WO2013089158A1 - Carter d'entrée d'échappement pour turbocompresseur - Google Patents

Carter d'entrée d'échappement pour turbocompresseur Download PDF

Info

Publication number
WO2013089158A1
WO2013089158A1 PCT/JP2012/082257 JP2012082257W WO2013089158A1 WO 2013089158 A1 WO2013089158 A1 WO 2013089158A1 JP 2012082257 W JP2012082257 W JP 2012082257W WO 2013089158 A1 WO2013089158 A1 WO 2013089158A1
Authority
WO
WIPO (PCT)
Prior art keywords
exhaust gas
exhaust
turbocharger
turbine
casing
Prior art date
Application number
PCT/JP2012/082257
Other languages
English (en)
Japanese (ja)
Inventor
白石　啓一
伊藤　仁一
Original Assignee
三菱重工業株式会社
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 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Publication of WO2013089158A1 publication Critical patent/WO2013089158A1/fr

Links

Images

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
    • F02B37/12—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
    • 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
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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 present invention relates to, for example, an exhaust inlet casing of a turbocharger (also referred to as “exhaust turbine turbocharger") used in combination with a (large) internal combustion engine such as a marine internal combustion engine or a power generation internal combustion engine. is there.
  • a turbocharger also referred to as "exhaust turbine turbocharger”
  • a (large) internal combustion engine such as a marine internal combustion engine or a power generation internal combustion engine.
  • the supercharger pressure of the turbocharger mounted on the internal combustion engines is set high, and the load on the internal combustion engines is high.
  • a so-called exhaust gas bypass system is put into practical use, in which the exhaust gas bypasses the supercharger to suppress an increase in supercharging pressure (see, for example, Patent Document 1). ).
  • the exhaust gas bypass system currently put to practical use is, as shown in FIG. 1 of Patent Document 1, connected at one end to the middle of the exhaust pipe L1 or directly connected to the exhaust manifold 7, and the other end is an exhaust pipe.
  • the bypass pipe L2 has to be routed around the engine room where space is limited.
  • the exhaust gas bypass system can not be applied to a ship which can not secure a space necessary to draw the bypass pipe L2.
  • a large-scale piping work must be performed to draw the bypass pipe L2 in the engine room, and there is a problem that the cost is not sufficient. .
  • the present invention has been made in view of the above circumstances, and an object thereof is to provide an exhaust inlet casing of a turbocharger capable of enabling application of an exhaust gas bypass system without conducting bypass pipe routing. I assume.
  • An exhaust inlet casing of a turbocharger according to a first aspect of the present invention is a turbocharger for compressing combustion air of an internal combustion engine and forcibly feeding high density air into a combustion chamber of the internal combustion engine.
  • An exhaust inlet casing wherein a separate inner casing and an outer casing are integrally joined together to form a space between the two casings, and an exhaust gas flow passage for guiding exhaust gas discharged from the internal combustion engine to a turbine nozzle
  • the exhaust gas is configured to be configured to guide exhaust gas branched off in the middle of the exhaust gas flow path to the downstream side in the exhaust gas flow of the gas guide cylinder attached to the end portion on the gas outlet side of the turbine nozzle A bypass flow path is provided.
  • a part (about 4 to 20%) of the exhaust gas introduced from the gas inlet of the exhaust inlet casing has a turbine nozzle and a turbine blade.
  • the gas guide cylinder attached to the end of the turbine nozzle on the gas outlet side is led to the downstream side of the exhaust gas flow. This enables the application of the exhaust gas bypass system without the need for the conventionally required bypass pipe routing.
  • the exhaust gas bypass channel is separated from the exhaust gas channel by a partition forming the inner casing, and the exhaust gas.
  • An exhaust gas pipe communicating the middle of a gas flow path with the exhaust gas bypass chamber, and the exhaust gas bypass chamber provided on the outer casing, the exhaust gas flow downstream side of the gas guide cylinder And a communicating exhaust gas bypass passage may be provided.
  • an open / close valve may be connected to the exhaust gas pipe.
