EP3610135A1 - Couronne directrice pour un turbocompresseur à gaz d'échappement - Google Patents

Couronne directrice pour un turbocompresseur à gaz d'échappement

Info

Publication number
EP3610135A1
EP3610135A1 EP18718134.2A EP18718134A EP3610135A1 EP 3610135 A1 EP3610135 A1 EP 3610135A1 EP 18718134 A EP18718134 A EP 18718134A EP 3610135 A1 EP3610135 A1 EP 3610135A1
Authority
EP
European Patent Office
Prior art keywords
nozzle ring
bearing housing
turbine
housing
base body
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP18718134.2A
Other languages
German (de)
English (en)
Inventor
Christoph MORATH
Tobias Gwehenberger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Turbo Systems Switzerland Ltd
Original Assignee
ABB Turbo Systems AG
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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP21195944.0A priority Critical patent/EP3954876A1/fr
Publication of EP3610135A1 publication Critical patent/EP3610135A1/fr
Pending legal-status Critical Current

Links

Classifications

    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F01D5/046—Heating, heat insulation or cooling means
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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 invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.
  • the invention relates to a nozzle ring of such an exhaust gas turbocharger.
  • exhaust gas turbochargers are used by default for the performance of an internal combustion engine, with a turbine in the exhaust system of the internal combustion engine and with one of the internal combustion engine upstream compressor.
  • the exhaust gases of the internal combustion engine are thereby relaxed in the turbine.
  • the work thus obtained is transmitted by means of a shaft to the compressor, which compresses the internal combustion engine supplied air.
  • the kinetic energy of the exhaust gas is used to drive the rotor of the turbocharger.
  • the exhaust gas jet must be directed to the turbine shaft.
  • a nozzle ring is installed at radial turbine stages at the outlet of the flow channel in front of the turbine shaft.
  • the working medium for.
  • the exhaust gases have a large temperature gradient. Therefore, nozzle rings of exhaust turbochargers loaders by changing operating conditions, ie increase or decrease in pressure and temperature of the working fluid, typically highly stressed and can be subjected to relatively high thermal expansions.
  • nozzle rings are often done by simply jamming in the housing of the exhaust gas turbine.
  • the nozzle ring can be held in position in which it is clamped axially, usually between the turbine housing and the bearing housing.
  • a separate heat shield can be installed insofar as the heat input is too high by the exhaust gas in the bearing housing or the exhaust gas is withdrawn too much energy by heat input in adjacent components.
  • a nozzle ring for a radial turbine according to independent claim 1 is provided. Further aspects, advantages and features of the present invention can be found in the dependent claims, the description and the enclosed figures.
  • a nozzle ring for a radial turbine is provided.
  • the nozzle ring comprises a rotationally symmetrical disk-shaped base body with a central opening for passing through a shaft.
  • the nozzle ring comprises guide vanes, which are arranged in the circumferential direction in a radially outer region of the base body and designed to guide exhaust gases on blades of a turbine wheel.
  • the main body of the nozzle ring is designed to form a heat shield between a storage space of a bearing housing and a turbine chamber in the mounted state.
  • a nozzle ring which enables a mounting and mounting concept, with which the positioning of the nozzle ring blades and the introduction of different turbine rear wall geometries independent of used clamping compound and / or an existing hot centering / sealing is / are.
  • a nozzle ring is provided with an integrated heat shield, so that reduces the number of interfaces joints. Furthermore, a clearance / clearance of the rear wall geometry of the turbine shaft is made possible because it is integrated in the nozzle ring, so that no different bearing housing variants are necessary.
  • a nozzle ring is provided, the fixation advantageously can be done outside of the clamping assembly "bearing housing / turbine housing", for example by attachment by means of temperature-resistant screws on the bearing housing.
  • the nozzle ring described herein allows an improved connection, particularly with regard to deformation (under the influence of temperature) and gas tightness, since the nozzle ring can advantageously be axially biased like a plate spring on the bearing housing.
  • an additional "containment" interface can be advantageously avoided,
  • the use of the nozzle ring described herein advantageously avoids an additional interface that affects gas tightness outwardly.
  • the scaling of the turbine head does not affect the nip / hot centering.
  • the maximum scaling is defined by dimensioning the bearing housing.
  • the nozzle ring described herein can be advantageously mounted in a central region around the turbine shaft to the bearing housing, so that a thermal expansion of the nozzle ring by a relatively far inner mounting advantageously little is affected.
  • Another advantage of the nozzle ring described herein is that the attachment elements for the nozzle ring are not in the region of the main flow.
