Turbine flow regulating valve system

• US 20060137342A1
• Filed: 12/02/2005
• Published: 06/29/2006
• Est. Priority Date: 12/14/2004
• Status: Abandoned Application

• Current Assignee: BorgWarner Incorporated, GM Global Technology Operations Incorporated (Motors Liquidation Co. GUC Trust)
• Original Assignee: BorgWarner Incorporated
• Inventors: Mudel, Roman, Grissom, Thomas A., Delavan, Matthew B., Wright, Christopher C.
• Application Number:
  US11/292,554
• Publication Number:
  US 20060137342A1
• Time in Patent Office: Days
• US Class Current: 60/602
• CPC Class Codes: F02B 37/004 with exhaust drives arranged in series
• CPC Class Codes: F02B 37/013 with exhaust-driven pumps arranged in series
• CPC Class Codes: F02B 37/025 Multiple scrolls or multiple gas passages guiding the gas to the pump drive
• CPC Class Codes: F02B 37/16 by bypassing charging air
• CPC Class Codes: F02B 37/18 by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
• 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: Y02T 10/12 Improving ICE efficiencies

Abstract

A regulated two-stage turbocharger system is described. The turbocharger system includes high-pressure and low-pressure turbocharger units in communication with one another. The turbocharger system includes a valve system having valve members that are independently controllable so as to selectively control the gas flow into the turbine portions of the high-pressure turbocharger and the low-pressure turbocharger units. The valve members are asymmetric, e.g., they possess differing areas (e.g., perimeters, diameters and/or the like) with respect to one another.

Claims

1. A turbocharger system, comprising:

a high-pressure turbocharger system;

a low-pressure turbocharger system operably associated with the high-pressure turbocharger system; and

a valve system operably associated with either of the high-pressure and low-pressure turbocharger systems;

wherein the valve system includes at least two valve members operable to selectively meter a gas flow to either of the high-pressure or low-pressure turbocharger systems;

wherein the valve members are asymmetric with respect to one another.

2. The invention according to claim 1, wherein the high-pressure turbocharger system includes a turbine portion and a compressor portion, wherein the turbine portion and the compressor portion of the high-pressure turbocharger system are operably associated therebetween.

3. The invention according to claim 2, wherein the low-pressure turbocharger system includes a turbine portion and a compressor portion, wherein the turbine portion and the compressor portion of the low-pressure turbocharger system are operably associated therebetween, wherein the compressor portion of the high-pressure turbocharger system is in fluid communication with the compressor portion of the low-pressure turbocharger system.

4. The invention according to claim 3, further comprising a compressor by-pass system operably associated with the high-pressure compressor system, wherein the compressor by-pass system is selectively operable to cause at least a portion of an air flow to by-pass the high-pressure compressor portion.

5. The invention according to claim 1, wherein the valve system includes at least two valve members selectively operable to meter an exhaust gas flow to the low-pressure turbine portion.

6. The invention according to claim 5, wherein the at least two valve members are operable to independently meter an exhaust flow to the low-pressure turbine portion.

7. The invention according to claim 5, wherein the at least two valve members are operable to sequentially meter an exhaust flow to the low-pressure turbine portion.

8. The invention according to claim 1, further comprising a turbine by-pass system operably associated with the low-pressure turbine portion, wherein the turbine by-pass system is selectively operable to cause at least a portion of the exhaust gas flow to by-pass the low-pressure turbine portion.

9. The invention according to claim 8, wherein at least one of the two valve members is in fluid communication with the turbine by-pass system.

10. A turbocharger system, comprising:

a high-pressure turbocharger system having a turbine portion;

a low-pressure turbocharger system having a turbine portion, wherein the low-pressure turbocharger system is operably associated with the high-pressure turbocharger system; and

a valve system operably associated with either of the turbine portions of the high-pressure and low-pressure turbocharger systems;

wherein the valve system includes at least two valve members operable to selectively meter a gas flow to either of the turbine portions of the high-pressure or low-pressure turbocharger systems;

wherein the valve members are asymmetric with respect to one another.

11. The invention according to claim 10, wherein the high-pressure turbocharger system includes a compressor portion, wherein the turbine portion and the compressor portion of the high-pressure turbocharger system are operably associated therebetween.

12. The invention according to claim 11, wherein the low-pressure turbocharger system includes a compressor portion, wherein the turbine portion and the compressor portion of the low-pressure turbocharger system are operably associated therebetween, wherein the compressor portion of the high-pressure turbocharger system is in fluid communication with the compressor portion of the low-pressure turbocharger system.

13. The invention according to claim 12, further comprising a compressor by-pass system operably associated with the high-pressure compressor system, wherein the compressor by-pass system is selectively operable to cause at least a portion of an air flow to by-pass the high-pressure compressor portion.

14. The invention according to claim 10, wherein the valve system includes at least two valve members selectively operable to meter an exhaust gas flow to the low-pressure turbine portion.

15. The invention according to claim 14, wherein the at least two valve members are operable to independently meter an exhaust flow to the low-pressure turbine portion.

16. The invention according to claim 14, wherein the at least two valve members are operable to sequentially meter an exhaust flow to the low-pressure turbine portion.

17. The invention according to claim 10, further comprising a turbine by-pass system operably associated with the low-pressure turbine portion, wherein the turbine by-pass system is selectively operable to cause at least a portion of the exhaust gas flow to by-pass the low-pressure turbine portion.

18. The invention according to claim 17, wherein at least one of the two valve members is in fluid communication with the turbine by-pass system.

19. A turbocharger system, comprising:

a high-pressure turbocharger system having a turbine portion;

a low-pressure turbocharger system having a turbine portion, wherein the low-pressure turbocharger system is operably associated with the high-pressure turbocharger system; and

a valve system operably associated with either of the turbine portions of the high-pressure and low-pressure turbocharger systems;

wherein the valve system includes at least two valve members operable to selectively meter a gas flow to either of the turbine portions of the high-pressure or low-pressure turbocharger systems;

wherein the valve members are operable to be independently or sequentially actuated by the valve system;

wherein the valve members are asymmetric with respect to one another.

20. The invention according to claim 19, wherein the valve system includes at least two valve members selectively operable to meter an exhaust gas flow to the low-pressure turbine portion.