EP2470753A1 - Turbine à gaz d'échappement pour un système de turborécupération - Google Patents

Turbine à gaz d'échappement pour un système de turborécupération

Info

Publication number
EP2470753A1
EP2470753A1 EP10742761A EP10742761A EP2470753A1 EP 2470753 A1 EP2470753 A1 EP 2470753A1 EP 10742761 A EP10742761 A EP 10742761A EP 10742761 A EP10742761 A EP 10742761A EP 2470753 A1 EP2470753 A1 EP 2470753A1
Authority
EP
European Patent Office
Prior art keywords
bearing
exhaust gas
turbine
housing
pinion
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Withdrawn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
EP10742761A
Other languages
German (de)
English (en)
Inventor
Thomas Figler
Markus Kley
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.)
Voith Patent GmbH
Original Assignee
Voith Patent GmbH
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 Voith Patent GmbH filed Critical Voith Patent GmbH
Publication of EP2470753A1 publication Critical patent/EP2470753A1/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Withdrawn legal-status Critical Current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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/54—Systems consisting of a plurality of bearings with rolling friction
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/02—Adaptations for driving vehicles, e.g. locomotives
    • 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
    • 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
    • F01D25/166—Sliding contact bearing
    • 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
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C21/00—Combinations of sliding-contact bearings with ball or roller bearings, for exclusively rotary movement
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
    • F16C27/02—Sliding-contact bearings
    • 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
    • F05D2240/50—Bearings
    • F05D2240/53—Hydrodynamic or hydrostatic bearings
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/12—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load
    • F16C17/18—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with floating brasses or brushing, rotatable at a reduced speed
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines
    • F16C2360/24—Turbochargers
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
    • F16C27/04—Ball or roller bearings, e.g. with resilient rolling bodies
    • F16C27/045—Ball or roller bearings, e.g. with resilient rolling bodies with a fluid film, e.g. squeeze film damping
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present invention relates to an exhaust gas turbine for a turbo-compound system, that is, a system in a drive train, in particular
  • Vehicle powertrain with an internal combustion engine for driving the
  • a Abgaspiturbine in the exhaust stream, a Abgassonurbine is arranged.
  • the exhaust gas turbine can be arranged for example in the exhaust stream behind the turbine of a turbocharger or additionally drive a compressor for charging the engine.
  • the exhaust gas turbine By means of the exhaust gas turbine, the exhaust gas is deprived of energy and in
  • the present invention has for its object to provide a Abgaspiturbine for a turbo-compound system, which allows the
  • the invention is based on the knowledge that the increasing
  • Efficiency decrease is caused by the fact that in the gear transmission between the exhaust gas turbine and the output shaft of the internal combustion engine, which serves for transmitting the drive power from the exhaust gas turbine to the output shaft, which is usually designed as a crankshaft, in
  • the teeth of the pinion are more affected by this wear compared to the teeth of the gear, since the pinion has a much smaller outer diameter than the gear and thus relative to the individual tooth of the pinion this much more often rolls on the teeth of the gear than a individual tooth of the gear on the teeth of the pinion rolls.
  • the superposition of the forces from the turbine shaft dynamics and the gear forces leads to a deflection of the turbine shaft at that axial end, which is associated with the pinion. Also at its opposite axial end, a corresponding deflection of the turbine shaft take place.
  • the turbine shaft according to the invention is stored in the region of the pinion by means of a radial roller bearing despite the high rotational speeds, whereas it is mounted in the region of the impeller of the exhaust gas turbine by means of a radial plain bearing.
  • the radial clearance in the radial roller bearing are lower than in a radial plain bearing.
