WO2012095212A1 - Dispositif directeur pour une turbine ainsi que turbocompresseur doté d'une telle turbine - Google Patents

Dispositif directeur pour une turbine ainsi que turbocompresseur doté d'une telle turbine Download PDF

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Publication number
WO2012095212A1
WO2012095212A1 PCT/EP2011/071061 EP2011071061W WO2012095212A1 WO 2012095212 A1 WO2012095212 A1 WO 2012095212A1 EP 2011071061 W EP2011071061 W EP 2011071061W WO 2012095212 A1 WO2012095212 A1 WO 2012095212A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
blade part
guide device
blade
turbocharger
Prior art date
Application number
PCT/EP2011/071061
Other languages
German (de)
English (en)
Inventor
Steffen Lippert
Martin Hopp
Jawor Seidel
Original Assignee
Pierburg Gmbh
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 Pierburg Gmbh filed Critical Pierburg Gmbh
Publication of WO2012095212A1 publication Critical patent/WO2012095212A1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/02—EGR systems specially adapted for supercharged engines
    • F02M26/09—Constructional details, e.g. structural combinations of EGR systems and supercharger systems; Arrangement of the EGR and supercharger systems with respect to the engine
    • F02M26/10—Constructional details, e.g. structural combinations of EGR systems and supercharger systems; Arrangement of the EGR and supercharger systems with respect to the engine having means to increase the pressure difference between the exhaust and intake system, e.g. venturis, variable geometry turbines, check valves using pressure pulsations or throttles in the air intake or exhaust system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/02—EGR systems specially adapted for supercharged engines
    • F02M26/04—EGR systems specially adapted for supercharged engines with a single turbocharger
    • F02M26/05—High pressure loops, i.e. wherein recirculated exhaust gas is taken out from the exhaust system upstream of the turbine and reintroduced into the intake system downstream of the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/31—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the invention relates to a guide device for a turbine with a blade ring arranged concentrically around a central axis of a turbine housing with a plurality of guide vanes, each having a fixed first blade part on the inlet side and a movable second blade part on the outlet side, an adjusting ring, via which the second blade part is adjustable, wherein the second turbine blade part is arranged in a first position at least partially in a receptacle of the first blade part and a turbine of a turbocharger with a guide and a bypass channel between an inlet and an outlet of the turbine and a waste gate valve, which dominates the flow area of the bypass channel.
  • Adjustable guide devices prior to entry into the turbine of a turbocharger serve to control the desired turbine power and to regulate the exhaust gas backpressure for the exhaust gas recirculation.
  • the guide devices usually consist of blade rings.
  • variable blade rings which are pushed axially into the gap between the annulus and turbine wheel and thus close the gap over a certain width and rotatable blades, over which the Angle of attack is adjusted to the turbine runner. Accordingly, both gas quantities and flow directions can be regulated via the guide grids.
  • a turbocharger with a guide grid for the turbine which is constructed in two parts.
  • a fixed upstream ring is composed of a fixed distance from each other and at a fixed angle to the central axis of the turbocharger arranged blade tips together, the back sides extend to a downstream thereto arranged second ring.
  • This second ring is rotatable and has blade ends which can be rotated away from or behind the blade tips by rotation of the ring.
  • the blade tips have a recess which is formed in a shape-accurate manner to the blade ends.
  • a vane ring for turbomachines in which the guide vanes are also made in two parts, wherein the upstream part is fixed and the downstream part is rotatably arranged for this purpose.
  • the blade ring Upon actuation of the blade ring is corresponding to the inflow angle adjusted to the impeller, but the free flow cross section is only slightly changed.
  • the disadvantages that the possible Verstellvariationen the guide devices are severely limited, so that an adaptation to all operating conditions is not possible.
  • the embodiments with a rotatable blade has the disadvantage that the distance to the impeller is changed with rotation of the blades, so that at a largely closed position of the blades no optimal flow of the impeller is given more.
  • the guide vanes by means of which the flow cross-section is restricted there is a considerable loss of efficiency.
  • the second blade part is rotatably mounted in the downstream region via an adjusting pin in the adjusting ring.
  • the movement of the adjusting ring can be transmitted to the second blade part in a simple manner, wherein a rotatability of the blade part is maintained.
  • the fixed first blade part essentially has a U-shape, in the open end of which the movable second blade part can be inserted.
  • a preferred mounting of the second blade part is achieved in that the second blade part in the upstream region is guided on both sides via journals in grooves. This double-sided storage increases stability with ease of manufacture.
  • the second blade part is guided in the first blade part.
  • the first blade part is formed from a bent sheet metal. This design reduces the weight and is inexpensive to produce.
  • the first blade part is cast with one of the turbine housing parts. This reduces the necessary assembly steps and increases the durability of the blade part.
  • the bypass duct is formed in the turbine housing and has a space in which a valve body of the wastegate valve is arranged. Thus, the total space required can be reduced. At the same time accounts for additional cables and housing parts, whereby the assembly costs and manufacturing costs are reduced.
  • the waste gate valve is mounted in the turbine housing, whereby the number of necessary components and thus the assembly costs are additionally reduced.
  • FIG. 2 shows a top view of the guide device in the retracted turbine.
  • FIG. 3 schematically shows a single second blade part in side view.
  • the turbine according to the invention of an exhaust-gas turbocharger has a turbine housing 2, which is fastened to a bearing housing, not shown, of a turbocharger and which has a spiral-shaped annular channel 4 into which exhaust gas can flow via a tangential inlet 6. After radially inward, the annular channel 4 is bounded by an annular gap 8, via which the annular channel 4 is fluidically connected to an impeller chamber 10 in which an impeller 12 of the turbine is arranged. On the turbine housing 2, an outlet 14 is formed, which extends from the impeller 12, concentric to this, axially.
  • a guide device 16 is arranged, which consists of a blade rim 18, which consists of a plurality of vanes 20 which are arranged on a concentric to the impeller 12 circle.
  • Each of these guide vanes 20 consists of an inlet-side first stationary blade part 22 and an outlet-side second movable blade part 24.
  • the annular gap 8 is bounded at its lower end facing the bearing housing and at its upper end remote from the bearing housing by two rings 25, 26.
  • the first blade parts 22 are fixedly arranged between the two rings 25, 26 in the annular gap 8 and have a U-shape, the open side opposite to the exhaust gas flow is aligned obliquely in the annular gap 8, wherein each first blade portion 22 forms a receptacle 27.
  • a groove 28, 30 is formed in the rings 25, 26, which groove extends along the extent of the first blade parts 22.
  • this groove 28, 30 project journals 32, 34, which are laterally guided by the groove walls and attached to the rings 25, 26 pointing ends of the second blade parts 24 or formed integrally therewith.
  • an adjustment tap 36 is formed, which is mounted in a bearing 38 of an adjusting ring 40.
  • the adjusting ring 40 surrounds the impeller 12 on the side directed towards the bearing housing and is disposed within the ring 25, wherein the two rings 25, 40 directly adjoin one another. Accordingly, the adjusting ring 40 also forms a lower side wall of the annular gap. 8
  • the adjusting ring 40 is rotatably mounted about its axis in the turbine housing, wherein the adjusting ring 40, a lever is fixed, which in turn is coupled to an actuator, in the actuation of the adjusting ring 40 is rotated.
  • By rotating the adjusting ring 40 slide the bearing pins 32, 34 of the second blade parts 24 along the grooves 28, 30.
  • the second blade parts 24 are rotated in the receptacles 27 of the first blade parts 22, while in the opposite direction of rotation, the second blade parts 24 move out of the receptacles 27, wherein the second blade parts 24 respectively perform a combined sliding movement in the linear direction and a circular movement.
  • the entire second blade parts 24 rotate about the bearing 38, that is to say around the rear part of the blade part 24, while the front end of the second blade part 24 is moved linearly along the groove 28, 30 upon actuation of the adjusting ring 40.
  • a bypass channel 44 branches off in the region of the annular gap 8, via which the annular channel 4 or the inlet 6 is fluidically connected to the outlet 14 without the exhaust gas flow Impeller 12 would have to flow through.
  • This bypass channel 44 is formed in the turbine housing 2 and is dominated by a waste gate valve 46, which is formed in the present embodiment as a flap valve, the shaft 48 is mounted in the turbine housing 2 and extends out of the turbine housing 2 for connection to an actuator.
  • the Bypasskanai 44 has a space 50 in which a valve seat is formed, which surrounds the flow cross-section of the bypass channel 44 to be controlled and on which the shaft 48 mounted on the valve-shaped valve body 52 is rotated to block the bypass flow.
  • the efficiency can thus be improved by the additionally existing controllability over the entire load range.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Abstract

