WO2009104232A1 - ターボチャージャ - Google Patents
ターボチャージャ Download PDFInfo
- Publication number
- WO2009104232A1 WO2009104232A1 PCT/JP2008/003657 JP2008003657W WO2009104232A1 WO 2009104232 A1 WO2009104232 A1 WO 2009104232A1 JP 2008003657 W JP2008003657 W JP 2008003657W WO 2009104232 A1 WO2009104232 A1 WO 2009104232A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- turbine housing
- exhaust nozzle
- peripheral end
- gap
- slit
- Prior art date
Links
- 238000007789 sealing Methods 0.000 claims abstract description 34
- 238000013459 approach Methods 0.000 claims abstract description 22
- 230000002093 peripheral effect Effects 0.000 claims description 41
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
-
- 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
- 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
- F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
Definitions
- the present invention relates to a turbocharger configured to prevent gas from leaking from a high pressure side to a low pressure side through a gap between a turbine housing and an exhaust nozzle.
- FIG. 1 shows an example of a conventional variable capacity turbocharger to which the present invention is applied.
- a turbine housing 1 and a compressor housing 2 are integrally assembled by fastening bolts 3 a and 3 b via a bearing housing 3, and a turbine impeller 4 disposed in the turbine housing 1 and an inside of the compressor housing 2 are assembled.
- a compressor impeller 5 disposed on the turbine housing 7 is connected to a bearing housing 3 by a turbine shaft 7 rotatably supported via a bearing 6.
- an exhaust nozzle 9 for introducing fluid (exhaust gas) introduced into the scroll passage 8 of the turbine housing 1 to the turbine impeller 4. is provided.
- the exhaust nozzle 9 is integrated by, for example, fixing members 12 provided at three locations in the circumferential direction in a state where a front exhaust introduction wall 10 on the bearing housing 3 side and a rear exhaust introduction wall 11 on the turbine housing 1 side maintain a predetermined interval. Is assembled. Further, a mounting member 13 is fixed to the front surface (side surface of the bearing housing 3) of the front exhaust introduction wall 10, and when the turbine housing 1 and the bearing housing 3 are assembled, the mounting member 13 is connected to the turbine housing 1 and the bearing. The exhaust nozzle 9 is fixed by being sandwiched between the housing 3. Further, the exhaust nozzle 9 is positioned with respect to the bearing housing 3 by the positioning pins 14 during the assembly.
- a plurality of nozzle vanes 15 are annularly arranged between the front exhaust introduction wall 10 and the rear exhaust introduction wall 11, and each nozzle vane 15 is forwardly moved by a vane shaft 16 a penetrating at least the front exhaust introduction wall 10.
- the exhaust introduction wall 10 is rotatably supported.
- vane shafts 16a and 16b fixed on both sides of the nozzle vane 15 pass through the front exhaust introduction wall 10 and the rear exhaust introduction wall 11, respectively, and each nozzle vane 15 is supported by both ends. In this case, only the vane shaft 16a passes through the front exhaust introduction wall 10 and the nozzle vane 15 is supported in a cantilever manner.
- 17a, 17b, 17c and 17d are link-type transmission mechanisms for adjusting the opening / closing angle of the nozzle vane 15, and 18 is a scroll passage formed in the compressor housing 2.
- a gap 19 is provided between the turbine housing 1 and the rear exhaust introduction wall 11 of the exhaust nozzle 9.
- the gap 19 is originally unnecessary, but is provided because the turbine housing 1 is thermally deformed between a cold time and a hot time, and there is a variation in accuracy among assembled parts. ing.
- an annular concave groove 22 is provided on the outer peripheral surface of the extending portion 11 ′ of the rear exhaust introduction wall 11, and normally two sealing piston rings 21 are provided in the concave groove 22.
- the sealing device 23 is configured by shifting the positions so that the joints (notches) do not overlap, and the outer peripheral surface of the sealing piston ring 21 is pressed against the inner surface 1 ′ of the turbine housing 1 by elastic force. This prevents gas leaks.
