EP1672177B1 - Turbocompresseur - Google Patents

Turbocompresseur Download PDF

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Publication number
EP1672177B1
EP1672177B1 EP04029586A EP04029586A EP1672177B1 EP 1672177 B1 EP1672177 B1 EP 1672177B1 EP 04029586 A EP04029586 A EP 04029586A EP 04029586 A EP04029586 A EP 04029586A EP 1672177 B1 EP1672177 B1 EP 1672177B1
Authority
EP
European Patent Office
Prior art keywords
layer
turbine
turbocharger according
housing
turbocharger
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.)
Active
Application number
EP04029586A
Other languages
German (de)
English (en)
Other versions
EP1672177A1 (fr
Inventor
Dirk Frankenstein
Ralf Böning
Hartmut Weiss
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.)
BorgWarner Inc
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 EP04029586A priority Critical patent/EP1672177B1/fr
Priority to JP2005355641A priority patent/JP4851178B2/ja
Priority to KR1020050122793A priority patent/KR101149083B1/ko
Priority to CN2005101317221A priority patent/CN1807847B/zh
Priority to US11/300,066 priority patent/US7600969B2/en
Publication of EP1672177A1 publication Critical patent/EP1672177A1/fr
Application granted granted Critical
Publication of EP1672177B1 publication Critical patent/EP1672177B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • 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
    • F05D2240/70—Slinger plates or washers
    • 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
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • 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

Definitions

  • the invention relates to a turbocharger according to the preamble of claim 1.
  • a turbocharger is from the WO 2004/048755 A known.
  • Another turbocharger is from the EP 1 398 463 A1 known.
  • a heat shield is provided around its shaft on the turbine side, which serves to protect the bearing housing from damage due to excessive temperatures due to the flowing through the turbine exhaust gases of the engine.
  • the known heat shield consists of a single-layer component, the thermal insulation properties, however, are in need of improvement.
  • turbocharger specified in the preamble of claim 1, which ensures a means of disc spring axial fixation of the cartridge of the variable turbine geometry in Turbinenradsupplementary and on the other hand by means of heat shield allows improved thermal insulation in the direction of the bearing housing ,
  • the disc spring of the turbocharger according to the invention is formed of at least two, but optionally several layers of material and includes both the function of Vorspannkrafter Wegung and the improvement of the shielding function by increasing the thermal resistance. This makes it possible to ensure the function, in particular also of the exhaust gas temperatures.
  • one of the material layers is pot-shaped or pot-like, with a raised peripheral edge, while the other material layer is preferably formed as a flat disk.
  • u. U. advantageously be dispensed liquid cooling of the bearing housing.
  • the material layers can form both an integral part as well as two separate parts which rest on one another in the assembled state.
  • the material layers consist of the same material or that different materials are chosen.
  • Fig. 1 is a portion of a turbocharger 1 according to the invention shown, since this representation is sufficient for explaining the principles of the invention.
  • the turbocharger 1 all commonly provided construction elements, which, as I said in Fig. 1 however, are omitted for simplicity of illustration.
  • a turbine housing 2 of a turbine shown which is arranged adjacent to a bearing housing 3.
  • This bearing housing 3 is arranged between the turbine housing 2 and a compressor housing (not shown) of a likewise not shown compressor wheel.
  • the bearing housing 3 has the storage for a shaft which in Fig. 1 symbolized by the dash-dotted center line W, since Fig. 1 only the upper portion of the turbocharger 1 according to the invention reproduces.
  • the shaft W carries the turbine and the compressor wheel and is mounted in the bearing housing 3 via a suitable bearing arrangement.
  • a disc spring 4 according to the invention is clamped, which is formed in multiple layers.
  • two material layers 5 and 6 are provided, which are described below with reference to Fig. 2 and 3 be explained in more detail.
  • Fig.1 illustrates the arrangement of the disc spring 4 between the turbine housing 2 and the bearing housing 3, wherein due to the stepped structure of the disc spring 4, two support areas 10, 11 result, with which the disc spring, as in detail the Fig. 1 can be removed, is supported on the corresponding parts of the turbine housing 2 and the cartridge of the variable turbine geometry and the bearing housing 3.
  • Fig. 2 a first embodiment of the disc spring 4 according to the invention is shown.
  • the two layers of material 5 and 6 are integrally connected to each other in this embodiment, so that there is a uniform part.
  • Fig. 2 illustrates that the material layer 5, which applies the axial biasing force, a pot-like configuration with a circumferential raised edge 13 has.
  • the material layer 5 has a central recess 9, which is arranged coaxially to a central recess 8 of the material layer 6, which serves as a heat shield for the material layer 5, but has an equal or larger diameter.
  • an air gap 7 is provided, which further improves the thermal insulation properties.
  • Fig. 3 an alternative embodiment of the disc spring is shown, which is designated in this figure by the reference numeral 4 'in their entirety. All other corresponding parts have the same reference numerals as in Fig. 2 Mistake.
  • Fig.2 and 3 illustrates the material layer 6 in both cases, a flat disc.

