EP2334961A1 - Dispositif permettant d'étanchéifier un logement de palier d'un turbocompresseur - Google Patents

Dispositif permettant d'étanchéifier un logement de palier d'un turbocompresseur

Info

Publication number
EP2334961A1
EP2334961A1 EP09814099A EP09814099A EP2334961A1 EP 2334961 A1 EP2334961 A1 EP 2334961A1 EP 09814099 A EP09814099 A EP 09814099A EP 09814099 A EP09814099 A EP 09814099A EP 2334961 A1 EP2334961 A1 EP 2334961A1
Authority
EP
European Patent Office
Prior art keywords
rotor
groove
sealing ring
guided
bearing housing
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.)
Withdrawn
Application number
EP09814099A
Other languages
German (de)
English (en)
Inventor
Dominique Bochud
Tobias Gwehenberger
Joel Schlienger
Christoph Häge
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.)
Accelleron Industries AG
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 EP09814099A priority Critical patent/EP2334961A1/fr
Publication of EP2334961A1 publication Critical patent/EP2334961A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/441—Free-space packings with floating ring
    • 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
    • F05D2240/55—Seals

Definitions

  • the invention relates to the field of exhaust gas turbochargers.
  • It relates to a device for sealing a bearing housing of an exhaust gas turbocharger according to the preamble of claim 1 and an exhaust gas turbocharger according to claim 5 with such a device.
  • an exhaust gas turbocharger the exhaust gases of an internal combustion engine are used for compression for the combustion air supplied to the internal combustion engine.
  • the turbocharger on a rotor with a turbine and a compressor sitting on a common shaft of the rotor.
  • the exhaust gases of the internal combustion engine are relaxed in the turbine and converted into rotational energy.
  • the obtained rotational energy is transmitted by means of the shaft to the compressor, which compresses the air supplied to the internal combustion engine.
  • a portion of the rotor is rotatably guided in a bearing housing on axial and radial bearings, which bearings are lubricated with a lubricant, in particular oil.
  • a lubricant in particular oil.
  • the section of the rotor mounted in the bearing housing is guided out of the bearing housing via two seals, one of which is the one
  • the sealing of the lubricant receiving bearing housing of the exhaust gas turbocharger toward the turbine shaft can be done with a designed as a piston ring seal ring, which is arranged with axial and radial play in a run around the axis of rotation of the rotor, annular groove of the rotor and clamped with bias in a seat of the bearing housing is.
  • a piston ring seal ring which is arranged with axial and radial play in a run around the axis of rotation of the rotor, annular groove of the rotor and clamped with bias in a seat of the bearing housing is.
  • Requirement may also be provided two or more sealing rings, which are also generally formed in each case as a piston ring and clamped with bias in other seats of the housing.
  • the device according to EP 1 507 106 B1 has a sealing ring designed as a piston ring with two regions of different materials, wherein the first region is made of a soft, easily abradable material and a Gleitf kaue, which cooperates with a rotor of the supercharger, and a second region is made of a high temperature resistant material.
  • a sealing ring has the advantage that it permanently enables the area required for the sealing ring to be clamped in a bearing housing of the supercharger with the region of highly heat-resistant material and at the same time optimally supports the desired grinding process between the sealing ring and the rotor with the region of soft, easily abradable material.
  • DE 1 247 097 B and EP 1 536 167 A1 describe shaft seals with a sealing ring mounted in a groove, in which the heat input into the sealing ring is reduced by a small dimensioned end face of the sealing ring (DE 1 247 097 B: column 1, lines 40 to 47 and Fig. 1.
  • EP 1 536 167 A1 column 10, paragraphs [0082] and [0083]).
  • the object is to provide a device for sealing a bearing housing of an exhaust gas turbocharger of the type mentioned and an exhaust gas turbocharger with such a device, which is difficult under Operating conditions of the loader characterized by high reliability and a long service life.
  • the exhaust gas turbocharger facing edge of a groove is formed annularly guided around the axis recess, the recess is bounded radially outwardly by an annular body molded into the rotor, the annular body forms a portion of a Outer surface of the rotor and the ring body has a to the outer surface subsequent, radially aligned annular edge, which serves to reduce the size of a grinding surface, which is formed when striking the sealing ring to the groove flank.
  • the reduced grinding surface keeps the heat input into the sealing ring small.
  • Heat input into the sealing ring can occur when the sealing ring abuts the turbine-side flank of the groove mounted on a rotor of the supercharger and in this case by a grinding process frictional heat from the rotor is entered via the grinding surface formed during abutment in the sealing ring.
  • An abutment of the sealing ring on the turbine-side groove flank is possible if the pressure of an exhaust gas of an internal combustion engine-containing mass flow on the turbine side of the exhaust gas turbocharger is lower than the pressure in the bearing housing, as is the case with an idling internal combustion engine.
  • the groove flank can be easily manufactured and is achieved by the special design of the groove flank a large distance between the bottom of the groove and the annular edge. In this way, a good guidance of the sealing ring is ensured in the groove and at the same time prevents dirt from a mass flow passed in the turbocharger passes into the groove because of the radially outwardly displaced annular edge.
  • Fig. 1 is a plan view of an axially guided section through a
  • FIG. 2 is an enlarged representation of a shaft seal shown in FIG. 1, designed according to the prior art, before the beginning of a grinding process
