EP2772652A2 - Partition for sealing the rear section of a radial compressor - Google Patents

Partition for sealing the rear section of a radial compressor Download PDF

Info

Publication number
EP2772652A2
EP2772652A2 EP14155860.1A EP14155860A EP2772652A2 EP 2772652 A2 EP2772652 A2 EP 2772652A2 EP 14155860 A EP14155860 A EP 14155860A EP 2772652 A2 EP2772652 A2 EP 2772652A2
Authority
EP
European Patent Office
Prior art keywords
intermediate wall
bearing housing
compressor
bearing
sealing
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.)
Granted
Application number
EP14155860.1A
Other languages
German (de)
French (fr)
Other versions
EP2772652A3 (en
EP2772652B1 (en
Inventor
Andrea Vacca
Matthias Jarusel
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
Publication of EP2772652A2 publication Critical patent/EP2772652A2/en
Publication of EP2772652A3 publication Critical patent/EP2772652A3/en
Application granted granted Critical
Publication of EP2772652B1 publication Critical patent/EP2772652B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/10—Shaft sealings
    • F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage
    • F05D2260/6022—Drainage of leakage having past a seal

Definitions

  • the invention relates to the field of exhaust gas turbochargers of supercharged internal combustion engines.
  • It relates to an intermediate wall for sealing the rear space of the compressor wheel of a centrifugal compressor with respect to a bearing space enclosed by a bearing housing, a bearing device for supporting the rotor of a compressor with such a partition, a centrifugal compressor with such a bearing device and an exhaust gas turbocharger with such a centrifugal compressor.
  • Exhaust gas turbochargers are used to increase the performance of internal combustion engines.
  • the exhaust gas turbine of the exhaust gas turbocharger is charged with the exhaust gases of the internal combustion engine and their kinetic energy used for sucking and compressing air for the internal combustion engine.
  • the impellers of the turbine and the compressor are connected to each other via a shaft mounted in a bearing housing shaft.
  • sealing air is often used to protect the storage area from penetrating hot exhaust gases from the flow channel or to actively cool the turbine wheel.
  • This barrier air may be externally supplied or removed from the airflow downstream of the compressor.
  • sealing air can also be discharged from the rear space of the compressor wheel, which brings about the positive effect of relieving the axial load on the compressor wheel, since the pressure in the rear space of the compressor wheel is reduced due to the discharge of the sealing air.
  • the air in the rear space of the compressor wheel penetrates from the flow channel of the compressor wheel in this area, since the gap between the rapidly rotating and larger temperature fluctuations exposed compressor wheel can not seal arbitrarily well.
  • the air discharged in this way is guided through several components to the turbine side. This results in housing transitions, which must be sealed against leakage of the sealing air.
  • the at least one barrier air transition between the immediately adjacent to the VerĂȘtrrad Wegraum intermediate wall and the bearing housing has hitherto been realized by means of a respective round pin, which was brought to the partition and was received in a corresponding opening in the bearing housing.
  • the at least one pin on the otherwise essentially rotationally symmetrical intermediate wall was produced by the complex machining method of circular milling.
  • the object of the invention is to optimize the intermediate wall for sealing the rear space of the compressor wheel of a centrifugal compressor, which has at least one bore for Sperr Kunststoffab Installation, with respect to a simplified production.
  • the intermediate wall has a circumferential, rotationally symmetrical shaped mounting flange which is provided for fastening the intermediate wall to the adjacent bearing housing and which has a planar contact surface for resting on a contact surface of the bearing housing.
  • a plurality of bores are embedded in a virtual circular line in the mounting flange, wherein the bores comprise at least one sealing air channel and a plurality of circumferentially distributed on the virtual circle arranged holes for receiving fasteners.
  • the intermediate wall is designed as a rotationally symmetrical disk, which can be brought into its final shape in production by the machining process of turning and without further milling.
  • a drill is necessary, which can also be used for drilling the holes for receiving the fasteners.
  • Fig. 1 shows an exhaust gas turbocharger according to the prior art with an axially flowed exhaust gas turbine 10 and a centrifugal compressor 70.
  • the partially cut exhaust gas turbocharger has a rotor consisting of turbine wheel 11, compressor 71 and intermediate shaft 20 on.
  • the rotor is rotatably mounted in the bearing housing 30.
  • the exhaust gas originating from the combustion chambers of an internal combustion engine is guided through the gas inlet housing 12 onto the rotor blades of the turbine wheel 11. Subsequently, the exhaust gas is collected in the diffuser region of the gas outlet housing 13 and discharged via the exhaust system.
  • the compressor wheel driven by the turbine via the shaft draws in fresh air in order to compress it and supply it under higher pressure to the combustion chambers of the internal combustion engine.
  • sealing air is often used on the turbine side to protect the storage area from penetrating hot exhaust or to cool the turbine hub.
  • This sealing air is usually a Beitechnische the VerĂȘtrradschubentlastung, in which the air pressure in the rear space the compressor wheel is reduced by the air from the flow channel of the compressor in this area penetrating air is removed.
  • Fig. 2 shows a guided along the shaft axis section through the centrifugal compressor of an exhaust gas turbocharger.
  • the compressor wheel 71 is arranged in the compressor housing 72.
  • the compressor wheel comprises a hub body and a plurality of blades.
  • a seal which is usually designed as a labyrinth seal. This seal ensures that no larger amount of fresh air under increased pressure escapes from the flow channel at the outlet of the compressor wheel in the rear space of the compressor wheel.
  • To the bearing housing 30 towards the rear space is limited by a disc-shaped partition 40.
  • the intermediate wall has a central opening in the interior, through which the shaft 20 is guided.
  • part of the compressor wheel 71 may project into or through the central opening in the intermediate wall. Between the rotor and the intermediate wall a bidirectionally effective sealing point is provided in the radially inner region. On the one hand, it should be prevented that too much fresh air escapes from the rear space of the compressor wheel into the storage area under ambient pressure (blow-by). On the other hand, it should be prevented that at certain operating points of the compressor in reverse pressure conditions, oil or oil-laden air can pass from the storage area in the rear space of the compressor wheel.
  • the intermediate wall is mounted in the radially outer region of the bearing housing and the transition is also secured with a seal 35.
  • the disc-shaped intermediate wall 40 has on the side facing the bearing area a circumferential mounting flange 41 which is provided according to the invention for support on a likewise circumferential mounting flange 31 of the bearing housing. Between intermediate wall 40 and bearing housing 30 results radially outside the peripheral flanges, a cavity 36 which can be used for cooling the housing portion at the outer edge or at the outlet of the compressor wheel. For example, a cooling medium (water or cool air) can be passed through the cavity.
  • a cooling medium water or cool air
  • the intermediate wall 41 several continuous openings are recessed in the region of the mounting flange, which are each either as a sealing air passage 42 of the discharge of sealing air from the rear space of the compressor wheel ( Fig. 2 , upper half), or as a bore 43 of the mounting of fastening means 50 (FIG. Fig. 2 , lower half).
  • a sealing air passage 42 of the discharge of sealing air from the rear space of the compressor wheel Fig. 2 , upper half
  • a bore 43 of the mounting of fastening means 50 FIG. Fig. 2 , lower half.
  • the bearing surfaces of the two flanges are formed in the illustrated embodiment as axial end faces and extend in a plane perpendicular to the axis.
  • the bearing surfaces may also be slightly conically aligned, wherein the bearing surfaces of the two flanges are strictly parallel to each other.
  • a sealing point 34 is located radially inside the openings arranged on a circle.
  • the groove on one side either in the bearing surface of the flange 41 of the intermediate wall, or - as in the illustrated embodiment - be embedded in the bearing surface of the flange 31 on the bearing housing, or on both sides in both bearing surfaces.
  • the sealing ring a conventional O-ring, is squeezed when placing the intermediate wall on the bearing housing in the axial direction in the groove and thus seals between the two opposite bearing surfaces.
  • the sealing air channel is sealed off from the storage area, so that no blow-by flow escapes into the storage area.
  • the fasteners are sealed according to the invention, so that in the above-mentioned operating point with reversed pressure ratios no oil or oil-laden air can pass from the storage area in the rear space of the compressor wheel.
  • the bores for receiving the fastening means may have the same diameter as the bore of the sealing air channel for receiving a screw head to a residual depth with a smaller diameter. This facilitates the production of the intermediate wall.
  • the arrangement of the two types of holes may be regular or irregular.
  • the fastening means 50 are regularly distributed along the circumference.
  • the at least one barrier air channel 42 may instead of as shown a fastening opening, or additionally arranged between two spaced apart attachment openings.
  • Fig. 3 shows a view in the axial direction of the intermediate wall 40 in the in Fig. 2 indicated, guided along III-III section through the rear space portion of the centrifugal compressor.
  • the depressions of the labyrinth seal 44 are indicated by a plurality of concentric circles.
  • the shaft 20 and the shaft enclosing, cylindrical extension of the compressor wheel is shown.
  • FIG. 4 shows partition wall and bearing housing along the in Fig. 2 indicated, along IV-IV guided section through the rear space region of the centrifugal compressor Fig. 2 , In this case, the bearing housing 30 is cut in the radially outer region. Subsequently, the section passes through the enclosed between the intermediate wall and the bearing housing cavity 36, which can optionally be used to cool the housing portion at the compressor wheel outlet.
  • the cavity 36 is bounded by the flange 31, in which according to the invention the bores 33 and at least one sealing air channel 32 are arranged.
  • the sealing point 34 can be seen, which extends in the region of the flange 31 but radially within the sealing air channel 32 and holes 33.
  • the shaft 20 In the radially innermost region, in turn, the shaft 20, the extension of the compressor wheel 71 and a piece of the in this area inclined to the bearing side intermediate wall 40 is indicated.
  • the intermediate wall 40 is according to the invention, despite existing sealing air feedthrough, a rotationally symmetrical disc, which can be brought into production by turning and without milling in its final form.
  • a drill is necessary, which can also be used for drilling the holes for receiving the fasteners.
  • the manufacturing process can be simplified compared to a conventional partition.
  • the intermediate wall has an additional positioning hole, which is provided for receiving a positioning pin, which on the bearing housing is mounted or introduced before mounting in a designated positioning hole in the bearing housing.
  • the positioning can be realized by an irregular distribution of the holes for receiving the fastening means.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

