EP2071134A2 - Turbine à géométrie variable - Google Patents

Turbine à géométrie variable Download PDF

Info

Publication number
EP2071134A2
EP2071134A2 EP08170220A EP08170220A EP2071134A2 EP 2071134 A2 EP2071134 A2 EP 2071134A2 EP 08170220 A EP08170220 A EP 08170220A EP 08170220 A EP08170220 A EP 08170220A EP 2071134 A2 EP2071134 A2 EP 2071134A2
Authority
EP
European Patent Office
Prior art keywords
vanes
turbine
guide
guide vane
rotation
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP08170220A
Other languages
German (de)
English (en)
Other versions
EP2071134A3 (fr
Inventor
Martin Rauscher
Andreas Wengert
Gunter Winkler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BMTS Technology GmbH and Co KG
Original Assignee
Bosch Mahle Turbo Systems GmbH and Co KG
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 Bosch Mahle Turbo Systems GmbH and Co KG filed Critical Bosch Mahle Turbo Systems GmbH and Co KG
Publication of EP2071134A2 publication Critical patent/EP2071134A2/fr
Publication of EP2071134A3 publication Critical patent/EP2071134A3/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated

Definitions

  • a Ablasseklappe Waaste gate
  • This can be done the control of the boost pressure, especially in turbochargers for internal combustion engines.
  • An alternative to the waste gate is the adjustment of the inflow to the turbine impeller of the turbine part of the exhaust gas turbocharger by means of rotatable or displaceable guide vanes.
  • exhaust gas turbochargers which are used in the automotive sector, to loader pressure increase of internal combustion engines, rotatable vanes have prevailed.
  • Rotatable vanes are also referred to as VTG (Variable Turbine Geometry). If the rotatable vanes are to be closed, ie the vanes are rotated so that the flow is directed almost radially, and only a small flow area remains between the vanes, the blade ends move away from the turbine inlet.
  • VTG Very Turbine Geometry
  • a variant for rotatable vanes is made US 3,033,519 known. It has been found that it is beneficial for the efficiency of variable turbine blade geometry, ie, variably arranged vanes, to enter a turbine wheel when the blade end of the rotatable vanes - and only these are considered below - especially at closed VTG position Radial is located very close to the turbine inlet and the distance between the blade end and the turbine inlet is minimal.
  • variable turbine geometry Upon normal positioning of the vane on an axis of rotation by which it is actuated, the vane end moves away from the periphery of the turbine wheel as the variable turbine geometry is closed as the vanes move.
  • the minimum blade length of the rotatably arranged vanes of the variable turbine geometry is determined by the circumference of the blade chain in closed Position of the vanes and the overlap of two vanes. When arranged relatively far outside arranged vanes, the disadvantage of larger size results. Leakage flows that run past the sides of the blade lead to disadvantages in the thermodynamic efficiency.
  • the gap surface extends between the turbine housing and the vanes of the Variable Turbine Geometry.
  • the portion of the flow passing between the vanes has a defined direction dictated by the vanes.
  • the part of the flow that flows through the sides, between the vanes and the housing of the turbine part disturbs this directed flow and leads to a false flow of the turbine wheel, which adversely affects the efficiency.
  • This can be remedied.
  • variable turbine geometry in particular a number of stator blades, which are arranged in a circle around a turbine wheel of a turbine part of a charging device, in particular an exhaust gas turbocharger, such that one blade end of the respective stator blades, in particular with closed variable turbine geometry (ie closed VTG ), radially possible close to the turbine inlet, that is as close as possible to the circumference of the turbine runner.
  • closed VTG closed variable turbine geometry
  • the individual blades which are arranged distributed on a blade ring around the entrance of the turbine runner wheel, are arranged eccentrically to their respective axes of rotation.
  • the eccentricity in which the wing-shaped profiled vanes are arranged in their axes of rotation along the blade ring, is selected so that the blade end of the respective vanes in the salaried state, ie in the position in which the guide vane is set in the direction of the circumference of the turbine runner , becomes minimal.