On connaît des grilles déflectrices variables de turbine pour améliorer le degré d'efficacité de turbocompresseurs. Cependant, on ne connaît pas encore une aptitude au réglage totale de la section d'écoulement avec une modification simultanée de l'angle d'incidence de l'écoulement de la roue de la turbine. L'invention concerne dès lors un dispositif directeur pour une turbine dotée d'une couronne d'aubes (18) agencée concentriquement autour de l'axe central d'un carter de turbine (2), comportant plusieurs aubes déflectrices (20), qui présentent chacune, côté entrée, une première partie d'aube (22) fixe et, côté sortie, une deuxième partie d'aube (24) mobile et une bague de réglage (40) via laquelle la deuxième partie d'aube (24) est réglable. La deuxième partie d'aube (24), dans une première position, est disposée au moins partiellement dans un logement (27) de la première partie d'aube (22). Selon l'invention, la deuxième partie d'aube (24) peut être déplacée dans la première partie d'aube (22) et est assemblée de manière rotative avec la bague de réglage (40) de façon à ce que la deuxième partie d'aube (24) effectue un mouvement combiné de rotation et linéaire lors d'un actionnement.
PCT/EP2011/071061 2011-01-13 2011-11-25 Dispositif directeur pour une turbine ainsi que turbocompresseur doté d'une telle turbine WO2012095212A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011008525.4 2011-01-13
DE102011008525A DE102011008525B4 (de) 2011-01-13 2011-01-13 Leitvorrichtung für eine Turbine sowie derartige Turbine eines Turboladers