  • an exhaust gas turbocharger with a nozzle ring according to one of the embodiments described herein is provided, so that advantageously an improved exhaust gas turbocharger can be provided.
  • the exhaust gas turbocharger comprises a turbine housing, a shaft mounted in a bearing housing on which a turbine wheel with blades is arranged. Furthermore, the exhaust gas turbocharger comprises an inlet channel for exhaust gases, which is formed in the turbine housing, upstream of the turbine wheel. Furthermore, the Abgasturbo loader comprises a nozzle ring according to one of the embodiments described herein, wherein the nozzle ring is designed such that the nozzle ring is axially held in the assembled state between the bearing housing and the turbine housing of a turbo charger.
  • Figure 1 is a schematic isometric view of a nozzle ring according to embodiments described herein in an assembled state with a turbine wheel.
  • Figure 2 is a schematic isometric view of a nozzle ring according to embodiments described herein in a mounted state without turbine wheel; a schematic isometric view of a bearing housing side of a nozzle ring according to embodiments described herein; a schematic isometric view of a bearing housing side of a nozzle ring with a recess according to further embodiments described herein; a schematic isometric view of a bearing housing side of a nozzle ring comprising a recess with radially extending ribs according to other embodiments described herein; and a schematic sectional view of a section of an exhaust gas turbocharger according to the description herein
  • FIG. 1 shows a schematic isometric view of a nozzle ring 10 according to embodiments described herein in an assembled state.
  • the turbine wheel 30 of a radial turbine is shown schematically.
  • the nozzle ring 10 comprises a rotationally symmetric, disc-shaped base body 11 having a central opening 12 for passing a shaft 20.
  • the nozzle ring 10 typically comprises guide vanes 14 arranged circumferentially in one radially outer region of the base body 11 are arranged.
  • the vanes 14 are arranged and configured to direct exhaust gases on blades of a turbine wheel 30.
  • the Guide vanes 14 extend from the base body 11 in the axial direction and be formed integrally with the base body. As can be seen from FIG.
  • the base body 11 of the nozzle ring described here is designed to form a heat shield between a storage space 40 of a bearing housing 41 and a turbine space 50 in the installed state.
  • the main body 11 of the nozzle ring extends radially outwardly from the central opening 12, as shown by way of example in FIGS. 3 to 5.
  • the main body of the nozzle ring is designed such that (apart from the holes 17), a closed surface between the central opening 12 and the outer edge of the base body is provided.
  • a nozzle ring is provided with an integrated heat shield, so that reduces the number of interfaces / joints in the area mounted nozzle ring. Furthermore, the design of the radially outwardly extending main body of the nozzle ring from the central opening enables clearance / clearance of the rear wall geometry of the turbine shaft since this can be integrated in the nozzle ring. Thus, no different bearing housing variants are necessary.
  • a nozzle ring is provided, the fixation of which can advantageously take place outside the clamping assembly "bearing housing / turbine housing", for example by fastening by means of heat-resistant screws to the bearing housing, as described below.
  • the nozzle ring may comprise a mounting flange 15, as shown by way of example in Figures 4, 5, and 6.
  • mounting flange 15 is typically in a radially inner region of the body 11 arranged.
  • the mounting flange 15 may have a contact surface 16 for bearing on a corresponding contact surface of the bearing housing 41, as shown by way of example in Figure 6.
  • one or more circumferentially arranged bores 17 comprise, for receiving one or more Fasteners are suitable to mount the nozzle ring on the bearing housing.
  • the fastening means may be pins, bolts, screws or the like.
  • the fasteners are heat resistant.
  • the nozzle ring described herein can be advantageously attached to the bearing housing in a central area around the turbine shaft so that thermal expansion of the nozzle ring is advantageously minimally affected by a relatively far inboard mounting. Furthermore, the attachment of the nozzle ring described herein has the advantage that the attachment elements for the nozzle ring are not in the region of the main flow.
  • the mounting flange 15 is an integral part of the main body 11. This advantageously leads to a reduction in component components.
  • the nozzle ring alternatively or in addition to a central attachment (eg by means of a mounting flange described hereinbefore and corresponding attachment means), be designed such that the nozzle ring in the assembled state under temperature axially between the bearing housing 40 and turbine housing and / or clamped radially in the bearing housing 40 and / or radially in the turbine housing.
  • a central attachment e.g by means of a mounting flange described hereinbefore and corresponding attachment means
  • an improved connection of the nozzle ring in the assembled state can be provided to the corresponding contact surfaces, in particular with regard to deformation (under the influence of temperature) and gas tightness, since the nozzle ring can advantageously be axially biased as a plate spring on the bearing housing advantageously.
