[특허]Variable geometry turbine

Iveco Motorenforschung AG

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Variable geometry turbine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-017/14 F02D-023/00 F03B-001/04 F04D-029/46
미국특허분류(USC)	060/602; 415/158; 417/407
출원번호	US-0153639 (2002-05-24)
우선권정보	IT-0000505 (2001-05-25)
발명자 / 주소	Lutz, Ernst Spuler, Juerg
출원인 / 주소	Iveco Motorenforschung AG
대리인 / 주소	Finnegan, Henderson, Farabow, Garrett & Dunner, L.L.P.
인용정보	피인용 횟수 : 9 인용 특허 : 4

초록
▼

A variable geometry turbine, particularly for a supercharger turbocompressor of an internal combustion engine, comprising an outer housing forming a spiral inlet channel for an operating fluid, a rotor supported in a rotary manner in the housing, and an annular vaned nozzle of variable geometry interposed radially between the channel and the rotor and comprising a control member moving axially in order to control of the flow of the operating fluid from the channel to the rotor, the control member being formed as an annular piston of a fluid actuator actu...

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청구항
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1. A variable geometry turbine comprising:a housing;a rotor supported in a rotary manner in said housing, said housing defining a spiral-shaped inlet channel for operating fluid, said inlet channel surrounding said rotor;a fluid control line;a fluid actuator;an auxiliary chamber connection means; andan annular vaned nozzle having a geometry interposed radially between the channel and the rotor, said annular vaned nozzle comprising an axially moving control member and a throat section, said control member being configured to control the flow of the operating fluid from the inlet channel to the rotor by varying said throat section,wherein said control member as constitutes an annular piston of said fluid actuator, and the control member being actuated directly by a control pressure via said fluid control line,wherein the control member further comprises a control surface subject to the control pressure and oriented axially so as to move the control member toward a closed configuration in response to an increase in this control pressure, the control member further having a reaction surface subject to the pressure of the operating fluid in the nozzle and oriented axially in a direction opposite to that of the control surface, andwherein the control member further comprises at least one auxiliary surface oriented axially in the same direction as the control surface, said control member being housed in said auxiliary chamber, and said connection means configured to supply the operating fluid from the annular vaned nozzle to the auxiliary chamber. 2. A turbine as claimed in claim 1, wherein the auxiliary surface is disposed radially outside with respect to the control surface, the connection means communicating with the nozzle upstream of the throat section of the nozzle. 3. A turbine as claimed in claim 1, characterised in that the auxiliary surface is disposed radially outside with respect to the control surface and housing in an auxiliary chamber and connection means for supplying the operating fluid from the nozzle to the auxiliary chamber. 4. A turbine as claimed in claim 1, wherein the control member is axially free, such that the axial position of the control member is defined by the equilibrium of the pressure forces acting thereon. 5. A turbine as claimed in claim 1, characterised in that the turbine further comprises elastic means adapted to urge the control member towards an open configuration of the nozzle. 6. A turbine as claimed in claim 1, characterised in that the annular vane nozzle of variable geormetry comprises a first vaned ring and a second vaned ring facing one another, each of the vaned rings comprising an annular member and a plurality of vanes rigidly connected to the annular member and extending towards the annular member of the other vaned ring, these vanes being tapered substantially as wedges such that the two pluralities of vanes can penetrate one another, at least one of the annular members being axially mobile with respect to the other annular member and formed the control member. 7. A turbocompressor for an internal combustion engine, characterised in that it comprises a variable geometry as claimed in claim 1. 8. A turbine as claimed in claim 1, wherein the control chamber is not in flow communication with the inlet channel. 9. A turbine as claimed in claim 1, further comprising a control chamber,wherein the control surface is subject to the control pressure in said control chamber, andwherein the auxiliary chamber is different from the control chamber. 10. A turbine as claimed in claim 9, wherein the control chamber is not in flow communication with the auxiliary chamber. 11. A variable geometry turbine comprising:a housing;a rotor supported in a rotary manner in said housing, said housing defining a spiral-shaped inlet channel for operating fluid, said inlet channel surrounding said rotor;a fluid control line;a fluid actuator;an auxiliary chamber connection means; andan annular vaned nozzle havin g a geometry interposed radially between the channel and the rotor, said annular vaned nozzle comprising an axially moving control member and a throat section, said control member being configured to control the flow of the operating fluid from the inlet channel to the rotor by varying said throat section,wherein said control member constitutes an annular piston of said fluid actuator, and the control member being actuated directly by a control pressure via said fluid control line,wherein the control member is an annular member provided with a plurality of vanes extending axially, the housing having a plurality of slots for housing the vanes in a closed or partially closed configuration of the nozzle,wherein the control member further comprises a control surface subject to the control pressure and oriented axially so as to move the control member toward a closed configuration in response to an increase in the control pressure, the control member further having a reaction surface subject to the pressure of the operating fluid in the nozzle and oriented axially in a direction opposite to that of the control surface. 12. A method for controlling a turbine inlet pressure in an internal combustion engine supercharged by a turbocompressor, the turbocompressor including a variable geometry turbine having an inlet channel in flow communication with a rotor via a nozzle, the rotor defining an axial direction, the nozzle including a plurality of vanes, the method comprising:providing the vanes;providing axially extending slots for slidably receiving the vanes;providing operating fluid to the inlet channel;providing a control member having a control surface and a reaction surface oriented axially in a direction opposite to that of (he control surface;flowing the operating fluid radially inward from the inlet channel to the rotor via the nozzle;moving the vanes axially within the slots via the control member, the movement of the vanes varying a flow area of the nozzle so as to control the amount of operating fluid flowing through the nozzle,placing a pressure on the reaction surface via the operating fluid; andplacing a control pressure on the control surface. 13. The method of claim 12, further comprising a step of providing an auxiliary surface oriented axially in the same direction as the control surface and housed in an auxiliary chamber; andplacing an auxiliary pressure on the auxiliary surface via the operating fluid.

이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 9

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특허 상세정보

Variable geometry turbine

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이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 9

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Variable geometry turbine

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이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 9

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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