Multiple airfoil vanes
View Patent ↗A vane for a turbine assembly of a turbocharger includes a first airfoil that includes a length between a leading edge and a trailing edge, a second airfoil that includes a length between a leading edge and a trailing edge where the length of the first airfoil optionally differs from the length of the second airfoil, and one or more intra-vane throats defined at least in part by the first airfoil and the second airfoil. 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:
a first airfoil that comprises a length between a leading edge and a trailing edge;
a second airfoil that comprises a length between a leading edge and a trailing edge;
one or more intra-vane throats defined at least in part by both the first airfoil and the second airfoil; and
a post connected to the first airfoil and the second airfoil for pivoting the vane as a unit.
2. The vane of claim 1 wherein the vane comprises a single intra-vane throat.
3. The vane of claim 1 wherein the vane comprises two intra-vane throats.
4. The vane of claim 3 further comprising a connector that connects the first airfoil and the second airfoil and separates the two intra-vane throats.
5. The vane of claim 1 wherein the post comprises a post axis and wherein one of the airfoils comprises an offset from the post axis.
6. The vane of claim 5 wherein the other airfoil is centered on the post axis.
7. The vane of claim 1 wherein the length of the first airfoil differs from the length of the second airfoil.
8. The vane of claim 1 wherein the airfoils comprise convex inner airfoil surfaces.
9. The vane of claim 8 wherein the convex inner airfoil surfaces define, at least in part, the one or more throats.
10. The vane of claim 1 wherein the airfoils comprise concave outer airfoil surfaces.
11. The vane of claim 1 comprising a connector that connects the first airfoil to the second airfoil and fixes position of the first airfoil with respect to position of the second airfoil to thereby fixedly shape the one or more intra-vane throats.
12. A variable nozzle turbine assembly comprising:
a plurality of vanes that define inter-vane throats wherein each vane comprises
a first airfoil that comprises a length between a leading edge and a trailing edge;
a second airfoil that comprises a length between a leading edge and a trailing edge;
one or more intra-vane throats defined at least in part by the first airfoil and the second airfoil; and
an axel connected to the first airfoil and the second airfoil for pivoting the vane as a unit.
13. The variable nozzle turbine assembly of claim 12 wherein the length of the second airfoil exceeds the length of the first airfoil and wherein the trailing edges of the second airfoils define at least in part the inter-vane throats.
14. The variable nozzle turbine assembly of claim 12 wherein pivotable adjustment of the plurality of vanes alters shape of the inter-vane throats.
15. The variable nozzle turbine assembly of claim 12 further comprising an annular ring that comprises openings configured for receipt of the axels.
16. The variable nozzle turbine assembly of claim 12 further comprising a turbine wheel, the turbine wheel configured with blades to match the flow dynamics of the plurality of vanes.
17. The variable nozzle turbine assembly of claim 12 comprising a connector that connects the first airfoil to the second airfoil and fixes position of the first airfoil with respect to position of the second airfoil to thereby fixedly shape the one or more intra-vane throats.
18. A method comprising:
providing a plurality of multiple airfoil vanes wherein each vane comprises at least one intra-vane throat and wherein adjacent vanes define inter-vane throats; and
pivotably adjusting the plurality of vanes to alter only shape of the inter-vane throats wherein the pivotably adjusting comprises rotating a post connected to the multiple airfoils of each of the vanes to pivot each vane as a unit.
19. The method of claim 18 further comprising closing the inter-vane throats by pivotably adjusting the plurality of vanes wherein the closing effectively closes the intra-vane throats.
20. The method of claim 18 further comprising providing a turbine wheel with improved efficiency, the improved efficiency resulting from blades configured for flow dynamics associated with the multiple airfoil vanes.
21. The method of claim 18 wherein each vane comprises a connector that connects its multiple airfoils and fixes positions of its multiple airfoils with respect to each other to thereby fixedly shape its at least one intra-vane throat.
22. A vane for a turbine assembly of a turbocharger, the vane comprising:
a first airfoil that comprises a length between a leading edge and a trailing edge;
a second airfoil that comprises a length between a leading edge and a trailing edge; and
two intra-vane throats defined at least in part by both the first airfoil and the second airfoil.
23. The vane of claim 22 further comprising a connector that connects the first airfoil and the second airfoil and separates the two intra-vane throats.