WO2012090662A1 - 多段過給装置 - Google Patents
多段過給装置 Download PDFInfo
- Publication number
- WO2012090662A1 WO2012090662A1 PCT/JP2011/078285 JP2011078285W WO2012090662A1 WO 2012090662 A1 WO2012090662 A1 WO 2012090662A1 JP 2011078285 W JP2011078285 W JP 2011078285W WO 2012090662 A1 WO2012090662 A1 WO 2012090662A1
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- WIPO (PCT)
- Prior art keywords
- pressure stage
- turbine
- exhaust
- low
- supercharger
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
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- 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
- 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
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- 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
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- 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
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- 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
- F02B37/183—Arrangements of bypass valves or actuators therefor
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- 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 present invention relates to a multistage turbocharger, and more particularly to a multistage supercharger having a first supercharger and a second supercharger that are driven by engine exhaust.
- a two-stage supercharging system (multistage supercharging device) is known as a system that efficiently recovers engine exhaust energy.
- this two-stage supercharging system is configured so that the high-pressure stage turbocharger (first supercharger) and the low-pressure stage turbocharger (second supercharger) have a low pressure sequentially from the upstream side of the exhaust flow into the exhaust passage.
- a stage turbine is arranged in series.
- a low-pressure stage compressor of a low-pressure stage turbocharger and a high-pressure stage compressor of a high-pressure stage turbocharger are arranged in series in this order from the upstream side of the intake flow. Then, the high-pressure turbine and the low-pressure turbine are rotationally driven by the exhaust of the engine, and the intake air compressed by the low-pressure compressor is further compressed by the high-pressure compressor, so that high supercharging is possible.
- Patent Document 1 discloses a multi-stage turbocharger including a high-pressure stage supercharger and a low-pressure stage supercharger, in which an intake passage and an intercooler are integrally formed to reduce the size of the entire apparatus. It is disclosed.
- the present invention has been made in view of the above points, and an object of the present invention is to improve the sealing performance at the connection portion between the high-pressure stage turbocharger and the low-pressure stage turbocharger in the multistage turbocharger, and to improve the supercharging efficiency. It is to improve effectively.
- a multi-stage turbocharger is a multi-stage supercharger having a first supercharger and a second supercharger that are driven by exhaust of an engine.
- the feeder includes a first turbine, a first turbine accommodating portion that accommodates the first turbine, and a first exhaust that is directly connected to the exhaust manifold of the engine and communicates the exhaust manifold and the first turbine accommodating portion.
- the second supercharger includes an inlet portion and a first exhaust outlet portion that extends from the first turbine housing portion in the axial direction of the first turbine and is bent upward so as to open upward.
- a second turbine a second turbine accommodating portion that accommodates the second turbine, and a second turbine that is directly connected to the first exhaust outlet portion and communicates the first exhaust outlet portion and the second turbine accommodating portion.
- the opening of the second exhaust inlet is placed in the opening of the first exhaust outlet, the second turbocharger, characterized in that it is supported by the first turbocharger.
- a first flange is provided at the opening of the first exhaust outlet, and a second flange is provided at the opening of the second exhaust inlet, and the first flange and the second flange are mutually connected. They may be directly connected with the flange surface horizontal.
- a bypass flow path that bypasses the first turbine housing portion and communicates the first exhaust inlet portion and the second exhaust inlet portion may be integrally formed with the first supercharger.
- a flow rate adjusting valve for adjusting the flow rate of the exhaust gas flowing through the bypass flow path may be further provided.
- the multistage supercharging device of the present invention it is possible to improve the sealing performance at the connection portion between the high pressure turbocharger and the low pressure turbocharger and to effectively improve the supercharging efficiency.
- FIG. 4 is a sectional view taken along line BB in FIG. 3.
- FIG. 3 is a sectional view taken along line AA in FIG. 2.
- a multistage supercharging device 1 is attached to a diesel engine (hereinafter simply referred to as an engine) 10 mounted on a vehicle.
- the low-pressure stage turbocharger 30 has a larger capacity than the high-pressure stage turbocharger 20.
- the high-pressure stage turbocharger 20 of the present embodiment corresponds to the first supercharger of the present invention.
- the low-pressure stage turbocharger 30 of the present embodiment corresponds to the second supercharger of the present invention.
- the cylinder head 11 of the engine 10 is provided with an intake manifold 13 and an exhaust manifold 14.
