Nozzle for partitioned volute
An assembly can include an exhaust gas turbine housing including an inner wall and an outer wall that define a first exhaust gas channel and a second exhaust gas channel to a turbine wheel space where the inner wall includes an inner wall end at the turbine wheel space and the outer wall includes an outer wall end at the turbine wheel space; a first flow body disposed adjacent to the inner wall end; a second flow body disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle vanes that define nozzle throats that direct flow of exhaust gas from at least one of the exhaust gas channels to the turbine wheel space, where at least one of the first flow body and the second flow body includes a concave trailing surface that is defined in part by an arc of a circle.
1. An assembly comprising:
an exhaust gas turbine housing that comprises an inner wall and an outer wall that define a first exhaust gas channel and a second exhaust gas channel to a turbine wheel space wherein the inner wall comprises an inner wall end at the turbine wheel space and the outer wall comprises an outer wall end at the turbine wheel space;
a first flow body disposed adjacent to the inner wall end;
a second flow body disposed adjacent to the outer wall end; and
at least one set of adjustable variable geometry nozzle vanes that define nozzle throats that direct flow of exhaust gas from at least one of the exhaust gas channels to the turbine wheel space,
wherein at least one of the first flow body and the second flow body comprises a concave trailing surface that is defined in part by an arc of a circle.
2. The assembly of claim 1 , wherein the first flow body and the second flow body are fixed.
3. The assembly of claim 1 , wherein the inner wall end forms a first tongue and wherein the first flow body is adjacent to the first tongue.
4. The assembly of claim 1 , wherein the outer wall end forms a second tongue and wherein the second flow body is adjacent to the second tongue.
5. The assembly of claim 1 , wherein the circle is centered on a pivot axis of one of the adjustable variable geometry vanes.
6. The assembly of claim 1 , wherein the circle comprises a radius that is greater than a radius swept by a leading edge of one of the adjustable variable geometry nozzle vanes in transitioning from a closed position to an open position.
7. The assembly of claim 1 , wherein the first flow body and the second flow body comprises a height approximately equal to a vane height.
8. The assembly of claim 1 , wherein the number of the adjustable variable geometry nozzle vanes is greater than 5.
9. The assembly of claim 1 , wherein the number of the adjustable variable geometry nozzle vanes is an odd number.
10. The assembly of claim 1 , wherein the first flow body comprises a leading surface, the concave trailing surface, and a first airfoil surface and a second airfoil surface that extend between the leading surface an the concave trailing surface.
11. The assembly of claim 10 , wherein the concave trailing surface comprises a first airfoil surface and a second airfoil surface end adjacent to the second airfoil surface.
12. The assembly of claim 11 , wherein the first airfoil surface end and the second airfoil surface end define an overlap pivot angle range for a leading edge of a respective one of the adjustable variable geometry nozzle vanes.
13. The assembly of claim 12 , wherein the overlap pivot angle range is less than a total pivot angle range of the leading edge of the respective one of the adjustable variable geometry nozzle vanes.
14. The assembly of claim 13 , wherein the overlap pivot angle range is greater than 50 percent of the total pivot angle range and less than 80 percent of the total pivot angle range.
15. The assembly of claim 13 , wherein the overlap pivot angle range is offset toward a closed position of the total pivot angle range.
16. The assembly of claim 11 , wherein second airflow surface end comproses a chamfer that defines a bypass clearance with respect to a leading edge of a corresponding one of the adjustable variable geometry nozzle vanes.
17. The assembly of claim 16 , wherein the first airflow surface end defines a clearance with respect to the leading edge of the corresponding one of the adjustable variable geometry nozzle vanes, wherein the bypass clearance is greater than the clearance.
18. The assembly of claim 16 , wherein the bypass clearance reduces pulsation pressure stress on an actuator for at the least one set of adjustable variable geometry nozzle vanes.