TURBINE ASSEMBLY

• US 20140178217A1
• Filed: 12/09/2013
• Published: 06/26/2014
• Est. Priority Date: 12/26/2012
• Status: Active Grant

• Current Assignee: Garrett Transportation I Inc. (Garrett Motion, Inc.)
• Original Assignee: Honeywell International Inc.
• Inventors: Kares, Vaclav
• Granted Patent: US 9,702,299 B2
• Time in Patent Office: Days
• US Class Current: 417/405
• 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 5/048 Form or construction
• CPC Class Codes: F02B 37/22 by varying cross-section of exhaust passages or air passages , e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits F02B37/24 takes precedence
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: F05D 2250/611 undulated
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

An assembly for a turbocharger can include a pinched nozzle cartridge that includes a base component, an insert component and vanes disposed at least in part between the base component and the insert component, where the insert component includes a shroud surface and an upper pinch profile, where the base component includes an annular surface that defines a turbine wheel opening and a lower profile and where the upper pinch profile and the lower profile form a pinched nozzle. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Claims

1. An assembly for a turbocharger comprising:

a pinched nozzle cartridge that comprises a base component, an insert component and vanes disposed at least in part between the base component and the insert component,

wherein the insert component comprises a shroud surface and an upper pinch profile,

wherein the base component comprises an annular surface that defines a turbine wheel opening and a lower profile and

wherein the upper pinch profile and the lower profile form a pinched nozzle.

2. The assembly of claim 1 wherein the vanes comprises a minimum open position and a maximum open position.

3. The assembly of claim 2 wherein for the maximum open position of the vanes, the vanes do not contact the pinch profile of the insert component.

4. The assembly of claim 2 wherein for the maximum open position of the vanes, trailing edges of the vanes overlap with the pinch profile.

5. The assembly of claim 4 wherein each of the vanes comprise a trailing edge chamfer that defines a clearance between each of the vanes and the pinch profile.

6. The assembly of claim 1 wherein the lower profile comprises a pinch profile.

7. The assembly of claim 2 further comprising a turbine wheel received via the turbine wheel opening of the base component wherein for the minimum open position of the vanes, the pinch profile directs exhaust passing through throats defined by the vanes axially downwardly toward leading edges of blades of the turbine wheel.

8. The assembly of claim 1 further comprising, disposed in the pinched nozzle cartridge via the turbine wheel opening, a turbine wheel that comprises a rotational axis, a hub and a plurality of blades that extend radially outwardly from the hub wherein each of the blades comprises a shroud edge and an inducer edge defined between an upper axial point and a lower axial point and wherein the upper pinch profile comprises a downward angle directed at the upper axial point of the inducer edge.

9. The assembly of claim 8 wherein the lower profile comprises a lower pinch profile that comprises an upward angle directed at the lower axial point of the inducer edge.

10. The assembly of claim 8 wherein each of the inducer edges of the turbine wheel comprises a scalloped edge.

11. The assembly of claim 10 wherein the scalloped edge comprises a maximum radius that exceeds a radius of the upper axial point and that exceeds a radius of the lower axial point.

12. The assembly of claim 1 wherein each of the vanes comprises a leading edge and a trailing edge and wherein, for a fully open orientation of the vanes, the trailing edges are displaced a radial distance from the pinched nozzle.

13. The assembly of claim 12 wherein the radial distance corresponds to a nozzle section of the pinched nozzle cartridge defined by substantially planar and parallel surfaces of the insert component and the base component.

14. The assembly of claim 1 further comprising a turbine housing that defines, in part, a volute.

15. The assembly of claim 14 wherein the insert component comprises a radial end that extends into the volute.

16. The assembly of claim 14 wherein a seal element is disposed between the insert component and the turbine housing.

17. The assembly of claim 1 wherein the base component is axially located between two components wherein one of the components applies a load to the base component.

18. A turbocharger comprising:

a center housing that comprises a through bore;

a compressor housing coupled to the center housing;

a turbine housing coupled to the center housing;

a bearing disposed in the bore of the center housing;

a shaft and turbine wheel assembly rotatably supported by the bearing in the bore of the center housing;

a compressor wheel coupled to the shaft and turbine wheel assembly; and

a pinched nozzle cartridge that comprises a base component, an insert component and vanes disposed at least in part between the base component and the insert component,

wherein the insert component comprises a shroud surface and an upper pinch profile,

wherein the base component comprises an annular surface that defines a turbine wheel opening and a lower profile and

wherein the upper pinch profile and the lower profile form a pinched nozzle.

19. The turbocharger of claim 18 wherein the turbine wheel comprises a rotational axis, a hub and a plurality of blades that extend radially outwardly from the hub wherein each of the blades comprises a shroud edge and an inducer edge defined between an upper axial point and a lower axial point and wherein the upper pinch profile comprises a downward angle directed at the upper axial point of the inducer edge.

20. The turbocharger of claim 19 wherein the each of the inducer edges of the turbine wheel comprises a scalloped edge.