WO2019201739A1 - Dispositif de turbocompresseur à plusieurs étages - Google Patents

Dispositif de turbocompresseur à plusieurs étages Download PDF

Info

Publication number
WO2019201739A1
WO2019201739A1 PCT/EP2019/059258 EP2019059258W WO2019201739A1 WO 2019201739 A1 WO2019201739 A1 WO 2019201739A1 EP 2019059258 W EP2019059258 W EP 2019059258W WO 2019201739 A1 WO2019201739 A1 WO 2019201739A1
Authority
WO
WIPO (PCT)
Prior art keywords
low
pressure turbine
pressure
shaft
compressor
Prior art date
Application number
PCT/EP2019/059258
Other languages
German (de)
English (en)
Inventor
Elmar Groeschel
Frank Hummel
Bent Aamand PHILLIPSEN
Original Assignee
Abb Turbo Systems 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 Abb Turbo Systems Ag filed Critical Abb Turbo Systems Ag
Priority to EP19718632.3A priority Critical patent/EP3781799A1/fr
Priority to CN201980026535.7A priority patent/CN112334640A/zh
Publication of WO2019201739A1 publication Critical patent/WO2019201739A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/004—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust drives arranged in series
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B29/00—Engines characterised by provision for charging or scavenging not provided for in groups F02B25/00, F02B27/00 or F02B33/00 - F02B39/00; Details thereof
    • F02B29/04—Cooling of air intake supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/013—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
    • 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
    • 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 a multi-stage Turboladervorrich device.
  • Multi-stage turbocharger devices are already known. By means of such multi-stage turbocharger devices can be achieved in comparison to single-stage turbocharger devices, a He increase in output power and a reduction of the fuel consumption of the motor in each case charged internal combustion engine. To keep the manufacturing and operating costs ei ner multi-stage turbocharger device low, the multi-stage turbocharger should be compact builds up.
  • a multi-rotor turbola which has a compressor and a turbine.
  • the compressor contains several opposing compaction terrotors.
  • the turbine contains several counter-rotating turbine rotors.
  • a first of these compressor rotors is connected via a first shaft to a first of the turbine rotors.
  • a first compressor rotor adjacent second Verdich terrotor is connected via a second shaft with a second turbine nenrotor.
  • the two shafts are arranged coaxially with each other and rotate about a common axis of rotation.
  • the object of the invention is to provide a space-saving and easily realizable multi-stage turbocharger device whose efficiency is improved.
  • This object is achieved by a multi-stage Turboladervorrich device having the features specified in claim 1.
  • Such a multi-stage turbocharger apparatus comprises a high pressure turbine, a low pressure turbine, a Niederdruckver denser, a high pressure compressor, a first shaft and a second shaft, wherein one of the turbines and one of the United denser on the first shaft and the other turbine and the other compressor on the second shaft are arranged, the two shafts have the same axis of rotation, the two shafts are arranged one behind the other in the axial direction and in the waves have an opposite direction of rotation.
  • the low-pressure turbine to the output of the high-pressure turbine is ruled out.
  • the high pressure turbine and the high pressure compressor are arranged on the first shaft and the low pressure turbine and the low pressure compressor on the second shaft.
  • the high pressure turbine and the low pressure compressor are arranged on the first shaft and the low pressure turbine and the high pressure compressor on the second shaft.
  • the high-pressure turbine and the low-pressure turbine are arranged in a common turbine housing Tur.
  • the high-pressure turbine in a gas inlet housing and the Niederbuchtur bine arranged in a gas outlet housing, wherein the Ga is housing housing connected to the gas outlet housing.
  • the high-pressure turbine Leitschaufein the high-pressure turbine Leitschaufein.
  • a inter mediate cooler is arranged between the low pressure compressor and the high pressure compressor.
  • a charge air cooler is connected to the outlet of the high-pressure compressor.
  • FIG. 1 shows a sketch of a multi-stage turbocharger device according to a first exemplary embodiment of the invention
  • FIG. 2 shows a sketch of a multistage turbocharger device according to a second exemplary embodiment of the invention
