Vanes and shrouds for a turbo-machine

Patent metadata

Field	Value
Publication number	US-11697997-B2
Application number	US-202217728855-A
Country	US
Kind code	B2
Filing date	Apr 25, 2022
Priority date	May 15, 2018
Publication date	Jul 11, 2023
Grant date	Jul 11, 2023

Abstract

A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

First claim

What is claimed is:

1. A turbine comprising:
(i) a turbine wheel,
(ii) a turbine housing for defining a chamber for receiving the turbine wheel for rotation of the turbine wheel about an axis, the turbine housing further defining a gas inlet, and an annular inlet passage from the gas inlet to the chamber,
(iii) a ring-shaped shroud defining a plurality of slots and encircling the axis;
(iv) a nozzle ring supporting a plurality of vanes which extend from the nozzle ring parallel to the axis, and project through respective ones of the slots, the shroud and nozzle ring being positioned on opposite sides of the inlet passage, one of the shroud and the nozzle ring being rotatable relative to the turbine housing about the axis by at least 0.1 degree; and
(v) a rotation mechanism for, in use, rotating the one of the shroud and nozzle ring around the axis.

2. The turbine according to claim 1 in which the other of the shroud and nozzle ring is angularly rotatable about the axis with respect to the housing by an amount less than 0.1 degree.

3. The turbine according to claim 1 in which the nozzle ring and shroud are relatively rotatable about the axis of the turbine by at least 0.3 degrees.

4. The turbine according to claim 1 , further comprising an actuator for displacing one of the nozzle ring or shroud axially with respect to the other, the actuator being mounted on the turbine housing and coupled to the one of the nozzle ring and shroud by a coupling mechanism which permits relative rotation of the one of the nozzle ring or shroud with respect to the actuator about the axis by at least 0.1 degree.

5. The turbine according to claim 4 in which the coupling mechanism includes at least one guide coupling, each guide coupling including:
(i) a first element fast with either the actuator or the one of the nozzle ring or shroud, and
(ii) a second element fast with the other of the actuator or the one of the nozzle ring and shroud, and being arranged to move within a limited region defined by the first element, the region being sized to permit the second element to rotate circumferentially about the axis relative to the first element by at least 0.1 degrees.

6. The turbine according to claim 1 in which the nozzle ring is rotatable relative to the turbine housing about the axis by at least 0.1 degree.

7. The turbine according to claim 1 in which the shroud is rotatable relative to the turbine housing about the axis by at least 0.1 degree, and the rotation mechanism comprises a plurality of gas interaction elements upstanding from a land surface of a face of the shroud, each gas interaction element including at least one wall surface arranged to develop a rotational force in use due to flow of the gas against the gas interaction element.

8. The turbine according to claim 7 , in which each gas interaction element is provided proximate to an edge of a respective one of the slots.

9. The turbine according to claim 8 in which, in use, each gas interaction element is proximate a suction portion of a slot surface of the respective slot, and defines a wall surface facing towards the respective slot and a wall surface facing away from the respective slot.

10. The turbine according to claim 9 in which no gas interaction element is provided proximate an edge of one of the slots which, in use, is a high pressure portion of the slot surface.

11. The turbine according to claim 7 in which each gas interaction element includes a wall surface which is an axial extension of a portion of an inwardly-facing surface of the slot.

12. The turbine according to claim 7 in which each gas interaction element is elongate.

13. The turbine according to claim 7 in which the gas interaction elements are connected together by rib elements upstanding from the face of the shroud.

14. The turbine according to claim 1 , wherein each of the vanes is spaced from the axis by a nozzle radius;
each of the slots having an inwardly-facing slot surface, and each of the vanes having:
an axially-extending vane surface which includes (i) a vane outer surface facing an outer surface of the corresponding slot, and (ii) an opposed vane inner surface facing an inner surface of the corresponding slot, and
a median line between the vane inner surface and the vane outer surface extending from a first end of the vane to a second end of the vane;
the vane surface including a conformal portion, extending along at least 15% of the length of the median line, and facing a corresponding conformal portion of the slot surface, wherein, at room temperature, the respective profiles of the conformal portion of the vane surface and the conformal portion of the slot surface diverge from each other by no more than 0.35% of the nozzle radius.

15. The turbine according to claim 1 in which the shroud is retained on the turbine housing, the turbine further comprising an annular retaining ring provided on a radially-inward edge of the shroud, the retaining ring being positioned to obstruct gas from passing into the inlet passage from a side of the shroud away from the inlet passage.

16. A turbocharger comprising a turbine comprising:
(i) a turbine wheel,
(ii) a turbine housing for defining a chamber for receiving the turbine wheel for rotation of the turbine wheel about an axis, the turbine housing further defining a gas inlet, and an annular inlet passage from the gas inlet to the chamber,
(iii) a ring-shaped shroud defining a plurality of slots and encircling the axis;
(iv) a nozzle ring supporting a plurality of vanes which extend from the nozzle ring parallel to the axis, and project through respective ones of the slots, the shroud and nozzle ring being positioned on opposite sides of the inlet passage, one of the shroud and the nozzle ring being rotatable relative to the turbine housing about the axis by at least 0.1 degree; and
(v) a rotation mechanism for, in use, rotating the one of the shroud and nozzle ring around the axis.

17. A ring-shaped shroud defining a plurality of slots, the shroud being for installation in a turbine, the ring-shaped shroud comprising:
a plurality of gas interaction elements upstanding from a land surface of a face of the shroud, each gas interaction element including at least one wall surface, the shroud being for installation in a turbine comprising:
(i) a turbine wheel,
(ii) a turbine housing for defining a chamber for receiving the turbine wheel for rotation of the turbine wheel about an axis, the turbine housing further defining a gas inlet, and an annular inlet passage from the gas inlet to the chamber, and being configured for supporting the shroud with the shroud encircling the axis and rotatable relative to the turbine housing about the axis by at least 0.1 degree, and
(iii) a nozzle ring supporting a plurality of vanes which extend from the nozzle ring parallel to the axis, and project through respective ones of the slots,
wherein the at least one wall surface of each gas interaction element is configured to develop a rotational force in use due to flow of the gas against the gas interaction element.

18. The ring-shaped shroud according to claim 17 , in which each gas interaction element is provided proximate to an edge of a respective one of the slots.

19. The ring-shaped shroud according to claim 18 , in which each gas interaction element is elongate and includes a wall surface which is an axial extension of a portion of an inwardly-facing surface of the respective slot.

20. The ring-shaped shroud according to claim 17 in which the

Assignees

• Cummins Ltd

Inventors

• Edwards Matthew William
• Conlon Karl
• Moore Simon David
• Parry Christopher
• Sullivan Andrew
• Ghosh Paul
• Holden Mark R
• Sandford George E
• Madhusudan Nandakishore Arcot
• Hughes Stephen David
• Shaw Christopher J

Classifications

• F02B37/22

  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 title

• F01D17/143

  the shiftable member being a wall, or part thereof of a radial diffuser · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F05D2240/128

  Nozzles · CPC title