- the exhaust manifold 14 is directly connected to the high-pressure stage exhaust inlet 25 a of the high-pressure stage turbocharger 20.
- the intake manifold 13 is connected to the downstream end of a high-pressure intake passage 15 for introducing high-pressure intake air sent from the high-pressure stage turbocharger 20.
- the high pressure intake passage 15 is provided with an intercooler 16 for cooling the intake air and a throttle valve 17 for adjusting the intake air amount.
- the upstream end of the high-pressure intake passage 15 is connected to the high-pressure stage intake outlet portion 26c of the high-pressure stage turbocharger 20, and the downstream end of the low-pressure intake passage 18 is connected to the high-pressure stage intake inlet portion 26a.
- the low-pressure stage exhaust inlet portion 35 a of the low-pressure stage turbocharger 30 is directly connected to the high-pressure stage exhaust outlet section 25 c of the high-pressure stage turbocharger 20. That is, the high-pressure turbocharger 20 rotates the high-pressure turbine 21 using the exhaust energy of the engine 10 and is compressed and supplied from the low-pressure compressor 32 by the rotation of the high-pressure compressor 22 provided coaxially. The low pressure intake air is further compressed and supplied to the engine 10.
- the upstream end of the low-pressure intake passage 18 is connected to the low-pressure stage intake outlet 36c of the low-pressure stage turbocharger 30.
- An air cleaner 42 is connected to the low-pressure stage intake inlet 36 a of the low-pressure stage turbocharger 30 via the intake passage 41.
- an exhaust purification device 44 is connected to the low-pressure stage exhaust outlet 35 c of the low-pressure stage turbocharger 30 via an exhaust passage 43. That is, the low-pressure stage turbocharger 30 rotates the low-pressure stage turbine 31 with the exhaust energy of the engine 10 and compresses the intake air introduced through the air cleaner 42 by the rotation of the low-pressure stage compressor 32 provided coaxially.
- the high-pressure compressor 22 is configured to be supplied.
- the high-pressure stage exhaust inlet 25a of the high-pressure stage turbocharger 20 and the low-pressure stage exhaust inlet part 35a of the low-pressure stage turbocharger 30 are communicated with each other by a bypass passage 25d that bypasses the high-pressure stage turbine housing part 25b.
- a flow rate adjusting valve 45 that adjusts the flow rate of the exhaust gas flowing through the bypass flow channel 25d is provided at the bypass outlet (downstream end) of the bypass flow channel 25d.
- the valve opening degree of the flow rate adjusting valve 45 is controlled according to the operating state of the engine 10 by an ECU (electronic control unit) (not shown). That is, in the low speed region of the engine 10, the valve opening degree of the flow rate adjusting valve 45 is controlled to zero (closed state). Then, as the rotation of the engine 10 increases, the valve opening degree of the flow rate adjustment valve 45 is controlled to increase.
- the high-pressure turbocharger 20 includes a high-pressure turbine 21 that is rotationally driven by exhaust gas, a high-pressure compressor 22 that compresses intake air, and a high-pressure turbine that connects the high-pressure turbine 21 and the high-pressure compressor 22.
- a stage rotor shaft 23 and a high-pressure stage housing 24 are provided. 2 and 4, the high-pressure stage housing 24 includes a high-pressure stage turbine housing part 25, a high-pressure stage compressor housing part 26, and a high-pressure stage bearing housing part 27.
- the high-pressure stage bearing housing part 27 is located in the central portion of the high-pressure stage housing 24, and the high-pressure stage turbine housing part 25 is attached to one end side (right side in FIGS. 2 and 4) by bolt fastening, and the other end side (FIG. 2). , 4 on the left side), a high-pressure compressor housing portion 26 is attached by bolt fastening.
- a pair of bearings 52 are provided in the high-pressure stage bearing housing portion 27, and the high-pressure stage rotor shaft 23 is rotatably supported by the bearings 52.
- the high-pressure stage turbine housing portion 25 includes a high-pressure stage exhaust inlet portion 25 a (see FIG. 5) for taking in exhaust from the engine 10, and a high-pressure stage turbine housing portion (see FIG. 5). 1st turbine accommodating part) 25b, the high pressure stage exhaust outlet part (1st exhaust outlet part) 25c which discharges exhaust_gas
- a flange 28a fixed to the exhaust outlet portion 14a of the exhaust manifold 14 by bolt fastening is provided at the upstream end of the high-pressure stage exhaust inlet portion (first exhaust inlet portion) 25a.
