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US 2019/0292924 A1Published application
Vane arrangement for a turbo-machine
AssigneeCummins Inc.
InventorsSimon David Moore, Matthew William Edwards, Stephen David Hughes, George E. Sanford, Nandakishore Arcot Madhusudan
Life of this patent
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Abstract
A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a close connection can be formed between the vane and the slot to inhibit leakage of gas between the vane and the slot surface.
Claims15
A turbine having:
- a turbine housing defining a gas inlet;
- a turbine wheel positioned for rotation within the turbine housing about an axis;
- a ring-shaped shroud defining a plurality of slots, and encircling the axis;
- 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, each of the vanes being spaced from the axis by a nozzle radius;
- and
- a coupling mechanism for coupling the shroud to the nozzle ring;
- 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, (ii) an opposed vane inner surface facing an inner surface of the corresponding slot, and (iii) 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 80% 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.
5 more elements
A turbocharger comprising a turbine, the turbine having:
- a turbine housing defining a gas inlet;
- a turbine wheel positioned for rotation with the turbine housing about an axis;
- a ring-shaped shroud defining a plurality of slots and encircling the axis;
- 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, each of the vanes being spaced from the axis by a nozzle radius;
- and
- a coupling mechanism for coupling the shroud to the nozzle ring;
- 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, (ii) an opposed vane innser surface facing an inner surface of the corresponding slot, and (iii) a median line between the vane inner surface and the vane outer surface extending from a first endof the vane to a second end of the vane;
- the vane surface including a conformal portion, extending along at least 80% 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.
5 more elements
Dependencies are inferred from the claim text.