GB2624550A - Nozzle ring for a variable geometry turbine - Google Patents
Nozzle ring for a variable geometry turbine Download PDFInfo
- Publication number
- GB2624550A GB2624550A GB2400649.6A GB202400649A GB2624550A GB 2624550 A GB2624550 A GB 2624550A GB 202400649 A GB202400649 A GB 202400649A GB 2624550 A GB2624550 A GB 2624550A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle ring
- nozzle
- intercept
- axis
- deck
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
- F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extend from a nozzle ring though slots in a shroud. The nozzle ring has a radially-inner corner which is a gentler curve than in a conventional system, and this is found to lead to improved efficiency of the turbine.
Claims (11)
1. A nozzle ring for a turbine, the nozzle ring having: a flat annular nozzle deck surface encircling an axis and facing in a direction parallel to the axis; a cylindrical inner surface of the nozzle ring encircling the axis; a plurality of vanes extending axially from the nozzle deck; a corner surface which is rotationally symmetric about the axis and extends from an inner surface intercept on the inner surface to a nozzle deck intercept on the nozzle deck surface; at least one point on the curve between the nozzle deck intercept and the inner surface intercept having a radius of curvature R, measured in a plane including the axis, greater than 2mm.
2. A nozzle ring according to claim 1 in which the ratio of (i) the radius of curvature R at the at least one point, to (ii) a radial distance q from the inner surface of the nozzle ring to the trailing edge of the vanes is more than 0.3.
3. A nozzle ring according to claim 1 or claim 2 in which an intersection of the corner with the plane is a portion of an ellipse or a circle.
4. A nozzle ring according to any preceding claim in which the intersection of the corner with the plane is a portion of a circle having a radius of curvature R, and a mismatch ratio of (i) the radius of curvature R, to (ii) an axial distance d from the inner surface intercept to the nozzle deck intercept is at least 1.4.
5. A nozzle ring according to claim 4 in which the mismatch ratio is at least 2.
6. A nozzle ring according to any of claims 1 to 3 in which an intersection of the corner with the plane is a portion of an ellipse having a radial long axis of length A and an axial short axis of length B, an eccentricity ratio A/B being at least 1.5.
7. A nozzle ring according to claim 6 in which the eccentricity ratio A/B is at least 2.
8. A nozzle ring according to any preceding claim in which a divergence ratio which is the ratio of (i) the radial distance h from the inner surface of the nozzle ring to a point on the corner which is half way in the axial direction from the inner surface intercept to the nozzle deck intercept, to (ii) the axial distance (d) from the inner surface intercept to the nozzle deck intercept, is greater than 0.2 .
9. A nozzle ring according to claim 8 in which the divergence ratio is greater than 0.3.
10. A turbine having: a turbine housing defining a gas inlet; and 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 according to any preceding claim; and a drive mechanism for selectively moving the nozzle ring towards or away from the shroud.
11. A turbocharger comprising a turbine according to claim 10.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GBGB2108695.4A GB202108695D0 (en) | 2021-06-17 | 2021-06-17 | Nozzle ring for a variable geometry turbine |
| PCT/GB2022/051510 WO2022263823A1 (en) | 2021-06-17 | 2022-06-15 | Nozzle ring for a variable geometry turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB202400649D0 GB202400649D0 (en) | 2024-02-28 |
| GB2624550A true GB2624550A (en) | 2024-05-22 |
Family
ID=77050496
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GBGB2108695.4A Ceased GB202108695D0 (en) | 2021-06-17 | 2021-06-17 | Nozzle ring for a variable geometry turbine |
| GB2400649.6A Pending GB2624550A (en) | 2021-06-17 | 2022-06-15 | Nozzle ring for a variable geometry turbine |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GBGB2108695.4A Ceased GB202108695D0 (en) | 2021-06-17 | 2021-06-17 | Nozzle ring for a variable geometry turbine |
Country Status (2)
| Country | Link |
|---|---|
| GB (2) | GB202108695D0 (en) |
| WO (1) | WO2022263823A1 (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006131724A1 (en) * | 2005-06-07 | 2006-12-14 | Cummins Turbo Technologies Limited | Variable geometry turbine |
| EP1900908A2 (en) * | 2006-09-12 | 2008-03-19 | Iveco Motorenforschung AG | Variable geometry turbine |
| WO2011015908A1 (en) * | 2009-08-04 | 2011-02-10 | Renault Trucks | Variable geometry turbine |
| WO2020120254A1 (en) * | 2018-12-14 | 2020-06-18 | Vitesco Technologies GmbH | Exhaust gas turbine with a variable geometry for a turbocharger |
-
2021
- 2021-06-17 GB GBGB2108695.4A patent/GB202108695D0/en not_active Ceased
-
2022
- 2022-06-15 GB GB2400649.6A patent/GB2624550A/en active Pending
- 2022-06-15 WO PCT/GB2022/051510 patent/WO2022263823A1/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006131724A1 (en) * | 2005-06-07 | 2006-12-14 | Cummins Turbo Technologies Limited | Variable geometry turbine |
| EP1900908A2 (en) * | 2006-09-12 | 2008-03-19 | Iveco Motorenforschung AG | Variable geometry turbine |
| WO2011015908A1 (en) * | 2009-08-04 | 2011-02-10 | Renault Trucks | Variable geometry turbine |
| WO2020120254A1 (en) * | 2018-12-14 | 2020-06-18 | Vitesco Technologies GmbH | Exhaust gas turbine with a variable geometry for a turbocharger |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2022263823A1 (en) | 2022-12-22 |
| GB202108695D0 (en) | 2021-08-04 |
| GB202400649D0 (en) | 2024-02-28 |
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