  • a bearing housing side IA of the main body 11 may comprise one or more recesses 18, as shown for example in Figure 4.
  • the recess 18 is typically formed to include one or more air-filled isolation spaces in the assembled state of the nozzle ring
  • a nozzle ring with integrated heat shield can be provided in a simple and effective manner.
  • the recess 18 may include extending in the radial direction ribs 19, as shown by way of example in Figure 5. Such ribs can have an advantageous effect on the stability as well as on the thermal expansion behavior of the nozzle ring.
  • the bores 17 in the mounting flange may be disposed on a first virtual circle having a first radius R1 around the central opening 12.
  • the vanes 14 may be disposed on a second virtual circle having a second radius R2 around the central opening 12.
  • the second radius R2 is greater than the first Radius Rl, for example, the second radius R2 may be> 1.5xRl.
  • the holes 17 for receiving one or more fasteners in the mounting flange may be arranged at regular or irregular angular intervals about the central opening 12 around.
  • a regular disorder for example, have the advantage of improved non-positive attachment of the nozzle ring on the bearing housing.
  • the nozzle ring described herein may also be a closed nozzle ring.
  • the nozzle ring on one of the main body 11 opposite side have a further arranged disc, which is connected to the guide vanes 14.
  • the further arranged disk may be configured to provide another heat shield.
  • a radially outboard portion of the body may include one or more centering cams (not shown) distributed along the circumference of the body.
  • Such Zentrianssnocken can engage for example in corresponding grooves in the turbine housing, resulting in a radial guidance of the turbine housing with respect to the main body of the nozzle ring.
  • the base body of the nozzle ring which is correspondingly aligned on the basis of the centering cam can be pushed into the turbine housing in the axial direction.
  • a nozzle ring is provided by the embodiments described herein, which can be used advantageously for an exhaust gas turbocharger, so that the positioning of the nozzle ring vanes and the introduction of different turbine rear wall geometries regardless of the used Klemmverbund and / or an existing hot centering / sealing is / are.
  • the heat shield may be geometrically integrated into an open nozzle ring as an extension of the bearing housing-side nozzle ring plate.
  • This nozzle ring plate (also referred to as the base body) is in this case carried out by the dimension so that the rear space of the turbine head is covered up to the transition of the shaft hub.
  • the nozzle ring vanes are integrally formed with the nozzle ring plate and can be created, for example, by machining or by precision casting.
  • the nozzle ring may be secured by means of fasteners, e.g. Screws, behind the turbine head (Turbinenenkoprepraum) be attached to a relatively small diameter.
  • fasteners e.g. Screws
  • the nozzle ring is located outside the clamping assembly turbine housing / bearing housing and the fasteners are in a non-critical for the scaling of the turbine head / nozzle ring paddle area.
  • FIG. 6 shows a schematic sectional view of a section of an exhaust gas turbocharger 60 according to embodiments described herein.
  • the exhaust gas turbocharger 60 includes a turbine housing 51, a shaft 20 mounted in a bearing housing 41. On the shaft 20, a turbine wheel 30 having blades 31 is disposed.
  • the exhaust gas turbocharger typically has an inlet channel 33 for exhaust gases, which is formed in the turbine housing 51, upstream of the turbine wheel 30.
  • the exhaust turbocharger loader a nozzle ring 10 according to one of the embodiments described herein, as shown schematically in Figure 6.
  • the nozzle ring 10 is designed such that the nozzle ring in the assembled state between the bearing housing 41 and the turbine housing of a turbo charger is held axially.
  • the nozzle ring may be fastened to the bearing housing 41 via a fastening flange 15 by means of heat-resistant fastening means 15A.
  • the heat resistant fasteners 15A may be heat resistant screws with which and the nozzle ring 10 is bolted to the bearing housing 41.
  • the nozzle ring 10 and the bearing housing 41 may be designed such that the nozzle ring is clamped axially in the mounted state between the bearing housing and turbine housing plate spring-like.
  • the nozzle ring 10 and the bearing housing 41 as an alternative or additional mounting option of the nozzle ring in the exhaust gas turbocharger, be designed such that the nozzle ring 10 in mounted state under temperature, ie heat, axially clamped between the bearing housing 41 and turbine housing and / or radially in the bearing housing 41 and / or in the turbine housing 51.
  • one or more anti-rotation (s) may be provided for the nozzle ring.
  • the nozzle ring 10 and the bearing housing 41 may be designed such that for the nozzle ring in the assembled state one or more anti-rotation (s) are provided.
  • the one or more anti-rotation (s) can be performed for example by means of positive / non-positive connections between the nozzle ring and bearing housing.
  • one or more anti-rotation lock (s) for example by means of positive / non-positive connections, between the nozzle ring and the turbine housing. This may be particularly advantageous if the nozzle ring is not attached to the bearing housing but is clamped axially between the bearing housing and turbine housing plate spring-like.

