EP2216517B1 - Burst protection device for radial compressor - Google Patents

Burst protection device for radial compressor Download PDF

Info

Publication number
EP2216517B1
EP2216517B1 EP10150616A EP10150616A EP2216517B1 EP 2216517 B1 EP2216517 B1 EP 2216517B1 EP 10150616 A EP10150616 A EP 10150616A EP 10150616 A EP10150616 A EP 10150616A EP 2216517 B1 EP2216517 B1 EP 2216517B1
Authority
EP
European Patent Office
Prior art keywords
compressor
housing
axial
support element
webs
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP10150616A
Other languages
German (de)
French (fr)
Other versions
EP2216517A1 (en
Inventor
Joel Schlienger
Patrick Aberle
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP10150616A priority Critical patent/EP2216517B1/en
Publication of EP2216517A1 publication Critical patent/EP2216517A1/en
Application granted granted Critical
Publication of EP2216517B1 publication Critical patent/EP2216517B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H37/00—Jokes; Confetti, streamers, or other dance favours ; Cracker bonbons or the like
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H29/00—Drive mechanisms for toys in general
    • A63H29/10—Driving mechanisms actuated by flowing media
    • A63H29/14—Driving mechanisms actuated by flowing media by a water stream
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H5/00—Musical or noise- producing devices for additional toy effects other than acoustical
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0292—Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B4/00—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
    • F42B4/04—Firecrackers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00—Application
    • F05B2220/40—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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.
  • It relates to a compressor of an exhaust gas turbocharger with a device for ensuring the compressor-side Berstschutzfind the exhaust gas turbocharger.
  • exhaust gas turbochargers are nowadays used by default with one of the combustion chamber of the internal combustion engine air for the combustion process supplying compressor and an exhaust gas turbine in the exhaust tract of the internal combustion engine. With the supercharging of the internal combustion engine, the amount of air and fuel in the cylinders is increased and from this a considerable increase in power for the internal combustion engine is obtained.
  • the exhaust gas turbocharger used for this purpose is composed of a rotor consisting of a compressor wheel and a turbine wheel as well as the shaft bearing, the flow-guiding housing parts (compressor housing, turbine housing) and the bearing housing.
  • the exhaust gas turbocharger of the exhaust gas turbocharger is charged accordingly with a large exhaust gas flow
  • very high peripheral speeds are achieved at the blade tips of the turbine and compressor wheels.
  • the maximum permissible rotor speed of a turbocharger is a function of the wheel size, the geometry and the strength values of the materials used. In general, the rotating components are subject to very high centrifugal forces and thus high material tensions. Defects in the material structure can possibly lead to bursting of the compressor or turbine wheel, with unpredictable consequences for the adjacent housing.
  • the initial failure pattern of a compressor wheel can be described by a blade break or a multi-part hub burst.
  • the blades When shovels burst, the blades fail in the foot area of the compressor, leaving the wheel hub intact.
  • the hub area usually breaks down into two to four fragments.
  • the most critical case of the compressor rupture is the 3-part hub break with three roughly equal fragments (3x120 ° sectors).
  • the burst protection concept (containment concept) of an exhaust gas turbocharger is to be interpreted as meaning that all fragments, in the case of a multi-part hub burst, are retained within the outer casing casing at a predetermined bursting speed.
  • WO 02/090722 is a predetermined breaking point in the flow channel over the blades of the compressor radially outwardly bounding housing insert wall provided to prevent in the case of Ver Whyrradberstens the axial thrown away housing parts or components attached to the compressor housing.
  • EP 1-586-745 is prevented by means of a support flange and a sufficiently large distance of the support flange to the housing insert wall that takes place in the case of a bursting compressor impeller direct axial momentum transferring wegfrise compressor wheel on the air inlet housing, thus reducing the load on the upper connections between the housing parts and the breaking of the compound and the Leakage of the fragments prevented.
  • the housing insert wall is supplemented with holding means to thereby catch the axially forwardly thrown fragments of the compressor wheel and the housing insert wall respectively to jam.
  • the object of the invention is to make the housing assembly of a compressor of an exhaust gas turbocharger burstable in the event of a failed compressor wheel by the outer housing connections between the compressor housing and the bearing housing are protected against failure.
