WO2011015908A1 - Turbine à géométrie variable - Google Patents

Turbine à géométrie variable Download PDF

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Publication number
WO2011015908A1
WO2011015908A1 PCT/IB2009/054055 IB2009054055W WO2011015908A1 WO 2011015908 A1 WO2011015908 A1 WO 2011015908A1 IB 2009054055 W IB2009054055 W IB 2009054055W WO 2011015908 A1 WO2011015908 A1 WO 2011015908A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
variable geometry
geometry turbine
wall member
flow path
Prior art date
Application number
PCT/IB2009/054055
Other languages
English (en)
Inventor
Loïc DURBIANO
Original Assignee
Renault Trucks
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Renault Trucks filed Critical Renault Trucks
Priority to PCT/IB2009/054055 priority Critical patent/WO2011015908A1/fr
Publication of WO2011015908A1 publication Critical patent/WO2011015908A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the present invention relates to a variable geometry turbine.
  • a variable geometry turbine may be linked with a compressor to form a turbocharger used in particular to equip trucks.
  • a turbocharger supplies compressed air to the intake of an internal combustion engine, i.e. air at a boost pressure above the atmospheric pressure.
  • the turbine stage of a turbocharger essentially comprises a turbine wheel mounted on a rotatable shaft within a turbine housing.
  • the turbine housing is connected downstream of an engine outlet manifold, in such a way that the exhaust gas flow drives the turbine wheel in rotation about the turbine axis.
  • the turbine wheel rotates a compressor wheel which is mounted on the other end of the shaft.
  • US-A-2009064679 describes a variable geometry turbine comprising an annular inlet flow path and an inlet chamber extending around the inlet flow path.
  • the inlet flow path is defined between a wall member and a wall portion of the turbine housing.
  • a turbocharger may further comprise vanes arranged about the inlet flow path in order to deflect gas flow towards the direction of rotation of the turbine wheel, so as to increase the turbine efficiency.
  • the inlet chamber collects all or part of the exhaust gas coming from the engine outlet manifold and guides it to the inlet flow path.
  • the inlet flow path guides the gas flow from the inlet chamber to the turbine wheel.
  • exhaust gas admitted into the inlet chamber flows through the inlet flow path and thence onto the turbine wheel down to an outlet arranged about the turbine axis. Exhaust gas thereby rotates the turbine wheel.
  • the wall member can be movable parallel to the turbine axis so as to vary a dimension of the inlet flow path.
  • exhaust gas flow rates and velocities can be optimized over a range of engine rotation speeds and torques, depending on the driver's command.
  • a minimum dimension of the inlet flow path may be required, either for adjusting the turbocharger performance to engine low speeds, or to enhance regeneration of the diesel particulate filter when the exhaust gas temperature is not high enough.
  • One of the purposes of the present invention is to reduce such a noise, by providing a variable geometry turbine designed to change the gas flow conditions upstream of the turbine wheel, thereby reducing such a noise.
  • variable geometry turbine for a turbocharger, comprising;
  • a wall member facing a wall portion of the housing so as to define an annular inlet flow path for guiding a gas flow to the turbine wheel, the wall member being movable to vary a dimension of the inlet flow path along a direction parallel to the turbine axis.
  • the inlet flow path includes at least one gas expansion volume diverging towards the turbine wheel.
  • the gas expansion volume extends, in a direction perpendicular to the turbine axis, only along a downstream portion of the inlet flow path.
  • the portions of the facing surfaces of the wall member and of the wall portion are generally plane and perpendicular to the turbine axis.
  • the gas expansion volume is delimited by a recess surface of the wall member.
  • the gas expansion volume is delimited by a recess surface of the wall portion.
  • the recess surface is convex or concave.
  • a cross-section of the recess surface, in a plane comprising the turbine axis, is frustoconical.
  • a cross-section of the recess surface, in a plane comprising the turbine axis, is in the shape of a shoulder.
  • a cross-section of the recess surface, in a plane comprising the turbine axis, has a curved shape.
  • the gas expansion volume extends, in a direction perpendicular to the turbine axis, all along the inlet flow path.
  • the surface of the wall member which faces the wall portion is generally plane and sloped with respect to the wall portion.
  • the surface of the wall member which faces the wall portion is generally curved.
  • the wall member is movable parallel to the turbine axis.
  • the wall member belongs to a nozzle ring.
