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EP1790830A1 - Turbocompresseur - Google Patents

Turbocompresseur Download PDF

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Publication number
EP1790830A1
EP1790830A1 EP20050025829 EP05025829A EP1790830A1 EP 1790830 A1 EP1790830 A1 EP 1790830A1 EP 20050025829 EP20050025829 EP 20050025829 EP 05025829 A EP05025829 A EP 05025829A EP 1790830 A1 EP1790830 A1 EP 1790830A1
Authority
EP
European Patent Office
Prior art keywords
blade
upper side
turbocharger
exhaust gas
profile
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.)
Granted
Application number
EP20050025829
Other languages
German (de)
English (en)
Other versions
EP1790830B1 (fr
Inventor
Mathias Dr. Weber
Jochen Zuck
Dietmar Metz
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.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
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 BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP16196372.3A priority Critical patent/EP3150805B1/fr
Priority to EP05025829.2A priority patent/EP1790830B1/fr
Priority to US12/094,819 priority patent/US8641382B2/en
Priority to JP2008541651A priority patent/JP4881390B2/ja
Priority to PCT/EP2006/011298 priority patent/WO2007059995A1/fr
Publication of EP1790830A1 publication Critical patent/EP1790830A1/fr
Application granted granted Critical
Publication of EP1790830B1 publication Critical patent/EP1790830B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated
    • 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
    • F05D2250/70—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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/713—Shape curved inflexed

Definitions

  • the invention relates to a turbocharger, in particular a VTG turbocharger, according to the preamble of claim 1.
  • Such a turbocharger is from the US 6,709,232 B1 (corresponding EP 1 534 933 A1 ) known.
  • variable-turbocharger turbochargers The benefits and success of direct-injection diesel engines in terms of driveability and low fuel consumption have been substantially supported by the use of variable-turbocharger turbochargers.
  • the possible operating range of the turbine can be significantly increased with good efficiency compared to bypass-controlled turbines.
  • variable turbine geometry (VTG) turbocharger When using a variable turbine geometry (VTG) turbocharger, it is known that the efficiency of using straight blades (i.e., straight skeleton blades and symmetrical thickness distribution blades) reaches their limits at high levels of turbocharging. This applies in particular to the starting range of the engine (low engine speed at full load). However, the properties of the straight blades with regard to their controllability can be described as good.
  • VGT variable turbine geometry
  • the blade geometry according to the invention has the advantage that the displacement of the axis of rotation compared to the known from the prior art blades must be made only by a smaller amount. Thus, a smaller radial space compared to known solutions is required.
  • the wave-shaped profile center line of the blade according to the invention consists of two counter-rotating shaft bellies. If this profile center line shape is entered in an XY coordinate system with horizontal X-axis and vertical Y-axis, following the leading edge of the blade, negative Y-values will first result, which will change into positive Y-values after passing through the X-axis and at where the profile centerline has a turning point.
  • thermodynamic properties results in a change in the orientation of the blade leading edge, which reduces the impact losses due to a shallower flow of the blade leading edge.
  • a blade according to the invention is defined as a self-negotiable object.
  • FIG. 1 shows a turbocharger 1 according to the invention in the form of a VTG exhaust gas turbocharger.
  • the turbocharger 1 has a turbine housing 2, which comprises an exhaust gas inlet opening 3 and an exhaust gas outlet opening 4.
  • a turbine wheel 5 is arranged in the turbine housing 2, which is mounted on a shaft 6.
  • a plurality of blades is arranged in the turbine housing 2 between the exhaust gas inlet opening 3 and the turbine wheel 5.
  • turbocharger 1 also has all other conventional components of a turbocharger such as a compressor wheel, which is mounted on the shaft 6 and arranged in a compressor housing, as well as the entire storage unit, which will not be described below, as they are for the explanation of Principles of the present invention are not required.
  • a turbocharger such as a compressor wheel, which is mounted on the shaft 6 and arranged in a compressor housing, as well as the entire storage unit, which will not be described below, as they are for the explanation of Principles of the present invention are not required.
  • FIG. 2 shows a first embodiment of a blade 7 according to the invention.
  • the blade 7 has a blade underside 8 which, when installed, is the blade side facing the turbine wheel 5.
  • the blade 7 has a blade upper side 9, which together with the blade underside 8 determines the thickness of the blade 7.
  • the blade underside 8 and the blade upper side 9 converge in the position of the blade 7 on the right-hand side in a blade leading edge 10 shown in FIG. 2 and in a blade trailing edge 11 on the left-hand side.
  • this profile center line 12 has two counter-curved regions 12A and 12B, the Embodiment yield a wavy contour of the profile centerline 12, wherein the regions 12A and 12B are each formed in the manner of shaft bellies.
  • FIG. 2 further illustrates that the profile center line 12 has a point of inflection WP and, furthermore, FIG. 2 illustrates the position of the angle of incidence ⁇ at the blade leading edge 10, which is also referred to as the nose of the profile of the blade 7.
  • the angle of incidence ⁇ is the acute angle of the tangent of the profile center line 12 at the inflection point and the tangent of the profile center line 12 B to the blade leading edge 10.
  • the profile of the profile center line 12 is plotted in an X-Y coordinate system, the X axis representing the blade length of the blade 7.
  • the representation chosen in FIG. 3 is a profile of the profile center line or skeleton line 12, formed as a vertical distance relative to the chord, which is formed by linear connection of the blade leading edge and the blade trailing edge and representing the length of the blade.
  • FIGS. 4 and 5 illustrate two basically conceivable embodiments of the blade 7 according to FIG. 2 Embodiment according to FIG. 4, the upper side 9 is formed curved in the region 13 following the blade trailing edge 11. This area is indicated in FIG. 5 by the reference numeral 13 'and is flattened, that is not curved, but flat.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05025829.2A 2005-11-25 2005-11-25 Aube de guidage de Turbocompresseur et Turbocompresseur Active EP1790830B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP16196372.3A EP3150805B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur
EP05025829.2A EP1790830B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de Turbocompresseur et Turbocompresseur
US12/094,819 US8641382B2 (en) 2005-11-25 2006-11-24 Turbocharger
JP2008541651A JP4881390B2 (ja) 2005-11-25 2006-11-24 ターボチャージャ
PCT/EP2006/011298 WO2007059995A1 (fr) 2005-11-25 2006-11-24 Turbocompresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05025829.2A EP1790830B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de Turbocompresseur et Turbocompresseur

