EP2147216B1 - Turbocompresseur à suralimentation de gaz d'échappement - Google Patents

Turbocompresseur à suralimentation de gaz d'échappement Download PDF

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Publication number
EP2147216B1
EP2147216B1 EP08717167.4A EP08717167A EP2147216B1 EP 2147216 B1 EP2147216 B1 EP 2147216B1 EP 08717167 A EP08717167 A EP 08717167A EP 2147216 B1 EP2147216 B1 EP 2147216B1
Authority
EP
European Patent Office
Prior art keywords
blade
intermediate blade
main
turbocharger
blades
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.)
Not-in-force
Application number
EP08717167.4A
Other languages
German (de)
English (en)
Other versions
EP2147216A1 (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.)
Aumovio Germany GmbH
Original Assignee
Continental Automotive Technologies 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 Technologies GmbH filed Critical Continental Automotive Technologies 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

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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 stream (outflow path), which is connected via a common shaft with a compressor in the intake (Anströmpfad).
  • 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 through this compression during the intake stroke, a larger amount of air in 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 to the leading main blade compared to the blade channel to trailing main blade at different speed profiles. This increases the efficiency losses within the turbine. It is the object of the present invention to reduce the aforementioned disadvantages.
  • the idea on which the present invention is based is to provide a device in the inflow path or outflow path of an internal combustion engine with which an incoming gas stream is conducted as uniformly 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 channels on the front side or on the rear side of the intermediate blade can be designed such that the loss of efficiency is reduced. Furthermore, the noise of the turbocharger is reduced and he increased the range of application of the turbocharger.
  • the lengths of the circular arc sections from the front side and the rear side of the intermediate vane to the trailing and leading main vane are substantially the same at the rotational axis-side end of the intermediate vane.
  • 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 102 with a turbine 118 and a compressor 116.
  • a turbine wheel 108 according to the invention 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 set back from 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 rotated.
  • the turbine wheel 108 has main blades 120 and intermediate blades 102.
  • the outlet side blade edges of the intermediate blades 102 are recessed from the outlet side edge of the main blades.
  • the exhaust flow leaves the turbine 118 through a turbine outlet 114.
  • the turbine 118 drives the compressor 116 via the shaft 110, which couples the turbine wheel 108 to the compressor wheel 104.
  • the compressor wheel 104 By means of the compressor wheel 104, the sucked air is compressed in Anströmpfad.
  • Fig. 2 , 10 shows a schematic plan view of a blade arrangement according to the invention, for example a compressor wheel with a clockwise rotation, comprising a trailing main blade 202, an intermediate blade 204 and a leading main blade 203.
  • the blades are arranged on a section of an axis of rotation at an angle ⁇ , the counting 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 flow guide between the leading and trailing main blade. Furthermore, the differences in the velocity profiles in the blade channel at the front and rear 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 202nd
  • the curvature of the main blade 202 in the axial direction is different at a given center distance, and preferably greater than the curvature of the intermediate blade 204.
  • Fig. 4 shows a schematic plot of the axial angle ⁇ as a function of the normal to the rotational axis distance r meridian coordinate m '.
  • the position of an intermediate blade according to the prior art is represented by the dashed line 210.
  • An intermediate blade with a changed angle is shown by the solid line. This makes it possible to set the ratio of the flow cross sections between the preceding and following main blade.
  • 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 relative to the main blade, the cross-sections of the flow channels along the front and back 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)

Claims (3)

  1. Turbocompresseur pour un véhicule automobile ou dans un véhicule automobile, comprenant à chaque fois une roue mobile avec une aube intermédiaire (204) située entre deux aubes principales (202),
    l'aube intermédiaire (204) présentant au moins en partie une allure angulaire différente de celle des aubes principales (202),
    caractérisé en ce que
    l'allure angulaire de l'aube intermédiaire (204) est réalisée de telle sorte que la section transversale du canal d'écoulement au niveau du côté arrière de l'aube intermédiaire (204) soit essentiellement égale à la section transversale du canal d'écoulement au niveau du côté avant de l'aube intermédiaire (204) et que pour une distance prédéfinie à l'axe de rotation, la longueur de la portion d'arc de cercle (206) depuis l'aube intermédiaire (204) jusqu'à l'aube principale arrière (202), soit inférieure à la longueur de la portion d'arc de cercle (207) jusqu'à l'aube principale avant (202).
  2. Turbocompresseur selon la revendication 1,
    caractérisé en ce que
    à l'extrémité côté axe de rotation de l'aube intermédiaire (204), les longueurs des portions d'arc de cercle (206, 207) depuis le côté avant et le côté arrière de l'aube intermédiaire (204) vers l'aube principale arrière et l'aube principale avant (202) sont essentiellement égales.
  3. Turbocompresseur selon l'une quelconque des revendications 1 ou 2,
    caractérisé en ce que
    la roue mobile est réalisée sous forme de roue de turbine (108) ou de roue de compresseur (104).
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 EP2147216A1 (fr) 2010-01-27
EP2147216B1 true 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)

Families Citing this family (17)

* 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
US10087947B2 (en) 2016-01-04 2018-10-02 Caterpillar Inc. Turbocharger compressor and method
US10167875B2 (en) 2016-01-04 2019-01-01 Caterpillar Inc. Turbocharger compressor and method
US10167876B2 (en) 2016-01-04 2019-01-01 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
SE543329C2 (en) 2019-06-13 2020-12-01 Scania Cv Ab Centrifugal Compressor Impeller for a Charging Device of an Internal Combustion Engine
DE102020216280A1 (de) * 2020-12-18 2022-06-23 Vitesco Technologies GmbH Verdichterrad für den Verdichter einer Brennkraftmaschine
JP2024113342A (ja) * 2023-02-09 2024-08-22 本田技研工業株式会社 ラジアルタービンインペラ

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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
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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
TW200722627A (en) * 2005-12-15 2007-06-16 Ind Tech Res Inst Centrifugal type pressure-increasing impeller structure
DE102007017822A1 (de) * 2007-04-16 2008-10-23 Continental Automotive Gmbh Abgasturbolader

Also Published As

Publication number Publication date
US20100254816A1 (en) 2010-10-07
WO2008125384A1 (fr) 2008-10-23
EP2147216A1 (fr) 2010-01-27
DE102007017822A1 (de) 2008-10-23
US8512000B2 (en) 2013-08-20

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