  • the nozzle ring comprises several vanes distributed over the wall member and extending generally parallel to the turbine axis, and the wall portion has an annular groove for totally or partially receiving the vanes.
  • FIG. 1 is an axial cross-section through a variable geometry turbine according to a first embodiment of the invention
  • figure 2 is a front view of a nozzle ring of the variable geometry turbine of figure 1 ;
  • figure 3 is an axial cross-section, at a scale larger than figure 1 , of a variable geometry turbine according to a second embodiment
  • - figure 4 is a view similar to figure 3 of a variable geometry turbine according to a third embodiment
  • - figure 5 is view similar to figure 3 of a variable geometry turbine according to a fourth embodiment
  • figure 6 is view similar to figure 3 of a variable geometry turbine according to a fifth embodiment
  • figure 7 is a view similar to figure 1 of a variable geometry turbine according to a sixth embodiment.
  • FIG. 8 is a view similar to figure 3 of a variable geometry turbine according to a seventh embodiment.
  • a variable geometry turbine T comprises a housing 1 and a turbocharger body 2 which together enclose various components of the turbine T.
  • the turbine housing 1 defines an inlet chamber 3 which is in the shape of a volute.
  • a turbine wheel 4 is mounted between the turbocharger body 2 and the housing 1 .
  • Turbine T further comprises a nozzle ring having a wall member 21 arranged to move in an axial direction X with respect to the turbocharger body 2 and to the housing 1.
  • wall member 21 is movable along a stroke illustrated by the double arrow 25.
  • the nozzle ring has an annular shape with a symmetry of revolution around turbine axis Xj.
  • the adjective “axial” refers to a direction parallel to the turbine axis X T , like axial direction X at figure 1.
  • the adjective “radial” refers to a direction perpendicular to the turbine axis, like radial direction Y at figure 1.
  • Wall member 21 and wall portion 10 both extend in the radial direction Y.
  • Wall member 21 faces a wall portion 10 of the housing 1 so as to define an annular inlet flow path 30.
  • Inlet flow path 30 hence extends between a radial surface 22 of wall member 21 and the corresponding surface of the wall portion 10. In service, inlet flow path 30 guides a gas flow 34 from the inlet chamber 3 towards the blades of the turbine wheel 4.
  • an upstream part 1 1 of the wall portion 10 is formed by the housing 1 itself.
  • a median part 12 of the wall portion 10 is formed by an annular plate 14.
  • a downstream portion 13 of the wall portion 10 is also formed by the housing 1 itself.
  • the nozzle ring is equipped with several vanes 24 which are distributed over the wall member 21 and which extend along an axial direction X from the radial surface 22 into a groove 15 of housing 1.
  • the vanes 24 extend between a minimum radius R mm and a maximum radius R ma ⁇ -
  • the vanes 24 deflect gas flow 34 through the inlet flow path 30 towards the direction of rotation of the turbine wheel 4 to increase the efficiency of the latter.
  • the nozzle ring and its wall member 21 are movable along an axial direction X to vary a dimension X 30 of the inlet flow path 30.
  • the dimension X 30 varies depending on the required turbocharger performance.
  • the wall member 21 is movable parallel to the turbine axis X T , hence varying only the axial dimension X 30 of the inlet flow path 30.
  • the opening represented by dimension X 30 is at a minimum which corresponds to a throttle position where the pressure in the turbine wheel 4 remains under a predetermined threshold, say 4.5 bars gage, during the regeneration of a Diesel particulate filter.
  • inlet flow path 30 includes a gas expansion volume 31 which is divergent towards the turbine wheel 4.
  • divergent means that the axial dimension of the inlet flow path 30 increases, continuously or discretely, to become greater than the minimum dimension X 30 .
  • volume 31 is called a "gas expansion" volume.
  • Gas expansion volume 31 extends, in a radial direction Y, only along a downstream portion of the inlet flow path 30. Indeed, gas expansion volume 31 is delimited by a recess surface 23 of wall member 21. Recess surface 23 radially extends inside the minimum radius R mm .
  • upstream and downstream refer to the general direction of exhaust gas flow 34, i.e. from the inlet chamber 3 to the turbine wheel 4. More accurately, the term “downstream” refers to a part of the wall member 21 or of the wall portion 10 which is located between the turbine wheel 4 and the part of the inlet flow path 30 which has the minimum dimension, say X30 on figure 1 , when considering the whole inlet flow path 30.
  • the portions of the facing radial surfaces respectively belonging to the wall portion 10 and to the wall member 21 , indicated as 22 on figure 1 are plane and perpendicular to the turbine axis X ⁇ .
