[특허]Variable geometry turbine

Cummins Turbo Technologies Limited

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Variable geometry turbine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02D-023/00 F01D-017/12 F01D-017/14
미국특허분류(USC)	060/602; 415/159; 415/158
출원번호	UP-0148287 (2008-04-17)
등록번호	US-7810327 (2010-11-01)
우선권정보	GB-0521354.1(2005-10-20)
발명자 / 주소	Parker, John
출원인 / 주소	Cummins Turbo Technologies Limited
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 7 인용 특허 : 7

초록
▼

A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a movable nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway. A substantially annular rib is provided either on the face of the nozzle ring (such that the minimum width of the inlet passageway is defined between the rib and the facing wall of the housing) or on the facing wall of the housing (su...

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The invention claimed is: 1. A method of operating a turbocharger fitted to an internal combustion engine, the turbocharger including a variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said facing wall of the housing such that the minimum width of the inlet passageway is defined between the rib and a portion of the face of the movable wall member; the method comprising operating the engine in an engine braking mode in which a fuel supply to the engine is stopped and the movable wall member is moved to reduce the width of the turbine inlet passageway. 2. A method according to claim 1, wherein in said engine braking mode the movable wall member is moved into a fully closed position in which the movable wall member abuts the opposing wall of the turbine housing. 3. A method of operating a turbocharger fitted to an internal combustion engine, the turbocharger including a variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said facing wall of the housing such that the minimum width of the inlet passageway is defined between the rib and a portion of the face of the movable wall member; the method comprising operating the engine in an exhaust gas heating mode in which the width of the inlet is reduced below a width appropriate to a normal engine operating range to raise the temperature of exhaust gas passing through the turbine. 4. A method according to claim 3, wherein in said exhaust gas heating mode the movable wall member is moved into a fully closed position in which the movable wall member abuts the opposing wall of the turbine housing. 5. A method of operating a turbocharger fitted to an internal combustion engine, the turbocharger including a variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said radial face such that the minimum width of the inlet passageway is defined between the rib and a portion of the facing wall of the housing; the movable wall member being movable into a fully closed position in which the rib abuts said portion of the facing wall of the housing; and wherein the rib is provided with at least one gas passage formation which defines at least part of a gas passage when the movable wall member is in said fully closed position to allow gas to flow through the inlet passageway past said rib; the method comprising operating the engine in an engine braking mode in which a fuel supply to the engine is stopped and the movable wall member is moved to reduce the width of the turbine inlet passageway. 6. A method according to claim 5, wherein in said engine braking mode the movable wall member is moved into a fully closed position in which the movable wall member abuts the opposing wall of the turbine housing. 7. A method of operating a turbocharger fitted to an internal combustion engine, the turbocharger including a variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said radial face such that the minimum width of the inlet passageway is defined between the rib and a portion of the facing wall of the housing; the movable wall member being movable into a fully closed position in which the rib abuts said portion of the facing wall of the housing; and wherein the rib is provided with at least one gas passage formation which defines at least part of a gas passage when the movable wall member is in said fully closed position to allow gas to flow through the inlet passageway past said rib; the method comprising operating the engine in an exhaust gas heating mode in which the width of the inlet is reduced below a width appropriate to a normal engine operating range to raise the temperature of exhaust gas passing through the turbine. 8. A method according to claim 7, wherein in said exhaust gas heating mode the movable wall member is moved into a fully closed position in which the movable wall member abuts the opposing wall of the turbine housing. 9. A method according to claim 7, wherein the movable wall member is moved to reduce the inlet width for exhaust gas heating in response to determination of the exhaust gas temperature falling below a threshold temperature. 10. A variable geometry turbine comprising; a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said radial face such that the minimum width of the inlet passageway is defined between the rib and a portion of the facing wall of the housing; the movable wall member being movable into a fully closed position in which the rib abuts said portion of the facing wall of the housing; and wherein the rib is provided with at least one gas passage formation which defines at least part of a gas passage when the movable wall member is in said fully closed position to allow gas to flow through the inlet passageway past said rib. 11. A variable geometry turbine according to claim 10, wherein in said fully closed position the rib forms a sealing contact with said portion of the facing wall of the housing effective to substantially prevent gas flow through the inlet passageway. 12. A variable geometry turbine according to claim 10, wherein said at least one gas passage formation comprises a circumferentially spaced array of slots provided in the rib. 13. A variable geometry turbine according to claim 12, wherein the slots extend from an axial end of the rib remote from the face of the movable wall member in a direction towards said face, thereby defining an annular array of rib portions spaced apart by said slots. 14. A variable geometry turbine according to claim 13, wherein at least one of said slots has a depth extending at least to the face of the movable wall member. 