  • a housing composite which comprises a voltage applied to an axial stop of the outer compressor housing housing insert and a bending element in the power flow between the flow channel limiting insert wall contour and the outer compressor housing.
  • the bending element is made up of a, at an angle, preferably perpendicular to the axial direction oriented support member which is optionally formed as a circumferential support ring, and in the axial direction upstream and downstream webs together, the webs axially in front of the support member and the webs axially after the support element in a direction perpendicular to the axial - so in the circumferential direction and / or in the radial direction - are arranged offset to one another.
  • the burst-caused axial force flow between the insert wall contour and the outer compressor housing is deflected twice, thereby achieving an axially soft bending construction.
  • the axial load in the outer housing connections (screws) is significantly reduced.
  • the bending element is plastically axially compressed in the area of the circumferential ring, thereby reducing kinetic rupture energy.
  • the outer compressor housing via the contact surfaces of the fastening webs of the housing insert and finally into the connection to the bearing housing to be protected.
  • the inventive bursting concept provides for the case of a compressor burst on the smallest possible space and with a small number of standard screws for a high axial relief of the connection between the compressor housing and the bearing housing.
  • the kinetic energy released during failure is mainly absorbed by a plastic deformation of the inner housing parts.
  • the outer housing casing and the housing connecting screws are largely relieved.
  • Fig. 1 shows an exhaust gas turbocharger according to the prior art with a centrifugal compressor and a radial turbine.
  • the turbine 9 is mounted on the shaft 8 or integral therewith.
  • the turbine housing 90 encloses the turbine wheel and limits the flow channels, which lead the hot exhaust gas from the internal combustion engine via the turbine wheel to the exhaust systems.
  • the compressor 1 is also mounted on the shaft 8.
  • the compressor housing 10 is usually composed of a plurality of housing parts and is screwed by means of an external attachment 7 on the bearing housing. Depending on the design concept, the multipart compressor housing is assembled in a specific order. In the illustrated case, only the inner compressor housing, the housing insert 10, in the outer compressor housing, the spiral housing 20, inserted and possibly force-locking or form-fitting fastened thereto with fasteners.
  • the unit of inner and outer compressor housing is pushed over the already arranged on the shaft compressor wheel 1 and connected to the bearing housing 80.
  • the inner compressor housing 10 as indicated in the illustrated case, pressed when connecting to the bearing housing in the region of the diffuser downstream of the compressor outlet via diffuser blades 19 against a contact surface of the bearing housing 80 and thus clamped in operation between the outer compressor housing 20 and the bearing housing 80 ,
  • Fig. 2 shows an enlarged section of a compressor housing which is constructed analogously to the preceding, but which has a has designed according to the invention housing insert 10.
  • the housing insert is secured to the outer compressor housing (volute) 20 and, in the case of a bladed diffuser, is optionally clamped between the outer compressor housing 20 and the bearing housing 80 via the blade 19 of the diffuser.
  • the housing insert 10 is formed in one piece, but comprises a plurality of functional subregions.
  • the insert wall contour 11 delimits the flow channel 61 against the radially inner side.
  • the air which is to be supplied to the combustion chambers of the internal combustion engine then flows between the hub of the compressor wheel 1 and the insert wall contour 11.
  • the insert wall contour 11 is aligned axially in a radial compressor in the input area and then extends in the radial direction and opens into a spiral collecting space 62 of the outer compressor housing.
  • the insert wall contour can be provided with a predetermined breaking point 17 which selectively breaks the insert wall contour in the event of a burst of the compressor wheel, thereby supporting the energy reduction in the interior of the housing insert provided according to the invention.
  • the housing insert For centering the housing insert 10 on the outer compressor housing 20, the housing insert comprises a centering ring 12, which rests on the outer compressor housing.
  • the bearing surface can be sealed by means of a sealing element (sealing ring).
  • the outer compressor housing 20 in the region of the support surface for centering a closer to the compressor inlet side (ie in the figure to the left) narrowing cross-section, which may result in bursting a jamming of the centering in the constriction of the support surface on the outer compressor housing. With such a jamming part of the rupture energy in the region of the centering ring 12 can be reduced.
  • the centering ring 12 is connected via a connecting web 16 with the inner insert wall contour 11.