  • recess surface 23 is concave when considered from the solid matter of wall member 21.
  • the concavity of the recess surface permits to make an important expansion at the beginning of the gas expansion volume 31 and then to smooth this expansion just before the gas flow 34 arrives onto the blades of the turbine wheel.
  • Gas expansion volume 31 decreases the gas pressure at the turbine wheel 4 and the velocities of gas flow 34. Gas expansion volume 31 permits to eliminate or to significantly reduce the noise generated by the gas flowing onto the blades of the turbine wheel of a background art variable geometry turbine.
  • Figure 3 illustrates a variable geometry turbine according to a second embodiment of the invention.
  • the essential parts of the variable geometry turbine of figure 3 have structures and/or functions which are quite similar to the structures and/or functions of the corresponding parts of variable geometry turbine T.
  • the description given above in relation with figure 1 can be transposed to figure 3, with the exception of the hereafter stated differences.
  • the reference numbers of a part of the variable geometry turbine of figure 3 can be directly derived, by adding 300 to it, from the reference number of the part of the variable geometry turbine T having the corresponding structure and/or function.
  • One can thus define a housing 301 , a turbine wheel 304, a wall portion 310, a wall member 321 , a radial surface 322, a recess surface 323, an inlet flow path 330, a gas expansion volume 331 and a gas flow 334.
  • variable geometry turbine of figure 3 differs from the variable geometry turbine T, because the cross-section of the recess surface 323, considered in a plane comprising the turbine axis X T , is frustoconical. Such a frustoconical cross- section provides a continuous increase of the axial dimension of the inlet flow path 330, hence a progressive gas expansion.
  • the recess surface 323 is convex. The convexity of the recess surface permits to make a smooth and progressive expansion all along the gas expansion volume 31.
  • Figure 4 illustrates a variable geometry turbine according to a third embodiment of the invention.
  • the essential parts of the variable geometry turbine of figure 4 have structures and/or functions which are quite similar to the structures and/or functions of the corresponding parts of variable geometry turbine T.
  • the description given above in relation with figure 1 can be transposed to figure 4, with the exception of the hereafter stated differences.
  • the reference numbers of a part of the variable geometry turbine of figure 4 can be directly derived, by adding 400 to it, from the reference number of the part of the variable geometry turbine T having the corresponding structure and/or function.
  • One can thus define a housing 401 , a turbine wheel 404, a wall portion 410, a wall member 421 , a radial surface 422, a recess surface 423, an inlet flow path 430 and a gas expansion volume 431.
  • variable geometry turbine of figure 4 differs from the variable geometry turbine T, because the cross-section of the recess surface 423, considered in a plane comprising the turbine axis X ⁇ , has a curved shape.
  • the recess surface 423 is formed by a fillet linking the wall member 421 with a perpendicular wall of the nozzle ring.
  • the recess surface 423 is convex.
  • Such a fillet cross-section provides a continuously increasing axial dimension of the inlet flow path 430.
  • Figure 5 illustrates a variable geometry turbine according to a fourth embodiment of the invention.
  • the essential parts of the variable geometry turbine of figure 5 have structures and/or functions which are quite similar to the structures and/or functions of the corresponding parts of variable geometry turbine T.
  • the description given above in relation with figure 1 can be transposed to figure 5, with the exception of the hereafter stated differences.
  • the reference numbers of a part of the variable geometry turbine of figure 5 can be directly derived, by adding 500 to it, from the reference number of the part of the variable geometry turbine T having the corresponding structure and/or function.
  • One can thus define a housing 501 , a turbine wheel 504, a wall portion 510, a wall member 521 , a radial surface 522, a recess surface 523, an inlet flow path 530 and a gas expansion volume 531.
  • variable geometry turbine of figure 5 differs from the variable geometry turbine T, because the cross-section of the recess surface 523, considered in a plane comprising the turbine axis X ⁇ , has a curved shape.
  • the recess surface 523 is convex. Unlike the fillet of recess surface 423, the recess surface 523 has a curvature which stops without joining the perpendicular wall of the nozzle ring.
  • Figure 6 illustrates a variable geometry turbine according to a fifth embodiment of the invention.