The wall (40) has a peripheral rotationally symmetrical disk-shaped base body provided with a central opening for passage of a rotor. A rotationally symmetrical shaped mounting flange (41) is provided for fixing the wall to a bearing housing (30) and provided with a planar contact surface for resting on a contact surface of the bearing housing. A sealing air passage (42) comprises holes (43) distributedly arranged in a circumferential direction of a virtual circumference for retaining of a fastening unit (50). A groove retains a seal ring. Independent claims are also included for the following: (1) a bearing device for supporting a rotor of a compressor (2) a radial compressor.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die Erfindung bezieht sich auf das Gebiet der Abgasturbolader von aufgeladenen Brennkraftmaschinen.The invention relates to the field of exhaust gas turbochargers of supercharged internal combustion engines.

Sie betrifft eine Zwischenwand zur Abdichtung des RĂŒckraums des Verdichterrades eines Radialverdichters bezĂŒglich eines von einem LagergehĂ€use umschlossenen Lagerraums, eine Lagervorrichtung zum Lagern des Rotors eines Verdichters mit einer derartigen Zwischenwand, einen Radialverdichter mit einer derartigen Lagervorrichtung sowie ein Abgasturbolader mit einem derartigen Radialverdichter.It relates to an intermediate wall for sealing the rear space of the compressor wheel of a centrifugal compressor with respect to a bearing space enclosed by a bearing housing, a bearing device for supporting the rotor of a compressor with such a partition, a centrifugal compressor with such a bearing device and an exhaust gas turbocharger with such a centrifugal compressor.

STAND DER TECHNIKSTATE OF THE ART

Abgasturbolader werden zur Leistungssteigerung von Brennkraftmaschinen eingesetzt. Dabei wird die Abgasturbine des Abgasturboladers mit den Abgasen der Brennkraftmaschine beaufschlagt und deren kinetische Energie zum Ansaugen und Verdichten von Luft fĂŒr die Brennkraftmaschine verwendet. Die LaufrĂ€der der Turbine und des Verdichters sind ĂŒber eine in einem LagergehĂ€use gelagerte Welle miteinander verbunden.Exhaust gas turbochargers are used to increase the performance of internal combustion engines. In this case, the exhaust gas turbine of the exhaust gas turbocharger is charged with the exhaust gases of the internal combustion engine and their kinetic energy used for sucking and compressing air for the internal combustion engine. The impellers of the turbine and the compressor are connected to each other via a shaft mounted in a bearing housing shaft.

Bei Abgasturboladern mit Axialturbinen wird auf der Turbinenseite hĂ€ufig Sperrluft eingesetzt, um den Lagerbereich vor eindringendem heissen Abgasen aus dem Strömungskanal zu schĂŒtzen oder um das Turbinenrad aktive zu kĂŒhlen. Diese Sperrluft kann extern zugefĂŒhrt werden oder aus dem Luftstrom stromabwĂ€rts des Verdichters entnommen werden. Alternativ lĂ€sst sich Sperrluft auch aus dem RĂŒckraum des Verdichterrades abfĂŒhren, was den positiven Effekt einer Entlastung der axialen Belastung des Verdichterrades mit sich bringt, da sich durch das AbfĂŒhren der Sperrluft der Druck im RĂŒckraum des Verdichterrades verringert. Die Luft im RĂŒckraum des Verdichterrades dringt aus dem Strömungskanal des Verdichterrades in diesen Bereich vor, da sich der Zwischenraum zwischen dem schnell drehenden und grösseren Temperaturschwankungen ausgesetzten Verdichterrad nicht beliebig gut abdichten lĂ€sst.In turbochargers with axial turbines on the turbine side sealing air is often used to protect the storage area from penetrating hot exhaust gases from the flow channel or to actively cool the turbine wheel. This barrier air may be externally supplied or removed from the airflow downstream of the compressor. Alternatively, sealing air can also be discharged from the rear space of the compressor wheel, which brings about the positive effect of relieving the axial load on the compressor wheel, since the pressure in the rear space of the compressor wheel is reduced due to the discharge of the sealing air. The air in the rear space of the compressor wheel penetrates from the flow channel of the compressor wheel in this area, since the gap between the rapidly rotating and larger temperature fluctuations exposed compressor wheel can not seal arbitrarily well.

