WO2008137410A2 - Turbocompresseur à géométrie de turbine variable - Google Patents

Turbocompresseur à géométrie de turbine variable Download PDF

Info

Publication number
WO2008137410A2
WO2008137410A2 PCT/US2008/061875 US2008061875W WO2008137410A2 WO 2008137410 A2 WO2008137410 A2 WO 2008137410A2 US 2008061875 W US2008061875 W US 2008061875W WO 2008137410 A2 WO2008137410 A2 WO 2008137410A2
Authority
WO
WIPO (PCT)
Prior art keywords
vanes
turbocharger
turbine wheel
extended tips
turbine
Prior art date
Application number
PCT/US2008/061875
Other languages
English (en)
Other versions
WO2008137410A3 (fr
Inventor
Paul Anschel
David G. Grabowska
Original Assignee
Borgwarner Inc.
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 Borgwarner Inc. filed Critical Borgwarner Inc.
Priority to US12/597,787 priority Critical patent/US20100104424A1/en
Priority to CN200880012437XA priority patent/CN101663472B/zh
Priority to BRPI0810328A priority patent/BRPI0810328A8/pt
Publication of WO2008137410A2 publication Critical patent/WO2008137410A2/fr
Publication of WO2008137410A3 publication Critical patent/WO2008137410A3/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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