- the downstream end of the high-pressure stage exhaust inlet 25a communicates with the inside of the high-pressure stage turbine accommodating part 25b via the high-pressure stage turbine scroll flow path 25e.
- the high-pressure stage exhaust outlet 25c extends from the high-pressure turbine housing 25b in the axial direction of the high-pressure stage rotor shaft 23 and is bent upward so as to open upward.
- a flange (first flange) 28b that is bolted to a flange (second flange) 38a of a low-pressure stage exhaust inlet portion 35a described later is provided at the opening (downstream end) of the high-pressure stage exhaust outlet portion 25c.
- the flange 28b of the high-pressure stage exhaust outlet 25c and the flange 38a of the low-pressure stage exhaust inlet 35a are fixed in a state where the flange surfaces are horizontal.
- the low pressure stage turbocharger 30 is configured to be supported by the high pressure stage turbocharger 20 by fixing the flange surfaces to each other in a horizontal state.
- the bypass flow path 25d bypasses the high-pressure stage turbine housing part 25b and communicates the high-pressure stage exhaust inlet part 25a and the low-pressure stage exhaust inlet part 35a.
- the bypass passage 25d has an upstream end of the bypass inlet provided in the high-pressure stage turbine accommodating portion 25b and a downstream end of the bypass outlet provided on the same flange surface as the flange 28b. 25a and the high-pressure stage exhaust outlet 25c are integrally formed.
- the high-pressure stage compressor housing part 26 includes a high-pressure stage intake inlet part 26 a that takes in the intake air from the low-pressure stage turbocharger 30, a high-pressure stage compressor housing part 26 b that houses the high-pressure stage compressor 22, And a high-pressure stage intake outlet portion 26c for discharging the intake air.
- An annular high-pressure compressor scroll passage 26 e is formed in the high-pressure compressor housing portion 26 b on the radially outer side of the high-pressure compressor 22.
- the downstream end of the low-pressure intake passage 18 is fixed to the upstream end of the high-pressure stage intake inlet portion 26a.
- the upstream end of the high-pressure intake passage 15 is fixed to the downstream end of the high-pressure stage intake outlet portion 26c.
- the low-pressure stage turbocharger 30 includes a low-pressure stage turbine (second turbine) 31 that is rotationally driven by exhaust, a low-pressure stage compressor 32 that compresses intake air, and the low-pressure stage turbine 31 and the low-pressure stage A low-pressure stage rotor shaft 33 that connects the compressor 32 and a low-pressure stage housing 34 are provided.
- the low pressure stage housing 34 includes a low pressure stage turbine housing part 35, a low pressure stage compressor housing part 36, and a low pressure stage bearing housing part 37.
- the low-pressure stage bearing housing part 37 is located in the central portion of the low-pressure stage housing 34, and the low-pressure stage turbine housing part 35 is attached to one end side (right side in FIGS. 2 and 4) by bolt fastening, and the other end side (FIG. 2). , 4) is attached to the low pressure compressor housing portion 36 by bolt fastening.
- a pair of bearings 53 are provided in the low pressure stage bearing housing portion 37, and the low pressure stage rotor shaft 33 is rotatably supported by the bearings 53.
- the low-pressure stage turbine housing part 35 includes a low-pressure stage exhaust inlet part (second exhaust inlet part) that takes in exhaust that has passed through the high-pressure stage turbocharger 20 or exhaust gas that has passed through the bypass passage 25 d. ) 35a, a low-pressure stage turbine housing part (second turbine housing part) 35b for housing the low-pressure stage turbine 31, and a low-pressure stage exhaust outlet part 35c for discharging exhaust gas.
- an annular low-pressure stage turbine scroll passage 35 e is formed in the low-pressure stage turbine housing portion 35 b on the radially outer side of the low-pressure stage turbine 31.
- a flange 38a fixed to the flange 28b of the high-pressure stage exhaust outlet portion 25c by bolt fastening is provided at the opening (upstream end) of the low-pressure stage exhaust inlet portion 35a. Further, the downstream end of the low-pressure stage exhaust inlet portion 35a communicates with the inside of the low-pressure stage turbine housing portion 35b via the low-pressure stage turbine scroll passage 35e. Further, the upstream end of the exhaust passage 43 is fixed to the downstream end of the low-pressure stage exhaust outlet portion 35c by bolt fastening via a flange.