Die auf diese Weise abgefĂŒhrte Sperrluft wird durch mehrere Bauteile bis zur Turbinenseite gefĂŒhrt. Dadurch entstehen GehĂ€useĂŒbergĂ€nge, welche gegen Austritt der Sperrluft abgedichtet werden mĂŒssen. Der mindestens eine Sperrluft-Übergang zwischen der unmittelbar an den VerdichterradrĂŒckraum angrenzenden Zwischenwand und dem LagergehĂ€use wurde bislang mittels jeweils eines runden Zapfens realisiert, welcher an der Zwischenwand abgebracht war und in einer entsprechenden Öffnung im LagergehĂ€use aufgenommen wurde. Der mindestens eine Zapfen an der ansonsten im wesentlichen rotationssymmetrisch ausgebildeten Zwischenwand wurde durch das aufwĂ€ndige Bearbeitungsverfahren ZirkularfrĂ€sen hergestellt.The air discharged in this way is guided through several components to the turbine side. This results in housing transitions, which must be sealed against leakage of the sealing air. The at least one barrier air transition between the immediately adjacent to the VerdichterradrĂŒckraum intermediate wall and the bearing housing has hitherto been realized by means of a respective round pin, which was brought to the partition and was received in a corresponding opening in the bearing housing. The at least one pin on the otherwise essentially rotationally symmetrical intermediate wall was produced by the complex machining method of circular milling.

KURZE DARSTELLUNG DER ERFINDUNGBRIEF SUMMARY OF THE INVENTION

Die Aufgabe der Erfindung besteht darin die Zwischenwand zur Abdichtung des RĂŒckraums des Verdichterrades eines Radialverdichters, welche mindestens eine Bohrung zur SperrluftabfĂŒhrung aufweist, hinsichtlich einer vereinfachten Herstellung zu optimieren.The object of the invention is to optimize the intermediate wall for sealing the rear space of the compressor wheel of a centrifugal compressor, which has at least one bore for SperrluftabfĂŒhrung, with respect to a simplified production.

ErfindungsgemÀss weist die Zwischenwand einen umlaufenden, rotationssymmetrisch geformten Befestigungsflansch auf, welcher zur Befestigung der Zwischenwand an dem benachbarten LagergehÀuse vorgesehen ist und welcher eine plane KontaktflÀche zur Auflage auf einer KontaktflÀche des LagergehÀuses aufweist. Dabei sind in den Befestigungsflansch mehrere Bohrungen auf einer virtuellen Kreislinie eingelassen, wobei die Bohrungen mindestens einen Sperrluftkanal sowie mehrere, in Umfangsrichtung auf der virtuellen Kreislinie verteilt angeordnete Bohrungen zur Aufnahme von Befestigungsmitteln umfassen.According to the invention, the intermediate wall has a circumferential, rotationally symmetrical shaped mounting flange which is provided for fastening the intermediate wall to the adjacent bearing housing and which has a planar contact surface for resting on a contact surface of the bearing housing. In this case, a plurality of bores are embedded in a virtual circular line in the mounting flange, wherein the bores comprise at least one sealing air channel and a plurality of circumferentially distributed on the virtual circle arranged holes for receiving fasteners.

Die Zwischenwand ist erfindungsgemĂ€ss als eine rotationssymmetrische Scheibe ausgebildet, welche in der Herstellung durch das Bearbeitungsverfahren Drehen und ohne weitere FrĂ€sbearbeitung in ihre endgĂŒltige Form gebracht werden kann. FĂŒr die SperrluftdurchfĂŒhrung ist lediglich ein Bohrer notwendig, welcher ebenfalls fĂŒr das Anbohren der Bohrungen zur Aufnahme der Befestigungsmittel verwendet werden kann. Dadurch kann der Herstellungsprozess gegenĂŒber einer herkömmlichen Zwischenwand vereinfacht werden.According to the invention, the intermediate wall is designed as a rotationally symmetrical disk, which can be brought into its final shape in production by the machining process of turning and without further milling. For the blocking air duct only a drill is necessary, which can also be used for drilling the holes for receiving the fasteners. As a result, the manufacturing process can be simplified compared to a conventional partition.

Weitere Vorteile ergeben sich aus den abhĂ€ngigen AnsprĂŒchen.Further advantages emerge from the dependent claims.

KURZE BESCHREIBUNG DER ZEICHNUNGENBRIEF DESCRIPTION OF THE DRAWINGS

Die Erfindung wird nachfolgend anhand von Zeichnungen nÀher erlÀutert. Hierbei zeigt:

Fig1
eine isometrische Darstellung eines teilweise aufgeschnittenen Abgasturboladers gemÀss dem Stand der Technik mit einem Radialverdichter und einer Axialturbine,
Fig. 2
einen entlang der Wellenachse gefĂŒhrten Schnitt durch den Radialverdichter eines Abgasturboladers nach Fig.1, mit einem im RĂŒckraum des Verdichterrades zwischen Zwischenwand und LagergehĂ€use erfindungsgemĂ€ss ausgestalteten SperrluftĂŒbergang,
Fig. 3
einen im Zwischenraum zwischen Verdichterrad und Zwischenwand entlang III-III gefĂŒhrten Schnitt durch die Anordnung nach Fig. 2, und
Fig. 4
einen durch die Trennstelle zwischen Zwischenwand und LagergehĂ€use entlang IV-IV gefĂŒhrten Schnitt durch die Anordnung nach Fig. 2.
The invention will be explained in more detail with reference to drawings. Hereby shows:
fig1
an isometric view of a partially cut-away exhaust gas turbocharger according to the prior art with a centrifugal compressor and an axial turbine,
Fig. 2
a guided along the shaft axis section through the radial compressor of an exhaust gas turbocharger after Fig.1 with a blocking air transition designed according to the invention in the rear space of the compressor wheel between intermediate wall and bearing housing,
Fig. 3
a guided in the space between the compressor wheel and intermediate wall along III-III section through the arrangement Fig. 2 , and
Fig. 4
a guided through the separation point between partition and bearing housing along IV-IV section through the arrangement Fig. 2 ,