  • This invention is directed to a turbocharging system for an internal combustion engine and more particularly to variable turbine geometry of a turbocharging system.
  • Turbochargers are a type of forced induction system. They compress the air flowing into an engine, thus boosting the engine's horsepower without significantly increasing weight. Turbochargers use the exhaust flow from the engine to spin a turbine, which in turn drives an air compressor. Since the turbine spins about 30 times faster than most car engines and it is hooked up to the exhaust, the temperature in the turbine is very high. Additionally, due to the resulting high velocity of flow, turbochargers are subjected to noise and vibration. Such conditions can have a detrimental effect on the components of the turbocharger, particularly on the rotating parts such as the turbine rotor, which can lead to failure of the system.
  • Turbochargers are widely used on internal combustion engines and, in the past, have been particularly used with large diesel engines, especially for highway trucks and marine applications. More recently, in addition to use in connection with large diesel engines, turbochargers have become popular for use in connection with smaller, passenger car power plants.
  • the use of a turbocharger in passenger car applications permits selection of a power plant that develops the same amount of horsepower from a smaller, lower mass engine. Using a lower mass engine has the desired effect of decreasing the overall weight of the car, increasing sporty performance, and enhancing fuel economy.
  • use of a turbocharger permits more complete combustion of the fuel delivered to the engine, thereby reducing the overall emissions of the engine, which contributes to the highly desirable goal of a cleaner environment.
  • the design and function of turbochargers are described in detail in the prior art, for example, U.S. Pat. Nos. 4,705,463, 5,399,064, and 6,164,931, the disclosures of which are incorporated herein by reference.
  • Turbocharger units typically include a turbine operatively connected to the engine exhaust manifold, a compressor operatively connected to the engine air intake manifold, and a shaft connecting the turbine and compressor so that rotation of the turbine wheel causes rotation of the compressor impeller.
  • the turbine is driven to rotate by the exhaust gas flowing in the exhaust manifold.
  • the compressor impeller is driven to rotate by the turbine, and, as it rotates, it increases the air mass flow rate, airflow density and air pressure delivered to the engine cylinders.
  • the radial turbine is provided with the rotor blade unit 100 attached to a rotation axis and a scroll 102 having a shape similar to a snail.
  • the rotor blade unit 100 has a hub 101 and a plurality of blades 103 arranged on the hub 101 in a radial direction.
  • a nozzle 104 is interposed between the scroll 102 and a rotating region of the blades 103.
  • a gas flows from the scroll 102 into the nozzle 104, and is accelerated and given rotation force by the nozzle 104 to produce high velocity flow 105, which flows into the direction of the rotor axis.
  • the flow energy of the high velocity flow 105 is converted into the rotation energy by the blades 103 arranged on the hub 101.
  • the blades 103 exhaust the gas 107 having lost the energy into the direction of the rotation axis.
  • the Higashimori radial flow system suffers from the drawback of providing only radial flow to the turbine wheel which would not operate efficiently over a wide range of incident angles.
  • the application of only radial flow would cause a drop in efficiency at required engine operating conditions in such a design.
  • the exemplary embodiments of the turbocharger drive the turbine wheel utilizing both an axial flow component and a radial flow component of the exhaust gas in a variable turbine geometry (VTG) environment.
  • the mixed flow can be provided by a number of techniques including extended tips of the turbine wheel, secondary flow and leakage flow.
  • a turbocharger having a turbine wheel with a plurality of extended tips; and a variable turbine geometry assembly in fluid communication with the turbine wheel and having a nozzle ring with a plurality of vanes movably attached thereto.
  • One or more of the extended tips are non-parallel with an edge of one or more of the plurality of vanes.
  • a the method involves providing an exhaust gas flow to a turbine wheel of a variable turbine geometry turbocharger, wherein the exhaust gas flow is a mixed flow having both a radial component and an axial component.
  • the mixed flow is formed by at least one of leakage gas, secondary flow and a non-parallel incidence angle of the turbine wheel.
  • FIG. 1 is a schematic representation of a contemporary turbocharger system with a radial flow to the turbine wheel
  • FIG. 2 is a cross-sectional view of a portion of a turbocharger in accordance with an exemplary embodiment of the invention
  • FIG. 3 is a cross-sectional view of a portion of the turbocharger of FIG. 2;
  • FIG. 4 is a cross-sectional view of a portion of a turbocharger in accordance with another exemplary embodiment of the invention.
  • FIG. 5 is another cross-sectional view of the turbocharger of FIG. 4.
  • FIG. 6 is a cross-sectional view of portion A of the turbocharger of FIG. 4.