  • the on-off valve is closed and the exhaust introduced from the gas inlet of the exhaust inlet casing The entire amount of gas will be led to the gas outlet of the exhaust inlet casing through the exhaust gas flow path.
  • the on-off valve is opened, and the majority (about 96 to 80%) of the exhaust gas introduced from the gas inlet of the exhaust inlet casing A portion (about 4 to 20%) of the exhaust gas introduced to the gas outlet through the gas flow path and introduced from the gas inlet of the exhaust inlet casing does not pass through the turbine nozzle and the turbine blade, and the exhaust gas bypass Through the chamber, the exhaust gas bypass passage, the gas guide cylinder attached to the end of the turbine nozzle on the gas outlet side is led to the downstream side in the exhaust gas flow. This enables the application of the exhaust gas bypass system without the need for the conventionally required bypass pipe routing.
  • a turbine side assembly of a turbocharger comprises a gas guide cylinder attached to an exhaust inlet casing of any one of the above turbochargers and an end portion on the gas outlet side of the turbine nozzle.
  • the gas guiding cylinder is provided with a through hole for penetrating the exhaust gas flowing out from the exhaust gas bypass passage through the gas guiding cylinder to the downstream side of the exhaust gas flow of the gas guiding cylinder.
  • a part (about 4 to 20%) of the exhaust gas introduced from the gas inlet of the exhaust inlet casing passes through the turbine nozzle and the turbine blade. Without passing through the exhaust gas bypass chamber, the exhaust gas bypass passage, and the through hole, the gas guide cylinder attached to the end on the gas outlet side of the turbine nozzle is led to the downstream side in the exhaust gas flow .
  • This enables the application of the exhaust gas bypass system without the need for the conventionally required bypass pipe routing.
  • a turbocharger according to a third aspect of the present invention includes the exhaust inlet casing of any of the above-described turbochargers.
  • a part (about 4 to 20%) of the exhaust gas introduced from the gas inlet of the exhaust inlet casing does not pass through the turbine nozzle and the turbine blade, Through the gas bypass flow path, the gas guide cylinder attached to the end on the gas outlet side of the turbine nozzle is led to the downstream side in the exhaust gas flow. This enables the application of the exhaust gas bypass system without the need for the conventionally required bypass pipe routing.
  • a turbocharger according to a fourth aspect of the present invention includes the turbine side assembly of the turbocharger.
  • a part (about 4 to 20%) of the exhaust gas introduced from the gas inlet of the exhaust inlet casing does not pass through the turbine nozzle and the turbine blade, Through the gas bypass flow path, the gas guide cylinder attached to the end on the gas outlet side of the turbine nozzle is led to the downstream side in the exhaust gas flow. This enables the application of the exhaust gas bypass system without the need for the conventionally required bypass pipe routing.
  • the exhaust inlet casing of the turbocharger According to the exhaust inlet casing of the turbocharger according to the present invention, a part (about 4 to 20%) of the exhaust gas introduced from the gas inlet of the exhaust inlet casing does not pass through the turbine nozzle and the turbine blade.
  • the gas guide cylinder attached to the end of the turbine nozzle on the gas outlet side is led to the downstream side in the exhaust gas flow. This has the effect that the application of the exhaust gas bypass system can be enabled without conducting the conventionally required bypass pipe routing.
  • FIG. 1 is a longitudinal sectional view of a turbine side showing a state where an exhaust inlet casing of a turbocharger according to the present embodiment is attached to the turbocharger
  • FIG. 2 is one on the turbine side of the turbocharger shown in FIG. It is the figure which notched the part and was bird's-eye view.
  • the exhaust inlet casing 10 of the turbocharger according to the present embodiment can be applied to, for example, a turbocharger 1 as shown in FIG.
  • the turbocharger 1 compresses combustion air for a (large-size) internal combustion engine (not shown) such as, for example, a marine internal combustion engine or a power generation internal combustion engine, and internal combustion of high density air. It is configured to be forcibly fed into a combustion chamber (not shown) of the engine.
  • the turbocharger 1 has a turbine 2 driven by exhaust gas discharged from an internal combustion engine, a rotor shaft (rotation shaft) 3 rotationally driven by the turbine 2, and rotation driving of the rotor shaft 3 to drive air.