WEG ZUR AUSFÜHRUNG DER ERFINDUNGWAY FOR CARRYING OUT THE INVENTION

Fig. 1 zeigt einen Abgasturbolader gemĂ€ss dem Stand der Technik mit einer axial durchströmten Abgasturbine 10 sowie einem Radialverdichter 70. Der teilweise aufgeschnittene Abgasturbolader weist einen Rotor bestehend aus Turbinenrad 11, Verdichterrad 71 und dazwischenliegender Welle 20 auf. Der Rotor ist drehbar im LagergehĂ€use 30 gelagert. Das aus den Brennkammern eines Verbrennungsmotors stammende Abgas wird durch das GaseintrittsgehĂ€use 12 auf die Laufschaufeln des Turbinenrades 11 gefĂŒhrt. Anschliessend wird das Abgas im Diffusorbereich des GasaustrittsgehĂ€uses 13 gesammelt und ĂŒber die Auspuffanlage abgefĂŒhrt. Das durch die Turbine ĂŒber die Welle angetriebene Verdichterrad saugt Frischluft an um diese zu verdichten und unter höherem Druck den Brennkammern des Verbrennungsmotors zuzufĂŒhren. Fig. 1 shows an exhaust gas turbocharger according to the prior art with an axially flowed exhaust gas turbine 10 and a centrifugal compressor 70. The partially cut exhaust gas turbocharger has a rotor consisting of turbine wheel 11, compressor 71 and intermediate shaft 20 on. The rotor is rotatably mounted in the bearing housing 30. The exhaust gas originating from the combustion chambers of an internal combustion engine is guided through the gas inlet housing 12 onto the rotor blades of the turbine wheel 11. Subsequently, the exhaust gas is collected in the diffuser region of the gas outlet housing 13 and discharged via the exhaust system. The compressor wheel driven by the turbine via the shaft draws in fresh air in order to compress it and supply it under higher pressure to the combustion chambers of the internal combustion engine.

Bei derartigen Abgasturboladern mit Axialturbinen wird auf der Turbinenseite hĂ€ufig Sperrluft eingesetzt, um den Lagerbereich vor eindringendem heissen Abgas zu schĂŒtzen oder um die Turbinenradnabe zu kĂŒhlen. Diese Sperrluft ist meist ein Beiprodukt der Verdichterradschubentlastung, bei welcher der Luftdruck im RĂŒckraum des Verdichterrades reduziert wird, indem die aus dem Strömungskanal des Verdichterrades in diesen Bereich eindringende Luft abgefĂŒhrt wird.In such exhaust gas turbochargers with axial turbines sealing air is often used on the turbine side to protect the storage area from penetrating hot exhaust or to cool the turbine hub. This sealing air is usually a Beiprodukt the Verdichterradschubentlastung, in which the air pressure in the rear space the compressor wheel is reduced by the air from the flow channel of the compressor in this area penetrating air is removed.

Fig. 2 zeigt einen entlang der Wellenachse gefĂŒhrten Schnitt durch den Radialverdichter eines Abgasturboladers. Das Verdichterrad 71 ist im VerdichtergehĂ€use 72 angeordnet. Das Verdichterrad umfasst einen Nabenkörper sowie eine Vielzahl von Laufschaufeln. Im RĂŒckraum des Verdichterrades 71, also der dem Lagerbereich zugewandten Seite, befindet sich im radial Ă€usseren Bereich des Verdichterrades eine Dichtung, welche in der Regel als Labyrinthdichtung ausgefĂŒhrt ist. Diese Dichtung sorgt dafĂŒr, dass keine grössere Menge der unter erhöhtem Druck stehenden Frischluft aus dem Strömungskanal am Austritt des Verdichterrades in den RĂŒckraum des Verdichterrades entweicht. Zum LagergehĂ€use 30 hin ist der RĂŒckraum durch eine scheibenförmige Zwischenwand 40 begrenzt. Die Zwischenwand weist im Innern eine zentrale Öffnung auf, durch die die Welle 20 gefĂŒhrt ist. Je nach Befestigungsweise des Verdichterrades auf der Welle kann auch ein Teil des Verdichterrades 71 in oder durch die zentrale Öffnung in der Zwischenwand hinein- oder hindurchragen. Zwischen dem Rotor und der Zwischenwand ist im radial inneren Bereich eine in zwei Richtungen wirksame Dichtstelle vorgesehen. Einerseits soll verhindert werden, dass zu viel Frischluft aus dem RĂŒckraum des Verdichterrades in den unter Umgebungsdruck stehenden Lagerbereich entweicht (blow-by). Andererseits soll verhindert werden, dass bei gewissen Betriebspunkten des Verdichters bei umgekehrt gerichteten DruckverhĂ€ltnissen Öl oder ölbehaftete Luft aus dem Lagerbereich in den RĂŒckraum des Verdichterrades gelangen kann. Fig. 2 shows a guided along the shaft axis section through the centrifugal compressor of an exhaust gas turbocharger. The compressor wheel 71 is arranged in the compressor housing 72. The compressor wheel comprises a hub body and a plurality of blades. In the rear space of the compressor wheel 71, that is, the side facing the bearing area, located in the radially outer region of the compressor wheel, a seal, which is usually designed as a labyrinth seal. This seal ensures that no larger amount of fresh air under increased pressure escapes from the flow channel at the outlet of the compressor wheel in the rear space of the compressor wheel. To the bearing housing 30 towards the rear space is limited by a disc-shaped partition 40. The intermediate wall has a central opening in the interior, through which the shaft 20 is guided. Depending on how the compressor wheel is fastened to the shaft, it is also possible for part of the compressor wheel 71 to project into or through the central opening in the intermediate wall. Between the rotor and the intermediate wall a bidirectionally effective sealing point is provided in the radially inner region. On the one hand, it should be prevented that too much fresh air escapes from the rear space of the compressor wheel into the storage area under ambient pressure (blow-by). On the other hand, it should be prevented that at certain operating points of the compressor in reverse pressure conditions, oil or oil-laden air can pass from the storage area in the rear space of the compressor wheel.

Die Zwischenwand ist im radial Ă€usseren Bereich am LagergehĂ€use befestigt und der Übergang ist ebenfalls mit einer Dichtung 35 gesichert.The intermediate wall is mounted in the radially outer region of the bearing housing and the transition is also secured with a seal 35.

Die scheibenförmige Zwischenwand 40 weist auf der dem Lagerbereich zugewandten Seite einen umlaufenden Befestigungsflansch 41 auf, welcher erfindungsgemĂ€ss zur Auflage an einem ebenfalls umlaufenden Befestigungsflansch 31 des LagergehĂ€uses vorgesehen ist. Zwischen Zwischenwand 40 und LagergehĂ€use 30 ergibt sich radial ausserhalb der umlaufenden Flansche ein Hohlraum 36, welcher zur KĂŒhlung des GehĂ€usebereichs am Ă€usseren Rand bzw. am Austritt des Verdichterrades verwendet werden kann. So kann beispielsweise ein KĂŒhlmedium (Wasser oder kĂŒhle Luft) durch den Hohlraum geleitet werden.The disc-shaped intermediate wall 40 has on the side facing the bearing area a circumferential mounting flange 41 which is provided according to the invention for support on a likewise circumferential mounting flange 31 of the bearing housing. Between intermediate wall 40 and bearing housing 30 results radially outside the peripheral flanges, a cavity 36 which can be used for cooling the housing portion at the outer edge or at the outlet of the compressor wheel. For example, a cooling medium (water or cool air) can be passed through the cavity.