  • Figure 3 is a first sketch to illustrate the central arrangement of the turbine stages in a multi-stage turbola dervorraum
  • Figure 4 is a second sketch to illustrate the central arrangement of the turbine stages in another multi-stage turbocharger device.
  • FIG. 1 shows a sketch of a multi-stage turbocharger device according to a first embodiment of the invention.
  • a two-stage turbocharger device as it can be used in particular in connection with large engines, such as marine engines.
  • This two-stage turbocharger device 1 has a high-pressure turbine 2, a low-pressure turbine 3, a low-pressure compressor 4 and a high-pressure compressor 5.
  • the high-pressure turbine 2 has a gas inlet housing 10 a.
  • the low-pressure turbine 3 has a gas outlet housing 1 Ob.
  • the low-pressure compressor 4 is arranged in a low pressure Verdich tergephase 4a.
  • the high pressure compressor 5 is arranged in a high pressure compressor housing 5a.
  • the high-pressure turbine 2 has an input region 18, to which a hot exhaust gas stream is fed to a not shown internal combustion engine. This hot exhaust stream is fed via Leitschaufein 11 the blades 15 of the high-pressure turbine 2. These blades 15 are part of a high-pressure turbine 31, which is rotatably connected to a first shaft 6 or integrated part of this first shaft 6. The high-pressure turbine wheel 31 is driven by the supplied hot exhaust gas flow and sets the first shaft 6 in a rotational movement.
  • the high-pressure compressor 5 which is supplied via its input portion 26, the pre-compressed air, has a high-pressure compressor wheel 28 which is keptstat tet with blades 16. Of these blades 16, the compressor in the high pressure further compressed air via Leitschaufein 5b in an output range 27 of the high-pressure compressor and output from there, not shown in the figure 1
  • the low-pressure turbine 32 of the low-pressure turbine 3 is rotatably fixed or integrated part of the second shaft 7.
  • the low-pressure turbine 32 has blades 14 on.
  • the second shaft 7 rotates in a direction of rotation 30, which is opposite to the direction of rotation of the first shaft 6.
  • de waves 6 and 7 rotate about a common axis of rotation 8.
  • the two shafts 6 and 7 are arranged in the axial direction 9 hinerei nander.
  • the output region 19 of the high-pressure turbine 2 forms the input region 20 of the low-pressure turbine 3. Consequently, the low-pressure turbine 3 is provided with the exhaust gas flow output by the high-pressure turbine 2 as input exhaust gas flow.
  • the blades 14 of the low-pressure turbine 3 can advantageously the blades 14 of the low-pressure turbine 3 directly, ie without the use of dazwi arranged Leitschaufein be supplied because of the high pressure turbine 2 made available from gas flow without previous diversion or , without the use of special guide elements for driving the blades 14 of the low-pressure turbine wheel 32 is suitable.
  • the low-pressure turbine wheel 32 output exhaust stream is forwarded in the administratbe region 21 of the low-pressure turbine 3 and output from the sem in a conventional manner to an exhaust pipe.
  • the low-pressure compressor 4 and the high-pressure compressor 5 each have Leitschaufein.
  • An alternative embodiment is to realize the low pressure compressor 4 and the high pressure compressor 5 without this Leitschaufein.
  • the high-pressure turbine 2 and the low-pressure turbine 3 are arranged in series with each other, wherein the high-pressure turbine 2 in a gas inlet housing 10a and the low-pressure turbine 3 in a gas outlet housing 1 is arranged is and wherein these two housing together verbun are the, for example, are bolted together.
  • This division of the two turbine stages on different Ge housing is advantageous for assembly and service reasons.
  • the high-pressure turbine 2 and the low pressure turbine 3 may be arranged within a single turbine housing 10, as illustrated in Figure 2 and is interpreted in Figures 3 and 4 with dashed lines on.
  • a separate housing for the low-pressure turbine is not necessary.
  • the number of components required to realize the two-stage turbocharger device is kept small. Because in a housing always Even energy losses occur, the energy V losses of the two-stage turbocharger device are redu ed by saving its own housing for the low-pressure turbine and thus increases their efficiency.
  • the two shafts 6 and 7 in the axial direction 9 are arranged behind the other, have opposite directions of rotation and the output of the high-pressure turbine exhaust gas flow of the low-pressure turbine can be fed directly, the be described two-stage turbocharger device can also be produced in simp cher manner. It is, inter alia, of importance that there is no need for storage and stable guidance coaxial with each other extending waves.