  • the turbine shaft is mounted in the region of the impeller by means of a floating bush in a housing which forms an outer oil-filled bearing gap with respect to the housing and an inner oil-filled bearing gap with respect to the turbine shaft and is rotatable relative to the housing and the turbine shaft, and Furthermore, the turbine shaft is mounted in the region of the pinion by means of a simple sliding bearing, thus a sliding bearing, which forms a single oil-filled bearing gap in the radial direction between the turbine shaft and the housing.
  • the housing may be the same component, in which the turbine shaft is also mounted in the region of the impeller. Alternatively, however, a separate component, referred to here as a further housing, may be provided.
  • the bearing in the region of the impeller also differs from the bearing in the region of the pinion by at least one oil-filled bearing gap.
  • the bearing in the region of the impeller is designed as a rolling bearing, which is enclosed by a sliding bearing with at least one oil-filled bearing gap and / or surrounds such a sliding bearing.
  • the bearing in the area of the pinion is as simple
  • Rolling executed, that is, in the bearing gap between the turbine shaft and the housing rolling elements are arranged, and there is no further only oil-filled bearing gap radially outside or radially provided within the rolling bearing.
  • the turbine shaft which carries the impeller of the exhaust gas turbine, which is designed in particular as a radial-axial turbine, supported in the region of the pinion by means of a Axialgleitlager
  • the Axialgleitlager and the Radialgleitlager may include the radial roller bearing in particular on both sides between them .
  • an axial roller bearing may be provided for supporting the turbine shaft, in particular in the region of the pinion, wherein a single combined axial-radial roller bearing is advantageous.
  • the thrust bearing whether designed as a rolling bearing or plain bearings, also be arranged at a different position, for example in the region of the impeller.
  • a single thrust bearing for supporting the turbine shaft is provided. Furthermore, can
  • the rolling bearing may have rolling elements made of a conventional rolling element material, in particular metal. Particularly advantageously, the rolling elements are made of ceramic.
  • rolling elements instead of balls as rolling elements, as they can be used in principle in an embodiment of the invention, rolling elements in cylindrical, conical or needle shape used, usually between an inner ring and an outer ring of the bearing. To the bearing wear of the bearing at the first
  • an oil damper can be integrated in the bearing or between the bearing and a housing in which the bearing is accommodated, and / or between the bearing and the turbine shaft.
  • Such an oil damper can be made, for example be that a bearing ring, which may be integral with the inner ring or the outer ring or may be provided in addition to this and in particular is mounted on the inner ring or the outer ring, in
  • a lubricating oil-filled annular gap is formed between the turbine shaft and the housing, and between the bearing ring and the housing and / or between the bearing ring and the turbine shaft.
  • pressure oil can be introduced into the annular gap.
  • a corresponding oil-filled annular gap may additionally or alternatively also be provided in or on the radial sliding bearing by there
  • the bearing rings have in particular a cylindrical shape, but may also have differently shaped shapes, for example a conical shape or a stepped shape.
  • the impeller of the exhaust gas turbine can be arranged,
  • Flying bearing here means that viewed in the axial direction outside of the corresponding component - pinion or impeller - no further bearing for supporting the turbine shaft and in particular for the storage of the corresponding component is provided. Under bearing in the sense of the present description are always understood such support points in the turbo-compound system in which two components rotate at different speeds to each other or in which one component rotates and the other is held stationary, that does not revolve.
  • Figure 1 shows a first inventively designed drive connection between an exhaust gas turbine and one with the output shaft of the
  • FIG. 2 shows a modified embodiment with respect to FIG. 1, in which the rolling bearing is designed as a combined axial-radial rolling bearing;
  • Figure 3 shows an embodiment according to the figure 1 with an additional
  • Crimping oil damper which encloses the radial rolling bearing in the circumferential direction
  • FIG. 4 shows an embodiment according to the second invention
  • FIG. 5 shows an embodiment according to the third invention
  • FIG. 1 shows an exhaust gas turbine 1 and its impeller 1.1 with a plurality of turbine blades 1.2, which are located in the exhaust gas flow (see FIGS