  • FIG. 2 is an enlarged view of an exhaust gas turbocharger shown in FIG.
  • Fig. 1 shows schematically a partial view of an exhaust gas turbocharger with a fixedly arranged housing G and a rotatable about an axis A rotor R.
  • a fixed on a shaft 3 compressor wheel 1 of an exhaust gas turbocharger is indicated.
  • the shaft 3 in turn is connected to a turbine wheel 2 of the exhaust gas turbocharger on the right side.
  • the turbine wheel 2 comprises vanes, not shown, via which it is driven by an exhaust gas flow generated in an internal combustion engine.
  • the compressor wheel also includes blades, not shown.
  • axial and radial bearings L are arranged, which absorb the axial and radial forces occurring in the leadership of the rotor R.
  • the housing G encloses the rotor R and has a housing part 4 designed as a fixed bearing housing, which accommodates the axial and radial bearings L and a section of the rotor R and shields them from remaining housing parts in which the part loaded with the hot exhaust gas
  • Turbine 2 of the exhaust turbine and provided for compressing air compressor wheel 1 are arranged.
  • the axial and radial bearings L are protected from exhaust gas or compressed air containing mass flows, each having high pressure, high temperature and high speed. So that these mass flows can not act in the bearing housing 4 and also no lubricating oil can escape from the bearing housing 4, between the bearing housing 4 and the rotor R two annular guided around the axis of rotation
  • a shaft seals D are arranged, of which one at a portion of Bearing housing 4 is located, through which the rotor is guided in the compressor, and the other at a portion of the bearing housing, through which the rotor is guided in the exhaust gas turbine.
  • a turbine-side arranged shaft seal D according to the prior art is shown schematically in Figures 2 and 3.
  • This seal comprises a sealing ring 5, which is arranged in a ring running around the rotational axis of the groove 22 of the rotor R and formed as a piston ring.
  • the sealing ring 5 and the groove 22 have along the axis of rotation cut each having a predominantly rectangular cross-section.
  • the shaft seal D further comprises a seat 43 arranged on the bearing housing 4, on which the sealing ring is largely gas-tight and liquid-tight with an outwardly directed lateral surface, and a radially extending separation gap T guided annularly about the axis of rotation of the rotor R two superimposed sliding surfaces is limited.
  • the one sliding surface is arranged on one end face 51 of the sealing ring 5, the other on a flank 21 of the groove 22.
  • the superimposed sliding surfaces and the very narrow separation gap T prevent the penetration of the exhaust gas mass flow into the bearing housing 4 and the escape of oil from the bearing housing 4th At the same time, they allow a rotation of the rotor R without the sealing ring 5 fastened to the bearing housing 4 heating in an inadmissible manner as a result of sliding friction.
  • the generally metal sealing ring 5 is introduced during assembly with play in the groove 22. Subsequently, a turbine wheel 2 comprehensive section of the rotor R is inserted from the right in the axial direction in the bearing housing 4. Since the housing 4 narrows continuously along the insertion path at one or more points 42 or else continuously, the sealing ring 5 is subjected to radial prestressing and finally jammed on the seat 43 in the bearing housing 4. When the seal D is put into operation for the first time, a grinding-in process takes place in the separation gap T. The fixed to the bearing housing 4 sealing ring 5 is pressed by the indicated in Fig. 2 with arrows high pressure of the exhaust gas mass flow against the rotating edge 21 of the groove 22 and ground from this as from a grinding wheel.
  • an annular recess is ground with a sliding surface 51 delimiting the separating gap T to the right.
  • an axial stop 41 is provided on the bearing housing 4. The axial stop limits the axial displaceability of the sealing ring 5 and thus improves the sealing effect of the seal D. In the operating state of the turbocharger thus takes place at high pressure of the exhaust gas mass flow in the region of the separation gap T no power transmission in the axial direction. The directed in the direction of arrow force on the sealing ring 5 is counteracted by the axial stop 41.
  • an indentation 26 guided annularly around the axis is formed in the flank 23 of the groove 22.
  • the recess undercuts the groove 22 and is bounded radially outward by an annular body 24 molded into the rotor.
  • the annular body 24 forms a portion of an outer surface of the rotor R and has a radially aligned annular edge 25 adjoining the outer surface. This annular edge reduces the size of a grinding surface, which is formed when the sealing ring 5 abuts the groove flank 23. As a result, the amount of heat formed during the grinding process by sliding friction and registered in the sealing ring 5 is reduced.
  • the annular edge is comparatively blunt in comparison.
  • a cylindrical surface 28 formed in the ring body 24 and guided on the annular edge 25 delimits the recess 26 radially outward.
  • the edge 25 is performed in production technology advantageously in general uninterrupted around the axis of rotation of the rotor R, but may also be formed by paragraphs, which are arranged in the circumferential direction of each other at a distance. They additionally reduce the grinding surface and thus ensure that the heat input in the sealing ring is further reduced.
  • the ring body 24 may also include two or more edges, which are arranged substantially coaxially and separated from each other by a guided around the axis A recess.
  • the seal D also further
  • Seals according to the invention can be provided both on the turbine-side and on the compressor-side bearing housing passage of the rotor. If the requirements for the turbocharger allow, a seal according to the invention can be used only on the turbine side, while the compressor-side rotor bushing can be sealed with a seal according to the prior art. LIST OF REFERENCE NUMBERS