  • Embodiments of the invention are directed to mixed flow along a turbine wheel in a turbocharger for driving a compressor for delivery of a compressed fluid to an internal combustion engine. Aspects of the invention will be explained in connection with a turbine section having a particular turbine wheel geometry, but the detailed description is intended only as exemplary. Exemplary embodiments of the invention are shown in FIGS. 2-6, but the present invention is not limited to the illustrated structure or application.
  • a turbocharger 1 has a turbine housing 2, a center housing 3 and a compressor housing 3a connected to each other and positioned along an axis of rotation R.
  • the turbine housing 2 has an outer guiding grid of guide vanes 7 over the circumference of a support ring 6.
  • the guide vanes 7 may be pivoted by pivoting shafts 8 inserted into bores of the support ring 6 so that each pair of vanes define nozzles of selectively variable cross-section according to the pivoting position of the vanes 7. This allows for a larger or smaller amount of exhaust gases to be supplied to a turbine rotor 4.
  • the exhaust gases are provided to the guide vanes 7 and rotor 4 by a supply channel 9 having an inlet 99.
  • the exhaust gases are discharged through a central short feed pipe 10, and the rotor 4 drives the compressor wheel, impeller or rotor 21 fastened to the shaft 20 of the wheel.
  • the present disclosure also contemplates one or more of turbine housing 2, center housing 3 and compressor housing 3a being integrally formed with each other.
  • an actuation device 11 can be provided having a control housing 12, which controls an actuation movement of a pestle member 14 housed therein, whose axial movement is converted into a rotational movement of an adjustment or control ring 5 situated behind the support ring 6.
  • the guide vanes 7 may be displaced from a substantially tangential extreme position into a substantially radially extending extreme position. In this way, a larger or smaller amount of exhaust gases from a combustion motor supplied by the supply channel 9 can be fed to the turbine rotor 4, and discharged through the axial feed pipe 10.
  • the vane support ring 6 Between the vane support ring 6 and a ring-shaped portion 15 of the turbine housing 2, there can be a relatively small space 13 to permit free movement of the vanes 7.
  • the shape and dimensions of the vane space 13 can be chosen to increase the efficiency of the turbocharger 1, while allowing for thermal expansion due to the hot exhaust gases.
  • the vane support ring 6 can have spacers 16 formed thereon.
  • Various other turbocharger components can also be used with compressor wheel 21 and turbocharger 1.
  • Turbocharger 1 can have a mixed flow turbine wheel 4 formed by a non-zero blade inlet angle, an inlet with a varying radius from the center axis or a combination of both.
  • the exemplary embodiment of FIGS. 2-3 illustrates a turbine wheel 4 with an extended tip 400.
  • the extended tip 400 can be at various angles to the axis of the turbocharger.
  • the mixed flow turbine wheel 4 to benefit from both the radial and axial components of the exhaust gas flow for improved efficiency.
  • the vanes 7 are the predominant factor controlling the relative turbine wheel blade incidence angle. As a result, the turbocharger can be forced to operate over a much wider range of incidence angles.
  • the use of the mixed flow turbine wheel 4 in combination with a variable turbine geometry, (i.e., vanes 7) allows the turbocharger 1 to maintain higher efficiency over a much wider range of incidence angles.
  • the variable turbine geometry can compensate for any increased inertia due to the turbine wheel geometry by throttling the inlet flow for an improved transient response.
  • Turbine wheel 4' has one or more extended tips 400' in proximity to the vanes 7.
  • the extended tips 400' are at an angle, i.e., non- parallel) with each of the trailing edges of the vanes 7.
  • all of the tips of the turbine wheel 4' are extended tips 400'.
  • the angle is between 1 and 60 degrees, preferably between 5 and 45 degrees, and more preferably between 10 and 30 degrees.
  • the extended tips 400' can extend into an inlet of the vane space 13.
  • the inlet is represented generally by broken line 500 in FIG. 5.
  • the VTG vanes 7 can control the flow angle into the turbine wheel 4' and can directly affect the magnitude of the tangential and radial flow vectors. In one embodiment, where the mixed flow turbine wheel 4' is less incidence angle sensitive, then the wheel can maintain a higher overall efficiency over a wider range of incidence angles (tangential/radial components) than a traditional radial inflow wheel.
  • a variable turbine geometry turbocharger can have an axial component of the exhaust gas flow generated by leakage flow, secondary flow or a combination of both. This can be used in combination with the extended tips 400 and 400'.
  • the vane 7 can be parallel to the angle of the turbine wheel. In such an embodiment, the VTG vane trailing edge is not radial and has a matching angle to the turbine wheel inlet (or similar angle).
  • turbochargers and/or housings can be used with other types of fluid impelling devices where a particular length of a diffuser is desired.
  • Such other fluid impelling devices include, but are not limited to, the following: superchargers; centrifugal pumps; centrifugal fans; single-stage gas compressors; multistage gas compressors; and other kinds of devices which generally use one or more rotating elements to compress gases and/or induce fluid flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Abstract