- the low-pressure compressor housing part 36 includes a low-pressure stage intake inlet 36a for taking in intake air via an air cleaner, a low-pressure stage compressor accommodating part 36b for accommodating the low-pressure compressor 32, and a low-pressure stage for discharging intake air. And an intake outlet portion 36c.
- An annular low-pressure compressor scroll passage 36e is formed in the low-pressure compressor housing portion 36b on the radially outer side of the low-pressure compressor 32.
- the downstream end of the intake passage 41 is fixed to the upstream end of the low-pressure stage intake inlet 36a.
- the upstream end of the low-pressure intake passage 18 is fixed to the downstream end of the low-pressure stage intake outlet 36c.
- the multistage supercharging device 1 has the following operational effects.
- the high-pressure stage exhaust outlet 25c of the high-pressure stage turbocharger 20 extends from the high-pressure stage turbine housing part 25b in the axial direction of the high-pressure stage rotor shaft 23 and is bent upward so as to open upward. .
- the flange 28b provided at the opening (downstream end) of the high-pressure stage exhaust outlet 25c and the flange 38a provided at the opening (upstream end) of the low-pressure stage exhaust inlet 35a have the flange surfaces horizontal to each other. In this state, it is fixed by bolt fastening.
- the low-pressure stage turbocharger 30 is supported by the high-pressure stage turbocharger 20 by mounting and fixing the flange 38a of the low-pressure stage exhaust inlet part 35a on the flange 28b of the high-pressure stage exhaust outlet part 25c.
- a support bracket for fixing the low-pressure stage turbocharger 30 to the engine 10 or the like can be omitted or simplified.
- the high-pressure stage turbocharger 20 and the low-pressure stage turbocharger 30 are fixed in a state in which the flange surfaces that are the connection parts are horizontal, so that the low-pressure stage turbo is connected to the connection part from above to below.
- the weight of the charger 30 will be multiplied.
- the high pressure stage exhaust inlet 25 a of the high pressure stage turbocharger 20 is directly connected to the exhaust manifold 14, and the high pressure stage exhaust outlet 25 c of the high pressure stage turbocharger 20 is connected to the low pressure stage exhaust inlet of the low pressure stage turbocharger 30. It is directly connected to the part 35a. Further, the bypass flow path 25d is integrally formed with the high-pressure stage exhaust inlet portion 25a and the high-pressure stage exhaust outlet portion 25c.
- connection between the high-pressure stage turbocharger 20 and the low-pressure stage turbocharger 30 can be made compact, the exhaust passage resistance can be reduced, and the supercharging efficiency of the multistage supercharging device 1 can be effectively improved. Can do.
- the low-pressure stage turbocharger 30 has been described as being supported by the high-pressure stage turbocharger 20 by the flange 38a being mounted and fixed on the upper part of the flange 28b, but the flanges 28b and 38a are omitted.
- the opening of the high-pressure stage exhaust outlet 25c and the opening of the low-pressure stage exhaust inlet 35a may be directly connected. In this case, the same effects as those of the above-described embodiment can be obtained.
- bypass outlet (downstream end) of the bypass channel 25d has been described as being provided on the same flange surface as the flange 28b, it may be provided in the high-pressure stage exhaust outlet 25c.
- the flow rate adjusting valve 45 may be provided in the bypass inlet (upstream end) of the bypass channel 25d or in the bypass channel 25d.