Landscapes

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

Abstract

L'invention concerne un dispositif permettant d'étanchéifier un logement de palier (4) d'un turbocompresseur, dont un rotor (R) est guidé dans un compartiment du turbocompresseur chargé d'un flux massique. Le dispositif comprend : une bague d'étanchéité (5) disposée dans une rainure (22) du rotor, un siège (43) disposé sur le logement de palier (4), siège sur lequel la bague d'étanchéité (5) est fixée par une surface latérale extérieure, ainsi qu'une fente de séparation s'étendant radialement, de manière annulaire autour de l'axe de rotation du rotor, ladite fente étant délimitée par deux surfaces de glissement superposées, dont la première est disposée sur une première face frontale (51) de la bague d'étanchéité (5), et la seconde sur un premier flanc (21) de la rainure (22). L'invention a pour but de réduire l'apport de chaleur dans la bague d'étanchéité (5), occasionné, lors du fonctionnement du turbocompresseur, par le frottement de ladite bague d'étanchéité (5). A cet effet, l'invention est caractérisée en ce qu'une cavité (26) logée de manière annulaire autour de l'axe (A) est formée dans le second flanc (23) de la rainure (22), en ce que la cavité (26) est délimitée radialement vers l'extérieur par un corps annulaire (24) formé dans le rotor (R), en ce que le corps annulaire (24) forme une partie d'une surface extérieure du rotor (R), ledit corps annulaire présentant une arête annulaire (25) orientée radialement et se raccordant à la surface extérieure, ladite arête annulaire servant à réduire la grandeur d'une surface de frottement qui se forme lorsque la bague d'étanchéité (5) vient buter contre le second flanc (23) de la rainure.
EP09814099A 2008-09-18 2009-05-20 Dispositif permettant d'étanchéifier un logement de palier d'un turbocompresseur Withdrawn EP2334961A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09814099A EP2334961A1 (fr) 2008-09-18 2009-05-20 Dispositif permettant d'étanchéifier un logement de palier d'un turbocompresseur

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08164600A EP2166259A1 (fr) 2008-09-18 2008-09-18 Dispositif d'étanchéification d'un logement de palier d'un turbocompresseur à gaz d'échappement
PCT/EP2009/056171 WO2010031604A1 (fr) 2008-09-18 2009-05-20 Dispositif permettant d'étanchéifier un logement de palier d'un turbocompresseur
EP09814099A EP2334961A1 (fr) 2008-09-18 2009-05-20 Dispositif permettant d'étanchéifier un logement de palier d'un turbocompresseur