- the sealing piston ring 21 has a predetermined resilience and is required to have a high strength in terms of a structure to be sealed by being pressed against the inner surface 1 ′ of the turbine housing 1. If the roundness of the sealing piston ring 21 is slightly out of order even if the inner surface 1 ′ of the turbine is machined with high roundness, there is a gap between the inner surface 1 ′ of the turbine housing 1 and the sealing piston ring 21. There is a problem that a gap is formed, which causes gas to leak from the outer peripheral portion of the sealing piston ring 21.
- the present invention has been made in view of the above circumstances, and has a simple configuration that can effectively prevent gas from leaking from the high pressure side to the low pressure side through a gap between the turbine housing and the exhaust nozzle. It is intended to provide a turbocharger.
- the present invention relates to an exhaust nozzle disposed between a scroll passage of a turbine housing and a turbine impeller, a gap formed between a rear surface of the exhaust nozzle and the turbine housing, and a seal device for closing the gap.
- the sealing device includes a sealing member having a shape in which one annular portion is cut out by a slit, and an inner peripheral end disposed along the turbine housing, and the sealing member Has a configuration in which the diameter is reduced so that the outer peripheral end approaches the rear surface of the exhaust nozzle, the slit ends approach each other, and the inner peripheral end approaches the turbine housing due to the gas pressure of the scroll passage. It is characterized by.
- the slit is formed so that a distance on an outer peripheral end side is larger than an inner peripheral end side.
- the seal member has a substantially conical shape having a truncated cone whose diameter gradually increases from the turbine housing side toward the exhaust nozzle side.
- the seal member when the inner peripheral end of the seal member is disposed along the step portion formed in the turbine housing, the seal member receives the action of the gas pressure of the scroll passage and the outer peripheral end is the rear surface of the exhaust nozzle. And the diameter of the seal member is reduced so that the slit ends approach each other and the inner peripheral end approaches the stepped portion due to the pressure difference between the gas pressure in the scroll passage and the pressure in the gap. Therefore, it is possible to achieve an excellent effect that the gap between the turbine housing and the rear surface of the exhaust nozzle can be closed with a high sealing property with a simple configuration.
- FIG. 2 is a cut side view of the vicinity of a nozzle portion in FIG. 1. It is a cutting side view near the nozzle part which shows one example of the present invention.
- FIG. 4 is a cut side view showing an example in which the support method for supporting the nozzle vanes of the exhaust nozzle is different from FIG. 3. It is a front view of the sealing member in FIG. 3, FIG. It is a front view which shows the example of a shape of the slit in the sealing member of FIG. It is a cutting
- FIG. 8 is a cut side view in the vicinity of a nozzle portion showing a modification of FIG. 7.
- FIG. 3 shows an embodiment of the present invention applied to the turbocharger of FIGS. 1 and 2, and the gas in the scroll passage 8 is formed between the turbine housing 1 and the rear surface 24 of the exhaust nozzle 9.
- a seal device 25 is provided between the turbine housing 1 and the rear surface 24 of the exhaust nozzle 9.
- vane shafts 16a and 16b fixed on both sides of the nozzle vane 15 pass through the front exhaust introduction wall 10 and the rear exhaust introduction wall 11, respectively, and the exhaust nozzle 9 in which each nozzle vane 15 is supported on both ends.
- the sealing device 25 can be applied to a turbocharger having the exhaust nozzle 9.
- the sealing device 25 is provided with a cylindrical step portion 27 parallel to the turbine shaft at an outer peripheral position of a portion 26 where the turbine housing 1 faces the rear surface 24 of the exhaust nozzle 9 and forms a gap 19.
- a sealing member 29 is arranged so that the inner peripheral end 28 is fitted to the stepped portion 27.
- the seal member 29 is made of a thin metal plate having a substantially frustoconical shape, and one shape in the circumferential direction is cut by a slit 30 having a width of about 0.2 to 0.8 mm (C-shape).
- the inner peripheral end 28 of the seal member 29 is bent in a direction away from the exhaust nozzle 9 as shown in FIGS. 3 and 4, and is fitted to the stepped portion 27.
- the outer peripheral end 33 of the seal member 29 is in close contact with the rear surface 24 of the exhaust nozzle 9 and the conical linear portion 31 whose diameter is expanded from the inner peripheral end 28 toward the outer peripheral end of the rear surface 24 of the exhaust nozzle 9. And a curved portion 32 that is bent.
