Variable geometry turbine

Patent metadata

Field	Value
Publication number	US-9945286-B2
Application number	US-201414416486-A
Country	US
Kind code	B2
Filing date	Apr 10, 2014
Priority date	Apr 10, 2013
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

A variable geometry turbine has annular inlet passageway defined between a first surface of a radial wall of a movable wall mounted within a cavity and a facing wall of the turbine housing. The radial wall defines a second surface that opposes the first surface. The moveable wall member comprises an annular flange that extends axially into the cavity and supports a radial flange defining opposing third and fourth surfaces. The radial flange seals against an annular sleeve in the cavity to define a first area within the cavity which includes the radial second and third surfaces and a second area within the cavity which includes the radial fourth surface. The first and second areas are in fluid communication with regions of the annular inlet passageway which are respectively upstream and downstream of a radial vane passage.

First claim

The invention claimed is:

1. A variable geometry turbine comprising:
a turbine wheel mounted within a housing for rotation about a turbine axis; and
an annular inlet passageway extending radially inwards towards the turbine wheel;
the annular inlet passageway being defined between a first surface of a radially extending wall of a movable wall member mounted within a cavity provided within the housing and a facing wall of the housing;
the movable wall member being movable in an axial direction so as to vary the size of the annular inlet passageway;
an array of inlet guide vanes extending across said annular inlet passageway to define a radial vane passage;
the radially extending wall of the movable wall member defining a radial second surface that opposes the first surface;
the moveable wall member further comprising an annular flange that extends axially into the cavity and which supports a radially extending flange that defines opposing radial third and fourth surfaces;
the radially extending flange sealing against an annular sleeve provided in the cavity so as to define a first area within the cavity which includes the radial second and third surfaces and a second area within the cavity which includes the radial fourth surface;
the first area within the cavity being in fluid communication with a region of the annular inlet passageway upstream of the radial vane passage; and
the second area within the cavity being in fluid communication with a region of the annular inlet passageway downstream of the radial vane passage,
wherein said fluid communication between the second area within the cavity and the region of the annular inlet passageway downstream of the radial vane passage is facilitated by a gas flow path defined between the annular flange and a wall of the cavity by a sealing arrangement between the annular flange and the wall of the cavity.

2. A variable geometry turbine according to claim 1 , wherein an extent to which the radially extending flange extends radially from a radially inner surface of the annular flange is not greater than a distance from the radially inner surface of the annular flange to an outer diameter of the vanes extending across the inlet passageway.

3. A variable geometry turbine according to claim 1 , wherein at least one of the moveable wall member and the housing is arranged to define a gas flow path into the cavity behind the moveable wall member.

4. A variable geometry turbine according to claim 1 , wherein a radially outer edge of the moveable wall member is sealed with respect to the housing and at least one aperture is defined by the moveable wall member upstream of the vane passage to define a gas flow path into the cavity.

5. A variable geometry turbine according to claim 1 , wherein the annular sleeve defines a leakage path to permit gas, during use, at the relatively high pre-turbine pressure within the first area to flow into the second area to increase the pressure of gas within the second area.

6. A variable geometry turbine according to claim 5 , wherein the leakage path is defined by at least one aperture provided at a location on the annular sleeve such that, during use, it is open to permit gas flow therethrough when the moveable wall member is positioned so that the axial width of the inlet passageway between the moveable wall member and the facing wall of the housing is less than 20% of its width when the moveable wall member is fully retracted into the cavity.

7. A variable geometry turbine according to claim 5 , wherein said fluid communication between the second area within the cavity and the region of the annular inlet passageway downstream of the radial vane passage is facilitated by a gas flow path defined between the annular flange and a wall of the cavity and the total cross-sectional area of the leakage path defined by the annular sleeve is similar to or less than the total cross-sectional area of the gas flow path defined by the sealing arrangement between the annular flange and the wall of the cavity.

8. A variable geometry turbine according to claim 1 , wherein the sealing arrangement is located radially inwardly of the position at which the radially extending flange seals against the annular sleeve.

9. A variable geometry turbine according to claim 8 , wherein the sealing arrangement defines a predetermined radial clearance to provide said gas flow path between the annular flange and the wall of the cavity.

10. A variable geometry turbine according to claim 8 , wherein the sealing arrangement defines at least one groove or cut-out section of predetermined dimension in its outer surface facing the wall of the cavity to provide said gas flow path between the annular flange and the wall of the cavity.

11. A variable geometry turbine according to claim 8 , wherein a radially inner surface of the annular flange defines at least one axially extending groove which extends to both sides of the sealing arrangement to provide said gas flow path between the annular flange and the wall of the cavity.

12. A variable geometry turbine according to claim 1 , wherein the moveable wall member is a shroud defining apertures for receipt of the vanes which are attached to a nozzle ring whose radial surface corresponds to the facing wall of the housing.

13. A variable geometry turbine according to claim 1 , wherein the moveable wall member is a nozzle ring which supports the vanes for receipt in apertures defined by a shroud plate whose radial surface corresponds to the facing wall of the housing.

14. A variable geometry turbine according to claim 1 , wherein the facing wall is secured to the housing.

15. A variable geometry turbine according to claim 12 , wherein the facing wall is secured to the housing via a locking screw connection.

16. A variable geometry turbine according to claim 13 , wherein complementary locking screw threads are defined by an outer circumferential surface of an axially extending flange connected to the facing wall and a radially inward facing surface of the housing or a ring secured to the housing.

17. A turbocharger comprising a variable geometry turbine according to claim 1 .

18. An engine comprising a variable geometry turbine according to claim 1 .

19. A variable geometry turbine comprising:
a turbine wheel mounted within a housing for rotation about a turbine axis; and
an annular inlet passageway extending radially inwards towards the turbine wheel;
the annular inlet passageway being defined between a first surface of a radially extending wall of a movable wall member mounted within a cavity provided within the housing and a facing wall of the housing;
the movable wall member being movable in an axial direction so as to vary the size of the annular inlet passageway;
an array of inlet guide vanes extending across said annular inlet passageway to define a radial vane passage;
the radially extending wall of the movable wall member defining a radial second surface that opposes the first surface;
the moveable wall member further comprising an annular flange that extends axially into the cavity and which supports a radially extending flange that defines opposing radial third and fourth surfaces;
the radially extending flange sealing against an annular sleeve provided in the cavity so as to define a first area and a second area;
the first area within the cavity being in fluid communication with a region of the annular inlet passageway upstream of the radial vane passage; and
the second area within the cavity being in fluid communication with a region of the

Assignees

• Cummins Ltd
• Cummins Ltd

Inventors

• Parker John Frederick
• Moore Simon David
• Sophian Ali

Classifications

• 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

• F05D2250/90

  Variable geometry · CPC title

• F01D17/165

  for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D17/143

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