  • the essential parts of the variable geometry turbine of figure 6 have structures and/or functions which are quite similar to the structures and/or functions of the corresponding parts of variable geometry turbine T.
  • the description given above in relation with figure 1 or figure 5 can be transposed to figure 6, with the exception of the hereafter stated differences.
  • the reference numbers of a part of the variable geometry turbine of figure 6 can be directly derived, by adding 600 to it, from the reference number of the part of the variable geometry turbine T having the corresponding structure and/or function.
  • One can thus define a housing 601 , a turbine wheel 604, a wall portion 610, a wall member 621 , a radial surface 622, a recess surface 623, an inlet flow path 630 and a gas expansion volume 631.
  • variable geometry turbine of figure 6 differs from the variable geometry turbine of figure 5, because the cross-section of the recess surface 623, considered in a plane comprising the turbine axis X T , has a concave curved recess surface 623, whereas the recess surface 523 is convex.
  • Figure 7 illustrates a variable geometry turbine according to a sixth embodiment of the invention.
  • the essential parts of the variable geometry turbine of figure 7 have structures and/or functions which are quite similar to the structures and/or functions of the corresponding parts of variable geometry turbine T.
  • the description given above in relation with figure 1 can be transposed to figure 7, with the exception of the hereafter stated differences.
  • the reference numbers of a part of the variable geometry turbine of figure 7 can be directly derived, by adding 700 to it, from the reference number of the part of the variable geometry turbine T having the corresponding structure and/or function.
  • variable geometry turbine of figure 7 differs from the variable geometry turbine T, because the gas expansion volume 731 extends, in a radial direction Y, all along the inlet flow path 730. Indeed, the front surface 722 of wall member 721 , which faces the wall portion 710, is generally plane and sloped with respect to the wall portion 710, hence not radial.
  • Gas expansion volume 731 almost wholly corresponds to the inlet flow path 730, since they have similar dimensions and locations. Such a gas expansion volume 731 permits a large gas expansion, thus strongly decreasing the pressure of the gas flow 734 before its arrival on the blades of turbine wheel 704.
  • Figure 8 illustrates a variable geometry turbine according to a seventh embodiment of the invention.
  • the essential parts of the variable geometry turbine of figure 8 have structures and/or functions which are quite similar to the structures and/or functions of the corresponding parts of variable geometry turbine T.
  • the description given above in relation with figure 1 can be transposed to figure 8, with the exception of the hereafter stated differences.
  • the reference numbers of a part of the variable geometry turbine of figure 8 can be directly derived, by adding 800 to it, from the reference number of the part of the variable geometry turbine T having the corresponding structure and/or function.
  • variable geometry turbine of figure 8 differs from the variable geometry turbine of figure 1 , because the gas expansion volume 831 is delimited by a recess surface 823 belonging to the wall portion 810. More accurately, a downstream portion 813 of the wall portion 810 is curved so as to enlarge the axial dimension of the inlet flow path 830.
  • the radial surface 822 of wall member 821 is plane on the whole extension of the inlet flow path 830, whereas the wall portion 810, in particular its downstream portion 813, turns away from the radial surface 822.
  • the recess surface 823 is convex.
  • the blades of the turbine wheel 804 are slightly longer than the blades of the previously described turbine wheels of figures 1 to 7, so as to compensate for the fact that the downstream part 813 turns away from the radial surface 822. Radial clearances between, on the one hand, the blades and the housing and, on the other hand, the blades and the nozzle ring are thus kept unchanged in order to keep the turbine wheel properly running with its usual efficiency.
  • the recess surface of the wall portion can have different shapes, e.g. frustoconical, shoulder, a fillet, etc.
  • the recess surface radially extends between the vanes, i.e. partly larger than the minimum radius R mm or even larger than the maximum radius R max .
  • the surface of the wall member which faces the wall portion is generally curved, in lieu of the plane surface 722.
  • a variable geometry turbine according to the present invention comprising a gas expansion volume diverging towards a turbine wheel, permits to eliminate or significantly reduce the noise generated by the gas flow arriving onto the blades of the turbine wheel.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

