IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0732757
(2010-03-26)
|
등록번호 |
US-8414249
(2013-04-09)
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발명자
/ 주소 |
|
출원인 / 주소 |
- Cummins Turbo Technologies Limited
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
10 |
초록
▼
A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstre
A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, in other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.
대표청구항
▼
1. A compressor comprising: a housing defining a gas inlet and a gas outlet;a radial impeller wheel having a plurality of vanes and mounted in the housing between said inlet and outlet, the wheel being rotatable about an axis;the inlet comprising a substantially tubular outer wall extending away fro
1. A compressor comprising: a housing defining a gas inlet and a gas outlet;a radial impeller wheel having a plurality of vanes and mounted in the housing between said inlet and outlet, the wheel being rotatable about an axis;the inlet comprising a substantially tubular outer wall extending away from the impeller wheel in an upstream direction and forming a gas intake, and a substantially tubular inner wall extending away from the impeller wheel in an upstream direction and within the outer wall, the inner wall defining an inner surface at least a portion of which is located in close proximity to radially outer edges of the vanes of the radial impeller which sweep across said surface as the radial impeller wheel rotates about its axis;a substantially tubular gas flow passage defined between the inner and outer walls and extending from an upstream end to a downstream end proximate to the radial impeller wheel;an upstream opening defined by the flow passage providing communication between said passage and said intake;at least one first aperture downstream of the upstream opening and providing communication between the passage and the inner surface of the inner wall;an axial impeller wheel having a plurality of vanes and supported for rotation in said inlet upstream of the radial impeller wheel; anda stator comprising a plurality of fixed vanes and disposed in the inner wall of the inlet between the radial and axial impeller wheels,wherein the at least one first aperture is located over the vanes of the radial impeller,and wherein there is provided at least one second aperture and at least one third aperture in said inner wall at locations axially spaced from the at least one first aperture, said second aperture being disposed over the vanes of the stator and the third aperture being disposed over the vanes of the axial impeller. 2. A compressor according to claim 1, wherein the axial impeller wheel is rotatable about the same axis as the radial impeller wheel. 3. A compressor according to claim 2, wherein the axial and radial impeller wheels are connected to a common rotational shaft for rotation about said axis. 4. A compressor according to claim 1, wherein the axial impeller wheel is disposed for rotation within the inner wall of the inlet. 5. A compressor according to claim 1, wherein the at least one first aperture is provided in the inner wall of the inlet. 6. A compressor according to claim 1, wherein the at least one first aperture is a slot. 7. A compressor according to claim 6, wherein said slot is discontinuous. 8. A compressor according to claim 6, wherein said slot is substantially annular. 9. A compressor according to claim 1, wherein the vanes of the radial impeller each comprise a radially outer edge, the at least one first aperture being adjacent to a radially outer edge. 10. A compressor according to claim 9, wherein the vanes of the radial impeller further comprise leading and trailing edges interconnected by said outer edges, the at least one first aperture being provided adjacent to a junction between the outer edges and the leading edges of the vanes. 11. A compressor according to claim 1, wherein the vanes of the stator each comprise a radially outer edge, a leading edge and a trailing edge, the at least one second aperture being disposed over said radially outer edge. 12. A compressor according to claim 11, wherein the at least one second aperture is disposed adjacent to leading edges of the vanes of the stator. 13. A compressor according to claim 12, wherein the at least one second aperture has an end that is coincident with, or is immediately adjacent to, a substantially radial plane that is normal to the axis and which intersects the vanes of the stator. 14. A compressor according to claim 13, wherein the radial plane intersects a junction between the leading edges and the outer edges of the vanes of the stator. 15. A compressor according to claim 13, wherein the radial plane intersects a junction between the trailing edges and the outer edges of the vanes of the stator. 16. A compressor according to claim 13, wherein the radial plane intersects the outer edges of the vanes of the stator at an axial location between the junction of the leading edges with the outer edges and the junction between the trailing edges and the outer edges of the vanes of the stator. 17. A compressor according to claim 13, wherein the vanes of the axial impeller each comprise a radially outer edge, a leading edge and a trailing edge, the at least one third aperture being disposed over the radially outer edge of the vanes of the axial impeller. 18. A compressor according to claim 17, wherein the at least one third aperture is disposed adjacent to a leading edge of at least one vane of the axial impeller. 19. A compressor according to claim 18, wherein the at least one third aperture has an end that is coincident with, or is immediately adjacent to, a substantially radial plane that is normal to the axis and which intersects the vanes of the axial impeller. 20. A compressor according to claim 19, wherein the radial plane intersects a junction between the leading edges and the outer edges of the vanes of the axial impeller. 21. A compressor according to claim 19, wherein the radial plane intersects a junction between the trailing edges and the outer edges of the vanes of the axial impeller. 22. A compressor according to claim 19, wherein the radial plane intersects the outer edges of the vanes of the axial impeller at an axial location between the junction of the leading edges with the outer edges and the junction between the trailing edges and the outer edges of the vanes of the axial impeller. 23. A compressor according to claim 1, wherein there is provided a dividing wall in said gas flow passage, dividing the passage into two portions. 24. A compressor according to claim 23, wherein the dividing wall is disposed between the at least one first aperture and the at least one third aperture. 25. A compressor according to claim 24, wherein the dividing wall is movable in an axial direction in the gas flow passage. 26. A compressor according to claim wherein the vanes of the axial and radial impellers each extend outwardly from a respective hub. 27. A compressor according to claim 1, wherein the stator comprises inner and outer walls. 28. A compressor according to claim 27, wherein the inner wall of the stator extends between hubs of the radial and axial impeller wheels. 29. A compressor according claim 1, wherein the at least one second aperture is a substantially annular second slot. 30. A compressor according to claim 29, wherein the substantially annular second slot is discontinuous. 31. A compressor according to claim 1, wherein the at least one third aperture is a substantially annular third slot. 32. A compressor according to claim 31, wherein the substantially annular third slot is discontinuous. 33. A turbocharger comprising a compressor according to claim 1 and a turbine that drives said axial and radial impeller wheels in rotation. 34. An internal combustion engine fitted with a turbocharger according to claim 33. 35. A method for operating a compressor in a turbocharger, comprising: rotating a radial impeller wheel in a housing so as compress a gas drawn into the housing from an inlet and to deliver it to an outlet in the housing, the inlet comprising inner and outer substantially tubular walls extending away from the impeller wheel in an upstream direction and forming a gas intake, and a substantially tubular gas flow passage defined between the inner and outer walls and extending from an opening at an upstream end to a downstream end proximate to the radial impeller; operating the compressor near surge conditions such that gas is recirculated from inside the inner wall through at least one first aperture in the inner wall and into the gas flow passage, rotating an axial impeller wheel having a plurality of vanes in said inlet upstream of the radial impeller wheel in order to compress incoming gas and delivering the gas to a vaned stator intermediate the axial and radial impellers, wherein the recirculating gas flows in the passage from the at least one first aperture to at least one axially spaced second aperture in the inner wall through which it then passes to the inner surface of the inner wall along which it flows axially upstream to at least one third aperture in the inner wall, the gas passing through the at least one third aperture so that it re-emerges in the gas flow passage for delivery to the opening, wherein the gas flow re-enters the inner wall at an axial position substantially over the stator, and wherein the gas flow re-emerges in the flow passage at an axial position substantially over the axial impeller vanes.
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