  • the storage of the shaft 6 can suc in a conventional manner in a bearing housing 22 conditions, the bearing of the shaft 7 in a corresponding manner in egg NEM bearing housing 23rd
  • the two turbines of the two-stage turbocharger device are arranged on different Wel len.
  • the first wave 6 where the high Pressure turbine 31 of the high-pressure turbine 2 is rotatably angeord net is, as shown in Figure 1, further arranged the Niederlichverêtrrad 13 of the low-pressure compressor 4.
  • the second shaft 7, on which the low-pressure turbine wheel 32 of the low-pressure turbine 3 is arranged rotationally fixed is also shown in Figure 1, further arranged the high-pressure compressor 28 of the high pressure Verdich age 5.
  • the high-pressure compressor wheel 28 of the high-pressure compressor 5 can furthermore be arranged on the first shaft 6, on which the high-pressure turbine wheel 31 of the high-pressure turbine 2 is arranged in a rotationally fixed manner.
  • the second shaft 7, on which the low-pressure turbine wheel 32 of the low-pressure turbine 3 is arranged rotationally fixed further arranged the Niederchristver dichterrad 13 of the low-pressure compressor 4.
  • the turbine stages are arranged centrally in the turbocharger device, currency end the two compressor stages are positioned at the outer ends of the turbocharger device. This will be explained in more detail hereinafter with reference to FIGS. 3 and 4, which show sketches of multi-stage turbocharger devices, in which the turbine stages are arranged centrally.
  • FIG. 3 shows a first sketch to illustrate the central arrangement of the turbine stages in a multistage turbocharger device.
  • the turbocharger apparatus 1 shown in FIG. 3 has a high-pressure turbine 2, a low-pressure turbine 3, a low-pressure compressor 4 and a high-pressure compressor 5.
  • the high-pressure turbine 2 the hot exhaust gas of an internal combustion engine 34 is supplied. This hot exhaust drives the high pressure turbine wheel of the high pressure turbine 2.
  • the high-pressure turbine wheel is firmly connected to a first shaft 6, on which further the high-pressure compressor wheel of the high pressure compressor 5 is arranged rotationally fixed.
  • the first shaft 6 has a direction of rotation 29.
  • the high-pressure turbine wheel driven by the hot exhaust gas displaces the first shaft 6 into a rotational movement which is transmitted to the high-pressure wheel via the first shaft 6 so that it is also rotated.
  • the exhaust gas discharged from the high-pressure turbine 2 is directly supplied to the low-pressure turbine 3 whose low-pressure turbine wheel is driven by the exhaust gas discharged from the high-pressure turbine 2.
  • the low-pressure turbine wheel is rotatably mounted on a second shaft 7 and transmits its rotational movement to the second shaft 7.
  • the second shaft 7, which rotates in the direction of rotation 30 in opposite directions to the first shaft 6, is further connected to the low-pressure compressor of the low pressure compressor 4 rotatably connected , Consequently, the rotational movement of the second shaft 7 is transmitted to the Niedertownverdich terrad, so that this is also set in rotation ver.
  • the intercooler 12 is preferably a heat exchanger which is operated with water, which is the precompressed air flow from the low pressure compressor 4 cools down.
  • the pre-compressed air in the low pressure compressor 4 is supplied to the intercooler 12 via a piping system.
  • the cooled in the intercooler 12 precompressed air is also forwarded via a piping system to the Hochdruckver dense 5.
  • FIG. 4 shows a second sketch to illustrate the central arrangement of the turbine stages in another multi-stage turbocharger device.
  • the turbocharger apparatus 1 shown in FIG. 4 has a high-pressure turbine 2, a low-pressure turbine 3, a low-pressure compressor 4 and a high-pressure compressor 5.
  • the high-pressure turbine 2 the hot exhaust gas of an internal combustion engine 34 is supplied.
  • This hot exhaust drives the high pressure turbine wheel of the high pressure turbine 2.
  • the high-pressure turbine wheel is firmly connected to a first shaft 6, on which further the low pressure compressor wheel of the low pressure compressor 4 is arranged rotationally fixed.
  • the first shaft 6 has a direction of rotation 29.
  • the high-pressure turbine wheel driven by the hot exhaust gas displaces the first shaft 6 into a rotational movement which is transmitted to the low-pressure compressor via the first shaft 6 so that it is also rotated. Due to this rotation of the low-pressure compressor wheel, the fresh air supplied from a fresh-air source 35 is precompressed in the low-pressure compressor 4.