  • the blade end can be positioned radially closer to the periphery of the turbine runner in the closed position, which can achieve an increase in the efficiency of the turbine part.
  • variable turbine geometry proposed according to the invention
  • a reduction in the gap area between the turbine housing and the guide vanes of the variable turbine geometry proposed according to the invention can be achieved.
  • the part of the exhaust gas flow passing through between the vanes of the VTG and the housing of the turbine part and the directional flow generated by the vanes can be negatively influenced to a false flow of the turbine wheel can be significantly reduced, which increases the achievable efficiency of the turbine part.
  • variable turbine geometry with the inventively proposed eccentrically arranged vanes
  • the open position in which a large flow cross-section is opened. If the vanes of the variable turbine geometry are nearly circumferentially, only a small area for flow in the radial direction with respect to the circumference of the turbine runner is available to the flow. This position is accordingly referred to as a closed position.
  • the blade chain ie the circumference of the guide vanes driven along in the closed position along the blade ring, is moved closer to the circumference of the turbine runner overall. Due to this measure can be achieved that the length of the individual wing-like profiled vanes and their number can be reduced or optimized. Shorter vanes reduce the adjusting aerodynamic forces on the vanes, thereby reducing the actuator force necessary for adjustment. A smaller number of blades results in cost advantages in terms of the number of parts and assembly.
  • an auxiliary blade or an auxiliary blade can be arranged on an axis of rotation, on which a guide blade is accommodated eccentrically to the axis of rotation, which favorably influences the moment required for actuating the respective axis of rotation, d , H. in the present case.
  • a reduction in the moment required to operate the vane ring of the Variable Turbine Geometry (VTG) allows the use of a smaller actuator.
  • the auxiliary blade or the auxiliary wing which is received at an angle to the guide vane on the axis of rotation, form with the guide vane a funnel-shaped channel whose inlet cross-section is larger on the upstream side than on the outflow side.
  • FIG. 1 shows a known from the prior art, a turbine wheel associated variable turbine geometry (VTG).
  • VFG turbine wheel associated variable turbine geometry
  • a turbine runner 10 which is in particular a turbine runner of a turbine part of a supercharger designed as a turbocharger, comprises a number of airfoils 18.
  • An exhaust gas flow 12 flows to an inflow side 14 of a circumference 32 of the turbine runner 10 and flows over an outflow side 16 from individual channels 20, which are bounded in each case by two blade leaves 18, at an outflow side 16 again.
  • the channels 20, which extend on the turbine runner 10 from the inflow side 14 to the outflow side 16, have a continuous cross-sectional widening 22 in the direction of the center of the turbine runner 10.
  • a blade ring 24 Concentric with the circumference 32 of the turbine runner 10, a blade ring 24 is arranged. On the blade ring 24 is a number of blades 28 of a variable turbine geometry (VTG).
  • VGT variable turbine geometry
  • the axis of the turbine runner 10, which coincides with the axis of the blade ring 24, is identified by reference numeral 26.
  • Figure 1.1 shows a vane according to the VTG in FIG. 1 in the closed state.
  • FIG. 2 shows that analogous to the turbine runner 10 according to FIG. 1
  • On the turbine runner 10 a number of blades 18 are formed, which extend from the inflow side 14 to the outflow side 16 to form channels 20.
  • the channels 20 have, starting from the inflow side 14 to the outflow side 16, a cross-sectional widening 22 extending continuously to the axis 26 of the turbine runner 10.
  • the periphery 32 of the turbine runner 10 as shown in FIG. 2 is analogous to the representation according to FIG. 1 surrounded by a blade ring 24, which has a number of axes of rotation 36, on which arranged in an eccentricity 42 vanes 40 of the variable turbine geometry (VTG) are arranged. From the illustration according to FIG. 2 It can be seen that the vane ends 38 of the variable geometry turbine vanes (VTG) have a second, minimized change in distance 48 that is less than the first change in distance 30 upon actuation of the vanes 40 from closed to open position, as shown in FIGS Figures 2.1 and 2.2 ,