  • the connecting web 16 can, as in the Fig. 2 is indicated, optionally double curved (S-shaped) to be executed.
  • S-shaped connecting web 16 is heavily loaded on bending and thereby achieves a high axial resilience of the housing insert with a burst-related impact load on the outer housing connections
  • axially directed webs 14 lead to a support ring 13 which rests on likewise axially directed fastening webs 15 on an axial stop 21 of the outer compressor housing 20.
  • the fastening webs are optionally fastened by means of fastening means 18 on the outer compressor housing, for example, screws or screw pins may be arranged in openings provided for this purpose in the fastening webs.
  • the support ring may optionally be divided into a plurality of ring-segment-shaped support elements, which support elements then each have at least one web on both axial end sides, wherein the webs are arranged offset to one another on the opposite end faces.
  • the webs 14 between the support ring 13 and the centering ring 12 are distributed along the circumference of the support ring.
  • the fastening webs 15 are also distributed along the circumference of the support ring, but are arranged offset to the webs 14.
  • the fastening webs and the webs can be arranged offset from each other in addition to or instead of the offset in the circumferential direction and in the radial direction.
  • the fastening webs 15, the support ring 13, the webs 14 between the support ring and the centering ring and the centering ring 12 together form a bending element 111.
  • Fig. 3 and Fig. 4 show the removed housing insert 10 with the flexure construction.
  • the webs of the bending element 111 are offset in this embodiment in each case by half a pitch in the circumferential direction. Thanks to this offset of the power flow between the centering ring 12 and the axial stop 21 on the outer compressor housing 20 via the webs 14 between the centering ring and the support ring, the peripheral support ring 13, and the fastening webs 15, twice deflected, thereby achieving an axially soft bending construction.
  • the housing insert 10 When Ver Whyrbersten the housing insert 10 can be rotated by the impact of the compressor wheel fragments in the circumferential direction, which can lead to a shearing of the connection 18 between the mounting webs 15 and the outer compressor housing and thus a partial dissipation of the kinetic burst energy.
  • the axial bursting forces are introduced via the housing insert 10 into the outer compressor housing 20 and finally into the outer housing connection 7.
  • the housing connection 7 remains intact and the bearing housing 80 and the outer compressor housing 20 holds together.
  • a large part of the energy degraded in the housing insert is thus always to ensure that the housing connection 7 remains intact and the bearing housing 80 and the outer compressor housing 20 holds together.
  • the fragments thrown outwards may become wedged between the housing insert and the bearing housing in such a way that high axial forces load the outer compressor housing as well as the bearing housing in addition to the housing insert.
  • the axial forces are transmitted to the centering ring 12.
  • the axial forces are transmitted via the webs 14 to the support ring 13.
  • the peripheral support ring 13 is plastically upset in the sequence in the region of the connection to the webs 14, as shown in the Fig. 4 is indicated by the dotted course of the support ring 13 '. Due to the plastic deformation of the support ring kinetic rupture energy is reduced.
  • only a fraction of the initially existing rupture energy reaches the outer compressor housing 20 via the bearing surfaces of the fastening webs 15 and finally into the housing connection 7 to be protected in the radially outer region of the compressor housing.
  • the webs and the rings of the flexure are constructively designed so that for normal turbocharger operation a sufficiently high rigidity is achieved and the insert wall is assumed to be rigid, so that the games between the compressor and the housing are not affected. Furthermore, when designing the bending element, it must be ensured that the natural frequencies of the insert wall obtained do not come within the frequency range of the motor-induced excitation spectrum.
  • the housing insert may be made of a cast material (e.g., GGG-40).
  • the insert wall contour 11 can optionally delimit a cavity surrounding the flow channel 61 radially against the flow channel, in which already partially compressed air from the region of the compressor wheel blades can be guided back into the suction region.
  • an at least partially circumferential slot in the area of the compressor wheel blades can optionally be embedded in the insert wall contour.
  • a support ring which is oriented strictly perpendicular to the axial direction, it is also possible to provide a support ring oriented at an angle, preferably at an angle in the range between 60 ° and 90 ° to the axial direction, which is also compressed according to the invention and can thus absorb rupture energy.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Description