Related Child Applications (2)

Application Number Title Priority Date Filing Date
EP16196372.3A Division EP3150805B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur
EP16196372.3A Division-Into EP3150805B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur

Publications (2)

Publication Number Publication Date
EP1790830A1 true EP1790830A1 (fr) 2007-05-30
EP1790830B1 EP1790830B1 (fr) 2019-03-27

Family

ID=36190525

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16196372.3A Active EP3150805B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur
EP05025829.2A Active EP1790830B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de Turbocompresseur et Turbocompresseur

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP16196372.3A Active EP3150805B1 (fr) 2005-11-25 2005-11-25 Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur

Country Status (4)

Country Link
US (1) US8641382B2 (fr)
EP (2) EP3150805B1 (fr)
JP (1) JP4881390B2 (fr)
WO (1) WO2007059995A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8172508B2 (en) 2010-06-20 2012-05-08 Honeywell International Inc. Multiple airfoil vanes
US8834104B2 (en) 2010-06-25 2014-09-16 Honeywell International Inc. Vanes for directing exhaust to a turbine wheel
EP2821616A4 (fr) * 2012-02-29 2016-01-13 Mitsubishi Heavy Ind Ltd Turbocompresseur à capacité variable
WO2016062531A1 (fr) * 2014-10-21 2016-04-28 Siemens Aktiengesellschaft Profilage d'aubes directrices de dispositifs directeurs pour turbomachines, en particulier compresseurs
DE102022203619A1 (de) 2022-04-11 2023-10-12 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verdichterschaufel zur Umlenkung eines strömenden Mediums in einem Verdichter, insbesondere Radialverdichter, Rotor und System

