GB2488136A - Two-stage Turbocharger for an Internal Combustion Engine - Google Patents

Two-stage Turbocharger for an Internal Combustion Engine Download PDF

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Publication number
GB2488136A
GB2488136A GB1102738.0A GB201102738A GB2488136A GB 2488136 A GB2488136 A GB 2488136A GB 201102738 A GB201102738 A GB 201102738A GB 2488136 A GB2488136 A GB 2488136A
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GB
United Kingdom
Prior art keywords
pressure
turbocharger
low
engine
exhaust manifold
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
GB1102738.0A
Other versions
GB201102738D0 (en
GB2488136B (en
Inventor
Eugenio Manta
Domenico Palmisani
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.)
GM Global Technology Operations LLC
Original Assignee
GM Global Technology Operations LLC
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 GM Global Technology Operations LLC filed Critical GM Global Technology Operations LLC
Priority to GB1102738.0A priority Critical patent/GB2488136B/en
Publication of GB201102738D0 publication Critical patent/GB201102738D0/en
Publication of GB2488136A publication Critical patent/GB2488136A/en
Application granted granted Critical
Publication of GB2488136B publication Critical patent/GB2488136B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F02B37/013—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/08—Other arrangements or adaptations of exhaust conduits
    • F01N13/10—Other arrangements or adaptations of exhaust conduits of exhaust manifolds
    • 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
    • F02B37/001—Engines characterised by provision of pumps driven at least for part of the time by exhaust using exhaust drives arranged in parallel
    • F02B37/002—Engines characterised by provision of pumps driven at least for part of the time by exhaust using exhaust drives arranged in parallel the exhaust supply to one of the exhaust drives can be interrupted
    • 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
    • F02B37/007—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel, e.g. at least one pump supplying alternatively
    • 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
    • F02B37/12—Control of the pumps
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • 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
    • F02B67/00—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for
    • F02B67/10—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for of charging or scavenging apparatus
    • 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

Landscapes

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

Abstract

A two-stage turbocharger and an exhaust manifold for an internal combustion engine, the two-stage turbocharger comprising: a high-pressure turbocharger having a high-pressure turbine, housed in volute 16, and a high-pressure compressor, a low-pressure turbocharger having a low-pressure turbine, housed in volute 14, and a low-pressure compressor, wherein the high-pressure turbine and the low-pressure turbine are housed in a common housing (12, fig.2), the common housing being provided with a first single flange 22 for connection to the exhaust manifold 24 of the engine. The exhaust manifold may additionally comprise a conduit that leads to the inlet of the high pressure turbine or a valve (36, fig.6) for bypassing the high pressure turbine.