In die Zwischenwand sind im Bereich des Befestigungsflansches 41 mehrere durchgehende Öffnungen eingelassen, welche jeweils entweder als Sperrluftkanal 42 der AbfĂŒhrung von Sperrluft aus dem RĂŒckraum des Verdichterrades (Fig. 2, obere HĂ€lfte), oder als Bohrung 43 der Aufnahme von Befestigungsmitteln 50 (Fig. 2, untere HĂ€lfte) dienen. Im Flansch 31 des LagergehĂ€uses sind mit den Öffnungen in der Zwischenwand korrespondierende Bohrungen vorgesehen. Die AuflageflĂ€chen der beiden Flansche sind in der dargestellten AusfĂŒhrungsform als axiale StirnflĂ€chen ausgebildet und verlaufen in einer Ebene senkrecht zur Achse. Optional können die AuflageflĂ€chen auch leicht konisch ausgerichtet sein, wobei die AuflageflĂ€chen der beiden Flansche streng parallel zueinander verlaufen. ErfindungsgemĂ€ss befindet sich radial innerhalb der auf einem Kreis angeordneten Öffnungen eine Dichtstelle 34, vorteilhafterweise als eine oder zwei Nuten mit eingesetztem Dichtungsring ausgebildet. Dabei kann die Nut einseitig entweder in die AuflageflĂ€che des Flansches 41 der Zwischenwand, oder - wie in der dargestellten AusfĂŒhrungsform - in die AuflageflĂ€che des Flansches 31 am LagergehĂ€use, oder aber beidseitig in beide AuflageflĂ€chen eingelassen sein. Der Dichtungsring, ein herkömmlicher O-Ring, wird beim Aufsetzen der Zwischenwand auf das LagergehĂ€use in axialer Richtung in die Nut gequetscht und dichtet somit zwischen den beiden gegenĂŒberliegenden AuflageflĂ€chen. Abgedichtet wird dabei insbesondere der Sperrluftkanal gegenĂŒber dem Lagerbereich, so dass keine Blow-By Strömung in den Lagerbereich entweicht. Aber auch die Befestigungsmittel werden erfindungsgemĂ€ss abgedichtet, so dass im oben erwĂ€hnten Betriebspunkt mit umgekehrt gerichteten DruckverhĂ€ltnissen kein Öl oder ölbehaftete Luft aus dem Lagerbereich in den RĂŒckraum des Verdichterrades gelangen kann.In the intermediate wall 41 several continuous openings are recessed in the region of the mounting flange, which are each either as a sealing air passage 42 of the discharge of sealing air from the rear space of the compressor wheel ( Fig. 2 , upper half), or as a bore 43 of the mounting of fastening means 50 (FIG. Fig. 2 , lower half). In the flange 31 of the bearing housing corresponding holes are provided with the openings in the intermediate wall. The bearing surfaces of the two flanges are formed in the illustrated embodiment as axial end faces and extend in a plane perpendicular to the axis. Optionally, the bearing surfaces may also be slightly conically aligned, wherein the bearing surfaces of the two flanges are strictly parallel to each other. According to the invention, a sealing point 34, advantageously designed as one or two grooves with an inserted sealing ring, is located radially inside the openings arranged on a circle. In this case, the groove on one side either in the bearing surface of the flange 41 of the intermediate wall, or - as in the illustrated embodiment - be embedded in the bearing surface of the flange 31 on the bearing housing, or on both sides in both bearing surfaces. The sealing ring, a conventional O-ring, is squeezed when placing the intermediate wall on the bearing housing in the axial direction in the groove and thus seals between the two opposite bearing surfaces. In particular, the sealing air channel is sealed off from the storage area, so that no blow-by flow escapes into the storage area. But also the fasteners are sealed according to the invention, so that in the above-mentioned operating point with reversed pressure ratios no oil or oil-laden air can pass from the storage area in the rear space of the compressor wheel.

Wie in Fig. 3 dargestellt, befinden sich mindestens ein Sperrluftkanal 42 und die mehreren Bohrungen zur Aufnahme von Befestigungsmittel 43 erfindungsgemÀss auf der gleichen radialen Höhe, liegen also auf einem Kreis konzentrisch zur kreisrunden, scheibenförmigen Zwischenwand. Die Bohrungen zur Aufnahme der Befestigungsmittel können dabei zur Aufnahme eines Schraubenkopfs bis auf eine Resttiefe mit geringerem Durchmesser den gleichen Durchmesser aufweisen wie die Bohrung des Sperrluftkanals. Dadurch erleichtert sich die Herstellung der Zwischenwand. Die Anordnung der beiden Typen von Bohrungen kann regelmÀssig oder unregelmÀssig sein. Vorteilhafterweise sind die Befestigungsmittel 50 regelmÀssig entlang des Umfangs verteilt. Der mindestens eine Sperrluftkanal 42 kann wie dargestellt anstelle einer Befestigungsöffnung, oder aber zusÀtzlich zwischen zwei in regelmÀssigem Abstand angeordneten Befestigungsöffnungen angeordnet sein.As in Fig. 3 shown, at least one sealing air channel 42 and the plurality of holes for receiving fastener 43 according to the invention at the same radial height, so are on a circle concentric with the circular disc-shaped partition. The bores for receiving the fastening means may have the same diameter as the bore of the sealing air channel for receiving a screw head to a residual depth with a smaller diameter. This facilitates the production of the intermediate wall. The arrangement of the two types of holes may be regular or irregular. Advantageously, the fastening means 50 are regularly distributed along the circumference. The at least one barrier air channel 42 may instead of as shown a fastening opening, or additionally arranged between two spaced apart attachment openings.

Fig. 3 zeigt eine Ansicht in axialer Richtung auf die Zwischenwand 40 in dem in Fig. 2 angedeuteten, entlang III-III gefĂŒhrten Schnitt durch den RĂŒckraumbereich des Radialverdichters. Im radial Ă€usseren Bereich der Zwischenwand sind die Vertiefungen der Labyrinthdichtung 44 mit mehreren konzentrischen Kreisen angedeutet. Im radial inneren Bereich ist die Welle 20 und der die Welle umschliessende, zylinderförmige Fortsatz des Verdichterrades dargestellt. Fig. 3 shows a view in the axial direction of the intermediate wall 40 in the in Fig. 2 indicated, guided along III-III section through the rear space portion of the centrifugal compressor. In the radially outer region of the intermediate wall, the depressions of the labyrinth seal 44 are indicated by a plurality of concentric circles. In the radially inner region, the shaft 20 and the shaft enclosing, cylindrical extension of the compressor wheel is shown.