Technisches GebietTechnical area

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

Sie betrifft einen Verdichter eines Abgasturboladers mit einer Vorrichtung zur Sicherstellung der verdichterseitigen Berstschutzsicherheit des Abgasturboladers.It relates to a compressor of an exhaust gas turbocharger with a device for ensuring the compressor-side Berstschutzsicherheit the exhaust gas turbocharger.

Stand der TechnikState of the art

Für die Leistungssteigerung einer Brennkraftmaschine (Verbrennungsmotor) werden heutzutage standardmässig Abgasturbolader mit einem der Brennkammer der Brennkraftmaschine Luft für den Verbrennungsvorgang zuführenden Verdichter und einer Abgasturbine im Abgastrakt der Brennkraftmaschine eingesetzt. Mit der Aufladung der Brennkraftmaschine wird die Luft- und Kraftstoffmenge in den Zylindern erhöht und daraus ein merklicher Leistungsanstieg für die Brennkraftmaschine gewonnen. Der dafür verwendete Abgasturbolader setzt sich standardmässig aus einem Rotor, bestehend aus einem Verdichterrad und einem Turbinenrad sowie der Wellenlagerung, den strömungsführenden Gehäuseteilen (Verdichtergehäuse, Turbinengehäuse) und dem Lagergehäuse zusammen.For the increase in performance of an internal combustion engine (internal combustion engine) exhaust gas turbochargers are nowadays used by default with one of the combustion chamber of the internal combustion engine air for the combustion process supplying compressor and an exhaust gas turbine in the exhaust tract of the internal combustion engine. With the supercharging of the internal combustion engine, the amount of air and fuel in the cylinders is increased and from this a considerable increase in power for the internal combustion engine is obtained. The exhaust gas turbocharger used for this purpose is composed of a rotor consisting of a compressor wheel and a turbine wheel as well as the shaft bearing, the flow-guiding housing parts (compressor housing, turbine housing) and the bearing housing.

Wird die Brennkraftmaschine unter Volllast betrieben, und die Abgasturbine des Abgasturboladers entsprechend mit einem grossen Abgasstrom beaufschlagt, werden sehr hohe Umfangsgeschwindigkeiten an den Laufschaufelspitzen der Turbinen- sowie der Verdichterräder erreicht. Die maximale zulässige Rotordrehzahl eines Turboladers ist eine Funktion der Radgrösse, der Geometrie sowie der Festigkeitswerte der verwendeten Materialien. Generell unterliegen die rotierenden Komponenten sehr hohen Fliehkraftbelastungen und somit hohen Materialspannungen. Fehlstellen im Materialgefüge können unter Umständen zum Bersten des Verdichter- oder Turbinenrades führen, mit unvorhersehbaren Folgen für die benachbarten Gehäuse.If the internal combustion engine is operated under full load, and the exhaust gas turbocharger of the exhaust gas turbocharger is charged accordingly with a large exhaust gas flow, very high peripheral speeds are achieved at the blade tips of the turbine and compressor wheels. The maximum permissible rotor speed of a turbocharger is a function of the wheel size, the geometry and the strength values of the materials used. In general, the rotating components are subject to very high centrifugal forces and thus high material tensions. Defects in the material structure can possibly lead to bursting of the compressor or turbine wheel, with unpredictable consequences for the adjacent housing.

Das initiale Versagensbild eines Verdichterrades lässt sich durch einen Schaufelbruch respektive ein mehrteiliges Nabenbersten beschreiben. Beim Schaufelbersten versagen die Schaufeln im Fussbereich des Verdichters, wobei die Radnabe intakt bleibt. Beim mehrteiligen Nabenbersten zerfällt der Nabenbereich meist in zwei bis vier Bruchstücke. Der kritischste Fall des Verdichterberstens ist der 3-teilige Nabenbruch mit drei etwa gleich grossen Bruchstücken (3x120° Sektoren). Das Berstschutzkonzept (Containmentkonzept) eines Abgasturboladers ist dahingehend auszulegen, dass sämtliche Bruchstücke, für den Fall eines mehrteiligen Nabenberstens, bei einer vorgegebenen Berstdrehzahl innerhalb der äusseren Gehäuseummantelung zurückgehalten werden. So wird bei der Konstruktion des Abgasturboladers darauf geachtet, dass die kinetische Energie des Verdichters bereits in den inneren, rotornahen Gehäusepartien durch plastische Deformation abgebaut wird und dadurch die verbleibende kinetische Energie der radial nach Aussen geschleuderten Bruchstücke nicht ausreicht, um die äussere Gehäuseummantelung zu durchdringen oder um die äusseren Gehäuseverbindungen (z.B. Schrauben) zum Versagen zu bringen.The initial failure pattern of a compressor wheel can be described by a blade break or a multi-part hub burst. When shovels burst, the blades fail in the foot area of the compressor, leaving the wheel hub intact. In the case of multipart hub bursting, the hub area usually breaks down into two to four fragments. The most critical case of the compressor rupture is the 3-part hub break with three roughly equal fragments (3x120 ° sectors). The burst protection concept (containment concept) of an exhaust gas turbocharger is to be interpreted as meaning that all fragments, in the case of a multi-part hub burst, are retained within the outer casing casing at a predetermined bursting speed. Thus, in the construction of the exhaust gas turbocharger care is taken that the kinetic energy of the compressor is degraded in the inner, rotor close housing parts by plastic deformation and thus the remaining kinetic energy of the radially outwardly thrown fragments is not sufficient to penetrate the outer casing casing or to bring the outer housing connections (eg screws) to failure.