  • a compressor (not shown) for compression and a bearing stand (not shown) provided between the turbine 2 and the compressor and bearing-supporting the rotor shaft 3 are provided.
  • the part shown by grid-like hatching in FIG. 1 is the heat insulating material 11 installed for the purpose of heat insulation and soundproofing.
  • the turbine 2 includes a turbine blade 4 rotationally driven by exhaust gas discharged from an internal combustion engine, a turbine nozzle 5 for guiding the exhaust gas to the turbine blade 4, and an exhaust inlet casing 10.
  • the turbine moving blade 4 is provided along the circumferential direction on the peripheral portion of the disk-shaped turbine disk 6 provided at one end of the rotor shaft 3 so as to be close to the downstream side which is the outlet of the turbine nozzle 5 Multiple pieces are attached. Then, the high temperature exhaust gas ejected from the turbine nozzle 5 passes through the turbine moving blade 4 and is expanded, whereby the turbine disk 6 and the rotor shaft 3 rotate.
  • the turbine nozzle 5 is disposed on a plurality of nozzle guide vanes 5a annularly disposed along the circumferential direction and at the root side (radially inward: inner circumferential side) of the nozzle guide vanes 5a.
  • the ring-shaped inner peripheral member 5b joined to the root and the blade end side (radial direction outer side: outer peripheral side) of the nozzle guide vane 5a are joined to the blade end of the nozzle guide vane 5a
  • a ring-shaped outer peripheral side member 5c which is generally called a nozzle ring, and is disposed to be close to the upstream side of the turbine moving blade 4.
  • the outer peripheral side member 5c is formed to expand in a trumpet shape from the gas outlet side (the downstream side of the exhaust gas flow) to the gas inlet side (the upstream side of the exhaust gas flow). Further, the end portion of the exhaust inlet casing 10 (more specifically, the outer casing 22) on the turbine disk 6 side is formed so that the inner peripheral surface of the exhaust inlet casing 10 is bent in the direction of the turbine disk 6 A stepped portion 12 is provided. And this level
  • a gas guide cylinder 7 is connected to an end of the outer peripheral side member 5c which is the gas outlet side (the downstream side of the exhaust gas flow).
  • the connection portion between the outer peripheral side member 5c and the gas guide cylinder 7 has an inlay structure in which the end portions thereof are fitted to each other.
  • the exhaust inlet casing 10 separate inner casing 21 and outer casing 22 are integrated by fastening means (for example, bolts 23), and a space formed between the inner casing 21 and the outer casing 22 is exhaust.
  • the exhaust gas flow path (main exhaust gas flow path) 26 for guiding the gas to the turbine nozzle 5 is configured.
  • the exhaust gas flow path 26 is formed over the entire circumference of the turbine rotor 4 in the rotational direction, and the arrow Gi in FIG. 1 from the gas inlet 10 a of the exhaust inlet casing 10.
  • the exhaust gas introduced as shown in FIG. 1 is discharged from the outlet of the exhaust outlet casing 28 to the outside as shown by the arrow Go in FIG. Ru.
  • the gas outlet 10 b is provided so as to open the exhaust gas to the turbine nozzle 5 all around the rotational direction of the turbine bucket 4.
  • one end of the inner casing 21 (the end on the right in FIG. 1) is a fastening means (for example, the end on the right in the FIG. It is fixed and supported by a bolt 23). That is, the inner casing 21 has a flange surface 21a formed at the end of the casing on the right side of the drawing, which is the opposite side of the turbine disk 6, and a flange surface 22a of the outer casing 22 formed opposite to the flange surface 21a. In an overlapping state, and in this state, the fastening means (for example, bolt 23) is fixed and supported by tightening.
  • Each of the flange surfaces 21 a and 22 a is a surface orthogonal to the axial direction of the rotor shaft 3 that rotates integrally with the turbine disk 6.
  • the inner peripheral side member 5b forming the turbine nozzle 5 is coupled (attached) There is.
  • the inner casing 21 and the outer casing 22 are integrated via a fastening means (for example, a bolt 23), whereby the exhaust at the one end (the right end in FIG. 1) of the exhaust inlet casing 10 is exhausted.
  • An exhaust gas bypass chamber 32 for guiding the exhaust gas branched in the middle of the gas flow path 26 to an exhaust gas bypass passage 22 b formed inside the outer casing 22 is formed in a part of the turbine rotor 4 in the rotational direction. ing.