15. A variable geometry turbine according to claim 13, wherein said slots have a length extending in a direction substantially radial to the turbine axis. 16. A variable geometry turbine according to claim 13, wherein said slots have a length extending in a direction swept forwards or backwards relative to a radial line extending from the turbine axis. 17. A variable geometry turbine according to claim 13, wherein the width of each slot is less than the width of each rib portion defined between said slots. 18. A variable geometry turbine according to claim 10, comprising an annular array of inlet vanes extending across said inlet passageway, such that said rib circumscribes said inlet vanes, and vane passages being defined between adjacent vanes. 19. A variable geometry turbine according to claim 18, wherein said inlet vanes extend from said face of the movable wall member, and said facing wall of the housing is provided with a cavity or cavities to receive said vanes as the movable member is moved towards said facing wall of the housing. 20. A variable geometry turbine according to claim 19, wherein aside from said vanes, the rib extends a greater distance from the face of the movable wall member than any other feature of the movable wall member. 21. A variable geometry turbine according to claim 18, comprising means for bypassing gas flow around at least a portion of said vane passages at inlet passageway widths less than a predetermined value. 22. A variable geometry turbine according to claim 21, wherein said means comprises at least one bypass flow path which opens only when the movable wall member is moved to define an inlet width below said predetermined value, the flow path directing at least some gas flow from the inlet through a cavity defined behind the face of the movable wall member and then to the turbine wheel downstream of the inlet vane passages. 23. A variable geometry turbine according to claim 10, wherein the movable wall member is mounted within an annular cavity provided within the housing, said face of the movable wall member being defined by a radial wall of the movable wall member, wherein a circumferential array of apertures is provided through said radial wall, the apertures being circumscribed by said annular rib such that the inlet passageway downstream of the rib is in fluid communication with said cavity via said apertures. 24. A variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said facing wall of the housing such that the minimum width of the inlet passageway is defined between the rib and a portion of the face of the movable wall member; and wherein at least one of the rib and said portion of the face of the movable wall member is provided with at least one gas passage formation which defines at least part of a gas passage when the movable wall member is in said fully closed position to allow gas to flow through the inlet passageway past said rib. 25. A variable geometry turbine according to claim 24, wherein the movable wall member is movable into a fully closed position in which the rib abuts said portion of the face of the movable wall member. 26. A variable geometry turbine according to claim 25, wherein in said fully closed position the rib forms a sealing contact with said portion of the face of the moveable wall member effective to substantially prevent gas flow through the inlet passageway. 27. A turbocharger including a variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said radial face such that the minimum width of the inlet passageway is defined between the rib and a portion of the facing wall of the housing; the movable wall member being movable into a fully closed position in which the rib abuts said portion of the facing wall of the housing; and wherein the rib is provided with at least one gas passage formation which defines at least part of a gas passage when the movable wall member is in said fully closed position to allow gas to flow through the inlet passageway past said rib. 28. A turbocharger including a variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said facing wall of the housing such that the minimum width of the inlet passageway is defined between the rib and a portion of the face of the movable wall member; and wherein at least one of the rib and said portion of the face of the movable wall member is provided with at least one gas passage formation which defines at least part of a gas passage when the movable wall member is in fully closed position to allow gas to flow through the inlet passageway past said rib. 29. A variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said radial face such that the minimum width of the inlet passageway is defined between the rib and a portion of the facing wall of the housing; an annular array of inlet vanes extending across said inlet passageway, such that said rib circumscribes said inlet vanes, and vane passages being defined between adjacent vanes; said inlet vanes extending from said face of the movable wall member, and said facing wall of the housing is provided with a cavity or cavities to receive said vanes as the movable member is moved towards said facing wall of the housing; and wherein aside from said vanes, the rib extends a greater distance from the face of the movable wall member than any other feature of the movable wall member. 30. A variable geometry turbine comprising: a turbine wheel supported in a housing for rotation about a turbine axis; an annular inlet passageway defined between a radial face of a movable wall member and a facing wall of the housing; the movable wall member being movable along the turbine axis to vary the width of the inlet passageway; a substantially annular rib being provided on said facing wall of the housing such that the minimum width of the inlet passageway is defined between the rib and a portion of the face of the movable wall member; an annular array of inlet vanes extending across said inlet passageway, such that said rib circumscribes said inlet vanes, and vane passages being defined between adjacent vanes; said inlet vanes extending from said facing wall of the housing and through respective vane slots provided in said face of the movable wall member to accommodate movement of the movable wall member towards the facing wall of the housing; and wherein aside from said vanes, the rib extends a greater distance from the facing wall of the housing than any other feature of the facing wall of the housing.

이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 7

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Variable geometry turbine

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이 특허에 인용된 특허 (7)

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