  • the exhaust gas turbine 1 is designed as a radial-axial turbine, that is, the turbine blades 1.2 are flowed radially from the outside of the exhaust, which then leaves them in the axial direction (flows).
  • the impeller 1.1 is supported by a turbine shaft 2 or is made in one piece with this.
  • the impeller 1.1 includes the Exhaust gas turbine at one axial end of the turbine shaft 2 flush with this from.
  • a pinion 3 is disposed on the turbine shaft 2 and is supported thereby.
  • the pinion 3 is pushed onto the turbine shaft 2 and is there by a suitable mechanical lock or through
  • the pinion 3 could also be made in one piece with the turbine shaft 2.
  • the pinion 3 meshes with a gear 11 which is rotatably connected to the impeller 12 of a hydrodynamic coupling 13.
  • the gear 11 is mounted together with the impeller 12 on a clutch shaft 14, that is, runs at a different speed than the shaft.
  • the clutch shaft 14 carries the turbine 15 of the hydrodynamic coupling, which together with the impeller 12 forms a hydrodynamic working space 16, rotatably.
  • the illustrated bearing of the impeller 12 of the hydrodynamic coupling or the coupling shaft 14 can be carried out independently of the configuration of the arrangement or mounting of the turbine shaft 2 in the form shown, in particular with four in the axial direction one behind the other connected rolling bearings 18, of which the two middle to a double bearing can be summarized. It is particularly pointed out that this bearing arrangement or generally the mounting of the coupling shaft 14 and the associated components in the region of the hydrodynamic coupling 13, in particular in turbo-compound systems without the invention illustrated storage of the turbine shaft of the exhaust gas turbine with a
  • Radial sliding bearing and a radial roller bearing can be performed.
  • the turbine shaft 2 is mounted in the region of the impeller 1.1 by means of a radial sliding bearing 4 and in the region of the pinion 3 by means of a radial roller bearing 5. Both bearings 4, 5 are viewed in the axial direction between the pinion 3 and the impeller 1.1 and arranged single
  • Both the radial roller bearing 5 and the radial sliding bearing 4 are enclosed by a common housing 7 in the circumferential direction.
  • the bearings can, as indicated, be supplied via a pressure oil system 19 with pressure oil or lubricating oil (without overpressure).
  • the radial sliding bearing 4 has a so-called
  • Floating bushing that is, viewed in the radial direction, two oil-filled annular gaps are arranged one behind the other.
  • One or both annular gaps may be filled with pressurized oil to exert a damping effect on the dynamic forces to which the turbine shaft 2 is subject.
  • the radial sliding bearing 4 has a bearing ring 4.1, in particular in cylindrical form, which is arranged in the radial direction of the turbine shaft 2 between the turbine shaft 2 and the housing 7, and forms the two said annular gaps 8, 9 with the housing 7 or with the turbine shaft 2 ,
  • the radial roller bearing 5 is free of such a floating bushing or a Quetschöldämpfer. Rather, the bearing outer ring (not shown) of the radial roller bearing 5 is used directly and non-rotatably in the housing 7 and the bearing inner ring (not shown) mounted directly and rotationally fixed on the turbine shaft 2. Between the bearing outer ring and the bearing inner ring a plurality of rolling elements are arranged so that the bearing outer ring and the bearing inner ring on this rolling elements (not shown) roll on each other.
  • the turbine shaft 2 is held in the axial direction by an axial sliding bearing 6. This is positioned in the region of the pinion 3 and, as shown, can be mounted on the outside of the housing 7 and, in particular, be covered by a bearing plate 20 from the outside.
  • the axial sliding bearing 6 comprises a bearing ring 6.1 which is fixedly mounted in or on the housing 7 and which is supported by means of a respective lubricating oil film on two spacers which are fixedly mounted in the axial direction on the turbine shaft 2.
  • the embodiment according to FIG. 2 differs from that of FIG. 1 in that the turbine shaft 2 is free of an axial sliding bearing and that
  • Radial rolling bearing 5 at the same time has a thrust bearing function.
  • the radial roller bearing 5 (then axial-radial roller bearing) either via rolling elements on
  • FIG. 3 differs from that of FIG. 1 in that the radial roller bearing 5 is likewise provided with a so-called
  • a bearing ring 5.1 is provided for this purpose, in which the outer ring of the radial rolling bearing 5 is pressed. Between the bearing ring 5.1 and the housing 7, an annular gap is formed, which is filled with lubricating oil, in particular pressure oil. As a result, an attenuation of the turbine shaft 2 and the bearing 5 acting dynamic forces achieved, and the wear of the bearing can be reduced.