Verschiedene Massnahmen zur Reduktion der Belastung der Gehäuseverbindung im Falle eines berstenden Verdichterrades sind bekannt.Various measures for reducing the load on the housing connection in the event of a bursting compressor wheel are known.

Gemäss WO 02/090722 ist eine Sollbruchstelle in der den Strömungskanal über den Laufschaufeln des Verdichterrades radial aussen begrenzenden Gehäuseeinsatzwand vorgesehen, um im Falle eines Verdichterradberstens das axiale Wegschleudern von Gehäuseteilen oder am Verdichtergehäuse befestigten Bauteilen zu verhindern.According to WO 02/090722 is a predetermined breaking point in the flow channel over the blades of the compressor radially outwardly bounding housing insert wall provided to prevent in the case of Verdichterradberstens the axial thrown away housing parts or components attached to the compressor housing.

In EP 1-586-745 wird mittels eines Stützflansches und eines ausreichend grossen Abstands des Stützflansches zur Gehäuseeinsatzwand verhindert, dass im Falle eines berstenden Verdichterrades eine direkte axiale Impulsübertragung von wegfliegenden Verdichterradteilen auf das Lufteintrittsgehäuse stattfindet und so die Belastung der oberen Verbindungen zwischen den Gehäuseteilen reduziert und das Aufbrechen der Verbindung sowie das Austreten der Bruchstücke unterbunden.In EP 1-586-745 is prevented by means of a support flange and a sufficiently large distance of the support flange to the housing insert wall that takes place in the case of a bursting compressor impeller direct axial momentum transferring wegfliegenden compressor wheel on the air inlet housing, thus reducing the load on the upper connections between the housing parts and the breaking of the compound and the Leakage of the fragments prevented.

In einer weiteren Variante gemäss GB 2-414-769 wird die axiale Belastung der Gehäuseeinsatzwand beim Nabenbersten durch die lange Dehnschrauben ausreichend aufgenommen und die geschraubte Flanschverbindung zwischen dem Verdichtergehäuse und dem Lagergehäuse hinreichend entlastet.In a further variant according to GB 2-414-769 the axial load of the housing wall when Hubbersten is sufficiently absorbed by the long expansion bolts and relieved the threaded flange connection between the compressor housing and the bearing housing sufficiently.

In der Variante nach DE 10-2004-028-133 wird eine derartige Dehnschraube mit einer zusätzlichen Passung zwischen der Schraube, der Gehäuseeinsatzwand und dem Verdichtergehäuse versehen. Durch die Passung werden die beim Bersten auftretenden Umfangskräfte aufgenommen und ein Verdrehen der Einsatzwand zum Verdichtergehäuse vermieden.In the variant after DE 10-2004-028-133 Such an expansion screw is provided with an additional fit between the screw, the housing insert wall and the compressor housing. The fit absorbs the circumferential forces that occur when bursting and avoids a twisting of the insert wall to the compressor housing.

In DE 10-2005-039-820 wird die Gehäuseeinsatzwand mit Halteeinrichtung ergänzt, um dadurch die axial nach vorne geschleuderten Bruchstücke des Verdichterrades sowie der Gehäuseeinsatzwand aufzufangen respektive zu verklemmen.In DE 10-2005-039-820 the housing insert wall is supplemented with holding means to thereby catch the axially forwardly thrown fragments of the compressor wheel and the housing insert wall respectively to jam.

Die oben beschriebenen Varianten benötigen meist grosse Bauvolumen zur Umsetzung der darin beschriebenen Merkmale. Weiter werden in einigen Varianten sehr lange Dehnpassschrauben benötigt, was höhere Anforderungen an die Genauigkeit der Gehäusefertigung, die Fertigungskosten sowie die Baumasse des Turboladers stellt. In DE 10-2005-039-820 , DE 10-2004-028-133 sowie GB 2-414-769 werden die axial wirkenden Berstkräfte zuerst durch die Dehnpassschrauben aufgenommen und erst anschliessend über die Gehäusewandung in die oberen, kürzeren Schraubverbindungen zwischen Verdichter- und Lagergehäuse geleitet. Diese letztgenannten Schraubenverbindungen sind die kritischen und zu schützenden Stellen eines verdichterseitigen Berstkonzepts.The variants described above usually require large volumes to implement the features described therein. Furthermore, in some variants very long Dehnpassschrauben required, which places higher demands on the accuracy of the housing production, the manufacturing costs and the building mass of the turbocharger. In DE 10-2005-039-820 . DE 10-2004-028-133 such as GB 2-414-769 The axially acting bursting forces are first absorbed by the Dehnpassschrauben and only then passed through the housing in the upper, shorter screw connections between the compressor and bearing housings. These last-mentioned screw connections are the critical points to be protected of a compressor-side bursting concept.