- Multistage turbocharger 10 Engine 14 Exhaust manifold 20 High-pressure turbocharger (first turbocharger) 21 High-pressure turbine (first turbine) 25a High-pressure stage exhaust inlet (first exhaust inlet) 25b High pressure stage turbine housing (first turbine housing) 25c High pressure stage exhaust outlet (first exhaust outlet) 25d Bypass channel 28b Flange (first flange) 30 Low-pressure turbocharger (second turbocharger) 31 Low-pressure turbine (second turbine) 35a Low-pressure stage exhaust inlet (second exhaust inlet) 35b Low-pressure stage turbine housing (second turbine housing) 38a Flange (second flange)
Abstract
Description
10 エンジン
14 排気マニホールド
20 高圧段ターボチャージャ(第1過給機)
21 高圧段タービン(第1タービン)
25a 高圧段排気入口部(第1排気入口部)
25b 高圧段タービン収容部(第1タービン収容部)
25c 高圧段排気出口部(第1排気出口部)
25d バイパス流路
28b フランジ(第1フランジ)
30 低圧段ターボチャージャ(第2過給機)
31 低圧段タービン(第2タービン)
35a 低圧段排気入口部(第2排気入口部)
35b 低圧段タービン収容部(第2タービン収容部)
38a フランジ(第2フランジ)
Claims (4)
- エンジンの排気により駆動される第1過給機と第2過給機とを有する多段過給装置であって、
前記第1過給機は、第1タービンと、前記第1タービンを収容する第1タービン収容部と、前記エンジンの排気マニホールドに直接連結されて該排気マニホールドと前記第1タービン収容部とを連通する第1排気入口部と、前記第1タービン収容部から前記第1タービンの軸方向に延びるとともに、上向きに開口するように上方に向けて屈曲した第1排気出口部とを備え、
前記第2過給機は、第2タービンと、前記第2タービンを収容する第2タービン収容部と、前記第1排気出口部に直接連結されて前記第1排気出口部と前記第2タービン収容部とを連通する第2排気入口部とを備え、
前記第2排気入口部の開口部を前記第1排気出口部の開口部に載置して、前記第2過給機が前記第1過給機により支持される
ことを特徴とする多段過給装置。 - 前記第1排気出口部の開口部に第1フランジが設けられるとともに、前記第2排気入口部の開口部に第2フランジが設けられ、
前記第1フランジと前記第2フランジとが、互いにフランジ面を水平にした状態で直接連結される請求項1記載の多段過給装置。 - 前記第1過給機に、前記第1タービン収容部を迂回して前記第1排気入口部と前記第2排気入口部とを連通するバイパス流路が一体形成される請求項1又は2記載の多段過給装置。
- 前記バイパス流路を流れる排気の流量を調整する流量調整バルブをさらに備える3記載の多段過給装置。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11854412.1A EP2660439B1 (en) | 2010-12-28 | 2011-12-07 | Multi-stage supercharging device |
US13/976,331 US9217394B2 (en) | 2010-12-28 | 2011-12-07 | Multi-stage supercharging apparatus |
AU2011351192A AU2011351192B2 (en) | 2010-12-28 | 2011-12-07 | Multi-stage supercharging apparatus |
CN201180063320.6A CN103282619B (zh) | 2010-12-28 | 2011-12-07 | 多级增压装置 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2010-293713 | 2010-12-28 | ||
JP2010293713A JP5879685B2 (ja) | 2010-12-28 | 2010-12-28 | 多段過給装置 |
Publications (1)
Publication Number | Publication Date |
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WO2012090662A1 true WO2012090662A1 (ja) | 2012-07-05 |
Family
ID=46382781
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/JP2011/078285 WO2012090662A1 (ja) | 2010-12-28 | 2011-12-07 | 多段過給装置 |
Country Status (6)
Country | Link |
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US (1) | US9217394B2 (ja) |
EP (1) | EP2660439B1 (ja) |
JP (1) | JP5879685B2 (ja) |
CN (1) | CN103282619B (ja) |
AU (1) | AU2011351192B2 (ja) |
WO (1) | WO2012090662A1 (ja) |
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JP7270087B2 (ja) * | 2020-09-25 | 2023-05-09 | ヤンマーパワーテクノロジー株式会社 | エンジン装置 |
JP7035146B2 (ja) * | 2020-09-25 | 2022-03-14 | ヤンマーパワーテクノロジー株式会社 | エンジン装置 |
JP7415068B2 (ja) | 2022-03-02 | 2024-01-16 | ヤンマーパワーテクノロジー株式会社 | エンジン装置 |
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Also Published As
Publication number | Publication date |
---|---|
EP2660439A4 (en) | 2014-12-10 |
US20130269341A1 (en) | 2013-10-17 |
EP2660439B1 (en) | 2018-06-20 |
EP2660439A1 (en) | 2013-11-06 |
JP5879685B2 (ja) | 2016-03-08 |
JP2012140890A (ja) | 2012-07-26 |
AU2011351192B2 (en) | 2016-09-15 |
CN103282619B (zh) | 2016-03-09 |
CN103282619A (zh) | 2013-09-04 |
US9217394B2 (en) | 2015-12-22 |
AU2011351192A1 (en) | 2013-07-18 |
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