate said first and second vane positions.

2. A turbine according to claim 1, wherein said at least one annular side wall is configured so that the clearance between the wall and the adjacent chordal edge of each vane is a minimum when each vane is in said first position.

3. A turbine according to claim 1, wherein said at least one annular side wall is configured so that the clearance between the side wall and the adjacent chordal edge of each vane is substantially constant along the vane edge when the vanes are in said first position.

4. A turbine according to claim 1, wherein the or each annular side wall is configured so that the axial width of the inlet increases from a minimum width to a maximum width with decreasing radius.

5. A turbine according to claim 4, wherein the rate of increase in axial width of the inlet with decreasing radius varies with decreasing radius.

6. A turbine according to claim 4, wherein the axial width of the inlet increases from a radial position corresponding to the radial position of the trailing edge of each vane when each vane is at a first intermediate position between said first and second positions.

7. A turbine according to claim 4, wherein the variation in axial width of the annular inlet begins at a radius smaller than the radial position of the trailing edge of each vane when in said first position.

8. A turbine according to claim 4, wherein the or each side wall is axisymmetrically contoured to produce said variation in axial width of the annular inlet.

9. A turbine according to claim 8, wherein the or each annular side wall is axisymmetrically tapered.

10. A turbine according to claim 9, wherein said taper is linear.

11. A turbine according to claim 9, wherein said taper is non-linear.

12. A turbine according to claim 4, wherein said at least one annular side wall is provided with a respective indentation for each vane, the indentation being formed in a portion of the surface of the annular wall member across which the respective vane sweeps in moving between said first and second positions, the indentation providing a gas leakage path around the adjacent vane chordal edge when the vane is at positions intermediate said first and second position corresponding to the location of the indentation.

13. A turbine according to claim 12, wherein each indentation has the same size and shape.

14. A turbine according to claim 12, wherein the width of each indentation in a circumferential direction relative to the axis of the turbine varies with radius relative to the axis of the turbine.

15. A turbine according to claim 12, wherein the axial depth of each indentation varies with radius relative to the axis of the turbine.

16. A turbine according to claim 12, wherein each indentation is confined to a radial region of the respective annular side wall defined between the radial position of the trailing edge of each vane when each vane is a first intermediate position between said first and second positions, and an inner radial edge of the respective annular wall member.

17. A turbine according to claim 12, wherein both of said annular side walls are provided with said indentations.

19. A turbine according to claim 2, wherein said at least one annular side wall is configured so that the clearance between the side wall and the adjacent chordal edge of each vane is substantially constant along the vane edge when the vanes are in said first position.

20. A turbine according to claim 2, wherein said at least one annular side wall is provided with a respective indentation for each vane, the indentation being formed in a portion of the surface of the annular wall member across which the respective vane sweeps in moving between said first and second positions, the indentation providing a gas leakage path around the adjacent vane chordal edge when the vane is at positions intermediate said first and second position corresponding to the location of the indentation.

21. A turbine according to claim 2, wherein the or each annular side wall is configured so that the axial width of the inlet increases from a minimum width to a maximum width with decreasing radius.

18. (canceled)