Kurze Darstellung der ErfindungBrief description of the invention

Die Aufgabe der Erfindung besteht darin, den Gehäuseverbund eines Verdichters eines Abgasturboladers für den Fall eines versagenden Verdichterrades berstsicher zu gestalten, indem die äusseren Gehäuseverbindungen zwischen dem Verdichtergehäuse und dem Lagergehäuse vor einem Versagen geschützt werden.The object of the invention is to make the housing assembly of a compressor of an exhaust gas turbocharger burstable in the event of a failed compressor wheel by the outer housing connections between the compressor housing and the bearing housing are protected against failure.

Erfindungsgemäss wird dies mit einem Gehäuseverbund erreicht, welcher einen an einem Axialanschlag des äusseren Verdichtergehäuses anliegenden Gehäuseeinsatzes sowie ein Biegeelement im Kraftfluss zwischen der den Strömungskanal begrenzenden Einsatzwandkontur und dem äusseren Verdichtergehäuse umfasst. Das Biegeelement setzt sich dabei aus einem, in einem Winkel, vorzugsweise senkrecht zur axialen Richtung ausgerichteten Tragelement, welches optional als ein umlaufender Tragring ausgebildet ist, und in axialer Richtung vor- und nachgelagerten Stegen zusammen, wobei die Stege axial vor dem Tragelement und die Stege axial nach dem Tragelement in einer Richtung senkrecht zur Axialen - also in Umfangsrichtung und/ oder in radialer Richtung - versetzt zueinander angeordnet sind. Dank diesen versetzt angeordneten Stegen wird der berstbedingte axiale Kraftfluss zwischen der Einsatzwandkontur und dem äusseren Verdichtergehäuse zweifach umgelenkt und dadurch eine axial weiche Biegekonstruktion erreicht. Dabei wird die axiale Belastung in den äusseren Gehäuseverbindungen (Schrauben) signifikant reduziert.According to the invention this is achieved with a housing composite, which comprises a voltage applied to an axial stop of the outer compressor housing housing insert and a bending element in the power flow between the flow channel limiting insert wall contour and the outer compressor housing. The bending element is made up of a, at an angle, preferably perpendicular to the axial direction oriented support member which is optionally formed as a circumferential support ring, and in the axial direction upstream and downstream webs together, the webs axially in front of the support member and the webs axially after the support element in a direction perpendicular to the axial - so in the circumferential direction and / or in the radial direction - are arranged offset to one another. Thanks to these staggered webs, the burst-caused axial force flow between the insert wall contour and the outer compressor housing is deflected twice, thereby achieving an axially soft bending construction. The axial load in the outer housing connections (screws) is significantly reduced.

Beim Verdichterbersten drücken die einzelnen Bruchstücke in axialer, radialer sowie in Umfangsrichtung auf den Gehäuseeinsatz. Das Biegeelement wird erfindungsgemäss im Bereich des umlaufenden Rings plastisch axial gestaucht und dadurch kinetische Berstenergie abgebaut. So gelangt nur ein Bruchteil der ursprünglich vorhandenen Berstenergie über die Auflageflächen der Befestigungsstege des Gehäuseeinsatzes ins äussere Verdichtergehäuse und schlussendlich in die zu schützende Verbindung zum Lagergehäuse.When Verdichterbersten press the individual fragments in the axial, radial and circumferential direction of the housing insert. According to the invention, the bending element is plastically axially compressed in the area of the circumferential ring, thereby reducing kinetic rupture energy. Thus, only a fraction of the originally existing rupture energy reaches the outer compressor housing via the contact surfaces of the fastening webs of the housing insert and finally into the connection to the bearing housing to be protected.

Das erfindungsgemässe Berstkonzept sorgt für den Fall eines Verdichterbersten auf einem möglichst kleinen Bauraum und mit einer geringen Anzahl Standardschrauben für eine hohe axiale Entlastung der Verbindung zwischen dem Verdichtergehäuse und dem Lagergehäuse.The inventive bursting concept provides for the case of a compressor burst on the smallest possible space and with a small number of standard screws for a high axial relief of the connection between the compressor housing and the bearing housing.