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3150805B1 (fr) * 2005-11-25 2020-09-23 BorgWarner, Inc. Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur
DE102008004014A1 (de) * 2008-01-11 2009-07-23 Continental Automotive Gmbh Leitschaufel für eine variable Turbinengeometrie
DE102009006209B4 (de) 2009-01-27 2022-12-01 BMTS Technology GmbH & Co. KG Ladeeinrichtung mit variabler Turbinengeometrie
DE102009031229A1 (de) * 2009-07-01 2011-01-20 Bosch Mahle Turbo Systems Gmbh & Co. Kg Leitschaufel
DE102009041027B4 (de) 2009-09-14 2012-02-09 Continental Automotive Gmbh Leitschaufel für einen Turbolader, Leitschaufelanordnung, Turbolader, Kraftfahrzeug und Verfahren
DE102013225642B4 (de) * 2013-12-11 2020-09-17 Vitesco Technologies GmbH Abgasturbolader mit einem verstellbaren Leitgitter
US10006341B2 (en) 2015-03-09 2018-06-26 Caterpillar Inc. Compressor assembly having a diffuser ring with tabs
US10066639B2 (en) 2015-03-09 2018-09-04 Caterpillar Inc. Compressor assembly having a vaneless space
US9822700B2 (en) 2015-03-09 2017-11-21 Caterpillar Inc. Turbocharger with oil containment arrangement
US9915172B2 (en) 2015-03-09 2018-03-13 Caterpillar Inc. Turbocharger with bearing piloted compressor wheel
US9777747B2 (en) 2015-03-09 2017-10-03 Caterpillar Inc. Turbocharger with dual-use mounting holes
US9683520B2 (en) 2015-03-09 2017-06-20 Caterpillar Inc. Turbocharger and method
US9650913B2 (en) 2015-03-09 2017-05-16 Caterpillar Inc. Turbocharger turbine containment structure
US9890788B2 (en) 2015-03-09 2018-02-13 Caterpillar Inc. Turbocharger and method
US9810238B2 (en) 2015-03-09 2017-11-07 Caterpillar Inc. Turbocharger with turbine shroud
US9732633B2 (en) 2015-03-09 2017-08-15 Caterpillar Inc. Turbocharger turbine assembly
US9638138B2 (en) 2015-03-09 2017-05-02 Caterpillar Inc. Turbocharger and method
US9739238B2 (en) 2015-03-09 2017-08-22 Caterpillar Inc. Turbocharger and method
US9903225B2 (en) 2015-03-09 2018-02-27 Caterpillar Inc. Turbocharger with low carbon steel shaft
US9752536B2 (en) 2015-03-09 2017-09-05 Caterpillar Inc. Turbocharger and method
US9879594B2 (en) 2015-03-09 2018-01-30 Caterpillar Inc. Turbocharger turbine nozzle and containment structure
DE102015205208A1 (de) * 2015-03-23 2016-09-29 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung mit variabler Turbinengeometrie
US20170152860A1 (en) * 2015-11-30 2017-06-01 Borgwarner Inc. Compressor inlet guide vanes
WO2020100222A1 (fr) * 2018-11-13 2020-05-22 三菱重工エンジン＆ターボチャージャ株式会社 Aube de distributeur
JP7386333B2 (ja) * 2020-04-23 2023-11-24 三菱重工マリンマシナリ株式会社 インペラ、及び遠心圧縮機

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH305524A (de) * 1952-10-23 1955-02-28 Tech Studien Ag Vorrichtung zur Drehrichtungsänderung eines Turbinenlaufrades.
US5299909A (en) * 1993-03-25 1994-04-05 Praxair Technology, Inc. Radial turbine nozzle vane
US6709232B1 (en) 2002-09-05 2004-03-23 Honeywell International Inc. Cambered vane for use in turbochargers
WO2005064121A1 (fr) * 2003-12-31 2005-07-14 Honeywell International, Inc. Aube cambree destinee a des turbocompresseurs