  • the precompressed air is fed via an intercooler 12 to the high pressure compressor 5 and sealed by this further ver.
  • the present at the output of the high pressure compressor 5 de compressed air is supplied via a charge air cooler 33 of the engine 34 to increase their performance.
  • the exhaust gas discharged from the high-pressure turbine 2 is directly supplied to the low-pressure turbine 3 whose low-pressure turbine wheel is driven by the exhaust gas discharged from the high-pressure turbine 2.
  • the low-pressure turbine wheel is rotatably mounted on a second shaft 7 and transmits its rotational movement to the second shaft 7.
  • the second shaft 7, which rotates in the direction of rotation 30 in opposite directions to the first shaft 6, is further rotatably connected to the high-pressure compressor wheel of the high-pressure compressor 5 , Consequently, the rotational movement of the second shaft 7 is transmitted to the high-pressure compressor wheel, so that this is also rotated.
  • the air pre-compressed by the low-pressure compressor 4 is compressed. This further compressed air is supplied via a charge air cooler 33 of the internal combustion engine 34 to their performance increase.
  • intercooler 12 is preferably egg nen heat exchanger, which is operated with water, which cools the pre-compressed air flow from the low-pressure compressor 4 from.
  • the pre-compressed air in the low pressure compressor 4 is supplied to the intercooler 12 via a piping system.
  • the cooled in the intercooler 12 precompressed air is also forwarded via a piping system to the Hochdruckver dense 5.
  • the turbocharger device shown in FIG. 4 is also a two-stage turbocharger system, which has two shafts, which are arranged one behind the other in the axial direction and rotate in opposite directions, and which are arranged centrally. Nete turbine stages, wherein the output from a high-pressure turbine exhaust turbine drives the turbine Niederdrucktur bine.
  • a multi-stage turbo 1ade V is provided orcardi having a high pressure turbine, a low pressure turbine, a low pressure compressor, a high pressure compressor, a first shaft and a second shaft.
  • one of the turbines and one of the compaction ter on the first shaft and the other turbine and the other compressor is arranged on the second shaft.
  • the two shafts are arranged one behind the other in the axial direction and have the same axis of rotation.
  • the two waves do not run into each other or. are axially spaced from each other.
  • the two waves have an opposite direction of rotation.
  • the output area of the high-pressure turbine forms the input area of the low-pressure turbine, so that the low-pressure turbine of the exhaust gas stream emitted by the high-pressure turbine is made available as input flow.
  • the exhaust gas flow provided by the high-pressure turbine can advantageously be fed directly to the rotor blades of the low-pressure turbine, ie H . without use of since between arranged special guide elements, are supplied.
  • the turbocharger device to a multi-stage compressor device, wherein the compressor from the low-pressure pre-compressed air flow, optionally via an inter mediate cooler, the high-pressure compressor is supplied.
  • the two turbine stages are arranged axially centrally in the turbocharger device, while the two compressor stages are positioned at the axial outer ends of the tur boladervoriques. In one aspect, give the two compressor stages, the two turbine stages axially from both opposite sides.
  • the two turbines of the turbocharger device are preferably axial turbines, i. H . Turbines, the impeller is in each case flows in the axial direction.
  • the respective blades of the two turbines cover at least 50%, preferably at least 80% overlapping, radial area, the radial area being related to the radial distance, measured in cross-section, of the entrance area of the blades.
  • the storage of the two shafts of the turbocharger device can be carried out in a conventional manner. There are no special requirements regarding this storage.
  • the low-pressure compressor can be arranged either on the same shaft as the high-pressure turbine or on the same shaft as the low-pressure turbine.
  • the high-pressure compressor is in each case arranged on the other shaft than the low-pressure compressor.
  • the high pressure turbine is connected to the low pressure compressor via the first shaft. In one aspect, the low pressure turbine is connected to the high pressure compressor via the first shaft.