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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une couronne directrice (10) pour une turbine radiale. La couronne directrice comporte un corps de base (11) en forme de disque à symétrie de révolution doté d'une ouverture centrale (12) servant au passage d'un arbre (20). La couronne directrice comporte en outre des aubes directrices (14) qui sont disposées dans une zone radialement extérieure du corps de base (11) dans la direction périphérique et sont conçues pour guider les gaz d'échappement vers les aubes mobiles (31) d'une roue de turbine (30). Le corps de base (11) de la couronne directrice est conçu pour former, à l'état monté, un bouclier thermique entre un espace de palier (40) d'un logement de palier (41) et un espace de turbine (50).
EP18718134.2A 2017-04-13 2018-04-12 Couronne directrice pour un turbocompresseur à gaz d'échappement Pending EP3610135A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP21195944.0A EP3954876A1 (fr) 2017-04-13 2018-04-12 Bague de buse pour un turbocompresseur à gaz d'échappement

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017108057.0A DE102017108057A1 (de) 2017-04-13 2017-04-13 Düsenring für einen abgasturbolader
PCT/EP2018/059439 WO2018189319A1 (fr) 2017-04-13 2018-04-12 Couronne directrice pour un turbocompresseur à gaz d'échappement

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP21195944.0A Division EP3954876A1 (fr) 2017-04-13 2018-04-12 Bague de buse pour un turbocompresseur à gaz d'échappement

Publications (1)

Publication Number Publication Date
EP3610135A1 true EP3610135A1 (fr) 2020-02-19

Family

ID=62002127

Family Applications (2)

Application Number Title Priority Date Filing Date
EP18718134.2A Pending EP3610135A1 (fr) 2017-04-13 2018-04-12 Couronne directrice pour un turbocompresseur à gaz d'échappement
EP21195944.0A Pending EP3954876A1 (fr) 2017-04-13 2018-04-12 Bague de buse pour un turbocompresseur à gaz d'échappement

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP21195944.0A Pending EP3954876A1 (fr) 2017-04-13 2018-04-12 Bague de buse pour un turbocompresseur à gaz d'échappement

Country Status (8)

