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WO2006018189A1 - Turbocompresseur a gaz d'echappement d'un moteur a combustion interne - Google Patents

Turbocompresseur a gaz d'echappement d'un moteur a combustion interne Download PDF

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Publication number
WO2006018189A1
WO2006018189A1 PCT/EP2005/008635 EP2005008635W WO2006018189A1 WO 2006018189 A1 WO2006018189 A1 WO 2006018189A1 EP 2005008635 W EP2005008635 W EP 2005008635W WO 2006018189 A1 WO2006018189 A1 WO 2006018189A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
turbine wheel
internal combustion
combustion engine
exhaust gas
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.)
Ceased
Application number
PCT/EP2005/008635
Other languages
German (de)
English (en)
Inventor
Wolfram Schmid
Siegfried Sumser
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.)
Mercedes Benz Group AG
Original Assignee
DaimlerChrysler AG
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 DaimlerChrysler AG filed Critical DaimlerChrysler AG
Publication of WO2006018189A1 publication Critical patent/WO2006018189A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • F05D2250/70—Shape
    • 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 an exhaust gas turbocharger for an internal combustion engine according to the preamble of claim 1.
  • the guide grid comprises a plurality of guide vanes distributed over the circumference of the guide grid.
  • the turbine blades of the turbine wheel are formed in such a way that the first natural frequency of each turbine blade depending on the number of guide vanes and the maximum supercharger speed follows an inequality and does not exceed a certain limit. This ensures that the first natural frequency of each turbine blade has a sufficient distance to the excitation frequency, which is calculated by multiplying the number of blades on the guide grid and the maximum supercharger speed in engine braking operation.
  • the invention is based on the problem to provide an exhaust gas turbocharger with a guide grid or a free annular nozzle without guide grid and with a thin-bladed turbine wheel, which has a high rigidity and high strength.
  • Turbine wheel blading the so-called fundamental tone to put on the maximum operating speed of the exhaust gas turbocharger in engine braking mode. If the operation of the exhaust gas turbocharger in resonance to this natural frequency, this can damage due to vibration fractures both in the exit region of the blade on a
  • Turbinenradaustrittskante as well as in the inlet region at a turbine wheel leading edge.
  • Turbine wheel leading edge to a blade height of a vane of a guide grid or a nozzle height of a free annular nozzle in relation to each other said ratio is greater than 2.0.
  • a ratio of a rear wall diameter of the turbine wheel to the turbine wheel inlet diameter is within a certain range, whereby a relative movement of the turbine blades is made possible with a vibration excitation of the turbine blades to each other. Furthermore, due to the not drawn up to Turbinenradeintritt rear wall of the turbine wheel an advantageous effect on the damping properties of the turbine wheel.
  • the turbine wheel diameter in an optimized engine turbocharger system is advantageously in a certain size ratio to the displacement of the internal combustion engine.
  • a free Strömungsgueritess which is located in a transition from a spiral channel of the turbine to the turbine, results in a turbo braking factor, which at maximum braking power in engine braking operation of a multiplication of the free flow cross-section with the inlet diameter of the turbine wheel and division with the displacement calculated internal combustion engine, which is in particular less than 0.006, possibly even less than 0.003.
  • this optimized value of the turbo-braking factor it is ensured that with maximum achievable engine braking power, the thermal load on the internal combustion engine and the exhaust-gas turbocharger is comparatively low.
  • the high engine braking powers and associated thermal and mechanical loads occurring with these turbo-braking factors can be absorbed by the turbine wheel without damage.
  • FIG. 1 is a schematic representation of a detail of a turbine wheel and a vane of an exhaust gas turbocharger according to the invention
  • FIG. 2 is a schematic plan view of the turbine wheel of the exhaust gas turbocharger according to the invention.
  • Fig. 3 shows a turbine wheel of the exhaust gas turbocharger according to the invention
  • FIG. 4 shows a twin-flow turbine of the exhaust gas turbocharger according to the invention.
  • Fig. 1 is a schematic representation of a detail of a turbine wheel 1 of a turbine 14 shown in FIG. 4 of an exhaust gas turbocharger, not shown in an exhaust duct, not shown, of an internal combustion engine, not shown, which is for example a gasoline or a diesel engine, mapped ,
