Turbomachine

Patent metadata

Field	Value
Publication number	US-10612458-B2
Application number	US-201815975204-A
Country	US
Kind code	B2
Filing date	May 9, 2018
Priority date	Oct 6, 2009
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

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.

First claim

The invention claimed is:

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 two axially offset inlet passages, and
wherein the inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

2. A variable geometry turbine according to claim 1 , wherein the inner diameter of the sleeve is less than or substantially equal to the outer diameter of the inlet passages.

3. A variable geometry turbine according to claim 1 , wherein the inner diameter of the sleeve is greater than the outer diameter of the inlet passages.

4. A variable geometry turbine according to claim 1 , wherein the sleeve is axially movable across the annular inlet in a direction towards the second inlet sidewall so as reduce the size of the gas flow path through the inlet, and wherein at least a portion of an end of the sleeve nearer to the first inlet sidewall than the second inlet sidewall is configured so as to be exposable to gases flowing through said annular inlet during use.

5. A variable geometry turbine according to claim 1 , wherein the sleeve is axially movable across the annular inlet in a direction towards the second inlet sidewall so as reduce the size of the gas flow path through the inlet, and wherein at least a portion of an end of the sleeve nearer to the first inlet sidewall than the second inlet sidewall is configured so as to be located in between said first and second inlet sidewall during axial movement of the sleeve across the annular inlet.

6. A variable geometry turbine according to claim 1 , wherein the sleeve possesses a small radial thickness.

7. A variable geometry turbine according to claim 1 , wherein the sleeve possesses a radial thickness which is less than the axial width of the annular inlet.

8. A variable geometry turbine according to claim 1 , wherein the annular inlet is divided into at least two axially offset inlet passages by at least one annular baffle axially spaced from the first and second inlet sidewalls.

9. A variable geometry turbine according to claim 8 , wherein inlet vanes extend axially across at least one of the axially offset inlet passages.

10. A variable geometry turbine according to claim 9 , wherein the minimum distance between a baffle and the turbine wheel is less than the minimum distance between an adjacent vane and the turbine wheel.

11. A variable geometry turbine according to claim 9 , wherein the trailing edges of at least some of the vanes extending across one of the axially offset inlet passages lie on a different radius to the trailing edges of at least some of the vanes extending across another of the axially offset inlet passages.

12. A variable geometry turbine according to claim 1 , wherein the annular inlet is divided into 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.

Assignees

• Cummins Ltd

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

Classifications

• F05D2250/283

  honeycomb · CPC title

• F02B37/24

  by using pumps or turbines with adjustable guide vanes · CPC title

• F02B37/22 Primary

  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

• F05D2220/40

  in turbochargers · CPC title

• F01D17/143

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