Publications (1)

Publication Number Publication Date
WO2012095212A1 true WO2012095212A1 (fr) 2012-07-19

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2011/071061 WO2012095212A1 (fr) 2011-01-13 2011-11-25 Dispositif directeur pour une turbine ainsi que turbocompresseur doté d'une telle turbine

Country Status (2)

Country Link
DE (1) DE102011008525B4 (fr)
WO (1) WO2012095212A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3301277A1 (fr) * 2016-09-30 2018-04-04 Honeywell International Inc. Turbocompresseur comportant une enveloppe de turbine à orifices

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014223013A1 (de) * 2014-11-12 2016-05-12 Volkswagen Aktiengesellschaft Turbinenlaufrad, Turbine und Abgasturbolader

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3540401A1 (de) 1985-11-14 1987-05-21 Mtu Muenchen Gmbh Leitschaufelkranz fuer turbomaschinen, insbesondere fuer gasturbinen
GB2264148A (en) * 1992-02-13 1993-08-18 Rolls Royce Plc Variable camber guide vanes for gas turbine engines.
DE4238550A1 (de) 1992-11-14 1994-05-19 Daimler Benz Ag Abgasturbolader für eine Brennkraftmaschine
DE102004033185A1 (de) * 2004-07-09 2006-02-02 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine mit axialem Drehschieberventil
EP1998026A2 (fr) * 2007-05-30 2008-12-03 Bosch Mahle Turbo Systems GmbH & Co. KG Dispositif de chargement
DE102008039086A1 (de) * 2008-08-21 2010-02-25 Daimler Ag Abgasturbolader für eine Brennkraftmaschine eines Kraftfahrzeugs
WO2010068557A2 (fr) * 2008-12-11 2010-06-17 Borgwarner Inc. Turbocompresseur simplifié à géométrie variable comportant des anneaux d'aubes directrices

Family Cites Families (3)

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Publication number Priority date Publication date Assignee Title
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
US4504190A (en) * 1983-03-09 1985-03-12 Gas Power Systems, Inc. Flow control apparatus and method
GB0801846D0 (en) * 2008-02-01 2008-03-05 Cummins Turbo Tech Ltd A variable geometry turbine with wastegate

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3540401A1 (de) 1985-11-14 1987-05-21 Mtu Muenchen Gmbh Leitschaufelkranz fuer turbomaschinen, insbesondere fuer gasturbinen
GB2264148A (en) * 1992-02-13 1993-08-18 Rolls Royce Plc Variable camber guide vanes for gas turbine engines.
DE4238550A1 (de) 1992-11-14 1994-05-19 Daimler Benz Ag Abgasturbolader für eine Brennkraftmaschine
DE102004033185A1 (de) * 2004-07-09 2006-02-02 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine mit axialem Drehschieberventil
EP1998026A2 (fr) * 2007-05-30 2008-12-03 Bosch Mahle Turbo Systems GmbH & Co. KG Dispositif de chargement
DE102008039086A1 (de) * 2008-08-21 2010-02-25 Daimler Ag Abgasturbolader für eine Brennkraftmaschine eines Kraftfahrzeugs
WO2010068557A2 (fr) * 2008-12-11 2010-06-17 Borgwarner Inc. Turbocompresseur simplifié à géométrie variable comportant des anneaux d'aubes directrices

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3301277A1 (fr) * 2016-09-30 2018-04-04 Honeywell International Inc. Turbocompresseur comportant une enveloppe de turbine à orifices
US10760437B2 (en) 2016-09-30 2020-09-01 Garrett Transportation I Inc. Turbocharger with ported turbine shroud

Also Published As

Publication number Publication date
DE102011008525B4 (de) 2013-04-04
DE102011008525A1 (de) 2012-07-19

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