Die beim Versagen frei werdende kinetische Energie wird hauptsächlich durch eine plastische Deformation der inneren Gehäuseteile aufgenommen. Dadurch werden die äussere Gehäuseummantelung und die Gehäuseverbindungsschrauben weitgehend entlastet.The kinetic energy released during failure is mainly absorbed by a plastic deformation of the inner housing parts. As a result, the outer housing casing and the housing connecting screws are largely relieved.

Weitere Vorteile ergeben sich aus den abhängigen Ansprüchen.Further advantages emerge from the dependent claims.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Folgend ist anhand der Zeichnungen eine Ausführungsform des erfindungsgemässen Berstkonzepts für den Verdichter eines Abgasturboladers beschrieben. Hierbei zeigt

Fig. 1
ein Schnittbild eines Abgasturboladers gemäss dem Stand der Technik, mit einem Radialverdichter mit einem äusseren Verdichtergehäuse (Spiralgehäuse) und einem Gehäuseeinsatz als inneres Verdichtergehäuse,
Fig. 2
ein Schnittbild eines Verdichtergehäuses mit dem äusseren Verdichtergehäuse und dem erfindungsgemäss ausgestalteten Gehäuseeinsatz,
Fig.3
eine isometrische Ansicht auf den erfindungsgemäss ausgestalteten Gehäuseeinsatz nach Fig. 2, und
Fig.4
eine Seitenansicht in radialer Richtung auf den erfindungsgemäss ausgestalteten Gehäuseeinsatz nach Fig. 2 mit angedeuteter Verbiegung im Berstfall.
An embodiment of the inventive bursting concept for the compressor of an exhaust gas turbocharger is described below with reference to the drawings. This shows
Fig. 1
a sectional view of an exhaust gas turbocharger according to the prior art, with a centrifugal compressor with an outer compressor housing (spiral housing) and a housing insert as an inner compressor housing,
Fig. 2
a sectional view of a compressor housing with the outer compressor housing and the inventively designed housing insert,
Figure 3
an isometric view of the inventively designed housing insert according to Fig. 2 , and
Figure 4
a side view in the radial direction on the inventively designed housing insert after Fig. 2 with indicated bending in case of bursting.

Weg zur Ausführung der ErfindungWay to carry out the invention

Fig. 1 zeigt einen Abgasturbolader gemäss dem Stand der Technik mit einem Radialverdichter und einer Radialturbine. Das Turbinenrad 9 ist auf der Welle 8 befestigt oder einteilig mit dieser ausgeführt. Das Turbinengehäuse 90 umschliesst das Turbinenrad und begrenzt die Strömungskanäle, welche das heisse Abgas von der Brennkraftmaschine über das Turbinenrad zu den Auspuffanlagen führen. Das Verdichterrad 1 ist ebenfalls auf der Welle 8 befestigt. Das Verdichtergehäuse 10 setzt sich in der Regel aus mehreren Gehäuseteilen zusammen und wird mittels einer äusseren Befestigung 7 am Lagergehäuse festgeschraubt. Je nach Aufbaukonzept wird das mehrteilige Verdichtergehäuse in bestimmter Reihenfolge zusammengesetzt. Im dargestellten Fall wird erst das innere Verdichtergehäuse, der Gehäuseeinsatz 10, in das äussere Verdichtergehäuse, das Spiralgehäuse 20, eingeschoben und allenfalls mit Befestigungsmitteln kraft- oder formschlüssig daran befestigt. Danach wird die Einheit aus innerem und äusserem Verdichtergehäuse über das bereits auf der Welle angeordnete Verdichterrad 1 geschoben und mit dem Lagergehäuse 80 verbunden. Optional kann das innere Verdichtergehäuse 10, wie im abgebildeten Fall angedeutet, beim Verbinden mit dem Lagergehäuse im Bereich des Diffusors stromab des Verdichteraustritts über Diffusorschaufeln 19 gegen eine Kontaktfläche des Lagergehäuses 80 gepresst und somit im Betrieb zwischen dem äusseren Verdichtergehäuse 20 und dem Lagergehäuse 80 festgeklemmt werden. Fig. 1 shows an exhaust gas turbocharger according to the prior art with a centrifugal compressor and a radial turbine. The turbine 9 is mounted on the shaft 8 or integral therewith. The turbine housing 90 encloses the turbine wheel and limits the flow channels, which lead the hot exhaust gas from the internal combustion engine via the turbine wheel to the exhaust systems. The compressor 1 is also mounted on the shaft 8. The compressor housing 10 is usually composed of a plurality of housing parts and is screwed by means of an external attachment 7 on the bearing housing. Depending on the design concept, the multipart compressor housing is assembled in a specific order. In the illustrated case, only the inner compressor housing, the housing insert 10, in the outer compressor housing, the spiral housing 20, inserted and possibly force-locking or form-fitting fastened thereto with fasteners. Thereafter, the unit of inner and outer compressor housing is pushed over the already arranged on the shaft compressor wheel 1 and connected to the bearing housing 80. Optionally, the inner compressor housing 10, as indicated in the illustrated case, pressed when connecting to the bearing housing in the region of the diffuser downstream of the compressor outlet via diffuser blades 19 against a contact surface of the bearing housing 80 and thus clamped in operation between the outer compressor housing 20 and the bearing housing 80 ,