  • the bearing ring 5.1 for example, as indicated, be fixed by Seegerringe in the axial direction, similar to that for the bearing ring 4.1 of the radial slide bearing 4 shown in the figures.
  • the pressure oil in the annular gap 10 between the bearing ring 5.1 and the housing 7 can, for example, in turn be provided by the pressure oil system 19, which is in a corresponding conductive connection with the annular gap 10.
  • Turbine shaft 2 may be provided.
  • the features shown in Figures 1, 2 and 3 may be provided independently or in combinations not shown.
  • the turbine shaft 2 of a turbo-compound system according to the invention runs, for example, at speeds of up to 70,000 rpm, in particular at maximum speeds above 20,000, 30,000 or 40,000 rpm.
  • a non-contact or a touching Shaft seal such as tip-to-tip seal, labyrinth seal or with an O-ring
  • the turbine shaft 2 is mounted in the region of the impeller 1.1 by means of a floating bush 21 in a housing 22.
  • the component designated here as a floating bush 21 corresponds in its function to the bearing ring 4.1 according to FIG. 1, and accordingly the radial plain bearing 4 according to FIG.
  • the floating bushing 21 forms an oil-filled outer bearing gap 23 with respect to the housing 22 and with respect to FIG. 4
  • Turbine shaft 2 an inner oil-filled bearing gap 24. Further, the
  • a plurality of plain bearings next to the pinion 3 may be provided, in particular exactly two plain bearings, preferably one each on each side of the pinion 3, which are then either all or both executed as a simple sliding bearing, or of which only one or more, but not all, can be designed as a simple slide bearing and the remaining or the remaining in particular as a floating bush bearing.
  • An axial slide bearing 6 is also provided in the embodiment shown in FIG. 4, in this special case on the side of the simple slide bearing 25 facing away from the impeller 1.1 next to the pinion 3.
  • FIG. 5 illustrates the third approach according to the present invention.
  • the pinion 3 is not stored on the fly, but between the camp next to the pinion 3 and the bearing next to the impeller 1.1.
  • the turbine shaft 2 is mounted in the region of the rotor 1.1 by means of a roller bearing 27, which is enclosed by a sliding bearing 28 with an oil-filled bearing gap 29.
  • a sliding bearing 28 In the sliding bearing 28 rotates the outer
  • the two bearings 27, 30 according to the embodiment in Figure 5 therefore differ from each other in that the impeller bearing is mounted as a roller bearing 27 via a sliding bearing 28 with a bearing gap 29 in the housing 22 (or other suitable component), whereas the Rolling bearings 30 next to the pinion 3 is mounted directly in the housing 22 (or other suitable component), that is without the interposition of a sliding bearing.
  • Bearing gap be provided outside of the rolling bearing 27 by the rolling bearing 27 is mounted for example in a floating bush, which forms a first oil-filled bearing gap against the rolling bearing 27 and a second oil-filled bearing gap relative to the housing 22 or other suitable component.
  • a floating bush bearing could be provided with two oil-filled bearing gaps or even an oil-filled position gap.
  • the exhaust gas turbine which is in a drive connection with a compressor for fresh air of the internal combustion engine, in particular directly via a rigid shaft, and which is arranged in particular in the flow direction of the exhaust gas in front of the exhaust gas turbine, which can be used for the exhaust gas turbine shown storage concept, also regardless of the provision of a turbo-compound system
  • Turbo compressor for a turbo-compound system or for a turbocharger, in particular a motor vehicle applicable. With such a will
  • the turbine shaft expediently designates the turbine shaft as a drive shaft and the impeller is a compressor impeller, not a turbine impeller. Further, the impeller is driven by drive power introduced to the drive shaft via the pinion, and compresses a fresh air flow supplied to the engine instead of converting exhaust gas energy into drive power.
  • the drive power can be provided by a turbine, in particular an exhaust gas turbine or by the crankshaft of the internal combustion engine. Instead of an exhaust gas turbine, another gas turbine or even a steam turbine is conceivable, For example, a steam turbine in a steam cycle, wherein the steam is generated in particular by means of exhaust gas energy.
  • the features described above apply correspondingly to the inventive design of a turbocompressor.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Support Of The Bearing (AREA)
  • Rolling Contact Bearings (AREA)
  • Sliding-Contact Bearings (AREA)
  • Mounting Of Bearings Or Others (AREA)