- the inner peripheral end 28 of the seal member 29 is fitted to the stepped portion 27 with a slight gap so as to be moved in the axial direction by the gas pressure in the scroll passage 8, and the seal member 29 is formed to have a deformation strength (thickness) in which the slit end portions 29a and 29b approach each other by the gas pressure in the scroll passage 8 and the diameter is reduced.
- the gas pressure of the scroll passage 8 acts on the seal member 29.
- the pressure of the slit 30 portion communicating with the gap 19 is lower than the gas pressure of the scroll passage 8. It has become.
- the slit end portions 29a and 29b receive forces attracted to each other and approach each other, and the inner peripheral end 28 is also a stepped portion. 27, so that the diameter of the seal member 29 is reduced.
- the operation is as follows.
- the seal member 29 arranged in the turbine housing 1 as shown in FIGS. 3 and 4 is pushed in the A direction by the gas pressure in the scroll passage 8 (the differential pressure between the pressure in the scroll flow path 8 and the pressure in the gap 19).
- the curved portion 32 of the outer peripheral end 33 of the seal member 29 is brought into close contact with the rear surface 24 of the rear exhaust introduction wall 11 in the exhaust nozzle 9.
- the space between the seal nozzle 29 and the exhaust nozzle 9 is closed, and the slit ends 29a and 29b of the seal member 29 approach each other.
- the clearance 19 between the turbine housing 1 and the exhaust nozzle 9 can be highly sealed with a simple configuration. Can be closed.
- the gap S2 on the outer peripheral end 33 side is made larger than the gap S1 on the inner peripheral end 28 side of the slit 30, the diameter of the seal member 29 is reduced. Since the slit end portions 29a and 29b come close to each other so as to be in close contact with each other, the sealing performance at the slit 30 portion can be further enhanced.
- FIG. 7 shows another embodiment of the present invention.
- a seal member 29 having a C-shape has a substantially L-shaped cross section, and the outer peripheral end 33 is formed at the exhaust nozzle 9 by the action of the gas pressure in the scroll passage 8. 5, and the slit end portions 29 a and 29 b approach each other and the inner peripheral end 28 approaches the stepped portion 27 formed in the turbine housing 1 as shown in FIG. 5. The diameter is reduced. Also in the shape of the seal member 29 in FIG. 7, it is possible to reduce leakage of exhaust gas through the gap 19 by closing the gap 19 using the pressure of the exhaust gas in the scroll passage 8. In the embodiment shown in FIG.
- a projecting portion 35 is provided so as to form an introduction interval 34 from the turbine housing 1 to the outer periphery of the rear exhaust introduction wall 11, and an introduction chamber 36 communicating with the introduction interval 34 is provided.
- a step portion 27 is formed by being provided in the turbine housing 1, and the seal member 29 is disposed on the step portion 27. Therefore, according to the shape of FIG. 7, the exhaust gas from the scroll passage 8 is stably guided to the exhaust nozzle 9 by the overhanging portion 35.
- the seal member 29 having a C-shape has an inner peripheral end 28 extending in the rear radial direction extending in the direction of the exhaust nozzle 9 along the step portion 27, and subsequently parallel to the turbine shaft.
- the outer peripheral end 33 may extend in the direction of the exhaust nozzle 9 and may be formed in a step shape so as to approach the rear surface of the rear exhaust introduction wall 11 in the exhaust nozzle 9, and may have various other shapes.
- the sealing member 29 can have a very simple configuration, it can be manufactured at a low price and with high productivity.
- the pressure in the gap 19 downstream of the seal member 29 is lower than the pressure of the exhaust gas passing through the exhaust nozzle 9, so that the exhaust gas in the exhaust nozzle 9 passes through the through hole 16 'of the vane shaft 16b.
- the nozzle vane 15 is pushed to the rear exhaust introduction wall 11 side and displaced by the pressure difference between the pressure inside the exhaust nozzle 9 and the pressure in the gap 19 to the vane shaft 16b.