Description

TWO-STAGE TURBOCHARGER FOR AU INTER&4L CCMBUSTION ENGINE EQfiAK?L flEW The present disclosure relates to a two-stage turbocharger for an internal combustion engine.
Two-stage turbocharged engine systems comprise two sequential turbochargers which are selectively operated in accordance with engine speed and engine load.
As a matter of fact, a known two-stage turbocharged engine system comprises a high-pressure turbocharger and a low-pressure turbocharger, both having a compressor and a turbine.
The compressor of high-pressure turbocharger is located in the intake line downstream the compressor of low-pressure turbocharger, relative to the flow direction.
The intake line comprises a low-pressure intake line for fluidly connecting the outlet of low-pressure compressor to the inlet of :1-High-pressure turbocharger and low-pressure turbocharger are arranged such that at low engine speeds both turbochargers are used for charging air into the engine, while as engine speed rises the high-pressure turbocharger is gradually disabled.
The intake line comprises a bypass device arranged for allowing the airflow to bypass the high-pressure compressor when the high-pressure turbocharger is disabled.
The bypass device generally comprises a bypass line for fluidly connecting low-pressure intake line directly to high-pressure intake line, and a valve which is located in said bypass line for opening or closing the passageway.
A system such as the one described above is disclosed in EP 1 843 019 and, while having good performance, it may have margins of improvement.
An aim of an embodiment of the present invention is to improve the packaging of the two-stage turbooharged engine system, in order to make possible a more compact design able to reduce the thermal materials for the turbine housing and for the exhaust manifold.
Another aim of the present invention is to meet these and other goals with a rather simple, rational and inexpensive solution.
The dependent claims delineate preferred and/or especially advantageous aspects.
stmtaRr An embodiment of the disclosure provides a two-stage turbocharger for an internal combustion engine, the two-stage turbocharger comprising: a high-pressure turbocharger having a high-pressure turbine and a high-pressure compressor, a low-pressure turbocharger having a low-pressure turbine and a low-pressure compressor, wherein the high-pressure turbine and the low-pressure turbine are housed in a corrwnon housing, the common housing being provided with a single flange for connection to an exhaust manifold of the engine.
An advantage of this embodiment is that it allows to have an exhaust manifold with a single outlet flange in a centered position with respect to the exhaust manifold increasing exhaust manifold expansion of the flange, compared with the know art that provided two different flanges and a wider area, allows to shift to cheaper housing materials, for example to Silicon-Molibdenum (SiMo).
Another advantage of this embodiment is that it allows to reduce the distance between high-pressure and low-pressure turbocharger, allowing for a more compact two-stage system.
Finally, this embodiment allow to increase the distance between the air filter and the compressor inlet.
According to another embodiment of the invention, the common turbine housing is provided as a single cast part and/or a single casting.
IAn advantage of this embodiment is that it allows for a more compact construction.
According to a further embodiment of the invention, a two-stage turbocharger and engine exhaust manifold assembly is provided, wherein a first single flange is connected to a second flange coupled to an exhaust manifold of an internal combustion engine.
According to a further embodiment of the invention, a two-stage turbocharger and engine exhaust manifold assembly is provided in which second flange is provided with conduit connected to a high pressure inlet of the high-pressure turbine and with a closed hole.
An advantage of this embodiment is that it improves structurally the performance of the flange in thermal stress conditions and avoids porosity due to high material thickness while reducing overall weight.
According to still another embodiment of the invention, a two-stage turbocharger and engine exhaust manifold assembly is provided, wherein internally to the second flange, a flap for a short-cut line valve for by-passing an high-pressure turbocharger of the two-stage turbocharger is provided.
An advantage of this embodiment is represented by the compactness of construction especially valuable in smaller vehicles.
A still further aspect of the disclosure provides an internal combustion engine specially arranged for the two-stage turbocharger.
Figure 1 is a schematic illustration of a two-stage turbocharged engine system suitable for employing an embodiment of the invention; Figure 2 is view of a portion of a two-stage turbocharger for an engine system according to an embodiment of the invention; Figure 3 is another view of the embodiment of figure 2; Figure 4 is a further view of the two-stage turbocharger portion of figures 2-3; Figure 5 is a sectional view according to line E-E of figure 3 of the two-stage turbocharger portion of figures 2-4; Figure 6 is a view of a two-stage turbocharger for an engine system according to an embodiment of the invention; Figure 7 is a view of a portion of exhaust manifold having a flange for the installation of the two-stage turbocharger; and Figure 8 is perspective illustration of a two-stage turbocharged Preferred embodiments will now be described with reference tc the enclosed drawings.
In figure 1, a two-stage turbocharger applied to an internal combustion engine 40 is schematically illustrated according to an exemplary actual implementation useful for understanding the various embodiments of the invention and their advantages.
The engine 40 has an intake manifold 42 and an exhaust manifold 24, each of which comprises a plurality of runners corresponding in number to the number of individual cylinders of the engine 40. The intake manifold 42 communicates with an air inlet 130 via an intake line 80.
The two-stage turbocharger comprises a low-pressure turbocharger 105, having a low-pressure turbine 50 and a low-pressure compressor 51, which is rotated by the turbine 50 by means of a connecting shaft 52.
The two-stage turbocharger further comprises a high-pressure turbocharger 106, having a high-pressure turbine 60 and an high-pressure compressor 61, which is rotated by the turbine 60 by means of a connecting shaft 62.
The outlet of the high-pressure turbine 60 coimiunicates with the inlet of low-pressure turbine 50 via a low-pressure exhaust line 71.