Landscapes

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

Abstract

La présente invention concerne un dispositif de turbocompresseur à plusieurs étages (1), qui comprend une turbine à haute pression (2), une turbine à basse pression (3), un compresseur à basse pression (4), un compresseur à haute pression (5), un premier arbre (6) et un second arbre (7). Une des turbines et un des compresseurs sont disposés sur le premier arbre et l'autre turbine et l'autre compresseur sont disposés sur le second arbre, les deux arbres ont le même axe de rotation, sont disposés l'un derrière l'autre dans la direction axiale et ont un sens de rotation opposé.
PCT/EP2019/059258 2018-04-17 2019-04-11 Dispositif de turbocompresseur à plusieurs étages WO2019201739A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19718632.3A EP3781799A1 (fr) 2018-04-17 2019-04-11 Dispositif de turbocompresseur à plusieurs étages
CN201980026535.7A CN112334640A (zh) 2018-04-17 2019-04-11 多级涡轮增压器装置

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102018109135 2018-04-17
DE102018109135.4 2018-04-17

Publications (1)

Publication Number Publication Date
WO2019201739A1 true WO2019201739A1 (fr) 2019-10-24

Family

ID=66240093

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2019/059258 WO2019201739A1 (fr) 2018-04-17 2019-04-11 Dispositif de turbocompresseur à plusieurs étages

Country Status (3)

Country Link
EP (1) EP3781799A1 (fr)
CN (1) CN112334640A (fr)
WO (1) WO2019201739A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115929460A (zh) * 2022-12-08 2023-04-07 重庆交通大学 适用于高空航空活塞发动机的组合式二级增压器

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1028280B (de) * 1952-04-30 1958-04-17 Sc Techn H C Alfred Buechi Dr Gegenlauf-Turbogeblaese oder -pumpe mit Antrieb durch Gegenlauf-Gasturbine
GB1438172A (en) * 1972-07-11 1976-06-03 Maschf Augsburg Nuernberg Ag Supercharged internal-combustion engine
WO2007061339A1 (fr) * 2005-11-22 2007-05-31 Volvo Lastvagnar Ab Moteur a combustion interne avec systeme a turbocompresseur a deux etages
WO2008125555A1 (fr) * 2007-04-16 2008-10-23 Napier Turbochargers Limited Dispositif de turbocompresseur
DE102014202399A1 (de) 2013-02-15 2014-08-21 Ford Global Technologies, Llc Mehrrotoriger turbolader
DE102014218345A1 (de) * 2014-09-12 2016-03-17 Ford Global Technologies, Llc Aufgeladene Brennkraftmaschine mit in Reihe angeordneten Abgasturboladern
EP3121413A1 (fr) * 2015-07-21 2017-01-25 Honeywell International Inc. Systèmes de turbocompresseur avec des interfaces de turbine directe