Abstract

L'invention concerne une turbine à gaz d'échappement (1) pour un système de turborécupération, en particulier d'un véhicule automobile. La turbine comprend un arbre de turbine (2) qui porte, à sa première extrémité ou dans la zone de la première extrémité, une roue mobile (1.1) pour l'alimentation en flux de gaz d'échappement provenant d'un moteur à combustion interne, afin de convertir l'énergie des gaz d'échappement en puissance d'entraînement. L'arbre de turbine porte, à sa seconde extrémité, un pignon (3) conçu de manière à venir en liaison d'entraînement avec le vilebrequin du moteur à combustion interne, afin de transmettre la puissance d'entraînement sur le vilebrequin. L'invention est caractérisée en ce que l'arbre de turbine est monté, dans la zone de la roue mobile, au moyen d'un palier lisse radial (4) et, dans la zone du pignon, au moyen d'un palier à roulement radial (5).
EP10742761A 2009-08-27 2010-08-06 Turbine à gaz d'échappement pour un système de turborécupération Withdrawn EP2470753A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009038772A DE102009038772A1 (de) 2009-08-27 2009-08-27 Abgasnutzturbine für ein Turbo-Compound-System
PCT/EP2010/004817 WO2011023282A1 (fr) 2009-08-27 2010-08-06 Turbine à gaz d'échappement pour un système de turborécupération

Publications (1)

Publication Number Publication Date
EP2470753A1 true EP2470753A1 (fr) 2012-07-04

Family

ID=43037158

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10742761A Withdrawn EP2470753A1 (fr) 2009-08-27 2010-08-06 Turbine à gaz d'échappement pour un système de turborécupération

Country Status (8)

Country Link
US (1) US20120297770A1 (fr)
EP (1) EP2470753A1 (fr)
JP (1) JP2013503283A (fr)
CN (1) CN102421992A (fr)
BR (1) BR112012001960A2 (fr)
DE (1) DE102009038772A1 (fr)
RU (1) RU2012106824A (fr)
WO (1) WO2011023282A1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011007250A1 (de) 2011-04-13 2012-10-18 Schaeffler Technologies AG & Co. KG Turboladerkartusche mit gleitlager gestütztem Wälzlager
DE102011087606A1 (de) 2011-12-01 2013-06-06 Robert Bosch Gmbh Kraftfahrzeugsystemeinrichtung sowie Verfahren zum Betreiben einer Kraftfahrzeugsystemeinrichtung
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DE102009038772A1 (de) 2011-03-03
CN102421992A (zh) 2012-04-18
RU2012106824A (ru) 2013-10-10
WO2011023282A1 (fr) 2011-03-03
JP2013503283A (ja) 2013-01-31
DE102009038772A8 (de) 2011-06-01
BR112012001960A2 (pt) 2019-09-24

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