Wie in Fig. 4 dargestellt, befinden sich die Fortsetzung des mindestens einen Sperrluftkanals 32 sowie die Bohrungen zur Aufnahme von Befestigungsmittel 33 ebenfalls auf gleicher radialen Höhe, liegen also ebenfalls auf einem Kreis konzentrisch zur Wellenachse. Fig. 4 zeigt Zwischenwand und LagergehĂ€use entlang dem in Fig. 2 angedeuteten, entlang IV-IV gefĂŒhrten Schnitt durch den RĂŒckraumbereich des Radialverdichters nach Fig. 2. Dabei ist im radial Ă€usseren Bereich das LagergehĂ€use 30 angeschnitten. Anschliessend fĂŒhrt der Schnitt durch den zwischen Zwischenwand und LagergehĂ€use eingeschlossenen Hohlraum 36, welcher optional zur KĂŒhlung des GehĂ€usebereichs am Verdichterrad-Austritt verwendet werden kann. Gegen innen ist der Hohlraum 36 durch den Flansch 31 begrenzt, in welchen erfindungsgemĂ€ss die Bohrungen 33 und wenigstens ein Sperrluftkanal 32 angeordnet sind. In dieser Darstellung ist auch die Dichtstelle 34 ersichtlich, welche im Bereich des Flansches 31 aber radial innerhalb von Sperrluftkanal 32 und Bohrungen 33 verlĂ€uft. Im radial innersten Bereich ist wiederum die Welle 20, der Fortsatz des Verdichterrades 71 sowie ein StĂŒck der in diesem Bereich zur Lagerseite hin geneigten Zwischenwand 40 angedeutet.As in Fig. 4 shown, the continuation of at least one sealing air channel 32 and the holes for receiving fasteners 33 are also at the same radial height, so are also on a circle concentric with the shaft axis. Fig. 4 shows partition wall and bearing housing along the in Fig. 2 indicated, along IV-IV guided section through the rear space region of the centrifugal compressor Fig. 2 , In this case, the bearing housing 30 is cut in the radially outer region. Subsequently, the section passes through the enclosed between the intermediate wall and the bearing housing cavity 36, which can optionally be used to cool the housing portion at the compressor wheel outlet. Against the inside, the cavity 36 is bounded by the flange 31, in which according to the invention the bores 33 and at least one sealing air channel 32 are arranged. In this illustration, the sealing point 34 can be seen, which extends in the region of the flange 31 but radially within the sealing air channel 32 and holes 33. In the radially innermost region, in turn, the shaft 20, the extension of the compressor wheel 71 and a piece of the in this area inclined to the bearing side intermediate wall 40 is indicated.

Die Zwischenwand 40 ist erfindungsgemĂ€ss, trotz vorhandener SperrluftdurchfĂŒhrung, eine rotationssymmetrische Scheibe, welche in der Herstellung durch Drehen und ohne FrĂ€sen in ihre endgĂŒltige Form gebracht werden kann. FĂŒr die SperrluftdurchfĂŒhrung ist lediglich ein Bohrer notwendig, welcher ebenfalls fĂŒr das Anbohren der Bohrungen zur Aufnahme der Befestigungsmittel verwendet werden kann. Dadurch kann der Herstellungsprozess gegenĂŒber einer herkömmlichen Zwischenwand vereinfacht werden.The intermediate wall 40 is according to the invention, despite existing sealing air feedthrough, a rotationally symmetrical disc, which can be brought into production by turning and without milling in its final form. For the blocking air duct only a drill is necessary, which can also be used for drilling the holes for receiving the fasteners. As a result, the manufacturing process can be simplified compared to a conventional partition.

Optional weist die Zwischenwand eine zusĂ€tzliche Positionierungsbohrung auf, welche zur Aufnahme eines Positionierungsstifts vorgesehen ist, welcher am LagergehĂ€use angebracht ist oder vor der Montage in eine dafĂŒr vorgesehenen Positionierungsbohrung im LagergehĂ€use eingebracht wird. Dadurch lĂ€sst sich die Zwischenwand bei der Montage bezĂŒglich der Winkellage gegenĂŒber dem LagergehĂ€use einfacher Positionieren. Optional lĂ€sst sich die Positionierung durch eine unregelmĂ€ssige Verteilung der Bohrungen zur Aufnahme der Befestigungsmittel realisieren.Optionally, the intermediate wall has an additional positioning hole, which is provided for receiving a positioning pin, which on the bearing housing is mounted or introduced before mounting in a designated positioning hole in the bearing housing. As a result, the intermediate wall during installation with respect to the angular position relative to the bearing housing easier position. Optionally, the positioning can be realized by an irregular distribution of the holes for receiving the fastening means.

BEZEICHNUNGSLISTENAME LIST

1010
Abgasturbineexhaust turbine
1111
Turbinenradturbine
1212
GaseintrittsgehÀuseGas inlet casing
1313
GasaustrittsgehÀuseGas outlet casing
2020
Wellewave
3030
LagergehÀusebearing housing
3131
Befestigungsflansch mit AuflageflÀcheMounting flange with support surface
3232
SperrluftkanalSealing air channel
3333
Bohrung zur Aufnahme von BefestigungsmittelnBore for receiving fasteners
34, 3534, 35
Dichtstelle, Umlaufende Nut mit DichtungsringSealing point, circumferential groove with sealing ring
3636
Hohlraum, fĂŒr KĂŒhlung des Verdichterrades nutzbarCavity usable for cooling the compressor wheel
4040
Zwischenwandpartition
4141
Befestigungsflansch mit AuflageflÀcheMounting flange with support surface
4242
SperrluftkanalSealing air channel
4343
Bohrung zur Aufnahme von BefestigungsmittelnBore for receiving fasteners
4444
Labyrinth-Dichtung zwischen Verdichterrad und ZwischenwandLabyrinth seal between compressor wheel and intermediate wall
5050
Befestigungsmittelfastener
7070
Verdichtercompressor
7171
Verdichterradcompressor
7272
VerdichtergehÀusecompressor housing

Claims (9)