  • the turbine wheel 1 with a turbine wheel inlet diameter D ⁇ has a turbine hub 2.
  • a turbine hub 2 which forms a rotationally fixed connection with the turbine hub 2, the turbine wheel 1 is rotatably coupled with a compressor, not shown in a non-illustrated intake of the engine and is driven by the turbine 1.
  • the compressor compresses sucked combustion air, which is supplied via not shown inlet ducts of the internal combustion engine.
  • the turbine wheel 1 is delimited by a turbine housing 4.
  • turbine blades 3 projecting approximately radially from the turbine hub 2 are arranged at uniform intervals, with only one turbine blade 3 being illustrated by way of example in FIG.
  • the turbine hub 2 has at its larger diameter end a turbine rear wall 5 with a diameter D 3 .
  • a turbine wheel inlet edge 6 of the turbine blade 3 is located perpendicular to the turbine wheel rear wall 5 at a distance H from the diameter D 8 of the turbine wheel rear wall 5.
  • the guide grid 7 is adjustable, so that via the guide grid 7, a free flow cross section A ⁇ , which is in a transition from a spiral channel 15 shown in FIG. 4 of the turbine 14 is located on the turbine 1 is adjustable.
  • This free flow cross-section A ⁇ determines the velocity of a flow medium and thus an inlet velocity of the flow medium into the turbine wheel 1 and thus also the rate of occurrence on a turbine blade 3 of the turbine wheel 1.
  • An arrow 9 represents the flow direction of the flow medium.
  • FIG. 2 shows the schematic plan view of a turbine blade 3 of the turbine wheel 1 of the exhaust gas turbocharger according to the invention.
  • a tangent 10 of the turbine blade 3 encloses an angle with a plane of the turbine wheel rear wall 5, the so-called
  • Rake angle ⁇ is advantageously less than 50 °.
  • S ER true length of the turbine wheel inlet edge 6 runs. The rotation of the turbine wheel 1 takes place in the direction of rotation 12.
  • the true length S ER of the turbine wheel leading edge 6 has a value of at least one quarter of the turbine wheel diameter D ⁇ and is at least twice as large as the blade height h Le or, in the case of a free annular nozzle, the height of the free annular nozzle.
  • the greater the ratio of the true length of the turbine wheel inlet edge S ER to the blade height h Le the more a pressure peak of a flow of the flow medium is reduced to the turbine blade 3.
  • Turbine wheel blading is exceeded at a maximum speed of the exhaust gas turbocharger.
  • Advantageously, thereby thin turbine blades 3 are used, which are operable damage-free under very high loads.
  • a ratio DD of the diameter D 5 of Turbinenrad Wegwand 5 to the turbine wheel inlet diameter D ⁇ is set within a range of values, which has the value of 0.6 as the minimum ratio and the value 0, 95 as the maximum ratio.
  • Fig. 3 the turbine wheel 1 of the exhaust gas turbocharger is shown to further illustrate the exhaust gas turbocharger according to the invention.
  • the turbine 14 is formed as a double-flow asymmetric turbine.
  • the turbine may also be designed as a single-flow turbine or a symmetrical multi-flow turbine.
  • a sizing rule may be considered. This dimensioning rule supports the design of the free flow cross-section A ⁇ and the
  • Ingress diameter D ⁇ of the turbine wheel 1 as a function of a stroke volume of the internal combustion engine which can be calculated as the sum of the difference volumes between the smallest and largest volumes of the combustion chambers of the internal combustion engine, in particular a reciprocating internal combustion engine.
  • a braking braking factor TBF is determined according to the relationship during braking operation at maximum braking power of the internal combustion engine
  • TBF A ⁇ • - V H determined, which is to achieve high braking performance while maintaining allowable load limits less than 0.006, in particular less than 0.003.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne un turbocompresseur à gaz d'échappement d'un moteur à combustion interne comprenant un compresseur situé dans la ligne d'admission et une turbine située dans la ligne d'échappement. Le compresseur est relié à la turbine par un arbre bloqué en rotation. La vraie longueur du bord d'attaque de la roue de turbine et du diamètre d'entrée de la roue de turbine ainsi que la vraie longueur du bord d'attaque de la roue de turbine et la hauteur des aubes directrices sont respectivement dans un rapport spécifique mutuel et ont une valeur minimale garantissant la rigidité et la robustesse de la roue de turbine.
PCT/EP2005/008635 2004-08-11 2005-08-09 Turbocompresseur a gaz d'echappement d'un moteur a combustion interne Ceased WO2006018189A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004038903A DE102004038903A1 (de) 2004-08-11 2004-08-11 Abgasturbolader für eine Brennkraftmaschine
DE102004038903.9 2004-08-11

