EP2147216A1 - Turbocompresseur à suralimentation de gaz d'échappement - Google Patents

Turbocompresseur à suralimentation de gaz d'échappement

Info

Publication number
EP2147216A1
EP2147216A1 EP08717167A EP08717167A EP2147216A1 EP 2147216 A1 EP2147216 A1 EP 2147216A1 EP 08717167 A EP08717167 A EP 08717167A EP 08717167 A EP08717167 A EP 08717167A EP 2147216 A1 EP2147216 A1 EP 2147216A1
Authority
EP
European Patent Office
Prior art keywords
blade
intermediate blade
main
turbocharger
turbine
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
EP08717167A
Other languages
German (de)
English (en)
Other versions
EP2147216B1 (fr
Inventor
Andre Kaufmann
Tobias Dettmann
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.)
Continental Automotive GmbH
Original Assignee
Continental Automotive 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 Continental Automotive GmbH filed Critical Continental Automotive GmbH
Publication of EP2147216A1 publication Critical patent/EP2147216A1/fr
Application granted granted Critical
Publication of EP2147216B1 publication Critical patent/EP2147216B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes

Definitions

  • An exhaust gas turbocharger or turbocharger for short is a charging system for an internal combustion engine, by means of which the cylinders of the internal combustion engine are subjected to an increased charge pressure.
  • a turbocharger consists of an exhaust gas turbine in the exhaust gas flow (Abstrompfad), which is connected via a common shaft with a compressor in the intake (Anstrompfad).
  • the turbine is set in rotation by the exhaust gas flow of the engine and thus drives the compressor.
  • the compressor increases the pressure in the intake tract of the engine, so that by this compression during the intake stroke, a larger amount of air into the cylinders of the internal combustion engine succeeded than in a conventional naturally aspirated engine. This provides more oxygen for combustion.
  • a disadvantage of the previous embodiments of the intermediate blades is that it comes in the blade channel leading to the main blade compared to the blade channel to trailing main blade at different speed profiles. This increases the efficiency losses within the turbine.
  • Turbocharger for or in a motor vehicle having an impeller provided with an intermediate blade located between two main blades, in which the intermediate schaufei at least partially has a relation to the main blades different angle course.
  • the idea on which the present invention is based is to provide a device in the flow path or discharge path of an internal combustion engine with which an incoming gas stream can be conducted as evenly as possible through a compressor or turbine-side impeller.
  • An advantage of the device according to the invention is that by means of an angular position of the intermediate blade deviating from the main blade, the flow ducts on the front side or on the rear side of the intermediate blade can be designed such that the efficiency loss is reduced. Furthermore, the noise development of the turbocharger is reduced and he increased use of the turbocharger.
  • the angle profile of the intermediate blade is designed such that the cross section of the flow channel at the rear side of the intermediate blade is substantially equal to the cross section of the flow channel at the front side of the intermediate blade.
  • the length of the circular arc section from the intermediate blade to the trailing main blade is less than the length of the circular arc section to the leading main blade.
