Turbocharger having inclined volutes

• US 20080104956A1
• Filed: 10/31/2006
• Published: 05/08/2008
• Est. Priority Date: 10/31/2006
• Status: Abandoned Application

• Current Assignee: Caterpillar Incorporated
• Original Assignee: Caterpillar Incorporated
• Inventors: Reisdorf, Paul W., Hafiz, Anees, Delvecchio, Kerry A., Kruiswyk, Richard W.
• Application Number:
  US11/589,965
• Publication Number:
  US 20080104956A1
• Time in Patent Office: Days
• US Class Current: 60/599
• CPC Class Codes: F01D 9/026 Scrolls for radial machines or engines
• CPC Class Codes: F02B 37/00 Engines characterised by provision of pumps driven at least for part of the time by exhaust
• CPC Class Codes: F02B 37/025 Multiple scrolls or multiple gas passages guiding the gas to the pump drive
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2240/40 Use of a multiplicity of similar components
• CPC Class Codes: F05D 2250/232 conical
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

A turbocharger for a power system is disclosed. The turbocharger has an impeller wheel, which is rotatable about a central axis and includes a back face at least partially defining a reference plane substantially perpendicular to the central axis. In addition, the turbocharger includes a housing configured to at least partially enclose the impeller wheel. The housing also has at least one volute configured to fluidly communicate fluid with the impeller wheel. The entire length of the at least one volute from a turbocharger inlet is axially inclined relative to the reference plane so the fluid flows in both a radial and axial direction.

Claims

1. A turbocharger, comprising:

an impeller wheel rotatable about a central axis and having a back face at least partially defining a reference plane substantially perpendicular to the central axis; and

a housing configured to at least partially enclose the impeller wheel and having at least one volute, including a vaned portion, configured to fluidly communicate a fluid with the impeller wheel, wherein the entire vaned portion of the at least one volute is inclined axially relative to the reference plane so that the fluid flows in both a radial and axial direction.

2. The turbocharger of claim 1, wherein the impeller wheel is a turbine wheel and the turbocharger further includes a compressor wheel and an outer periphery of the at least one volute is located axially closer to the compressor wheel than an inner periphery of the at least one volute.

3. The turbocharger of claim 2, wherein the at least one volute includes a substantially planar inner-side wall.

4. The turbocharger of claim 3, wherein the at least one volute has an annular opening in communication with the turbine wheel, and the axial inclination of the at least one volute extends to the annular opening.

5. The turbocharger of claim 4, wherein the vane portion includes a plurality of annularly disposed vane members inclined axially toward the compressor wheel relative to the reference plane.

6. The turbocharger of claim 1, wherein the at least one volute is axially inclined at substantially the same angle as the entire vaned portion.

7. The turbocharger of claim 5, wherein each annularly disposed vane member is radially inclined relative to a reference plane originating from the central axis and passing through a tip end portion of each vane member closest to the central axis, and the angle of radial inclination is within a range of approximately 65 to 70 degrees.

8. The turbocharger of claim 7, wherein the angle of radial inclination is approximately 68 degrees.

9. The turbocharger of claim 2, further including a second volute configured to fluidly communicate exhaust with the turbine wheel.

10. The turbocharger of claim 9, wherein the first and second volutes are axially inclined at substantially the same angle.

11. The turbocharger of claim 10, further including a wall member dividing the first and second volutes, wherein the wall member is substantially planar.

12. The turbocharger of claim 11, wherein an angle of axial inclination is within a range of approximately 20-30 degrees.

13. The turbocharger of claim 12, wherein the angle of axial inclination is approximately 25 degrees.

14. A method of operating a turbocharger, comprising:

receiving a first flow of exhaust;

simultaneously receiving a second flow of exhaust at a location axially offset and separate from the first flow of exhaust; and

radially and axially directing the first and second flows of exhaust through a vaned area and a power generating device at the same inclined angle relative to a reference plane perpendicular to a central axis of the power generating device.

15. The method of claim 14, wherein directing the first and second flows of exhaust further includes distributing the first and second flows of exhaust gas through a plurality of finite locations around a periphery of the power generating device.

16. The method of claim 15, wherein the angle of inclination is within a range of approximately 20-30 degrees.

17. The method of claim 16, wherein the angle of inclination is approximately 25 degrees.

18. A power system, comprising:

an engine having a plurality of combustion chambers and being configured to produce a power output and a flow of exhaust gases;

a first exhaust passageway associated with at least a first of the plurality of combustion chambers;

a second exhaust passageway associated with at least a second of the plurality of combustion chambers; and

a turbocharger in fluid communication with the first and second exhaust passageways, the turbocharger including;

a turbine wheel rotatable about a central axis and having a back face at least partially defining a reference plane substantially perpendicular to the central axis; and

a housing configured to at least partially enclose the turbine wheel and having;

a first volute configured to fluidly communicate exhaust with the turbine wheel, wherein at least a portion of the first volute is inclined axially toward a compressor wheel relative to the reference plane so that an outer periphery of the first volute is located axially closer to the compressor wheel than an inner periphery of first volute and the exhaust flows in both a radial and axial direction;

a second volute configured to fluidly communicate exhaust with the turbine wheel, wherein at least a portion of the second volute is inclined axially toward a compressor wheel relative to the reference plane so that an outer periphery of the second volute is located axially closer to the compressor wheel than an inner periphery of second volute and the exhaust flows in both a radial and axial direction;

a vaned portion including a plurality of annularly disposed vane members associated with at least one of the first and second volutes, wherein the axial inclination of the at least one of the first and second volutes extends through the entire vaned portion; and

an annular opening associated with each of the first and second volutes and in communication with the turbine wheel, wherein the axial inclination of the first and second volutes extends to the annular opening.

19. The turbocharger of claim 18, wherein the first and second volutes are axially inclined at substantially the same angle.

20. The turbocharger of claim 19, further including a wall member dividing the first and second volutes, wherein the wall member is substantially planar.