Turbomachine

• US 10,167,774 B2
• Filed: 11/12/2015
• Issued: 01/01/2019
• Est. Priority Date: 10/06/2009
• Status: Active Grant

• Current Assignee: Cummins Limited (Cummins Incorporated)
• Original Assignee: Cummins Limited (Cummins Incorporated)
• Inventors: Parker, John F., Holroyd, Robert L., Roberts, Tom J., McEwen, James Alexander, Denholm, Tim, Moore, Simon, Voong, Michael, Normington, Christopher, Vijayakumar, Arun, Garrett, Stephen
• Primary Examiner(s): Lee, Jr., Woody
• Application Number:
  US14/939,714
• Publication Number:
  US 20160061103A1
• Time in Patent Office: 1,146 Days
• Field of Search: 415162-165, 415194, 415195
• CPC Class Codes: F01D 17/143 the shiftable member being a wall, or part thereof of a radial diffuser
• CPC Class Codes: F02B 37/22 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 Class Codes: F02B 37/24 by using pumps or turbines with adjustable guide vanes
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: F05D 2250/283 honeycomb
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

Claims

1. A variable geometry turbine comprising

a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls;

and

a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet;

wherein the annular inlet is divided into at least three axially offset inlet passages by two or more inlet passage walls disposed between the first and second inlet sidewalls.

2. A variable geometry turbine according to claim 1, wherein the inlet passage walls are axially spaced annular baffles, the baffles dividing the annular inlet into axially adjacent annular portions.

3. A variable geometry turbine according to claim 2, wherein the number of baffles is one of 2, 3, 4, 5 or 6.

4. A variable geometry turbine according to claim 2, further comprising inlet vanes which extend axially across at least two of said axially adjacent annular portions;

wherein the cylindrical sleeve is axially movable across the annular inlet to vary the size of a gas flow path through the inlet between a free end of the sleeve and the first inlet sidewall; and

wherein the axial width of the inlet vanes extending across a first annular portion of the inlet is less than the axial width of the inlet vanes extending across a second annular portion of the inlet, the first annular portion being closer to the first inlet sidewall than the second annular portion is to the first inlet sidewall.

5. A variable geometry turbine according to claim 1, wherein the two or more inlet passage walls define an annular array of substantially tubular inlet passages extending generally towards the turbine wheel, wherein the annular array of inlet passages comprises at least three axially offset inlet passages.

6. A variable geometry turbine according to claim 5, wherein the sleeve is axially movable between an open position in which there is a gas flow path through the inlet, between a free end of the sleeve and the first inlet sidewall, through at least one of said at least three axially offset inlet passages, and a closed position in which the size of said gas flow path through the inlet between the free end of the sleeve and the first inlet sidewall is reduced compared to that when the sleeve is in the open position;

and wherein the sleeve moves in a direction towards said first inlet sidewall when the sleeve is moved from the open position towards the closed position.

7. A variable geometry turbine according to claim 6, wherein, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall is less than each of the respective axial distances between at least two of the two or more inlet passage walls and the first inlet sidewall.

8. A variable geometry turbine according to claim 6, wherein, when the sleeve is in the closed position, the axial distance between all of the free end of the sleeve and the first inlet sidewall is less than each of the respective axial distances between at least two of the two or more inlet passage walls and the first inlet sidewall.

9. A variable geometry turbine according to claim 6, wherein, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall is less than each of the respective axial distances between each of the two or more inlet passage walls and the first inlet sidewall.

10. A variable geometry turbine according to claim 6, wherein, when the sleeve is in the closed position, the axial distance between all of the free end of the sleeve and the first inlet sidewall is less than each of the respective axial distances between each of the two or more inlet passage walls and the first inlet sidewall.

11. A variable geometry turbine according to claim 6, wherein, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall is less than the axial distance between one of the two or more inlet passage walls and the first inlet sidewall, and wherein said one of the two or more inlet passage walls is located such that the axial distance between said one of the two or more inlet passage walls and the first inlet sidewall is less than or equal to substantially 50% of the axial distance between the first and second inlet sidewalls.

12. A variable geometry turbine according to claim 6, wherein, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall is less than the axial distance between one of the two or more inlet passage walls and the first inlet sidewall, and wherein the sleeve substantially does not contact said one of the two or more inlet passage walls when the sleeve is in the closed position.

13. A variable geometry turbine according to claim 6, wherein, when the sleeve is in the closed position, the axial distance between at least a portion of the free end of the sleeve and the first inlet sidewall is less than the axial distance between one of the two or more inlet passage walls and the first inlet sidewall, and wherein the sleeve is mounted such that gas may pass between said one of the two or more inlet passage walls and the sleeve when the sleeve is in the closed position, the gas then passing through the inlet.

14. A variable geometry turbine according to claim 6, wherein the sleeve is mounted such that, when the sleeve is in the closed position, the sleeve substantially does not contact any of the two or more inlet passage walls.

15. A variable geometry turbine according to claim 6, wherein an axial dimension of a first of said axially offset inlet passages is less than an axial dimension of a second of said axially offset inlet passages, and wherein the first of said axially offset inlet passages is located closer the first inlet sidewall than the second of said axially offset inlet passages.

16. A variable geometry turbine according to claim 1, wherein the annular inlet is in communication with a volute through which, during operation, gas flows to the annular inlet, such that the annular inlet is downstream of the volute.

17. A variable geometry turbine according to claim 16, wherein the first and second inlet sidewalls of the annular inlet are continuations of walls which define the volute.