  • the exhaust gas bypass chamber 32 is provided on the side of one end (the end on the right side in FIG. 1) of the exhaust gas flow channel 26, and the exhaust gas flow channel 26 and the exhaust gas bypass chamber 32 form the inner casing 21. It is divided by the partition 34 to form.
  • an on-off valve for example, a butterfly valve
  • the exhaust gas bypass passage 22b is provided parallel to the axial direction of the rotor shaft 3 that rotates integrally with the turbine disk 6, and one end thereof (upstream end in the flow direction of the exhaust gas) is an exhaust gas bypass
  • the exhaust gas bypass chamber 32 is opened at the radially outer side (outer peripheral side) of the chamber 32.
  • the other end (the downstream end in the flow direction of the exhaust gas) of the exhaust gas bypass passage 22b is the other end surface 22c forming the other end (the end on the left side in FIG. 1) of the outer casing 22;
  • the space S1 and the space S2 formed on the radially outer side (outer peripheral side) of the gas guide cylinder 7 in the exhaust outlet casing 28 have a surface 7a and the other surface 7b located on the opposite side in the thickness direction It communicates through the through-hole 48 penetrated. That is, the exhaust gas bypass chamber 32 and the space S2 communicate with each other via the exhaust gas bypass passage 22b, the space S1, and the through hole 48.
  • the entire amount of exhaust gas introduced from the gas inlet 10a of the exhaust inlet casing 10 is conducted to the gas outlet 10b through the exhaust gas flow path 26. It is eaten.
  • the exhaust gas led to the gas outlet 10 b is led from the gas outlet 10 b to the turbine nozzle 5, passes through the turbine nozzle 5, is then led out from the downstream side of the turbine nozzle 5, and is led over the entire turbine rotor blade 4. It will be.
  • the exhaust gas thus introduced to the entire turbine moving blade 4 expands as it passes through the turbine moving blade 4 and rotates the turbine disk 6 and the rotor shaft 3.
  • the exhaust gas guided to the exhaust gas bypass chamber 32 is guided to the space S2 through the exhaust gas bypass passage 22b, the space S1, and the through hole 48, and is expanded as it passes through the turbine rotor 4 and is expanded to the turbine disk 6 And the exhaust gas used to rotate the rotor shaft 3, the exhaust gas is exhausted from the outlet of the exhaust outlet casing 28 to the outside.
  • the air compressed by the compressor is sucked through a filter (not shown), and the exhaust gas expanded by the turbine rotor 4 is guided to the gas outlet guide cylinder 7 and the gas outlet casing 28, and the turbine nozzle 5 is And without passing through the turbine blade 4 (as bypassing the turbine nozzle 5 and the turbine blade) together with the exhaust gas led to the space S2 to the outside.
  • the pressure of air delivered (discharged) from the compressor or the pressure of air supplied to the combustion chamber of the internal combustion engine is lower than 0.2 MPa (2 bar) in absolute pressure, for example, That is, when the internal combustion engine is operated at low load, it is fully closed, and the pressure of the air delivered (discharged) from the compressor or the pressure of the air supplied to the combustion chamber of the internal combustion engine is 0 in absolute pressure.
  • 2 MPa (2 bar) or more that is, when the internal combustion engine is operated at high load, it is fully opened.
  • turbocharger 1 having the exhaust inlet casing 10 of the turbocharger 1 according to the present embodiment and the exhaust inlet casing 10 of the turbocharger 1 according to the present embodiment
  • a part (about 4 to 20%) of the exhaust gas introduced from the gas inlet 10 a does not pass through the turbine nozzle 5 and the turbine blade 4, and the exhaust gas flow path 26, the flange 42, the on-off valve 40, the pipe 44, the flange 46, through the exhaust gas bypass chamber 32, the exhaust gas bypass passage 22b, the space S1, and the through hole 48, in the exhaust gas flow of the gas guide cylinder 7 attached to the end portion on the gas outlet side of the turbine nozzle 5 It will be led to the space S2 formed on the downstream side. This enables the application of the exhaust gas bypass system without the need for the conventionally required bypass pipe routing.
  • the axial flow turbine has been described.
  • the present invention is also applicable to a centrifugal / slant flow turbine and a rotating machine such as a power turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supercharger (AREA)

