WO2019020281A1 - Dispositif de turbocompresseurs pour un moteur à combustion interne - Google Patents

Dispositif de turbocompresseurs pour un moteur à combustion interne Download PDF

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Publication number
WO2019020281A1
WO2019020281A1 PCT/EP2018/066337 EP2018066337W WO2019020281A1 WO 2019020281 A1 WO2019020281 A1 WO 2019020281A1 EP 2018066337 W EP2018066337 W EP 2018066337W WO 2019020281 A1 WO2019020281 A1 WO 2019020281A1
Authority
WO
WIPO (PCT)
Prior art keywords
exhaust gas
pressure
low
pressure turbine
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.)
Ceased
Application number
PCT/EP2018/066337
Other languages
German (de)
English (en)
Inventor
Simon Hummel
Nicolas Stanzel
Thomas Streule
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
Daimler 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 Daimler AG filed Critical Daimler AG
Publication of WO2019020281A1 publication Critical patent/WO2019020281A1/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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • 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
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components
    • 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 device for a
  • DE 10 2014 218 345 A1 describes two exhaust gas turbochargers connected in series, each comprising a turbine and a compressor and of which a first exhaust gas turbocharger as a low pressure stage and a second exhaust gas turbocharger as
  • High pressure stage is used.
  • EP 0 014 778 A1 discloses a two-stage turbocharger unit with a low-pressure turbocharger and a high-pressure turbocharger. To make room for
  • Low-pressure turbocharger selected at least 40% larger than a pressure ratio of a high-pressure compressor of the high-pressure turbocharger.
  • DE 25 50 054 A1 describes a two-stage exhaust gas turbocharger with in one
  • each shaft carries a turbine wheel and a compressor wheel.
  • the arranged on each wave wheels belong to the same stage.
  • Object of the present invention is to provide an exhaust gas turbocharger device of the type mentioned, which is operable with particularly high efficiency and very compact.
  • the invention is based on an exhaust gas turbocharger device for a
  • Internal combustion engine comprising a low pressure exhaust gas turbocharger, which coupled to the exhaust gas of the internal combustion engine low pressure turbine and a rotatably mounted in a housing of the exhaust gas turbocharger device first shaft coupled to the low pressure turbine, with air to supply the
  • Internal combustion engine through-flowable low-pressure compressor comprises and with a high-pressure exhaust gas turbocharger, which a istströmmbare with the exhaust gas
  • High-pressure turbine and one, via a rotatably mounted in the housing second shaft coupled to the high-pressure turbine, with the air to supply the
  • Internal combustion engine comprises flow-through high pressure compressor.
  • the high-pressure turbine is designed as asymmetric Halbaxial high-pressure turbine, in particular as a twin high-pressure turbine, and is coupled fluidly with the low-pressure turbine.
  • asymmetric Halbaxial high-pressure turbine in particular as a twin high-pressure turbine, and is coupled fluidly with the low-pressure turbine.
  • fluidically coupled is meant that the
  • High-pressure turbine exhaust gas is connected to the low-pressure turbine.
  • the invention is based on the general knowledge that the designed as a Halbaxial high-pressure turbine high-pressure turbine can be supplied with asymmetric flows with exhaust gas, which is an adaptation to particularly good Turbine efficiency levels compared to radial turbines from single-stage systems allows lower pressure ratios.
  • Low-pressure turbocharger directly in extension to the high-pressure turbocharger allows.
  • the respective shafts can also be oriented coaxially to each other, whereby a particularly space-saving arrangement is possible.
  • the high-pressure turbine can be designed to be at least double-flowed, that is to say have at least one first flow through which exhaust gas can flow and a second flow through which exhaust gas can flow.
  • the first flood can be configured as a so-called AGR flood.
  • the second flood can be configured as a so-called ⁇ -flood.
  • the floods may at least partially have different sized flow cross-sections and thereby be asymmetric, whereby different Abgaströmungs horren in the respective floods can be achieved.
  • the first tide may have a smaller flow cross-section than the second tide, wherein a vane tip of respective vanes of the high-pressure turbine can be targeted by means of the first tide.
  • a vane tip of respective vanes of the high-pressure turbine can be targeted by means of the first tide.
  • Shovel foot of respective blades of the high pressure turbine to be anströmbar.
  • At least in the ⁇ -flood may preferably be arranged an exhaust flap, whereby a targeted adjustment of passing through the ⁇ -flood
  • the low-pressure turbine is designed as an axial low-pressure turbine.
  • the axial low pressure turbine may also be referred to as an axial low pressure turbine.
  • a discharge of the exhaust gas into a housing-solid volute with slight residual twist can take place.
  • the low-pressure compressor is designed as a half-axial low-pressure compressor.
  • the semi-axial low pressure compressor may also be referred to as a semi-axial low pressure compressor.
  • Such a configuration favors the efficiency of the exhaust gas turbocharger device targeted adaptation of the compressor geometry to lower pressure conditions and no unnecessary map reserve as in the radial compressor.