Country Link
US (1) US11313275B2 (fr)
EP (2) EP3610135A1 (fr)
JP (1) JP7130665B2 (fr)
KR (1) KR102554216B1 (fr)
CN (1) CN110475945B (fr)
CA (1) CA3058826A1 (fr)
DE (1) DE102017108057A1 (fr)
WO (1) WO2018189319A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020171813A1 (fr) * 2019-02-21 2020-08-27 Abb Turbo Systems Ag Bague de buse pour une turbine radiale et turbocompresseur à gaz d'échappement comprenant celle-ci
JP7424752B2 (ja) * 2019-03-25 2024-01-30 株式会社豊田自動織機 ターボチャージャ
US11530615B1 (en) * 2022-03-01 2022-12-20 Garrett Transportation I Inc. Method for constructing a fixed-vane ring for a nozzle of a turbocharger turbine

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4969805A (en) * 1989-05-02 1990-11-13 Allied-Signal Inc. Unidirectional turbocharger assembly
DE69308377T2 (de) * 1992-05-21 1997-06-19 Alliedsignal Ltd Regelbarer Turbolader
GB9222133D0 (en) 1992-10-21 1992-12-02 Leavesley Malcolm G Turbocharger apparatus
DE4238550A1 (de) * 1992-11-14 1994-05-19 Daimler Benz Ag Abgasturbolader für eine Brennkraftmaschine
DE4330487C1 (de) * 1993-09-09 1995-01-26 Daimler Benz Ag Abgasturbolader für eine Brennkraftmaschine
DE19615237C2 (de) * 1996-04-18 1999-10-28 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE19838754C1 (de) * 1998-08-26 2000-03-09 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE10048105A1 (de) 2000-09-28 2002-04-11 Daimler Chrysler Ag Angasturbolader für eine Brennkraftmaschine mit variabler Turbinengeometrie
JP2004514840A (ja) * 2000-11-30 2004-05-20 ハネウェル・ギャレット・ソシエテ・アノニム 摺動ピストンを具備する可変形状ターボチャージャー
GB0121864D0 (en) * 2001-09-10 2001-10-31 Leavesley Malcolm G Turbocharger apparatus
JP2003227344A (ja) * 2001-11-28 2003-08-15 Hitachi Ltd ターボチャージャ
GB0227473D0 (en) 2002-11-25 2002-12-31 Leavesley Malcolm G Variable turbocharger apparatus with bypass apertures
DE10256418A1 (de) * 2002-12-02 2004-06-09 Abb Turbo Systems Ag Abgasturbinengehäuse
WO2004074642A1 (fr) * 2003-02-19 2004-09-02 Honeywell International Inc. Turbine a gorge variable
US7631497B2 (en) * 2005-04-21 2009-12-15 Borgwarner Inc. Turbine heat shield with ribs
GB0724022D0 (en) * 2007-12-07 2008-01-16 Cummins Turbo Tech Ltd Compressor
JP2012107527A (ja) 2010-11-15 2012-06-07 Ihi Corp ターボチャージャ
EP2455590A1 (fr) 2010-11-18 2012-05-23 Fiat Powertrain Technologies S.p.A. Distributeur à géométrie variable pour turbine, particulièrement pour un ensemble de turbocompresseur de véhicule à moteur
US9797409B2 (en) * 2012-03-30 2017-10-24 Borgwarner Inc. Turbocharger bearing housing with integrated heat shield
KR20140063474A (ko) * 2012-11-16 2014-05-27 에이비비 터보 시스템즈 아게 노즐 링
EP2778349A1 (fr) * 2013-03-15 2014-09-17 Continental Automotive GmbH Turbosoufflante de gaz d'échappement avec boîtier de turbine traité
JP6349745B2 (ja) 2014-01-29 2018-07-04 株式会社Ihi 可変ノズルユニット及び可変容量型過給機
US9732633B2 (en) * 2015-03-09 2017-08-15 Caterpillar Inc. Turbocharger turbine assembly

Also Published As

Publication number Publication date
JP7130665B2 (ja) 2022-09-05
CN110475945A (zh) 2019-11-19
DE102017108057A1 (de) 2018-10-18
US20200392895A1 (en) 2020-12-17
KR102554216B1 (ko) 2023-07-12
JP2020516810A (ja) 2020-06-11
US11313275B2 (en) 2022-04-26
EP3954876A1 (fr) 2022-02-16
WO2018189319A1 (fr) 2018-10-18
CA3058826A1 (fr) 2018-10-18
CN110475945B (zh) 2023-04-21
KR20190138802A (ko) 2019-12-16

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