- the provided gutter 16 ′′ is pressed against the rear exhaust introduction wall 11 so as to block the through hole 16 ′, whereby the gas of the exhaust nozzle 9 flows into the gap 19 through the through hole 16 ′ of the vane shaft 16b. To the to prevent thereby enhancing the sealing property.
- this invention is not limited only to the said Example, Of course, a various change can be added in the range which does not deviate from the summary of this invention.
- the present invention is configured such that the diameter is reduced so that the outer peripheral end approaches the rear surface of the exhaust nozzle, the slit ends approach each other, and the inner peripheral end approaches the turbine housing by the action of the gas pressure in the scroll passage.
- the sealing member can be provided in the turbocharger and used when enhancing the sealing performance of the turbocharger.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
Description
4 タービンインペラ
8 スクロール通路
9 排気ノズル
19 隙間
25 シール装置
28 内周端
29 シール部材
29a,29b スリット端部
30 スリット
33 外周端
図3は、図1、図2のターボチャージャに適用した本発明の一実施例を示すもので、スクロール通路8のガスが、タービンハウジング1と排気ノズル9の後面24との間に形成される隙間19を通してタービンインペラ4側に漏出するのを防止するために、タービンハウジング1と排気ノズル9の後面24との間にシール装置25を設けている。
Claims (3)
- タービンハウジングのスクロール通路とタービンインペラとの間に配置される排気ノズルと、該排気ノズルの後面と前記タービンハウジングとの間に形成される隙間と、該隙間を閉塞するシール装置とを有するターボチャージャであって、前記シール装置は、環状の一個所がスリットで切り取られた形状を有して内周端が前記タービンハウジングに沿って配置されたシール部材を有し、該シール部材は、スクロール通路のガス圧の作用により外周端が排気ノズルの後面に接近し、且つスリット端部が互いに接近すると共に内周端が前記タービンハウジングに接近するように径が縮小する構成としたことを特徴とするターボチャージャ。
- 前記スリットは、内周端側に対して外周端側の間隔が大きくなるように形成されていることを特徴とする、請求項1に記載のターボチャージャ。
- 前記シール部材は、タービンハウジング側から排気ノズル側に向かうに従い次第に径が大きくなる略截頭円錐形状を有することを特徴とする、請求項1又は2に記載のターボチャージャ。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/863,055 US20100310365A1 (en) | 2008-02-20 | 2008-12-09 | Turbocharger |
KR1020107016526A KR101182121B1 (ko) | 2008-02-20 | 2008-12-09 | 터보 챠저 |
CN2008801271304A CN101946069B (zh) | 2008-02-20 | 2008-12-09 | 涡轮增压器 |
EP08872563A EP2243939A4 (en) | 2008-02-20 | 2008-12-09 | TURBO |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2008038423A JP2009197633A (ja) | 2008-02-20 | 2008-02-20 | ターボチャージャ |
JP2008-038423 | 2008-02-20 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009104232A1 true WO2009104232A1 (ja) | 2009-08-27 |
Family
ID=40985127
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2008/003657 WO2009104232A1 (ja) | 2008-02-20 | 2008-12-09 | ターボチャージャ |
Country Status (6)
Country | Link |
---|---|
US (1) | US20100310365A1 (ja) |
EP (1) | EP2243939A4 (ja) |
JP (1) | JP2009197633A (ja) |
KR (1) | KR101182121B1 (ja) |
CN (1) | CN101946069B (ja) |
WO (1) | WO2009104232A1 (ja) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011093075A1 (ja) * | 2010-01-29 | 2011-08-04 | 株式会社Ihi | ターボチャージャのシール装置 |
CN102762838A (zh) * | 2010-02-25 | 2012-10-31 | 株式会社Ihi | 可变容量式涡轮增压器 |
WO2018168931A1 (ja) * | 2017-03-17 | 2018-09-20 | 株式会社Ihi | 可変ノズルユニットのシール構造および可変容量型過給機 |
US11459907B2 (en) | 2018-10-18 | 2022-10-04 | Ihi Corporation | Variable capacity turbocharger |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201105726D0 (en) * | 2011-04-04 | 2011-05-18 | Cummins Ltd | A turbine |