  • the lengths of the circular arc sections from the front side and the rear side of the intermediate blade to the trailing and leading main blade are essentially the same at the end of the intermediate blade at the rotational axis side.
  • the impeller of the exhaust gas turbocharger is formed as a turbine wheel (108) or compressor wheel (104).
  • FIG. 1 shows an elevation of a turbocharger with an inventive impeller.
  • FIG. 2 shows a schematic plan view of a compressor-side blade arrangement
  • 3 is a schematic plan view of the course of the meridian coordinate
  • Fig. 4 is a schematic representation of the axial angle of
  • Fig.l shows an elevation of a turbocharger 102 with a turbine 118 and a compressor 116.
  • a turbine according to the invention 108 is rotatably mounted and connected to one end of a shaft 110.
  • a compressor wheel 104 according to the invention is also rotatably mounted and connected to the other end of the shaft 110.
  • the compressor wheel 104 has a main vane 203 and an intermediate vane 204, the vane surface of which is reset relative to the main vane.
  • hot exhaust gas is introduced into the turbine 118 by an internal combustion engine, not shown here, whereby the turbine wheel 118 is set in rotation.
  • the door- Binenrad 108 has a main vane 120 and an intermediate vane 102.
  • the outlet side vane edge of the intermediate vane 102 is recessed from the outlet side edge of the main vane.
  • the exhaust gas flow leaves the turbine 118 through a turbine outlet 114.
  • the turbine 118 drives the compressor 116.
  • the intake air is compressed in the flow path.
  • FIG. 2 shows a schematic plan view of a blade arrangement according to the invention, for example a compressor wheel with a clockwise direction, comprising a trailing main vane 202, an intermediate vane 204 and a leading main vane 203.
  • the vanes are on a portion of an axis of rotation at an angle ⁇ arranged, wherein the payment direction of the angle ⁇ is opposite to the direction of rotation.
  • the length of the circular arc portion 206 from the intermediate blade 204 to the trailing main blade 202 is smaller than the length of the circular arc portion 207 between the intermediate blade 204 to the leading main blade 203.
  • An advantage of the arrangement according to the invention is that the differences in the lengths of the circular arc sections the surfaces are reduced perpendicular to the Stromungs leadership between the leading and trailing main blade. Furthermore, the differences in the velocity profiles in the blade channel at the front and back sides of the intermediate blade are reduced and the efficiency is increased.
  • FIG. 3 schematically shows the difference in the course of the meridian coordinate m of the intermediate blade 204 and the main blade 202.
  • FIG. 4 shows a schematic plot of the axial angle ⁇ as a function of the meridial coordinate m 'normalized to the rotational axis distance r.
  • the position of an intermediate blade according to the prior art is represented by the dashed line 210.
  • An advantage of the device according to the invention is that due to the special design, i. the different angular arrangement of the intermediate blades in both the axial and in the radial direction in comparison to the Hauptschau- fei the cross sections of the flow ducts along the front and rear sides of the intermediate blades reliably align. In addition to increasing the efficiency and the smoothness of the turbocharger is improved.