L'invention porte sur une turbine à géométrie variable (T) qui comprend une roue de turbine (4) ; un boîtier (1) destiné à supporter la roue de turbine (4) mobile en rotation autour d'un axe de turbine ; un élément de paroi (21) qui fait face à une partie de paroi (10) du boîtier (1) de manière à définir un trajet d'écoulement d'entrée annulaire (30) destiné à guider un écoulement de gaz (34) jusqu'à la roue de turbine (4), l'élément de paroi (21) étant mobile pour faire varier une dimension (X30) du trajet d'écoulement d'entrée (30) le long d'une direction (X) parallèle à l'axe (XT) de la turbine. Le trajet d'écoulement d'entrée annulaire (30) comprend au moins un volume d'expansion de gaz (31) qui diverge en direction de la roue de turbine (4).
PCT/IB2009/054055 2009-08-04 2009-08-04 Turbine à géométrie variable WO2011015908A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/IB2009/054055 WO2011015908A1 (fr) 2009-08-04 2009-08-04 Turbine à géométrie variable

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2009/054055 WO2011015908A1 (fr) 2009-08-04 2009-08-04 Turbine à géométrie variable

Publications (1)

Publication Number Publication Date
WO2011015908A1 true WO2011015908A1 (fr) 2011-02-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2009/054055 WO2011015908A1 (fr) 2009-08-04 2009-08-04 Turbine à géométrie variable

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014167336A1 (fr) * 2013-04-10 2014-10-16 Cummins Ltd Turbine à géométrie variable
US20170356333A1 (en) * 2014-11-19 2017-12-14 Brunel University London Variable geometry turbocharger turbine
WO2022263823A1 (fr) * 2021-06-17 2022-12-22 Cummins Ltd Bague de buse pour une turbine à géométrie variable

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR667306A (fr) * 1928-02-02 1929-10-15 Rateau Soc Dispositif de réglage des conditions de marche des machines centrifuges
US4445815A (en) * 1980-06-09 1984-05-01 United Technologies Corporation Temperature regulation of air cycle refrigeration systems
WO2000020726A1 (fr) * 1998-10-05 2000-04-13 Alliedsignal, Inc. Mecanisme de commande d'une turbine a geometrie variable a aubes coulissantes
WO2001053679A1 (fr) * 2000-01-14 2001-07-26 Alliedsignal Turbo S.A. Turbocompresseur a ailettes coulissantes avec surfaces aerodynamiques et ecran thermique combines et dispositif d'actionnement axial decouple
EP1260676A1 (fr) * 2001-05-25 2002-11-27 Iveco Motorenforschung AG Dispositif pour commander un bec variable d'une turbine
GB2413830A (en) * 2004-05-06 2005-11-09 Cummins Inc Control of exhaust gas temperature of turbocharger

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR667306A (fr) * 1928-02-02 1929-10-15 Rateau Soc Dispositif de réglage des conditions de marche des machines centrifuges
US4445815A (en) * 1980-06-09 1984-05-01 United Technologies Corporation Temperature regulation of air cycle refrigeration systems
WO2000020726A1 (fr) * 1998-10-05 2000-04-13 Alliedsignal, Inc. Mecanisme de commande d'une turbine a geometrie variable a aubes coulissantes
WO2001053679A1 (fr) * 2000-01-14 2001-07-26 Alliedsignal Turbo S.A. Turbocompresseur a ailettes coulissantes avec surfaces aerodynamiques et ecran thermique combines et dispositif d'actionnement axial decouple
EP1260676A1 (fr) * 2001-05-25 2002-11-27 Iveco Motorenforschung AG Dispositif pour commander un bec variable d'une turbine
GB2413830A (en) * 2004-05-06 2005-11-09 Cummins Inc Control of exhaust gas temperature of turbocharger

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014167336A1 (fr) * 2013-04-10 2014-10-16 Cummins Ltd Turbine à géométrie variable
CN104334836A (zh) * 2013-04-10 2015-02-04 康明斯有限公司 可变几何涡轮机
KR101753198B1 (ko) 2013-04-10 2017-07-04 커민스 리미티드 가변 구조 터빈
US9945286B2 (en) 2013-04-10 2018-04-17 Cummins Ltd. Variable geometry turbine
US20170356333A1 (en) * 2014-11-19 2017-12-14 Brunel University London Variable geometry turbocharger turbine
WO2022263823A1 (fr) * 2021-06-17 2022-12-22 Cummins Ltd Bague de buse pour une turbine à géométrie variable
GB2624550A (en) * 2021-06-17 2024-05-22 Cummins Ltd Nozzle ring for a variable geometry turbine

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