Turbine
There is provided a nozzle ring for a turbine of a turbocharger. The nozzle ring comprises: a nozzle dividing wall, at least on nozzle vane, and a circumferentially extending outer rim. The nozzle dividing wall extends generally perpendicular to a longitudinal axis of the nozzle ring. The at least one nozzle vane extends from the nozzle dividing wall and has a leading edge defining a first radius relative to the longitudinal axis. The circumferentially extending outer rim defines a second radius relative to the longitudinal axis. The ratio of the second radius to the first radius is at least around 1.05.
1. The nozzle ring for a turbine of a turbocharger, the nozzle ring comprising:
a nozzle dividing wall extending generally perpendicular to a longitudinal axis of the nozzle ring; and
at least one nozzle vane extending from the nozzle dividing wall and having a leading edge defining a first radius relative to the longitudinal axis;
wherein the nozzle dividing wall further comprises a circumferentially extending outer rim defining a second radius relative to the longitudinal axis; and
wherein the ratio of the second radius to the first radius is at least around 1.05, and wherein at least one of:
the nozzle dividing wall comprises an annular flange from which the at least one nozzle vane extends, and wherein the outer rim is radially outwards of
the annular flange relative to the longitudinal axis so as to facilitate widening of
the outer rim relative to the nozzle dividing wall and
the outer rim of the nozzle dividing wall comprises a circumferentially extending groove configured to receive a sealing element.
2. The nozzle ring according to claim 1 , wherein the ratio of the second radius to the first radius is at most 1.4.
3. The nozzle ring according to claim 1 , wherein the outer rim defines a first width and the annular flange defines a second width, the first width being wider than the second width.
4. The nozzle ring according to claim 3 , wherein the ratio of the first width to the second width is at most 3.
5. The nozzle ring according to claim 3 , wherein the ratio of the first width to the second width is at least 2.
6. The nozzle ring according to claim 1 , wherein the nozzle dividing wall comprises a neck that transitions in thickness between the outer rim and the annular flange.
7. The nozzle ring assembly comprising:
a nozzle ring according to any preceding claim , wherein the nozzle ring is a first nozzle ring; and
a second nozzle ring, the second nozzle ring comprising: a side wall extending generally perpendicular to the longitudinal axis; and at least one nozzle vane extending from the side wall;
wherein the at least one nozzle vane of the first nozzle ring is configured to engage a radially extending surface of a turbine housing such that the nozzle dividing wall of the first nozzle ring and the turbine housing define a first inlet passage therebetween, and
wherein the at least one nozzle vane of the second nozzle ring is configured to engage the nozzle dividing wall of the first nozzle ring such that the side wall of the second nozzle ring and the nozzle dividing wall of the first nozzle ring define a second inlet passage therebetween.
8. The nozzle ring assembly according to claim 7 , wherein the second nozzle ring comprises an axially extending flange defining a third radius relative to the longitudinal axis, and wherein the third radius is equal to or greater than the second radius.
9. The nozzle ring assembly according to claim 8 , wherein the axially extending flange comprises at least one circumferentially extending groove configured to receive a sealing element.
10. The turbine for a turbocharger, the turbine comprising:
a turbine wheel supported for rotation about a turbine axis;
a turbine housing comprising:
a first volute housing portion at least partially defining a first inlet volute;
a second volute housing portion at least partially defining a second inlet volute;
a housing dividing wall at least partially defining the first and second inlet volutes so as to separate the first inlet volute from the second inlet volute; and
a nozzle ring or nozzle ring assembly according to any preceding claim , the nozzle ring or nozzle ring assembly being arranged such that the longitudinal axis is collinear with the turbine axis;
wherein the nozzle dividing wall and the housing dividing wall are substantially aligned with one another along the turbine axis.
11. The turbine according to claim 10 , wherein the second volute housing portion further comprises an inner surface at least partially defining an aperture configured to receive the nozzle ring, and wherein the inner surface defines a radius relative to the turbine axis that is equal to or greater than the second radius.
12. The turbine according to claim 10 , wherein the turbine further comprises a bearing housing comprising bearings configured to support the turbine wheel for rotation, the bearing housing further comprising a mounting flange configured for connection to the second volute housing portion.
13. The turbine according to claim 12 , wherein:
the second volute housing portion comprises a threaded bore configured to receive a fastening element;
the turbine further comprises a holding plate having an aperture through which the fastening element is received to fasten the holding plate to the second volute housing portion; and
the holding plate extends radially inwards such that it overlaps with a portion of the mounting flange of the bearing housing to fasten the turbine housing to the bearing housing.
14. The turbine according to claim 12 , wherein:
the mounting flange of the bearing housing comprises a threaded bore configured to receive a fastening element;
the turbine further comprises a holding plate having an aperture through which the fastening element is received to fasten the holding plate to the mounting flange; and
the holding plate extends radially outwards such that it overlaps with a portion of the second volute housing portion of the turbine housing to fasten the turbine housing to the bearing housing.
15. The turbine according to claim 10 , wherein the turbine further comprises a sealing element disposed between the nozzle dividing wall and the housing dividing wall to substantially form a seal therebetween.
16. The turbine according to claim 15 , wherein one or both of the nozzle dividing wall and the housing dividing wall comprises a circumferentially extending groove, and wherein the sealing element comprises a laminar labyrinth seal ring.
17. The nozzle ring of claim 1 , wherein the widening of the outer rim relative to the nozzle dividing wall is such that the nozzle dividing wall extends upstream of the nozzle vanes such that the outer rim is positioned radially outward into a region where the volutes begin to taper outward and the housing dividing wall thickens, allowing the outer rim to be made wider in a direction parallel to the turbine axis.
18. The nozzle ring of claim 1 , wherein the widening of the outer rim relative to the nozzle dividing wall provides at least one of: (i) an increased distance between the first and second inlet volutes along the clearance between the outer cylindrical surfaces of the nozzle dividing wall and the inner edge of the housing dividing wall and (ii) an increased capacity of the outer rim to accommodate mechanical sealing features.