The inlet of the low-pressure turbine 50 directly corrmunicates with the exhaust manifold 24 via a short-cut line 72 leading into the low-pressure exhaust line 71.
The short-cut line 72 comprises a valve 73 for opening and closing the passageway.
The outlet of low-pressure turbine 50 corrmunicates with the exhaust outlet 140 via a muffler line 74.
The low-pressure exhaust line 71 directly communicates with a muffler line 74 via a bypass line 75 which comprises a waste gate valve 76 for opening and closing such passageway.
The inlet of low-pressure compressor 51 communicates with the air inlet 130 via connecting intake line 80.
The outlet of low-pressure compressor 51 communicates with the inlet recirculated into the intake manifold 42 of the engine 40.
The two-stage turbocharger also comprises a by-pass arranged for allowing the airflow to bypass the high-pressure compressor 61 when the high-pressure turbocharger 106 is disabled by means of a by-pass line 91 for directly fluidly connecting the low-pressure intake line 81 to an high-pressure intake line 82. A valve 94 located in said by-pass line 91 is provided for selectively opening or closing such passageway.
In operation, at low engine speed, the valves 73, 94 and the waste gate valve 76 are closed, and the intake air is charged in series by both low-pressure compressor 51 and high-pressure compressor 61, making the system work according a two-stage operating mode.
With increasing engine speed, the flow capacity of the high-pressure turbocharger 106 becomes limited, thereby limiting further performance to be obtained. The valve 73 opens the short-cut line 72, allowing part of the exhaust gas to flow from exhaust manifold 24 directly into low-pressure exhaust line 71. At the same time, the flow and pressure within high-pressure exhaust line 70 continue to energize the high-pressure turbocharger 106 to thereby cause charging energize low-pressure turbocharger 105. Therefore, the pressure within high-pressure intake line 81 can be adjusted such that it does not exceed the allowed limit.
When the engine performs at higher speed the opening area of valve 73 reaches a maximum, thus almost all of the exhaust gas flows thrcugh the short-cut line 72 into low-pressure exhaust pipe 71 to thereby lose the function of high-pressure turbocharger 106, while energizing low-pressure turbocharger 105 to thereby produce a predetermined charging pressure, making the system work according a single-stage operating mode.
At higher engine speed the high-pressure turbocharger 106 is disabled and the valve 94 opens the bypass line 91, then the air discharged from low-pressure compressor 51 flows directly in the second portion 83 of the high-pressure intake line, thereby bypassing the major portion of the low-pressure intake line 81, the high-pressure compressor 61 and the high-pressure intake line 82.
Finally, when the low pressure turbocharger reaches its limit an actuator 151 opens waste gate valve 76 protecting the turbocharger from overpressure.
turbine housing 12 being provided as a single cast part and/or a single casting.
The turbine housing 12 comprises a low-pressure volute 14 for accommodating the turbine 50 of the low-pressure turbocharger 105, and a high-pressure volute 16 for accommodating the turbine 60 of the high-pressure turbocharger 106.
The high-pressure volute 16 communicates with the exhaust manifold 24 of the engine 40 via high-pressure exhaust line 70 that in turn communicates with an high pressure inlet 20.
The low-pressure volute 14 corrmunicates with high-pressure outlet of high-pressure turbine 60 via low-pressure exhaust line 71 that in turn communicates with a low pressure inlet 34 (fig. 4).
In fig. 3 it is also visible the waste gate valve 76 in the low-pressure turbocharger by-pass line 75 and the corresponding waste gate actuator 151.
According to an embodiment of the invention, the turbine housing 12 that houses low-pressure volute 14 and the high-pressure volute 16 is e Correspondingly, the exhaust manifold 24 of the engine has a single connecting flange 26 for coupling with flange 22.
Flange 26 is also provided with a conduit 27 that leads to high pressure inlet 20 and with a closed hole 25 useful to reduce weight of flange 26. (fig.7) The connecting flanges 22,26 are provided with a number of holes 30 (six holes in the non-limitative exarrple shown in the figures) for corresponding connecting bolts 32.
As shown in fig. 7, internally to the connecting flange 26 of the exhaust manifold, a flap 36 is provided for the valve 73 that intercepts the short-cut line 72 that allows part of the exhaust gas to flow from exhaust manifold 24 directly into low-pressure exhaust line 71. The flap 36 of the short-cut line valve 73 is acted upon by actuator 161.
In fig. 8 the two-stage turbocharged engine system is represented illustrating an actuator 171 for the valve 94.
As a further advantage it may be mentioned the fact that the two-While at least one exemplary embodiment has been presented in the foregoing surnraary and detailed description, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only exariples, and are not intended to limit the scope, applicability, or configuration in any way. Rather, the foregoing summary and detailed description will provide those skilled in the art with a convenient road map for implementing at least one exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope as set forth in the appended claims and their legal equivalents.
REFEREt4E Nt4BERS two-stage turbocharger 12 turbine housing 14 low-pressure volute 16 high-pressure volute high-pressure inlet 22 connecting flange (of the housing) 24 engine exhaust manifold closed hole 26 connecting flange (of the exhaust manifold) 27 conduit to high-pressure inlet holes 32 bolts 34 low-pressure inlet 36 flap of short-cut line valve engine 42 intake manifold low-pressure turbine 51 low-pressure compressor 52 connecting shaft (low-pressure turbocharger) 61 high-pressure compressor 62 connecting shaft (high-pressure turbocharger) high-pressure intake line 71 low-pressure exhaust line 72 short-cut line 73 short-cut line valve 74 muffler line low-pressure turbocharger by-pass line 76 waste gate valve 80 intake line 81 low-pressure intake line 82 portion of high-pressure intake line 83 final portion of high-pressure intake line 84 line from air cooler to intake manifold 94 valve (on high-pressure turbocharger by-pass line) high-pressure turbocharger by-pass line low-pressure turbocharger 106 high-pressure turbocharger 107 air cooler 108 connecting means air inlet exhaust outlet 151 actuator of waste gate valve 161 actuator of short-cut line valve 171 actuator of high-pressure turbocharger by-pass valve