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL115026B (fr) * 1943-12-11 1949-04-15
US2484554A (en) * 1945-12-20 1949-10-11 Gen Electric Centrifugal impeller
GB1495708A (en) * 1974-01-11 1977-12-21 Kamelmacher E Blade for a centrifugal pump impeller
US4243357A (en) * 1979-08-06 1981-01-06 Cummins Engine Company, Inc. Turbomachine
US5088894A (en) * 1990-05-02 1992-02-18 Westinghouse Electric Corp. Turbomachine blade fastening
EP0567874B1 (fr) * 1992-04-27 1995-09-06 Gebrüder Becker GmbH & Co. Machine à courant pour la compression d'un gaz
DE50205993D1 (de) * 2002-08-26 2006-05-04 Borgwarner Inc Turbolader und Schaufellagerring hierfür
US7147433B2 (en) * 2003-11-19 2006-12-12 Honeywell International, Inc. Profiled blades for turbocharger turbines, compressors, and the like
US7255530B2 (en) * 2003-12-12 2007-08-14 Honeywell International Inc. Vane and throat shaping
JP2008520881A (ja) * 2004-11-16 2008-06-19 ハネウェル・インターナショナル・インコーポレーテッド 可変ノズルターボ過給機
DE602005011683D1 (de) * 2005-07-19 2009-01-22 Honeywell Int Inc Turbolader mit variabler düse
EP3150805B1 (fr) * 2005-11-25 2020-09-23 BorgWarner, Inc. Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur
JP4691002B2 (ja) * 2006-11-20 2011-06-01 三菱重工業株式会社 斜流タービンまたはラジアルタービン
US8517664B2 (en) * 2010-01-19 2013-08-27 Ford Global Technologies, Llc Turbocharger

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH305524A (de) * 1952-10-23 1955-02-28 Tech Studien Ag Vorrichtung zur Drehrichtungsänderung eines Turbinenlaufrades.
US5299909A (en) * 1993-03-25 1994-04-05 Praxair Technology, Inc. Radial turbine nozzle vane
US6709232B1 (en) 2002-09-05 2004-03-23 Honeywell International Inc. Cambered vane for use in turbochargers
EP1534933A1 (fr) 2002-09-05 2005-06-01 Honeywell International, Inc. Aube cambree perfectionnee destinee a etre utilisee dans des turbocompresseurs
WO2005064121A1 (fr) * 2003-12-31 2005-07-14 Honeywell International, Inc. Aube cambree destinee a des turbocompresseurs

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8172508B2 (en) 2010-06-20 2012-05-08 Honeywell International Inc. Multiple airfoil vanes
US8834104B2 (en) 2010-06-25 2014-09-16 Honeywell International Inc. Vanes for directing exhaust to a turbine wheel
EP2821616A4 (fr) * 2012-02-29 2016-01-13 Mitsubishi Heavy Ind Ltd Turbocompresseur à capacité variable
US9926938B2 (en) 2012-02-29 2018-03-27 Mitsubishi Heavy Industries, Ltd. Variable geometry turbocharger
WO2016062531A1 (fr) * 2014-10-21 2016-04-28 Siemens Aktiengesellschaft Profilage d'aubes directrices de dispositifs directeurs pour turbomachines, en particulier compresseurs
CN107109960A (zh) * 2014-10-21 2017-08-29 西门子公司 在涡轮机械中、尤其压缩机中的导向器的导向叶片的轮廓部
RU2674844C2 (ru) * 2014-10-21 2018-12-13 Сименс Акциенгезелльшафт Радиальный компрессор
CN107109960B (zh) * 2014-10-21 2019-07-09 西门子公司 在涡轮机械中、尤其压缩机中的导向器的导向叶片的轮廓部
US10634156B2 (en) 2014-10-21 2020-04-28 Siemens Aktiengesellschaft Centrifugal compressor
DE102022203619A1 (de) 2022-04-11 2023-10-12 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verdichterschaufel zur Umlenkung eines strömenden Mediums in einem Verdichter, insbesondere Radialverdichter, Rotor und System

Also Published As

Publication number Publication date
EP3150805B1 (fr) 2020-09-23
JP4881390B2 (ja) 2012-02-22
EP1790830B1 (fr) 2019-03-27
EP3150805A1 (fr) 2017-04-05
US20080260528A1 (en) 2008-10-23
US8641382B2 (en) 2014-02-04
JP2009517578A (ja) 2009-04-30
WO2007059995A1 (fr) 2007-05-31

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