JP5849445B2 (ja) * | 2011-06-13 | 2016-01-27 | 株式会社Ihi | 可変ノズルユニット及び可変容量型過給機 |
DE102011108195B4 (de) * | 2011-07-20 | 2022-10-27 | Ihi Charging Systems International Gmbh | Turbine für einen Abgasturbolader |
US8763393B2 (en) | 2011-08-08 | 2014-07-01 | Honeywell International Inc. | Sealing arrangement between a variable-nozzle assembly and a turbine housing of a turbocharger |
DE102011081187A1 (de) * | 2011-08-18 | 2013-02-21 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Variable Turbinen-/Verdichtergeometrie |
DE102012206302A1 (de) | 2011-08-18 | 2013-02-21 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Variable Turbinen-/Verdichtergeometrie |
US8820072B2 (en) * | 2011-08-23 | 2014-09-02 | Honeywell International Inc. | Compressor diffuser plate |
DE102011111702A1 (de) | 2011-08-24 | 2013-02-28 | Ihi Charging Systems International Gmbh | Turbine für einen Abgasturbolader |
DE102012006711A1 (de) * | 2012-01-18 | 2013-07-18 | Ihi Charging Systems International Gmbh | Abgasturbolader |
CN103375197B (zh) * | 2012-04-17 | 2016-12-07 | 博世马勒涡轮系统有限两合公司 | 可变涡轮/压缩机几何结构 |
US9353637B2 (en) | 2012-05-11 | 2016-05-31 | Honeywell International Inc. | Turbine exhaust housing |
US9011089B2 (en) | 2012-05-11 | 2015-04-21 | Honeywell International Inc. | Expansion seal |
JP5949164B2 (ja) * | 2012-05-29 | 2016-07-06 | 株式会社Ihi | 可変ノズルユニット及び可変容量型過給機 |
JP5966786B2 (ja) | 2012-09-10 | 2016-08-10 | 株式会社Ihi | 可変容量型過給機 |
US9556880B2 (en) | 2013-06-26 | 2017-01-31 | Honeywell International Inc. | Turbine exhaust seal |
RU154639U1 (ru) * | 2013-07-09 | 2015-08-27 | ФОРД ГЛОУБАЛ ТЕКНОЛОДЖИЗ, ЭлЭлСи | Двигатель внутреннего сгорания с наддувом |
US10240480B2 (en) * | 2014-11-21 | 2019-03-26 | Borgwarner Inc. | Variable turbine geometry vane with single-axle, self-centering pivot feature |
US10087940B2 (en) | 2014-12-10 | 2018-10-02 | Honeywell International Inc. | Exhaust turbine assembly |
US10550705B2 (en) | 2014-12-10 | 2020-02-04 | Garrett Transportation I Inc. | Turbine exhaust seal |
EP3299634B1 (en) * | 2015-10-29 | 2020-02-26 | Mitsubishi Heavy Industries, Ltd. | Scroll casing and centrifugal compressor |
EP3388686B1 (en) * | 2016-01-20 | 2020-07-15 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Stationary-blade-type rotating machine |
CN112096514B (zh) * | 2016-08-24 | 2022-05-31 | 株式会社Ihi | 可变容量型增压器 |
US11136900B2 (en) * | 2017-12-20 | 2021-10-05 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Turbine and turbocharger |
US10746099B1 (en) * | 2019-04-03 | 2020-08-18 | GM Global Technology Operations LLC | Multi-step bore turbocharger |
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JPH0712765U (ja) * | 1993-06-30 | 1995-03-03 | ヤンマーディーゼル株式会社 | 回転蓄熱式熱交換器のシール装置 |
JP2000265845A (ja) * | 1999-03-11 | 2000-09-26 | Ishikawajima Harima Heavy Ind Co Ltd | 可変容量型過給機のガスシール装置 |
JP2006125588A (ja) | 2004-11-01 | 2006-05-18 | Ishikawajima Harima Heavy Ind Co Ltd | 過給機および密封装置 |
JP2006220053A (ja) * | 2005-02-10 | 2006-08-24 | Mitsubishi Heavy Ind Ltd | 可変容量型排気ターボ過給機のスクロール構造及びその製造方法 |