  • Figure 2.1 shows that the wing-like profiled vane 40 of the variable turbine geometry (VTG) with respect to the center of the axis of rotation 36 is received in an eccentricity 42.
  • the arrow provided with reference numeral 34 indicates the pivoting movement about which the rotation axis 36 is actuated by a not shown, preferably electrically formed actuator.
  • the individual along the blade ring 24 at axes of rotation 36 recorded guide vanes 40 are flown on its inflow side 44 of the exhaust gas flow 12. In the in FIG. 2 illustrated closed position 50, the guide vanes 40 are almost in the circumferential direction, so that the exhaust gas flow is only a small area for flow available.
  • a comparison of the displacement movements of the blade 28 of the variable turbine geometry (VTG) according to the Figures 1.1 and 1.2 for adjusting the arranged in the eccentricity 42 vanes 40 according to FIGS. 2.1 and 2.2 shows that in the proposed inventive eccentric positioning of the vanes 40 of the variable turbine geometry (VTG) to the rotation axis 36, a smaller change in the position of the respective blade end 38 to the periphery 32 of the turbine runner 10 results.
  • a further advantage of the variable turbine geometry solution proposed according to the invention is the fact that the axis of rotation 36 can be arranged radially further away from the axis 26 of the turbine runner 10, but the guide vanes 40 are not displaced. This results from the inventive eccentric mounting of the guide vanes 40, at the axes of rotation 36.
  • the adjustment mechanism for adjusting the vanes 40 of the variable turbine geometry is located on the bearing housing side of the bearing of the turbine runner 10. The size of this bearing housing in not to the same extent to reduce the circumference of the turbine runner 10. Thus, it is difficult for small turbine runners 10, the axes of rotation 36 of the vanes 40 to be placed close to the periphery of the turbine wheel 10, without resulting in overlaps between the adjustment mechanism and the bearing housing.
  • the solution proposed according to the invention makes it possible to remove the axes of rotation 86 of the guide vanes 40 radially further from the turbine wheel 10, but not to displace the guide vanes 40 themselves.
  • Reference numeral 50 denotes the closed position of the vane 40.
  • reference numeral 50 denotes the closed position of the vane 40.
  • FIG. 3 shows that on the axis of rotation 36, which is actuated by a not shown, preferably electrically formed actuator, the guide vane 40 is arranged in the eccentric 42 with respect to the axis of symmetry of the axis of rotation 36.
  • the vane 40 has a wing-shaped profile 46 and has the already mentioned upstream side 44 and the blade end 38.
  • an auxiliary blade 54 is also located on the axis of rotation 36 in an eccentricity 42 with respect to its axis of symmetry.
  • the auxiliary blade 54 is arranged at an angle of attack 58 with respect to the guide blade 40.
  • the auxiliary blade 54 like the vane 40 mounted in the eccentric 42, includes an upstream side 56 and a blade end.
  • the upstream sides 44, 56 and the blade ends of the guide vanes 40 and the auxiliary blade 54 each extend in the same directions.
  • Between the auxiliary blade 54 and the assigning this wing side of the vane 40 has a shape of a funnel 60 having channel is formed. Its inlet cross section is dimensioned to be larger than the outflow cross section defined by the blade end 38 of the guide vane 40 and the auxiliary vane 54.
  • the exhaust gas flow 12 around the vanes 40 see illustration according to FIG. 2 , generates an aerodynamic moment which acts on the vane 40 arranged in the eccentricity 42 relative to the axis of rotation 36.
  • this moment must not change its direction of rotation over the entire adjustment range of the variable turbine geometry (VTG) and thus over the entire adjustment range of the individual guide vanes 40.
  • this moment must not be too great in any position of the guide vane 40, since otherwise the actuator required for actuation for the adjustment of the axis of rotation 36 must be made larger. This would require, in particular when using an electric actuator, a significantly larger actuator, a larger torque applying actuator.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP08170220A 2007-12-13 2008-11-28 Turbine à géométrie variable Withdrawn EP2071134A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200710060044 DE102007060044A1 (de) 2007-12-13 2007-12-13 Variable Turbinengeometrie

