Vane and throat shaping

• US 7,255,530 B2
• Filed: 12/08/2004
• Issued: 08/14/2007
• Est. Priority Date: 12/12/2003
• Status: Active Grant

• Current Assignee: Garrett Transportation I Inc. (Garrett Motion, Inc.)
• Original Assignee: Honeywell International Inc.
• Inventors: Vogiatzis, Costas, Ghizawi, Nidal A.
• Primary Examiner(s): Look; Edward K.
• Assistant Examiner(s): Hanan; Devin
• Application Number:
  US11/007,769
• Publication Number:
  US 20050220616A1
• Time in Patent Office: 979 Days
• Field of Search: 415/159, 415/160, 415/162, 415/163, 415/164
• US Class Current: 415/159
• 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: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: F05D 2250/70 Shape

Abstract

An exemplary vane for a radial turbine assembly includes a hub end and a shroud end that define vane height, a leading edge and a trailing edge that define vane length along a camberline and an inner surface and an outer surface that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of the vane, vane length and vane thickness vary with respect to vane height. Other exemplary vanes, assemblies, methods, etc., are also disclosed.

Claims

1. A vane for a radial turbine assembly, the vane comprising:

a hub end and a shroud end that define vane height with respect to a radial turbine;

an arcuate leading edge and an arcuate trailing edge that define vane length and that define a minimum vane length along a camberline, the minimum vane length located between the hub end and the shroud end; and

an inner surface and an outer surface that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness;

wherein, for at least a portion of the vane, vane length and vane thickness vary with respect to vane height.

2. The vane of claim 1 further comprising a vane pivot axis extending from the hub end to the shroud end.

3. The vane of claim 2 further comprising a post positioned substantially along the pivot axis.

4. The vane of claim 2 further comprising a prong to facilitate rotation of the vane about the pivot axis.

5. The vane of claim 1 further comprising an identical vane positioned adjacent the vane to thereby form a throat between the trailing edge of the vane and the inner surface of the identical vane wherein, for at least a portion of the throat, throat width varies with respect to vane height.

6. The vanes of claim 5 wherein the throat has a maximum width between the hub end and the shroud end.

7. A variable geometry mechanism for a radial turbine, the mechanism comprising:

a plurality of vanes wherein each vane includes

a hub end and a shroud end that define vane height with respect to a radial turbine,

an arcuate leading edge and an arcuate trailing edge that define vane length and that define a minimum vane length along a camberline, the minimum vane length located between the hub end and the shroud end, and

an inner surface and an outer surface that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of each vane, vane length and vane thickness vary with respect to vane height and wherein adjacent vanes form a throat defined by a trailing edge of one vane and an inner surface of another vane; and

adjustment means for adjusting the plurality of vanes.

8. The variable geometry mechanism of claim 7 wherein each throat has a maximum width located between the hub ends and the shroud ends of adjacent vanes.

9. The variable geometry mechanism of claim 7 wherein the hub ends and the shroud ends comprise substantially crescent shapes.

10. The variable geometry mechanism of claim 7 wherein the outer surfaces are convex and the inner surfaces are concave.

11. The variable geometry mechanism of claim 7 wherein stagger angle of each vane has a minimum located between the hub end and the shroud end of the vane.

12. A turbine assembly comprising:

a radial turbine wheel having an axis of rotation; and

a variable geometry mechanism that comprises

a plurality of vanes wherein each vane includes

a hub end and a shroud end that define vane height parallel to the axis of rotation of the turbine wheel,

an arcuate leading edge and an arcuate trailing edge that define vane length and that define a minimum vane length along a camberline, the minimum vane length located between the hub end and the shroud end, and

an outer surface substantially facing away from the turbine wheel and an inner surface substantially facing the turbine wheel that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of each vane, vane length and vane thickness vary with respect to vane height and wherein adjacent vanes form a throat defined by a trailing edge of one vane and an inner surface of another vane wherein the throat has a maximum width between the hub end and the shroud end; and

adjustment means for adjusting the plurality of vanes to thereby adjust throats with respect to the turbine wheel.

13. A turbine assembly comprising:

a radial turbine wheel having an axis of rotation; and

a variable geometry mechanism that comprises

a plurality of vanes wherein each vane includes

a hub end and a shroud end that define vane height parallel to the axis of rotation of the turbine wheel,

an arcuate leading edge and an arcuate trailing edge that define vane length and that define a minimum vane length along a camberline, the minimum vane length located between the hub end and the shroud end, and

an outer surface substantially facing away from the turbine wheel and an inner surface substantially facing the turbine wheel that extend from the hub end to the shroud end and meet at the leading edge and the trailing edge and that define vane thickness wherein, for at least a portion of each vane, vane stagger angle varies with respect to vane height and wherein adjacent vanes form a throat defined by a trailing edge of one vane and an inner surface of another vane; and

adjustment means for adjusting the plurality of vanes to thereby adjust throats with respect to the turbine wheel.

14. The turbine assembly of claim 13 wherein vane height varies with respect to vane length along the camberline.

15. The turbine assembly of claim 13 wherein vane thickness varies with respect to vane height.

16. The turbine assembly of claim 13 wherein vane length along the camberline and vane thickness vary with respect to vane height.

17. The turbine assembly of claim 13 wherein the stagger angle comprises a modified stagger angle based in part on a pivot axis and a trailing edge of a vane.