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8915082B2 (en) * 2011-02-03 2014-12-23 Ford Global Technologies, Llc Regenerative assisted turbocharger system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1028280B (de) * 1952-04-30 1958-04-17 Sc Techn H C Alfred Buechi Dr Gegenlauf-Turbogeblaese oder -pumpe mit Antrieb durch Gegenlauf-Gasturbine
GB1438172A (en) * 1972-07-11 1976-06-03 Maschf Augsburg Nuernberg Ag Supercharged internal-combustion engine
WO2007061339A1 (fr) * 2005-11-22 2007-05-31 Volvo Lastvagnar Ab Moteur a combustion interne avec systeme a turbocompresseur a deux etages
WO2008125555A1 (fr) * 2007-04-16 2008-10-23 Napier Turbochargers Limited Dispositif de turbocompresseur
DE102014202399A1 (de) 2013-02-15 2014-08-21 Ford Global Technologies, Llc Mehrrotoriger turbolader
DE102014218345A1 (de) * 2014-09-12 2016-03-17 Ford Global Technologies, Llc Aufgeladene Brennkraftmaschine mit in Reihe angeordneten Abgasturboladern
EP3121413A1 (fr) * 2015-07-21 2017-01-25 Honeywell International Inc. Systèmes de turbocompresseur avec des interfaces de turbine directe

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115929460A (zh) * 2022-12-08 2023-04-07 重庆交通大学 适用于高空航空活塞发动机的组合式二级增压器

Also Published As

Publication number Publication date
CN112334640A (zh) 2021-02-05
EP3781799A1 (fr) 2021-02-24

Similar Documents

Publication Publication Date Title
DE69930876T2 (de) Vorrichtung und verfahren zur leistungssteigerung einer turbine
DE60221403T2 (de) Doppelstrom - verdichter
DE112014002983T5 (de) Turbolader, der eine Axialstromturbine mit einer Kompressorstufe kombiniert, die eine aktive Gehäusebehandlung einsetzt
DE102015203171A1 (de) Abgasturboaufgeladene Brennkraftmaschine umfassend einen Radialverdichter mit im Diffusor angeordneter Leiteinrichtung und Verfahren zum Betreiben einer derartigen Brennkraftmaschine
DE112016005560T5 (de) Turboladerverdichter und Verfahren dafür
DE102021122921A1 (de) Einlasssystem, beinhaltend einen turbolader mit geteiltem spiralgehäuse, der eine variable turbinengeometrie mit aerodynamischen abstandshaltern und einen leitschaufelkranz mit einer mehrzahl von drehbaren leitschaufeln aufweist
DE102009024568A1 (de) Verdichterlaufrad
WO2019201739A1 (fr) Dispositif de turbocompresseur à plusieurs étages
EP2185802A1 (fr) Système de suralimentation pour un moteur à combustion interne
DE102014212606B4 (de) Kraftfahrzeug und Luftfilterbox
DE202015101916U1 (de) Zweistufig aufladbare Brennkraftmaschine mit Abgasturbolader
WO2010043298A1 (fr) Ensemble turbocompresseur
DE102014226341A1 (de) Verdichter, Abgasturbolader und Brennkraftmaschine
DE102014215885B3 (de) Aufgeladene Brennkraftmaschine mit Mixed-Flow-Turbine
DE102014220680A1 (de) Brennkraftmaschine mit Mixed-Flow-Turbine umfassend eine Leiteinrichtung
DE112016005499T5 (de) Turboladerverdichter und Verfahren dafür
DE112016005563B4 (de) Turboladerverdichter und verfahren dafür
DE102017012253B4 (de) Verdichter für einen Turbolader einer Brennkraftmaschine sowie Turbolader für eine Brennkraftmaschine
DE102020201754A1 (de) Turbo-cluster-gasturbinensystem und aktivierungsverfahren davon
DE102007024527A1 (de) Turbolader-Vorrichtung für eine Brennkraftmaschine
DE102018109138A1 (de) Turbolader mit integrierter Nutzturbine
DE102014220679B4 (de) Brennkraftmaschine mit Mixed-Flow-Turbine umfassend eine Leiteinrichtung und Abgasrückführung
EP4031752B1 (fr) Introduction concentrique d'un flux massique waste-gate dans un diffuseur axial à écoulement optimisé
WO2018177864A1 (fr) Turbocompresseur pour un moteur à combustion interne ainsi que carter de turbine
DE102015205910A1 (de) Zweistufig aufladbare Brennkraftmaschine mit Abgasturbolader und Verfahren zum Betreiben einer derartigen Brennkraftmaschine

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19718632

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

ENP Entry into the national phase

Ref document number: 2019718632

Country of ref document: EP

Effective date: 20201117