Zwischenwand (40) zur Abdichtung des RĂŒckraums des Verdichterrades eines Radialverdichters bezĂŒglich eines von einem LagergehĂ€use umschlossenen Lagerraums, umfassend einen rotationssymmetrischen, scheibenförmigen Grundkörper, mit einer zentralen Öffnung zum DurchfĂŒhren eines Rotors, wobei im Bereich der zentralen Öffnung Mittel vorgesehen sind, um den Übergang zum Rotor abzudichten, dadurch gekennzeichnet, dass die Zwischenwand einen umlaufenden, rotationssymmetrisch geformten Befestigungsflansch (41) umfasst, welcher zur Befestigung der Zwischenwand an einem LagergehĂ€use vorgesehen ist und welcher eine plane KontaktflĂ€che zur Auflage auf einer KontaktflĂ€che eines LagergehĂ€uses aufweist, wobei in den Befestigungsflansch (41) auf einer virtuellen Kreislinie mehrere Bohrungen (42, 43) eingelassen sind, wobei die Bohrungen mindestens einen Sperrluftkanal (42) sowie mehrere, in Umfangsrichtung auf der virtuellen Kreislinie verteilt angeordnete Bohrungen (43) zur Aufnahme von Befestigungsmitteln umfassen.An intermediate wall (40) for sealing the rear space of the compressor wheel of a centrifugal compressor with respect to a bearing space enclosed by a bearing housing, comprising a rotationally symmetrical, disc-shaped base body, with a central opening for passing through a rotor, wherein means are provided in the region of the central opening to the transition to Seal the rotor, characterized in that the intermediate wall comprises a circumferential, rotationally symmetrical shaped mounting flange (41) which is provided for fastening the intermediate wall to a bearing housing and which has a flat contact surface for bearing on a contact surface of a bearing housing, wherein in the mounting flange (41 ) on a virtual circular line a plurality of bores (42, 43) are embedded, wherein the bores at least one sealing air channel (42) and a plurality of circumferentially distributed on the virtual circle arranged holes (43) for receiving B. solidifying agents. Zwischenwand (40) nach Anspruch 1, wobei in die KontaktflĂ€che eine Nut zur Aufnahme eines Dichtungsrings eingelassen ist.Intermediate wall (40) according to claim 1, wherein in the contact surface a groove for receiving a sealing ring is embedded. Zwischenwand (40) nach Anspruch 1 oder 2, wobei die Bohrungen zur Aufnahme von Befestigungsmitteln (43) und der mindestens eine Sperrluftkanal (42) im Befestigungsflansch in regelmĂ€ssigen WinkelabstĂ€nden auf der virtuellen Kreislinie angeordnet sind.Intermediate wall (40) according to claim 1 or 2, wherein the holes for receiving fastening means (43) and the at least one sealing air channel (42) are arranged in the mounting flange at regular angular intervals on the virtual circle. Zwischenwand (40) nach Anspruch 1 oder 2, wobei die Bohrungen (43) zur Aufnahme von Befestigungsmitteln im Befestigungsflansch in regelmĂ€ssigen WinkelabstĂ€nden auf der virtuellen Kreislinie angeordnet sind, und der mindestens eine Sperrluftkanal (42) jeweils zwischen zwei benachbart angeordneten Bohrungen (43) zur Aufnahme von Befestigungsmitteln angeordnet ist.The intermediate wall (40) of claim 1 or 2, wherein the bores (43) are arranged for receiving fasteners in the mounting flange at regular angular intervals on the virtual circle, and the at least one barrier air channel (42) between each two adjacent holes arranged (43) Recording of fasteners is arranged. Lagervorrichtung zum Lagern des Rotors eines Verdichters, umfassend ein LagergehĂ€use (30), welches einen Lagerraum mit einer zentralen Öffnung zur Aufnahme eines Rotors umschliesst, sowie eine Zwischenwand nach einem der AnsprĂŒche 1 bis 4 zur Abdichtung des RĂŒckraums des Verdichterrades eines Verdichters bezĂŒglich des Lagerraums, wobei das LagergehĂ€use einen umlaufenden, Befestigungsflansch (41) umfasst welcher zur Befestigung der Zwischenwand (40) an dem LagergehĂ€use (30) vorgesehen ist und welcher eine plane KontaktflĂ€che zur Auflage auf der KontaktflĂ€che des Befestigungsflansches (41) der Zwischenwand aufweist, wobei in den Befestigungsflansch (31) des LagergehĂ€uses auf einer virtuellen Kreislinie mehrere Bohrungen (32, 33) eingelassen sind, wobei die Bohrungen mindestens einen Sperrluftkanal (32) sowie mehrere, in Umfangsrichtung auf der virtuellen Kreislinie verteilt angeordnete Bohrungen (43) zur Aufnahme von Befestigungsmitteln umfassen.A bearing device for supporting the rotor of a compressor, comprising a bearing housing (30) which encloses a storage space with a central opening for receiving a rotor, and an intermediate wall according to one of claims 1 to 4 for sealing the rear space of the compressor wheel of a compressor with respect to the storage space, wherein the bearing housing a circumferential, mounting flange (41) which is provided for fastening the intermediate wall (40) on the bearing housing (30) and which has a flat contact surface for bearing on the contact surface of the mounting flange (41) of the intermediate wall, wherein in the mounting flange (31) of Bearing housing on a virtual circle line a plurality of bores (32, 33) are recessed, wherein the bores comprise at least one sealing air channel (32) and a plurality of circumferentially distributed on the virtual circular line arranged holes (43) for receiving fastening means. Lagervorrichtung nach Anspruch 5, wobei im Bereich der KontaktflĂ€chen, radial innerhalb der virtuellen Kreislinien Mittel (34) zur Abdichtung des Übergangs zwischen LagergehĂ€use und Zwischenwand vorgesehen sind.Bearing device according to claim 5, wherein means (34) are provided for sealing the transition between the bearing housing and intermediate wall in the region of the contact surfaces, radially within the virtual circle lines. Lagervorrichtung nach Anspruch 6, wobei in die KontaktflĂ€che am Flansch (31) des LagergehĂ€uses (30), radial innerhalb der virtuellen Kreislinien eine Nut zur Aufnahme eines Dichtungsrings eingelassen ist.Bearing device according to claim 6, wherein in the contact surface on the flange (31) of the bearing housing (30), radially inside the virtual circular lines, a groove for receiving a sealing ring is embedded. Radialverdichter, umfassend einen Rotor mit einer in einer Lagervorrichtung nach einem der AnsprĂŒche 5 bis 7 drehbar gelagerten Welle (20) und einem Verdichterrad (71), wobei dasA radial compressor comprising a rotor having a shaft (20) rotatably mounted in a bearing device according to any one of claims 5 to 7, and a compressor wheel (71), the Abgasturbolader, umfassend einen Radialverdichter nach Anspruch 8.Exhaust gas turbocharger, comprising a radial compressor according to claim 8.
EP14155860.1A 2013-02-28 2014-02-20 Partition for sealing the rear section of a radial compressor Active EP2772652B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013203455.5A DE102013203455A1 (en) 2013-02-28 2013-02-28 Partition wall for sealing the rear space of a centrifugal compressor

Publications (3)

Publication Number Publication Date
EP2772652A2 true EP2772652A2 (en) 2014-09-03
EP2772652A3 EP2772652A3 (en) 2018-03-28
EP2772652B1 EP2772652B1 (en) 2021-10-06

Family

ID=50137527

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14155860.1A Active EP2772652B1 (en) 2013-02-28 2014-02-20 Partition for sealing the rear section of a radial compressor

Country Status (5)

Country Link
EP (1) EP2772652B1 (en)
JP (1) JP5850965B2 (en)
KR (1) KR101617938B1 (en)
CN (1) CN104018933B (en)
DE (1) DE102013203455A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109209520A (en) * 2018-09-13 2019-01-15 äž­ć›œç§‘ć­Šé™ąć·„çš‹çƒ­ç‰©ç†ç ”ç©¶æ‰€ A kind of centripetal turbine back cavity leakage stream loss inhibition sealing technique

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015005054A1 (en) * 2015-04-21 2016-10-27 Man Diesel & Turbo Se flow machine
DE102017208117A1 (en) * 2017-05-15 2018-11-15 Man Diesel & Turbo Se turbocharger
US20190277159A1 (en) * 2018-03-09 2019-09-12 GM Global Technology Operations LLC Turbocharger assembly