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GB2102897B (en) * | 1981-07-27 | 1985-06-19 | Gen Electric | Annular seals |
US5303592A (en) * | 1991-12-05 | 1994-04-19 | Livingston Waylon A | Method and apparatus for coiled tubing inspection |
DE19703033A1 (de) * | 1997-01-29 | 1998-07-30 | Asea Brown Boveri | Abgasturbine eines Turboladers |
US6076835A (en) * | 1997-05-21 | 2000-06-20 | Allison Advanced Development Company | Interstage van seal apparatus |
US6199871B1 (en) * | 1998-09-02 | 2001-03-13 | General Electric Company | High excursion ring seal |
DE102004039473A1 (de) * | 2004-08-14 | 2006-03-23 | Ihi Charging Systems International Gmbh | Dichtung |
EP1672177B1 (de) * | 2004-12-14 | 2011-11-23 | BorgWarner, Inc. | Turbolader |
GB0505186D0 (en) * | 2005-03-14 | 2005-04-20 | Cross Mfg 1938 Company Ltd | Improvements to a retaining ring |
JP4035140B2 (ja) * | 2005-07-22 | 2008-01-16 | 川崎重工業株式会社 | タービンロータのシールリング |
EP1816317B1 (en) * | 2006-02-02 | 2013-06-12 | IHI Corporation | Turbocharger with variable nozzle |
US7559199B2 (en) * | 2006-09-22 | 2009-07-14 | Honeywell International Inc. | Variable-nozzle cartridge for a turbocharger |
JP4952558B2 (ja) * | 2007-12-12 | 2012-06-13 | 株式会社Ihi | ターボチャージャ |
-
2008
- 2008-02-20 JP JP2008038423A patent/JP2009197633A/ja not_active Withdrawn
- 2008-12-09 CN CN2008801271304A patent/CN101946069B/zh not_active Expired - Fee Related
- 2008-12-09 WO PCT/JP2008/003657 patent/WO2009104232A1/ja active Application Filing
- 2008-12-09 KR KR1020107016526A patent/KR101182121B1/ko active IP Right Grant
- 2008-12-09 EP EP08872563A patent/EP2243939A4/en not_active Withdrawn
- 2008-12-09 US US12/863,055 patent/US20100310365A1/en not_active Abandoned
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Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
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WO2011093075A1 (ja) * | 2010-01-29 | 2011-08-04 | 株式会社Ihi | ターボチャージャのシール装置 |
JP2011157841A (ja) * | 2010-01-29 | 2011-08-18 | Ihi Corp | ターボチャージャのシール装置 |
CN102713198A (zh) * | 2010-01-29 | 2012-10-03 | 株式会社Ihi | 涡轮增压器的密封装置 |
US9074687B2 (en) | 2010-01-29 | 2015-07-07 | Ihi Corporation | Sealing device for turbocharger |
CN102762838A (zh) * | 2010-02-25 | 2012-10-31 | 株式会社Ihi | 可变容量式涡轮增压器 |
WO2018168931A1 (ja) * | 2017-03-17 | 2018-09-20 | 株式会社Ihi | 可変ノズルユニットのシール構造および可変容量型過給機 |
JPWO2018168931A1 (ja) * | 2017-03-17 | 2019-06-27 | 株式会社Ihi | 可変ノズルユニットのシール構造および可変容量型過給機 |
US11326615B2 (en) | 2017-03-17 | 2022-05-10 | Ihi Corporation | Seal structure of variable nozzle unit, and variable capacity type turbocharger |
US11459907B2 (en) | 2018-10-18 | 2022-10-04 | Ihi Corporation | Variable capacity turbocharger |
Also Published As
Publication number | Publication date |
---|---|
EP2243939A1 (en) | 2010-10-27 |
US20100310365A1 (en) | 2010-12-09 |
EP2243939A4 (en) | 2011-08-03 |
JP2009197633A (ja) | 2009-09-03 |
CN101946069B (zh) | 2012-07-18 |
CN101946069A (zh) | 2011-01-12 |
KR20100093617A (ko) | 2010-08-25 |
KR101182121B1 (ko) | 2012-09-13 |
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