Publications (1)

Publication Number Publication Date
WO2006018189A1 true WO2006018189A1 (fr) 2006-02-23

Family

ID=35207431

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2005/008635 Ceased WO2006018189A1 (fr) 2004-08-11 2005-08-09 Turbocompresseur a gaz d'echappement d'un moteur a combustion interne

Country Status (2)

Country Link
DE (1) DE102004038903A1 (fr)
WO (1) WO2006018189A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2012500357A (ja) * 2008-08-21 2012-01-05 ダイムラー・アクチェンゲゼルシャフト 自動車の内燃機関用エグゾーストターボチャージャ
WO2015119828A1 (fr) * 2014-02-04 2015-08-13 Borgwarner Inc. Bouclier thermique pour turbocompresseurs à roue de turbine à écoulement mixte
WO2017045738A1 (fr) * 2015-09-19 2017-03-23 Daimler Ag Roue de turbine pour turbine de turbocompresseur à gaz d'échappement

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012103411A1 (de) * 2012-04-19 2013-10-24 Ihi Charging Systems International Gmbh Turbine für einen Abgasturbolader
CN104854325B (zh) 2012-12-27 2017-05-31 三菱重工业株式会社 辐流式涡轮动叶片

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4305698A (en) * 1978-10-12 1981-12-15 Nissan Motor Co., Ltd. Radial-flow turbine wheel
EP0336064A1 (fr) * 1988-03-31 1989-10-11 Daimler-Benz Aktiengesellschaft Suralimenteur à gaz perdu pour moteur à combustion interne
DE3908285C1 (en) * 1989-03-14 1990-06-07 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Turbine wheel of an exhaust turbocharger for an internal combustion engine with radial and/or mixed-flow gas feed
DE10121390A1 (de) * 2001-05-02 2002-11-07 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE10212032A1 (de) * 2002-03-19 2003-10-02 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE10217470A1 (de) * 2002-04-19 2003-11-06 Daimler Chrysler Ag Abgasturbine
DE10220097A1 (de) * 2002-05-04 2003-11-13 Daimler Chrysler Ag Turbine für einen Abgasturbolader
DE10228003A1 (de) * 2002-06-22 2004-01-15 Daimlerchrysler Ag Turbine für einen Abgasturbolader

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4288051B2 (ja) * 2002-08-30 2009-07-01 三菱重工業株式会社 斜流タービン、及び、斜流タービン動翼

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4305698A (en) * 1978-10-12 1981-12-15 Nissan Motor Co., Ltd. Radial-flow turbine wheel
EP0336064A1 (fr) * 1988-03-31 1989-10-11 Daimler-Benz Aktiengesellschaft Suralimenteur à gaz perdu pour moteur à combustion interne
DE3908285C1 (en) * 1989-03-14 1990-06-07 Daimler-Benz Aktiengesellschaft, 7000 Stuttgart, De Turbine wheel of an exhaust turbocharger for an internal combustion engine with radial and/or mixed-flow gas feed
DE10121390A1 (de) * 2001-05-02 2002-11-07 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE10212032A1 (de) * 2002-03-19 2003-10-02 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE10217470A1 (de) * 2002-04-19 2003-11-06 Daimler Chrysler Ag Abgasturbine
DE10220097A1 (de) * 2002-05-04 2003-11-13 Daimler Chrysler Ag Turbine für einen Abgasturbolader
DE10228003A1 (de) * 2002-06-22 2004-01-15 Daimlerchrysler Ag Turbine für einen Abgasturbolader

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2012500357A (ja) * 2008-08-21 2012-01-05 ダイムラー・アクチェンゲゼルシャフト 自動車の内燃機関用エグゾーストターボチャージャ
US8522547B2 (en) 2008-08-21 2013-09-03 Daimler Ag Exhaust gas turbocharger for an internal combustion engine of a motor vehicle
WO2015119828A1 (fr) * 2014-02-04 2015-08-13 Borgwarner Inc. Bouclier thermique pour turbocompresseurs à roue de turbine à écoulement mixte
CN105960515A (zh) * 2014-02-04 2016-09-21 博格华纳公司 用于混流式涡轮机叶轮涡轮增压器的隔热罩
CN105960515B (zh) * 2014-02-04 2019-01-15 博格华纳公司 用于混流式涡轮机叶轮涡轮增压器的隔热罩
US10669889B2 (en) 2014-02-04 2020-06-02 Borgwarner Inc. Heat shield for mixed flow turbine wheel turbochargers
WO2017045738A1 (fr) * 2015-09-19 2017-03-23 Daimler Ag Roue de turbine pour turbine de turbocompresseur à gaz d'échappement
US10577934B2 (en) 2015-09-19 2020-03-03 Daimler Ag Turbine wheel for a turbine of an exhaust gas turbocharger

Also Published As

Publication number Publication date
DE102004038903A1 (de) 2006-02-23

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