La présente invention concerne un turbocompresseur possédant une roue de turbine (4, 4') avec une pluralité d'extrémités prolongées (400, 400'); et un ensemble à géométrie de turbine variable en communication fluide avec la roue de turbine et possédant un distributeur annulaire (6) avec une pluralité d'aubes (7) fixées de manière amovible à celui-ci. Une ou plusieurs des extrémités prolongées sont non parallèles par rapport à un bord d'une ou plusieurs de la pluralité d'aubes. L'angle d'incidence peut varier et peut aller d'1 à 60 degrés. Les extrémités prolongées peuvent se prolonger dans une entrée de l'espace à aubes qui abrite les aubes.
PCT/US2008/061875 2007-05-04 2008-04-29 Turbocompresseur à géométrie de turbine variable WO2008137410A2 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US12/597,787 US20100104424A1 (en) 2007-05-04 2008-04-29 Variable turbine geometry turbocharger
CN200880012437XA CN101663472B (zh) 2007-05-04 2008-04-29 可变涡轮几何形状的涡轮增压器
BRPI0810328A BRPI0810328A8 (pt) 2007-05-04 2008-04-29 turbocompressor e método de operação de um turbocompressor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US91617507P 2007-05-04 2007-05-04
US60/916,175 2007-05-04

Publications (2)

Publication Number Publication Date
WO2008137410A2 true WO2008137410A2 (fr) 2008-11-13
WO2008137410A3 WO2008137410A3 (fr) 2009-01-08

Family

ID=39944188

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2008/061875 WO2008137410A2 (fr) 2007-05-04 2008-04-29 Turbocompresseur à géométrie de turbine variable

Country Status (4)

Country Link
US (1) US20100104424A1 (fr)
CN (1) CN101663472B (fr)
BR (1) BRPI0810328A8 (fr)
WO (1) WO2008137410A2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012071254A2 (fr) * 2010-11-24 2012-05-31 Borgwarner Inc. Turbocompresseur pour gaz d'échappement
DE102013225642A1 (de) * 2013-12-11 2015-06-11 Continental Automotive Gmbh Abgasturbolader
WO2017165768A1 (fr) * 2016-03-24 2017-09-28 Borgwarner Inc. Turbocompresseur à géométrie variable
DE102018221812A1 (de) * 2018-12-14 2020-06-18 Continental Automotive Gmbh Abgasturbine mit einer Abgasleiteinrichtung für einen Abgasturbolader und Abgasturbolader

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5811548B2 (ja) * 2011-02-28 2015-11-11 株式会社Ihi ツインスクロール型の斜流タービン及び過給機
DE102012012000B4 (de) * 2012-06-16 2022-12-01 Volkswagen Aktiengesellschaft Turbine für einen Abgasturbolader
CN105960515B (zh) * 2014-02-04 2019-01-15 博格华纳公司 用于混流式涡轮机叶轮涡轮增压器的隔热罩
US20160160653A1 (en) * 2014-12-08 2016-06-09 Hyundai Motor Company Turbine wheel for turbo charger
JP2023077852A (ja) * 2021-11-25 2023-06-06 株式会社豊田自動織機 燃料電池用流体機械

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06299861A (ja) * 1993-03-25 1994-10-25 Abb Manag Ag 半径方向に貫流される排ガスターボ過給タービン
JPH0861005A (ja) * 1994-08-25 1996-03-05 Mitsubishi Heavy Ind Ltd 斜流タービンのノズル
JPH08121184A (ja) * 1994-10-12 1996-05-14 Mercedes Benz Ag 内燃機関用排気ガスタービン過給機
JP2000120442A (ja) * 1998-10-12 2000-04-25 Toyota Central Res & Dev Lab Inc 可変容量形ターボチャージャ
US6877955B2 (en) * 2002-08-30 2005-04-12 Mitsubishi Heavy Industries, Ltd. Mixed flow turbine and mixed flow turbine rotor blade

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3059415A (en) * 1959-07-08 1962-10-23 Birmann Rudolph Turbocharger for internal combustion engines
US3232043A (en) * 1964-01-13 1966-02-01 Birmann Rudolph Turbocompressor system
US3495921A (en) * 1967-12-11 1970-02-17 Judson S Swearingen Variable nozzle turbine
US3972644A (en) * 1975-01-27 1976-08-03 Caterpillar Tractor Co. Vane control arrangement for variable area turbine nozzle
CN2419375Y (zh) * 1999-12-23 2001-02-14 北京理工大学 混流转叶式可变截面涡轮增压器
US8240984B2 (en) * 2005-08-02 2012-08-14 Honeywell International Inc. Variable geometry compressor module

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06299861A (ja) * 1993-03-25 1994-10-25 Abb Manag Ag 半径方向に貫流される排ガスターボ過給タービン
JPH0861005A (ja) * 1994-08-25 1996-03-05 Mitsubishi Heavy Ind Ltd 斜流タービンのノズル
JPH08121184A (ja) * 1994-10-12 1996-05-14 Mercedes Benz Ag 内燃機関用排気ガスタービン過給機
JP2000120442A (ja) * 1998-10-12 2000-04-25 Toyota Central Res & Dev Lab Inc 可変容量形ターボチャージャ
US6877955B2 (en) * 2002-08-30 2005-04-12 Mitsubishi Heavy Industries, Ltd. Mixed flow turbine and mixed flow turbine rotor blade