Claims (6)

1. Two-stage turbocharger (10) for an internal combustion engine (40), the two-stage turbocharger (10) comprising: a high-pressure turbocharger (106) having a high-pressure turbine (60) and a high-pressure compressor (61), a low-pressure turbocharger (105) having a low-pressure turbine (50) and a low-pressure compressor (51), wherein the high-pressure turbine (60) and the low-pressure turbine (50) are housed in a common housing (12), the common housing (12) being provided with a first single flange (22) for connection to an exhaust manifold (24) of the engine (40).
2. Two-stage turbocharger (10) according to claim 1, in which the common turbine housing (12) is provided as a single cast part and/or a single casting.
3. Two-stage turbocharger (10) and engine exhaust manifold (24) assembly, wherein a first single flange (22) is connected to a second flange (26) coupled to an exhaust manifold (24) of an internal combustion engine (40).
4. Two-stage turbocharger (10) and engine exhaust manifold (24) assembly, according to claim 3, in which second flange (26) is provided with a conduit (27) that lead to high pressure inlet (20) of high-pressure turbine (60) and with a closed hole (25).
5. Two-stage turbocharger (10) and engine exhaust manifold (24) assembly, according to claim 3, wherein internally to the second flange (26), a flap (36) for a short-cut line valve (73) for by-passing an high-pressure turbocharger (106) of the two-stage turbocharger is provided.
6. Internal corrbustion engine (40) having associated a two-stage turbocharger (10) and an engine exhaust manifold (24) according to any of the preceding claims.
GB1102738.0A 2011-02-17 2011-02-17 Two-stage turbocharger for an internal combustion engine Expired - Fee Related GB2488136B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1102738.0A GB2488136B (en) 2011-02-17 2011-02-17 Two-stage turbocharger for an internal combustion engine

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Application Number Priority Date Filing Date Title
GB1102738.0A GB2488136B (en) 2011-02-17 2011-02-17 Two-stage turbocharger for an internal combustion engine

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GB201102738D0 GB201102738D0 (en) 2011-03-30
GB2488136A true GB2488136A (en) 2012-08-22
GB2488136B GB2488136B (en) 2016-04-13

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8499559B2 (en) * 2006-04-05 2013-08-06 GM Global Technology Operations LLC Two-stage turbo-charger engine system

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS63201319A (en) * 1987-02-18 1988-08-19 Fuji Heavy Ind Ltd Twin turbosupercharger
JPH07301122A (en) * 1994-05-06 1995-11-14 Mitsubishi Motors Corp Internal combustion engine with turbocharger
DE19822874A1 (en) * 1998-05-22 1999-11-25 Man Nutzfahrzeuge Ag Charging system for internal combustion engine
US20040040300A1 (en) * 2002-08-30 2004-03-04 Dieter Klingel Turbocharger for an internal combustion engine
WO2008125555A1 (en) * 2007-04-16 2008-10-23 Napier Turbochargers Limited Turbocharger arrangement
EP2267285A2 (en) * 2009-06-24 2010-12-29 Benteler Automobiltechnik GmbH & Co. KG Exhaust assembly

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5655364B2 (en) * 2010-04-30 2015-01-21 いすゞ自動車株式会社 Turbocharger

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS63201319A (en) * 1987-02-18 1988-08-19 Fuji Heavy Ind Ltd Twin turbosupercharger
JPH07301122A (en) * 1994-05-06 1995-11-14 Mitsubishi Motors Corp Internal combustion engine with turbocharger
DE19822874A1 (en) * 1998-05-22 1999-11-25 Man Nutzfahrzeuge Ag Charging system for internal combustion engine
US20040040300A1 (en) * 2002-08-30 2004-03-04 Dieter Klingel Turbocharger for an internal combustion engine
WO2008125555A1 (en) * 2007-04-16 2008-10-23 Napier Turbochargers Limited Turbocharger arrangement
EP2267285A2 (en) * 2009-06-24 2010-12-29 Benteler Automobiltechnik GmbH & Co. KG Exhaust assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8499559B2 (en) * 2006-04-05 2013-08-06 GM Global Technology Operations LLC Two-stage turbo-charger engine system

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GB201102738D0 (en) 2011-03-30
GB2488136B (en) 2016-04-13

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PCNP Patent ceased through non-payment of renewal fee

Effective date: 20180217