Landscapes

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

Abstract

L'invention concerne un turbocompresseur à suralimentation pour un ou dans un véhicule à moteur comportant une roue à aubes avec une aube intermédiaire se trouvant entre deux aubes principales. L'aube intermédiaire présente au moins partiellement un tracé angulaire différent des aubes principales.
EP08717167.4A 2007-04-16 2008-02-27 Turbocompresseur à suralimentation de gaz d'échappement Not-in-force EP2147216B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007017822A DE102007017822A1 (de) 2007-04-16 2007-04-16 Abgasturbolader
PCT/EP2008/052360 WO2008125384A1 (fr) 2007-04-16 2008-02-27 Turbocompresseur à suralimentation de gaz d'échappement

Publications (2)

Publication Number Publication Date
EP2147216A1 true EP2147216A1 (fr) 2010-01-27
EP2147216B1 EP2147216B1 (fr) 2017-11-22

Family

ID=39526264

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08717167.4A Not-in-force EP2147216B1 (fr) 2007-04-16 2008-02-27 Turbocompresseur à suralimentation de gaz d'échappement

Country Status (4)

Country Link
US (1) US8512000B2 (fr)
EP (1) EP2147216B1 (fr)
DE (1) DE102007017822A1 (fr)
WO (1) WO2008125384A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007017822A1 (de) * 2007-04-16 2008-10-23 Continental Automotive Gmbh Abgasturbolader
FR2946399B1 (fr) * 2009-06-05 2016-05-13 Turbomeca Rouet centrifuge de compresseur.
DE102009024568A1 (de) * 2009-06-08 2010-12-09 Man Diesel & Turbo Se Verdichterlaufrad
JP5574951B2 (ja) * 2010-12-27 2014-08-20 三菱重工業株式会社 遠心圧縮機の羽根車
JP5665535B2 (ja) * 2010-12-28 2015-02-04 三菱重工業株式会社 遠心圧縮機
IL212729A (en) * 2011-05-05 2015-03-31 Rafael Advanced Defense Sys Compressor and fan integrated impeller
US20160281732A1 (en) * 2015-03-27 2016-09-29 Dresser-Rand Company Impeller with offset splitter blades
US10167876B2 (en) 2016-01-04 2019-01-01 Caterpillar Inc. Turbocharger compressor and method
US10167875B2 (en) 2016-01-04 2019-01-01 Caterpillar Inc. Turbocharger compressor and method
US10087947B2 (en) 2016-01-04 2018-10-02 Caterpillar Inc. Turbocharger compressor and method
US10082153B2 (en) 2016-01-04 2018-09-25 Caterpillar Inc. Turbocharger compressor and method
JP2017193985A (ja) * 2016-04-19 2017-10-26 本田技研工業株式会社 タービンインペラ
US10669854B2 (en) 2017-08-18 2020-06-02 Pratt & Whitney Canada Corp. Impeller
RU2667251C1 (ru) * 2017-10-05 2018-09-18 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Коробка приводных агрегатов
SE1950700A1 (en) 2019-06-13 2020-12-01 Scania Cv Ab Centrifugal Compressor Impeller for a Charging Device of an Internal Combustion Engine

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DE345616C (fr) *
DE174855C (de) * 1905-08-19 1906-10-01 Wittig Emil Laufrad für ventilatoren
US2484554A (en) * 1945-12-20 1949-10-11 Gen Electric Centrifugal impeller
US3006603A (en) * 1954-08-25 1961-10-31 Gen Electric Turbo-machine blade spacing with modulated pitch
GB941343A (en) * 1961-08-29 1963-11-13 Rudolph Birmann Improvements in or relating to impeller blading for centrifugal compressors
US4093401A (en) * 1976-04-12 1978-06-06 Sundstrand Corporation Compressor impeller and method of manufacture
JPS6017296A (ja) * 1983-07-08 1985-01-29 Matsushita Electric Ind Co Ltd 横断流送風機の羽根車
FR2550585B1 (fr) * 1983-08-09 1987-01-16 Foueillassar Jean Marie Moyens d'uniformiser la vitesse d'un fluide a la sortie d'un rouet centrifuge
US4693669A (en) * 1985-03-29 1987-09-15 Rogers Sr Leroy K Supercharger for automobile engines
US4904158A (en) * 1988-08-18 1990-02-27 Union Carbide Corporation Method and apparatus for cryogenic liquid expansion
US5002461A (en) * 1990-01-26 1991-03-26 Schwitzer U.S. Inc. Compressor impeller with displaced splitter blades
US5639217A (en) * 1996-02-12 1997-06-17 Kawasaki Jukogyo Kabushiki Kaisha Splitter-type impeller
GB2337795A (en) * 1998-05-27 1999-12-01 Ebara Corp An impeller with splitter blades
US6663347B2 (en) * 2001-06-06 2003-12-16 Borgwarner, Inc. Cast titanium compressor wheel
JP3876195B2 (ja) * 2002-07-05 2007-01-31 本田技研工業株式会社 遠心圧縮機のインペラ
US7147433B2 (en) * 2003-11-19 2006-12-12 Honeywell International, Inc. Profiled blades for turbocharger turbines, compressors, and the like
US7841506B2 (en) * 2004-08-11 2010-11-30 Honeywell International Inc. Method of manufacture of dual titanium alloy impeller
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DE102007017822A1 (de) * 2007-04-16 2008-10-23 Continental Automotive Gmbh Abgasturbolader

Non-Patent Citations (1)

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Title
See references of WO2008125384A1 *

Also Published As

Publication number Publication date
DE102007017822A1 (de) 2008-10-23
US20100254816A1 (en) 2010-10-07
WO2008125384A1 (fr) 2008-10-23
EP2147216B1 (fr) 2017-11-22
US8512000B2 (en) 2013-08-20

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