Publications (1)

Publication Number Publication Date
EP2334961A1 true EP2334961A1 (fr) 2011-06-22

Family

ID=40328262

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08164600A Withdrawn EP2166259A1 (fr) 2008-09-18 2008-09-18 Dispositif d'étanchéification d'un logement de palier d'un turbocompresseur à gaz d'échappement
EP09814099A Withdrawn EP2334961A1 (fr) 2008-09-18 2009-05-20 Dispositif permettant d'étanchéifier un logement de palier d'un turbocompresseur

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08164600A Withdrawn EP2166259A1 (fr) 2008-09-18 2008-09-18 Dispositif d'étanchéification d'un logement de palier d'un turbocompresseur à gaz d'échappement

Country Status (7)

Country Link
US (1) US20110162359A1 (fr)
EP (2) EP2166259A1 (fr)
JP (1) JP2012503155A (fr)
KR (1) KR20110050673A (fr)
CN (1) CN102159860A (fr)
DE (1) DE202009007436U1 (fr)
WO (1) WO2010031604A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014011849A1 (de) * 2014-08-08 2016-02-11 Man Diesel & Turbo Se Wellendichtungssystem und Abgasturbolader
FR3031799B1 (fr) 2015-01-19 2017-02-17 Snecma Dispositif d'etancheite ameliore entre un systeme d'injection et un nez d'injecteur de carburant de turbomachine d'aeronef
WO2016203970A1 (fr) 2015-06-16 2016-12-22 株式会社Ihi Structure d'étanchéité et superchargeur
DE102016113198A1 (de) * 2016-07-18 2018-01-18 Abb Turbo Systems Ag Kolbenring, Turbolader mit Kolbenring und Verfahren zum Herstellen eines Kolbenrings
CN106871966B (zh) * 2017-03-24 2020-04-10 中国北方发动机研究所(天津) 增压器密封环产生轴向滑移的温度与压力测量装置
JP6373502B1 (ja) * 2017-05-30 2018-08-15 Ｔｐｒ株式会社 過給機用コンプレッサハウジングの製造方法および過給機用コンプレッサハウジング
US10724533B2 (en) * 2018-03-30 2020-07-28 Borgwarner Inc. Bearing anti-rotation spacer with integrated oil deflection features
CN209569264U (zh) * 2018-08-09 2019-11-01 博格华纳公司 支承系统和增压装置
DE102019101258A1 (de) 2019-01-18 2020-07-23 Bayerische Motoren Werke Aktiengesellschaft Abgasturbolader
CN117553010A (zh) * 2022-08-05 2024-02-13 盖瑞特动力科技(上海)有限公司 具有用于压缩机的叶片式扩散器的涡轮增压器

Family Cites Families (10)

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Publication number Priority date Publication date Assignee Title
GB962133A (en) 1961-04-06 1964-07-01 Brown Tractors Ltd New or improved sealing means
DE1247097B (de) * 1965-12-24 1967-08-10 Goetzewerke Dichtring
US3887198A (en) * 1973-10-26 1975-06-03 Caterpillar Tractor Co Pressure balanced ring seal
JPS53162264U (fr) * 1977-05-26 1978-12-19
GB2149860B (en) * 1983-11-18 1987-08-05 Trw Cam Gears Ltd Valve assemblies having sealing means
CH689427A5 (de) * 1991-07-09 1999-04-15 Daimler Benz Ag Abdichtung an einem rotierenden Koerper.
JP3437312B2 (ja) * 1995-02-16 2003-08-18 株式会社リケン シールリングおよびシール装置
GB2359863B (en) * 2000-03-04 2003-03-26 Alstom Turbocharger
AU2003241928A1 (en) * 2002-05-29 2003-12-12 Nok Corporation Seal ring
EP1507106B1 (fr) * 2003-08-15 2007-07-18 ABB Turbo Systems AG Garniture d'étanchéité rotative

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010031604A1 *

Also Published As

Publication number Publication date
DE202009007436U1 (de) 2009-09-10
EP2166259A1 (fr) 2010-03-24
CN102159860A (zh) 2011-08-17
KR20110050673A (ko) 2011-05-16
WO2010031604A1 (fr) 2010-03-25
JP2012503155A (ja) 2012-02-02
US20110162359A1 (en) 2011-07-07

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