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012071254A2 (fr) * 2010-11-24 2012-05-31 Borgwarner Inc. Turbocompresseur pour gaz d'échappement
WO2012071254A3 (fr) * 2010-11-24 2012-07-19 Borgwarner Inc. Turbocompresseur pour gaz d'échappement
DE102013225642A1 (de) * 2013-12-11 2015-06-11 Continental Automotive Gmbh Abgasturbolader
WO2015086205A1 (fr) * 2013-12-11 2015-06-18 Continental Automotive Gmbh Turbocompresseur à gaz d'échappement
CN105814279A (zh) * 2013-12-11 2016-07-27 大陆汽车有限公司 废气涡轮增压器
DE102013225642B4 (de) * 2013-12-11 2020-09-17 Vitesco Technologies GmbH Abgasturbolader mit einem verstellbaren Leitgitter
US10808569B2 (en) 2013-12-11 2020-10-20 Continental Automotive Gmbh Turbocharger
WO2017165768A1 (fr) * 2016-03-24 2017-09-28 Borgwarner Inc. Turbocompresseur à géométrie variable
DE102018221812A1 (de) * 2018-12-14 2020-06-18 Continental Automotive Gmbh Abgasturbine mit einer Abgasleiteinrichtung für einen Abgasturbolader und Abgasturbolader
DE102018221812B4 (de) 2018-12-14 2021-08-19 Vitesco Technologies GmbH Abgasturbine mit einer Abgasleiteinrichtung für einen Abgasturbolader und Abgasturbolader

Also Published As

Publication number Publication date
CN101663472A (zh) 2010-03-03
BRPI0810328A2 (pt) 2014-10-14
BRPI0810328A8 (pt) 2018-10-30
US20100104424A1 (en) 2010-04-29
CN101663472B (zh) 2012-06-20
WO2008137410A3 (fr) 2009-01-08

Similar Documents

Publication Publication Date Title
US20100104424A1 (en) Variable turbine geometry turbocharger
US7694518B2 (en) Internal combustion engine system having a power turbine with a broad efficiency range
US7571607B2 (en) Two-shaft turbocharger
US20100098532A1 (en) Compressor housing
US8632304B2 (en) Turbocharger diffuser
EP2279337B1 (fr) Compresseur
US7189059B2 (en) Compressor including an enhanced vaned shroud
CN101270759A (zh) 具有延伸前缘的压缩机转轮
US9759164B2 (en) Fluid energy machine, in particular for an exhaust gas turbocharger of an automobile
CN103403298B (zh) 涡轮机叶轮、涡轮机及其使用
US9068499B2 (en) Turbine housing with integrated ribs
CN102220900A (zh) 具有轮毂球的高扩散涡轮机叶轮
US20160024999A1 (en) Turbine housing with dividing vanes in volute
CN104421201B (zh) 结构非对称的双侧涡轮增压器叶轮
US20150159547A1 (en) Cross Flow Turbine
US9915199B2 (en) Bi-directional compression fan rotor for a gas turbine engine
JP4448854B2 (ja) ラジアルタイプのコンプレッサからなるとともに後退翼を有するインペラを備えた内燃エンジンのためのターボコンプレッサシステム
KR20110083363A (ko) 임펠러 및 압축기
FI4031752T3 (fi) Hukkaportin massavirran johtaminen samankeskisesti virtausoptimoituun aksiaalidiffuusoriin

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 200880012437.X

Country of ref document: CN

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

Ref document number: 08747097

Country of ref document: EP

Kind code of ref document: A2

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 3987/KOLNP/2009

Country of ref document: IN

122 Ep: pct application non-entry in european phase

Ref document number: 08747097

Country of ref document: EP

Kind code of ref document: A2

ENP Entry into the national phase

Ref document number: PI0810328

Country of ref document: BR

Kind code of ref document: A2

Effective date: 20091104