  • the low-pressure compressor may have a housing-fixed, in the radial direction outwardly curved, first diffuser.
  • the high-pressure compressor is designed as a semi-axial high-pressure compressor.
  • the semi-axial high pressure compressor may also be referred to as a semi-axial high pressure compressor.
  • the high-pressure compressor may have a housing-fixed, in the radial direction outwardly curved, second diffuser.
  • the high-pressure turbine is arranged in the exhaust gas flow direction of the exhaust gas upstream of the low-pressure turbine. This is advantageous, since in this way a particularly efficient utilization of
  • Exhaust gas energy is made possible by means of the exhaust gas turbocharger device.
  • the high-pressure turbine is first flowed through during operation of the internal combustion engine and thus before the low-pressure turbine with exhaust gas.
  • the single FIGURE shows a schematic sectional view of a
  • the exhaust gas turbocharger device 10 comprises a low-pressure exhaust gas turbocharger 20 which can flow through an exhaust gas 14 of the internal combustion engine
  • Low-pressure turbine 24 and one, via a rotatable in a housing 12 of the
  • Exhaust gas turbocharger device 10 mounted first shaft 22 coupled to the low-pressure turbine 24, with air 16 for supplying the internal combustion engine
  • flow-through low-pressure compressor 26 includes.
  • the exhaust gas turbocharger device 10 comprises a
  • High-pressure turbine 44 and one, via a rotatably mounted in the housing 12 second shaft 42 coupled to the high-pressure turbine 44, with the air 16 for supplying the internal combustion engine can be flowed through high-pressure compressor 46 includes.
  • the shafts 22, 42 are rotatably mounted in the housing 12 via respective roller bearings 50.
  • the high-pressure turbine 44 has a double-flow design and can be supplied with the exhaust gas 14 via a first flow 60 through which exhaust gas 14 can flow and a second flow 62 through which exhaust gas 14 can flow.
  • the first flood 60 may be configured as a so-called EGR flood.
  • the second flood 62 may be configured as a so-called ⁇ -flood.
  • the floods 60, 62 may have different sized flow cross sections at least in regions, as a result of which different exhaust gas flow velocities in the respective floods 60, 62 can be achieved.
  • the first flow 60 may have a smaller flow cross-section than the second flow 62, wherein a blade tip of respective blades of the high-pressure turbine 44 can be targeted by means of the first flow.
  • a blade root of respective blades of the high-pressure turbine 44 can be targeted.
  • a particularly high turbine efficiency can be achieved.
  • At least in the ⁇ -flood (second flood 62) can preferably be arranged here not shown exhaust flap, whereby a targeted adjustment of passing through the ⁇ -flood exhaust gas mass flow is made possible.
  • the high-pressure turbine 44 is arranged upstream of the low-pressure turbine 24 in the exhaust gas flow direction of the exhaust gas 14.
  • the exhaust gas 14 is presently represented by an arrow, wherein the exhaust gas flow direction of the exhaust gas 14 is oriented in the arrow direction of this arrow.
  • the air 16 is also shown by an arrow, wherein an air flow direction of the air 16 is oriented in the arrow direction of this arrow.
  • the high-pressure turbine 44 is designed as an asymmetrical, semi-axial twin-high-pressure turbine and is fluidically coupled to the low-pressure turbine 24.
  • the low-pressure turbine 24 is in the present case designed as an axial low-pressure turbine.
  • a discharge of the exhaust gas 14 from the low-pressure turbine 24 may in a
  • the low-pressure compressor 26 is in the present case designed as a half-axial low-pressure compressor.
  • the low-pressure compressor 26 has a housing-fixed, in the radial direction outwardly curved, the first diffuser 28.
  • the high-pressure compressor 46 is in the present case designed as a half-axial high-pressure compressor.
  • the high-pressure compressor 46 has a housing-fixed, in the radial direction outwardly curved, second diffuser 48.
  • the invention is based on the general knowledge that the execution of
  • Compressors as Halbaxialmaschinen generally lowers their maximum pressure ratio and offers the possibility for efficiency-optimal operation within their maps compared to a conventional compressor design with radial outflow.
  • the High-pressure turbine 44 which is designed as a high pressure half-axial turbine and may have a variable turbine geometry, with the present asymmetric floods 60, 62 allows adaptation to particularly good turbine efficiencies compared to radial turbines from single-stage systems lower pressure ratios.
  • Low pressure turbine offers ideal installation conditions.
  • the low-pressure exhaust gas turbocharger 20 may be arranged directly in extension to the Hochdruckabgasturbolader 40, as shown in the figure, with even a coaxial shaft arrangement of the shafts 22, 42 is made possible.
  • a slight angular offset or lateral offset of the shafts 22, 42 of the low-pressure exhaust gas turbocharger 20 and the high-pressure exhaust gas turbocharger 40 is also possible by adapting a connecting piece between the high-pressure turbocharger 40 and the low-pressure turbocharger 20. Due to a low
  • Low pressure exhaust gas turbocharger 20 a good, transient startup behavior can be achieved. Due to small surfaces, particularly low heat losses are achieved. In addition, there is a weight advantage and a very compact arrangement in the narrow engine compartment. Direct connection of the axial low-pressure exhaust gas turbocharger 20 after outflow of the high-pressure turbine 44 results in very low pressure losses. In addition - in contrast to radial turbines - can be dispensed with a flow deflection.