Publications (2)

Publication Number Publication Date
EP2071134A2 true EP2071134A2 (fr) 2009-06-17
EP2071134A3 EP2071134A3 (fr) 2010-10-27

Family

ID=40418455

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08170220A Withdrawn EP2071134A3 (fr) 2007-12-13 2008-11-28 Turbine à géométrie variable

Country Status (2)

Country Link
EP (1) EP2071134A3 (fr)
DE (1) DE102007060044A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2397652A3 (fr) * 2010-06-20 2014-12-17 Honeywell International Inc. Aube de turbocompresseur à plusieurs profils aérodynamiques

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009020592A1 (de) * 2009-05-09 2010-11-11 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102012101974A1 (de) * 2012-03-08 2013-09-12 Ihi Charging Systems International Gmbh Turbine für einen Abgasturbolader
DE102019127980A1 (de) * 2019-10-16 2021-04-22 Ihi Charging Systems International Gmbh Verstellbarer Leitapparat für einen Abgasführungsabschnitt eines Abgasturboladers und Abgasturbolader

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3033519A (en) 1958-09-12 1962-05-08 United Aircraft Corp Turbine nozzle vane construction

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1071420B (de) * 1956-05-31 1959-12-17 The Garrett Corporation, Los Aneles, Calif. (V. St. A.) Verstellbarer Leitapparat für Turbinen, insbesondere Gasturbinen
US3101926A (en) * 1960-09-01 1963-08-27 Garrett Corp Variable area nozzle device
US3069070A (en) * 1961-11-14 1962-12-18 Worthington Corp Diffuser vane system for turbomachinery

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3033519A (en) 1958-09-12 1962-05-08 United Aircraft Corp Turbine nozzle vane construction

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2397652A3 (fr) * 2010-06-20 2014-12-17 Honeywell International Inc. Aube de turbocompresseur à plusieurs profils aérodynamiques

Also Published As

Publication number Publication date
DE102007060044A1 (de) 2009-06-18
EP2071134A3 (fr) 2010-10-27

Similar Documents

Publication Publication Date Title
DE112015005540B4 (de) Abgasturbolader mit kombinierter Einstelleinrichtung für Bypassventil und Flutenverbindung
DE60213906T2 (de) Steuerungsmethode für eine variable Einlassdüse einer Turbine
DE102012202907B4 (de) Abgasturbolader mit relativ zueinander verdrehbaren Leitgitterringen
EP2989298B1 (fr) Turbocompresseur à gaz d'échappement
EP3682118B1 (fr) Compresseur radial comprenant un mécanisme à diaphragme iris pour un dispositif de charge d'un moteur à combustion interne, dispositif de charge et lamelle pour le mécanisme à diaphragme iris
EP2715089B1 (fr) Turbocompresseur à gaz d'échappement comportant une vanne à décharge/à boisseau sphérique pourvue d'un bras de manivelle à détente des contraintes
WO2011101005A1 (fr) Turbine pour turbocompresseur à gaz d'échappement
EP3455477B1 (fr) Turbine pour une turbocompresseur avec un carter deux volutes et agencement de vanne pour la connection des deux volutes et contrôle de vanne de décharge
DE19924228A1 (de) Mehrflutiger, regelbarer Abgasturbolader
EP1530671B1 (fr) Turbocompresseur à gaz d'échappement pour moteur à combustion
DE102017216329A1 (de) Radialverdichter mit einem Irisblendenmechanismus für eine Aufladevorrichtung eines Verbrennungsmotors, Aufladevorrichtung und Lamelle für den Irisblendenmechanismus
EP1672178B1 (fr) Turbine casing of an exhaust turbocharger with variable turbine geometry
DE112014005008T5 (de) Turbine mit variabler Eintrittsquerschnittsfläche
EP1998026A2 (fr) Dispositif de chargement
EP2071134A2 (fr) Turbine à géométrie variable
DE60305011T2 (de) Verbesserte schaufelausführung zur verwendung in turboladern mit variabler geometrie
DE102007058962B4 (de) Variable Turbinengeometrie
WO2011137984A1 (fr) Dispositif de réglage, en particulier pour des aubes directrices d'un turbocompresseur à gaz d'échappement
DE102007017844B4 (de) Abgasturbolader, Brennkraftmaschine mit diesem Abgasturbolader und Verfahren zum Regeln des Ladedrucks des Abgasturboladers
EP1637783A1 (fr) Combinaison de soupape pour turbine à vapeur avec une soupape à fermeture rapide et une soupape de régulation
EP1391585B1 (fr) Turbocompresseur à géométrie variable
WO2014012725A1 (fr) Diffuseur parallèle pour une machine à fluide
DE102019000252A1 (de) Axialschieber-Turbine mit axial verschiebbarem Leitgitterträger
WO2013072294A2 (fr) Turbocompresseur à gaz d'échappement présentant une géométrie de turbine variable et une rondelle ressort d'étanchéité
DE102009012130A1 (de) Verstelleinrichtung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

REG Reference to a national code

Ref country code: DE

Ref legal event code: R108

AKY No designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: R108

Effective date: 20110701

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20110428