Landscapes

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

Claims (8)

  1. Turbocompresseur (1) comprenant :
    - un carter de turbine (2) d'un rotor de turbine ;
    - une cartouche (K) disposée dans le carter de turbine (2) pour la géométrie de turbine variable ;
    - un carter de support (3), qui est disposé entre le carter de turbine (2) et un carter de compresseur d'un rotor de compresseur et dans lequel est disposé un agencement de palier pour un arbre (W), qui porte le rotor de turbine et le rotor de compresseur ; et
    - un ressort à disque (4 ; 4') qui est disposé entre la cartouche (K) et le carter de support (3) et qui est constitué d'au moins deux couches de matériau (5, 6), dont une couche de matériau (6) sert de couche de protection thermique pour l'autre couche de matériau (5) formant la couche de ressort à disque,
    caractérisé en ce que
    - la couche de ressort à disque (5) est réalisée en forme de pot avec un bord rehaussé (13) périphérique, et
    - la couche de protection thermique (6) est réalisée sous forme de disque plan sur lequel la couche de ressort à disque (5) repose dans l'état de montage avec son bord rehaussé (13) périphérique.
  2. Turbocompresseur selon la revendication 1, caractérisé en ce qu'un entrefer (7) est disposé entre les couches de matériau (5, 6).
  3. Turbocompresseur selon la revendication 1 ou 2, caractérisé en ce que la couche de matériau (5) fixe la cartouche (K) axialement dans le carter de turbine (2).
  4. Turbocompresseur selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les couches de matériau (5, 6) sont connectées l'une à l'autre d'une seule pièce.
  5. Turbocompresseur selon l'une quelconque des revendications 1 à 4, caractérisé en ce que les couches de matériau (5, 6) sont des pièces séparées.
  6. Turbocompresseur selon l'une quelconque des revendications 1 à 5, caractérisé en ce que les couches de matériau (5, 6) se composent du même matériau.
  7. Turbocompresseur selon l'une quelconque des revendications 1 à 5, caractérisé en ce que les couches de matériau (5, 6) se composent de matériaux différents.
  8. Turbocompresseur selon l'une quelconque des revendications 1 à 6, caractérisé en ce que la couche de matériau (6) constitue une isolation thermique pour la couche de matériau (5).
EP04029586A 2004-12-14 2004-12-14 Turbocompresseur Active EP1672177B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP04029586A EP1672177B1 (fr) 2004-12-14 2004-12-14 Turbocompresseur
JP2005355641A JP4851178B2 (ja) 2004-12-14 2005-12-09 ターボ過給機
KR1020050122793A KR101149083B1 (ko) 2004-12-14 2005-12-13 터보차저
CN2005101317221A CN1807847B (zh) 2004-12-14 2005-12-13 涡轮增压器
US11/300,066 US7600969B2 (en) 2004-12-14 2005-12-14 Turbocharger

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04029586A EP1672177B1 (fr) 2004-12-14 2004-12-14 Turbocompresseur

Publications (2)

Publication Number Publication Date
EP1672177A1 EP1672177A1 (fr) 2006-06-21
EP1672177B1 true EP1672177B1 (fr) 2011-11-23

Family

ID=34927770

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04029586A Active EP1672177B1 (fr) 2004-12-14 2004-12-14 Turbocompresseur

Country Status (5)

Country Link
US (1) US7600969B2 (fr)
EP (1) EP1672177B1 (fr)
JP (1) JP4851178B2 (fr)
KR (1) KR101149083B1 (fr)
CN (1) CN1807847B (fr)

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EP1816317B1 (fr) * 2006-02-02 2013-06-12 IHI Corporation Turbocompresseur à géométrie variable
CN101395358B (zh) * 2006-03-14 2013-11-20 博格华纳公司 涡轮增压器
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US9903225B2 (en) 2015-03-09 2018-02-27 Caterpillar Inc. Turbocharger with low carbon steel shaft
US9683520B2 (en) 2015-03-09 2017-06-20 Caterpillar Inc. Turbocharger and method
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US9890788B2 (en) 2015-03-09 2018-02-13 Caterpillar Inc. Turbocharger and method
US10006341B2 (en) 2015-03-09 2018-06-26 Caterpillar Inc. Compressor assembly having a diffuser ring with tabs
US9739238B2 (en) 2015-03-09 2017-08-22 Caterpillar Inc. Turbocharger and method
US9777747B2 (en) 2015-03-09 2017-10-03 Caterpillar Inc. Turbocharger with dual-use mounting holes
US20180252160A1 (en) * 2015-08-28 2018-09-06 Borgwarner Inc. Turbocharger with insulation device
JP6644130B2 (ja) * 2016-03-07 2020-02-12 三菱重工エンジン＆ターボチャージャ株式会社 ターボチャージャー
CN109891056B (zh) * 2016-11-02 2022-06-24 博格华纳公司 具有多部件涡轮壳体的涡轮
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DE102018218395A1 (de) * 2018-10-26 2020-04-30 BMTS Technology GmbH & Co. KG Abgasturbolader
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CN112576365A (zh) * 2020-11-18 2021-03-30 潍柴动力股份有限公司 发动机及其控制方法
DE102021108686A1 (de) * 2021-04-07 2022-10-13 Borgwarner Inc. Turbinenanordnung mit separater leiteinrichtung
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Also Published As

Publication number Publication date
CN1807847A (zh) 2006-07-26
CN1807847B (zh) 2011-10-05
US7600969B2 (en) 2009-10-13
JP4851178B2 (ja) 2012-01-11
JP2006170200A (ja) 2006-06-29
KR101149083B1 (ko) 2012-05-25
EP1672177A1 (fr) 2006-06-21
KR20060067864A (ko) 2006-06-20
US20060127244A1 (en) 2006-06-15

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