Abstract

Dans ce carter (10) d'entrée d'échappement d'un turbocompresseur (1) qui comprime l'air pour la combustion d'un moteur à combustion interne et envoie de force l'air très dense dans la chambre de combustion du moteur à combustion interne, un espace formé entre deux carters (21, 22), de sorte qu'un carter intérieur (21) et un carter extérieur (22) distincts soient intégrés par liaison, est configuré de manière à être un conduit (26) de gaz d'échappement qui amène les gaz d'échappement depuis le moteur à combustion interne jusqu'à une buse (5) de turbine; et des conduits de dérivation (44, 32, 22b) de gaz d'échappement sont prévus, conduisant les gaz d'échappement bifurquant à mi-chemin le long du conduit (26) de gaz d'échappement vers le côté aval dans l'écoulement des gaz d'échappement d'un tube de guidage (7) de gaz fixé à l'extrémité de la buse (5) de turbine qui est le côté sortie de gaz.
PCT/JP2012/082257 2011-12-15 2012-12-12 Carter d'entrée d'échappement pour turbocompresseur WO2013089158A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2011274786A JP2013124626A (ja) 2011-12-15 2011-12-15 ターボ過給機の排気入口ケーシング
JP2011-274786 2011-12-15

Publications (1)

Publication Number Publication Date
WO2013089158A1 true WO2013089158A1 (fr) 2013-06-20

Family

ID=48612601

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2012/082257 WO2013089158A1 (fr) 2011-12-15 2012-12-12 Carter d'entrée d'échappement pour turbocompresseur

Country Status (2)

Country Link
JP (1) JP2013124626A (fr)
WO (1) WO2013089158A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6165564B2 (ja) 2013-09-05 2017-07-19 三菱重工業株式会社 軸流タービン、ターボ過給機、内燃機関、及び船舶
JP6101297B2 (ja) * 2015-02-26 2017-03-22 三菱重工業株式会社 タービン及びターボ過給機
JP7143234B2 (ja) 2019-02-13 2022-09-28 三菱重工マリンマシナリ株式会社 過給機のケーシング及びそれを備えた過給機
CN114876580B (zh) * 2022-07-12 2022-09-27 陕西联信材料科技有限公司 一种飞机制造用航空发动机涡轮叶片组件及其制备方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60178931A (ja) * 1984-02-24 1985-09-12 Nissan Motor Co Ltd 排気タ−ボチヤ−ジヤの過給圧制御装置
JPH10103071A (ja) * 1996-08-02 1998-04-21 Mitsubishi Heavy Ind Ltd 排気ガスタービン過給機
JPH11324691A (ja) * 1998-05-12 1999-11-26 Mitsubishi Heavy Ind Ltd 排気ガスタービン過給機の漏洩ガス排出装置
JP2001012251A (ja) * 1999-06-24 2001-01-16 Mitsubishi Heavy Ind Ltd 排気ガスタービン過給機のスラストフォースバランス機構
JP2009024584A (ja) * 2007-07-19 2009-02-05 Toyota Motor Corp 内燃機関の排気通路制御装置

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60178931A (ja) * 1984-02-24 1985-09-12 Nissan Motor Co Ltd 排気タ−ボチヤ−ジヤの過給圧制御装置
JPH10103071A (ja) * 1996-08-02 1998-04-21 Mitsubishi Heavy Ind Ltd 排気ガスタービン過給機
JPH11324691A (ja) * 1998-05-12 1999-11-26 Mitsubishi Heavy Ind Ltd 排気ガスタービン過給機の漏洩ガス排出装置
JP2001012251A (ja) * 1999-06-24 2001-01-16 Mitsubishi Heavy Ind Ltd 排気ガスタービン過給機のスラストフォースバランス機構
JP2009024584A (ja) * 2007-07-19 2009-02-05 Toyota Motor Corp 内燃機関の排気通路制御装置

Also Published As

Publication number Publication date
JP2013124626A (ja) 2013-06-24

Similar Documents

Publication Publication Date Title
JP4875654B2 (ja) 過給装置
JP4950082B2 (ja) 舶用ディーゼル機関
JP5222274B2 (ja) 軸流タービンを備えたターボ過給機
JP2009047163A (ja) 効率範囲が広い出力タービンを備えた内燃機関装置
JP5369723B2 (ja) 遠心圧縮機
WO2006046609A1 (fr) Turbocompresseur de gaz d’echappement
JP2009257097A (ja) 排気エネルギー回収装置
US20090196739A1 (en) Axial flow fluid device
WO2013089158A1 (fr) Carter d'entrée d'échappement pour turbocompresseur
WO2015005252A1 (fr) Silencieux pour compresseur à suralimentation
KR101529411B1 (ko) 터보 과급기
JP5448703B2 (ja) 舶用ディーゼル機関
US20080229743A1 (en) Turbocharger system
US20160003096A1 (en) Turbocharger internal turbine heat shield having axial flow turning vanes
JP6165564B2 (ja) 軸流タービン、ターボ過給機、内燃機関、及び船舶
JP5922685B2 (ja) 排気タービン装置、過給機および排気エネルギー回収装置
WO2018230108A1 (fr) Compresseur de suralimentation à plusieurs étages
EP2873830A1 (fr) Turbocompresseur, tuyère de turbine et navire
JP5402078B2 (ja) 過給装置
EP2799688A1 (fr) Turbocompresseur

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: 12857575

Country of ref document: EP

Kind code of ref document: A1

DPE1 Request for preliminary examination filed after expiration of 19th month from priority date (pct application filed from 20040101)
NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 12857575

Country of ref document: EP

Kind code of ref document: A1