Vanes for directing exhaust to a turbine wheel
View Patent ↗A vane for a turbine assembly of a turbocharger includes an airfoil that has a pair of flow surfaces disposed between a hub end and a shroud end and a leading edge and a trailing edge where the airfoil further includes a non-zero sweep angle, a non-zero lean angle, a non-zero twist angle or any two or more combinations thereof. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
1. A vane for a turbine assembly of a turbocharger, the vane comprising:
an airfoil that comprises a pair of flow surfaces disposed between a hub end and a shroud end and a leading edge and a trailing edge; a negative sweep angle, a positive lean angle and a positive twist angle; and at least two inflection points along a camberline.
2. The vane of claim 1 further comprising at least three anti-nodes along a camberline.
3. The vane of claim 1 further comprising a post.
4. The vane of claim 3 wherein the post comprises a portion extending from the hub end and a portion extending from the shroud end.
5. The vane of claim 1 comprising the sweep angle defined by a point on the trailing edge or the leading edge at the hub end and a point on the trailing edge or the leading edge at the shroud end.
6. The vane of claim 1 comprising the lean angle defined by a point on one of the flow surfaces at the hub end and a point on the one of the flow surfaces at the shroud end.
7. The vane of claim 1 comprising the twist angle defined by a camberline of the hub end of the airfoil and a camberline of the shroud end of the airfoil.
8. The vane of claim 1 wherein the angles are approximately −17 degrees, approximately +9 degrees and approximately +2 degrees, respectively.
9. A vane for a turbine assembly of an exhaust gas turbocharger comprising: a vane, the vane comprising:
an airfoil that comprises a pair of flow surfaces disposed between a leading edge and a trailing edge wherein the airfoil further comprises positive and negative camber, at least two inflection points and at least three anti-nodes along a camberline that extends between the leading edge and the trailing edge.
10. The vane of claim 9 wherein a normalized length of the camberline ranges from 0 at the leading edge to 1 at the trailing edge and wherein at least one inflection point comprises a position of at least 0.75.
11. The vane of claim 9 wherein a normalized length of the camberline ranges from 0 at the leading edge to 1 at the trailing edge and wherein at least two of the anti-nodes comprise positions of less than 0.75.
12. The vane of claim 9 wherein a normalized length of the camberline ranges from 0 at the leading edge to 1 at the trailing edge and wherein the vane comprises three anti-nodes positioned at approximately 0.2, approximately 0.7 and approximately 0.9, respectively.
13. The vane of claim 9 wherein the anti-node closest to the trailing edge comprises the smallest magnitude.
14. The vane of claim 9 wherein an intermediate one of the anti-nodes comprises the greatest magnitude.
15. A turbocharger comprising:
a center housing disposed between a compressor and a variable geometry turbine wherein the variable geometry turbine comprises a plurality of vanes wherein each vane comprises an airfoil that comprises a pair of flow surfaces disposed between a leading edge and a trailing edge and wherein the airfoil further comprises positive and negative camber, at least two inflection points and at least three anti-nodes along a camberline that extends from the leading edge to the trailing edge.
16. A vane for a turbine assembly of a turbocharger, the vane comprising:
an airfoil that comprises a pair of flow surfaces disposed between a hub end and a shroud end and a leading edge and a trailing edge; a negative sweep angle, a positive lean angle and a positive twist angle; and at least three anti-nodes along a camberline.
17. The vane of claim 16 further comprising a post.
18. The vane of claim 17 wherein the post comprises a portion extending from the hub end and a portion extending from the shroud end.
19. A vane for a turbine assembly of a turbocharger, the vane comprising:
an airfoil that comprises a pair of flow surfaces disposed between a hub end and a shroud end and a leading edge and a trailing edge; a negative sweep angle of approximately −17 degrees; a positive lean angle of approximately +9 degrees; and a positive twist angle of approximately +2 degrees.
20. The vane of claim 19 further comprising a post.
21. The vane of claim 20 wherein the post comprises a portion extending from the hub end and a portion extending from the shroud end.