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4225625A1 (en) * 1992-08-03 1994-02-10 Asea Brown Boveri Exhaust gas turbo-charger with compression and turbine on common shaft - has increased space round ribbed cross-section and jacketed intermediate wall between compressor and turbine
CN1030342C (en) * 1992-08-03 1995-11-22 äșšç‘žäșšÂ·ć‹ƒæœ—ć‹ƒćšćŠ›æœ‰é™ć…Źćž Exhaust gas turbocharger
JPH06346749A (en) * 1993-06-04 1994-12-20 Mitsubishi Heavy Ind Ltd Exhaust turbo-supercharger
JP3606293B2 (en) * 1996-02-14 2005-01-05 çŸłć·ćł¶æ’­çŁšé‡ć·„æ„­æ ȘćŒäŒšç€Ÿ Exhaust turbine turbocharger
EP0903465B1 (en) * 1997-09-19 2003-09-03 ABB Turbo Systems AG Compressor wheel-shaft connection for high speed turbomachinery
DE19845375A1 (en) * 1998-10-02 2000-04-06 Asea Brown Boveri Indirect cooling process for flow in gap between turbine rotor and stator, involving use of water to cool stator part adjacent to gap
KR100339827B1 (en) * 1999-07-22 2002-06-07 ìŽìą…ì‹ Apparatus for combusting waste synthetic resins
KR100607424B1 (en) * 1999-10-20 2006-08-01 에읎ëč„ëč„ í„°ëłŽ 시슀템슈 아êȌ Method and device for the indirect cooling of a flow regime in radial slits formed between rotors and stators of turbomachines
JP2002180841A (en) * 2000-12-14 2002-06-26 Toyota Motor Corp Turbocompressor and turbocharger
WO2003093651A1 (en) * 2002-05-06 2003-11-13 Abb Turbo Systems Ag Device for fixing a rotor on a shaft
JP4539487B2 (en) * 2005-08-05 2010-09-08 æ ȘćŒäŒšç€ŸïŒ©ïœˆïœ‰ Supercharger with electric motor
DE102006048784A1 (en) * 2006-10-12 2008-04-17 Man Diesel Se Compressor for a turbocharger and method for its cooling
EP2067999A1 (en) * 2007-12-06 2009-06-10 Napier Turbochargers Limited Liquid cooled turbocharger impeller and method for cooling an impeller
DE102009024679B4 (en) * 2009-06-12 2016-04-07 Man Diesel & Turbo Se Compressor impeller and thus equipped centrifugal compressor
DE102009034962B3 (en) * 2009-07-28 2011-01-13 Man Diesel & Turbo Se Radial compressor for consolidating and compressing e.g. natural gas in supercharger of internal-combustion engine, has rib provided in cooling fluid passage, and impeller-side wall section connected with interior-side wall section over rib
US9228497B2 (en) * 2010-12-30 2016-01-05 Rolls-Royce Corporation Gas turbine engine with secondary air flow circuit
JP5637899B2 (en) * 2011-02-25 2014-12-10 æ ȘćŒäŒšç€ŸïŒ©ïœˆïœ‰ć›žè»ąæ©Ÿæą° Expansion turbine barrier plate

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109209520A (en) * 2018-09-13 2019-01-15 äž­ć›œç§‘ć­Šé™ąć·„çš‹çƒ­ç‰©ç†ç ”ç©¶æ‰€ A kind of centripetal turbine back cavity leakage stream loss inhibition sealing technique

Also Published As

Publication number Publication date
JP5850965B2 (en) 2016-02-03
KR101617938B1 (en) 2016-05-18
EP2772652A3 (en) 2018-03-28
EP2772652B1 (en) 2021-10-06
JP2014169699A (en) 2014-09-18
CN104018933B (en) 2016-10-12
KR20140108123A (en) 2014-09-05
DE102013203455A1 (en) 2014-08-28
CN104018933A (en) 2014-09-03

Similar Documents

Publication Publication Date Title
DE112008002729B4 (en) turbomachine
EP1394365B1 (en) Turbocharger shaft sealing
EP1394451B1 (en) Shaft seal for turbocharger
DE60314476T2 (en) Arrangement of a housing of a gas turbine and a rotor blade
DE102016002701A1 (en) Turbocharger turbine assembly
EP2824282A1 (en) Gas turbine with high pressure turbine cooling system
DE102014114556A1 (en) Locking spacer assembly
EP2218877A1 (en) Seal device of a exhaust gas turbocharger
DE102010043198A1 (en) Burst protection
EP2503246A2 (en) Segmented combustion chamber head
DE112013002029T5 (en) Centrifugal oil seal and turbocharger with centrifugal oil seal
DE102014114695A1 (en) Locking spacer assembly
CH708769A2 (en) Interlocking spacer assembly for insertion EADERSHIP in a peripheral attachment slot between platforms of adjacent blades.
EP1079070B1 (en) Heatshield for a turbine rotor
DE102014114555A1 (en) Locking spacer assembly
EP2772652B1 (en) Partition for sealing the rear section of a radial compressor
DE102016002722A1 (en) Turbocharger turbine nozzle and safety structure
DE102014114553A1 (en) Locking spacer assembly
DE60217049T2 (en) Ölluftseparatorplug
DE102004027707A1 (en) Compressor of a turbomachine and compressor wheel for this
EP1705339B1 (en) Rotor shaft, in particular for a gas turbine
DE102012211882A1 (en) Oil-free bearing of an exhaust gas turbocharger
DE102016111855A1 (en) Oil distribution system and turbomachinery with an oil distribution system
DE112015005131T5 (en) Cooling structure for turbine, and gas turbine
EP2090755A1 (en) Turboloader housing

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140220

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/10 20060101AFI20180221BHEP

Ipc: F04D 29/056 20060101ALI20180221BHEP

Ipc: F01D 11/04 20060101ALI20180221BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

R17P Request for examination filed (corrected)

Effective date: 20180912

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20200116

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ABB SCHWEIZ AG

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: ABB SCHWEIZ AG

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/10 20060101AFI20210330BHEP

Ipc: F04D 29/056 20060101ALI20210330BHEP

Ipc: F01D 11/04 20060101ALI20210330BHEP

Ipc: F01D 5/04 20060101ALN20210330BHEP

INTG Intention to grant announced

Effective date: 20210504

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1436472

Country of ref document: AT

Kind code of ref document: T

Effective date: 20211015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502014015917

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: FI

Ref legal event code: FGE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20211006

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220106

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: TURBO SYSTEMS SWITZERLAND LTD.

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220206

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220207

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220106

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20220107

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502014015917

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20220707

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20220922 AND 20220928

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20220228

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502014015917

Country of ref document: DE

Owner name: TURBO SYSTEMS SWITZERLAND LTD., CH

Free format text: FORMER OWNER: ABB SCHWEIZ AG, BADEN, CH

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220220

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220220

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1436472

Country of ref document: AT

Kind code of ref document: T

Effective date: 20220220

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220220

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20140220

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211006

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FI

Payment date: 20240219

Year of fee payment: 11

Ref country code: DE

Payment date: 20240219

Year of fee payment: 11

Ref country code: GB

Payment date: 20240219

Year of fee payment: 11