Landscapes

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

Abstract

L'invention concerne un dispositif de turbocompresseurs (10) pour un moteur à combustion interne, comprenant un turbocompresseur à gaz d'échappement basse pression (20), lequel comprend une turbine à basse pression (24) pouvant être traversée par un gaz d'échappement (14) du moteur à compression interne et un compresseur basse pression (26) couplé à la turbine à basse pression (24) au moyen d'un premier arbre logé de manière rotative dans un boîtier (12) du dispositif de turbocompresseurs (10) et pouvant être traversé par de l'air (16) pour l'alimentation du moteur à combustion interne, et comprenant un turbocompresseur à gaz d'échappement haute pression (40), lequel comprend une turbine à haute pression (44) pouvant être traversée par le gaz d'échappement (14) et un compresseur haute pression (46) couplé à la turbine à haute pression (24) au moyen d'un deuxième arbre logé de manière rotative dans le boîtier (12) et pouvant être traversé par l'air (16) pour l'alimentation du moteur à combustion interne. La turbine à haute pression (44) est conçue comme une turbine à haute pression semi-axiale asymétrique, en particulier comme une turbine à haute pression jumelle et couplée de manière fluidique avec la turbine à basse pression (24).
PCT/EP2018/066337 2017-07-22 2018-06-20 Dispositif de turbocompresseurs pour un moteur à combustion interne Ceased WO2019020281A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017006974.3 2017-07-22
DE102017006974.3A DE102017006974A1 (de) 2017-07-22 2017-07-22 Abgasturboladervorrichtung für eine Verbrennungskraftmaschine

Publications (1)

Publication Number Publication Date
WO2019020281A1 true WO2019020281A1 (fr) 2019-01-31

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ID=62873296

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2018/066337 Ceased WO2019020281A1 (fr) 2017-07-22 2018-06-20 Dispositif de turbocompresseurs pour un moteur à combustion interne

Country Status (2)

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DE (1) DE102017006974A1 (fr)
WO (1) WO2019020281A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2550054A1 (de) 1975-10-17 1977-04-21 Bbc Brown Boveri & Cie Zweistufiger abgasturbolader mit ineinanderliegenden wellen
EP0014778A1 (fr) 1979-02-19 1980-09-03 BBC Aktiengesellschaft Brown, Boveri & Cie. Turbo-compresseur à gaz d'échappement ayant deux étages
DE19948220A1 (de) 1999-10-06 2001-01-25 Daimler Chrysler Ag Brennkraftmaschine mit zwei Abgasturboladern
DE112013005624T5 (de) * 2012-12-21 2015-08-13 Borgwarner Inc. Doppelschnecken-Halbaxial-Turbolader mit Einzelventil
DE102014218345A1 (de) 2014-09-12 2016-03-17 Ford Global Technologies, Llc Aufgeladene Brennkraftmaschine mit in Reihe angeordneten Abgasturboladern

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2550054A1 (de) 1975-10-17 1977-04-21 Bbc Brown Boveri & Cie Zweistufiger abgasturbolader mit ineinanderliegenden wellen
EP0014778A1 (fr) 1979-02-19 1980-09-03 BBC Aktiengesellschaft Brown, Boveri & Cie. Turbo-compresseur à gaz d'échappement ayant deux étages
DE19948220A1 (de) 1999-10-06 2001-01-25 Daimler Chrysler Ag Brennkraftmaschine mit zwei Abgasturboladern
DE112013005624T5 (de) * 2012-12-21 2015-08-13 Borgwarner Inc. Doppelschnecken-Halbaxial-Turbolader mit Einzelventil
DE102014218345A1 (de) 2014-09-12 2016-03-17 Ford Global Technologies, Llc Aufgeladene Brennkraftmaschine mit in Reihe angeordneten Abgasturboladern

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DE102017006974A1 (de) 2019-01-24

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