Alternativ gibt es Aufbaukonzepte, bei welchen das innere Verdichtergehäuse, also der Gehäuseeinsatz, nachträglich in das bereits mit dem Lagergehäuse verbunden äussere Verdichtergehäuse eingesetzt und von der Verdichterseite her mittels Schrauben am äusseren Verdichtergehäuse befestigt wird.Alternatively, there are design concepts in which the inner compressor housing, so the housing insert, subsequently inserted into the already connected to the bearing housing outer compressor housing and is fastened by the compressor side by means of screws on the outer compressor housing.

Fig. 2 zeigt einen vergrössert dargestellten Ausschnitt eines Verdichtergehäuses welches analog dem vorhergehenden aufgebaut ist, welches jedoch über einen erfindungsgemäss ausgestalteten Gehäuseeinsatz 10 verfügt. Der Gehäuseeinsatz ist am äusseren Verdichtergehäuse (Spiralgehäuse) 20 befestigt und, im Fall eines beschaufelten Diffusors, optional zwischen dem äusseren Verdichtergehäuse 20 und dem Lagergehäuse 80 über die Schaufel 19 des Diffusors festgeklemmt. Der Gehäuseeinsatz 10 ist einteilig ausgebildet, umfasst jedoch mehrere funktionelle Teilbereiche. Fig. 2 shows an enlarged section of a compressor housing which is constructed analogously to the preceding, but which has a has designed according to the invention housing insert 10. The housing insert is secured to the outer compressor housing (volute) 20 and, in the case of a bladed diffuser, is optionally clamped between the outer compressor housing 20 and the bearing housing 80 via the blade 19 of the diffuser. The housing insert 10 is formed in one piece, but comprises a plurality of functional subregions.

Gegen radial innen begrenzt die Einsatzwandkontur 11 den Strömungskanal 61. Zwischen der Nabe des Verdichterrades 1 und der Einsatzwandkontur 11 strömt demnach die Luft, welche den Brennkammern der Brennkraftmaschine zugeführt werden soll. Die Einsatzwandkontur 11 ist bei einem Radialverdichter im Eingangsbereich axial ausgerichtet und verläuft anschliessend in die radiale Richtung gekrümmt und mündet in einem spiralförmigen Sammelraum 62 des äusseren Verdichtergehäuses. Im Bereich des Diffusors stromab des Verdichteraustritts kann die Einsatzwandkontur mit einer Sollbruchstelle 17 versehen sein, welche im Berstfall des Verdichterrades die Einsatzwandkontur gezielt brechen lässt, und dadurch den erfindungsgemäss vorgesehenen Energieabbau im Innern des Gehäuseeinsatzes unterstützt.The insert wall contour 11 delimits the flow channel 61 against the radially inner side. The air which is to be supplied to the combustion chambers of the internal combustion engine then flows between the hub of the compressor wheel 1 and the insert wall contour 11. The insert wall contour 11 is aligned axially in a radial compressor in the input area and then extends in the radial direction and opens into a spiral collecting space 62 of the outer compressor housing. In the region of the diffuser downstream of the compressor outlet, the insert wall contour can be provided with a predetermined breaking point 17 which selectively breaks the insert wall contour in the event of a burst of the compressor wheel, thereby supporting the energy reduction in the interior of the housing insert provided according to the invention.

Zur Zentrierung des Gehäuseeinsatzes 10 am äusseren Verdichtergehäuse 20 umfasst der Gehäuseeinsatz einen Zentrierring 12, welcher am äusseren Verdichtergehäuse aufliegt. Optional kann die Auflagefläche mittels eines Dichtelementes (Dichtungsring) abgedichtet werden. Optional kann, wie das in der Fig. 2 angedeutet ist, das äussere Verdichtergehäuse 20 im Bereich der Auflagefläche zum Zentrierring einen zur Verdichtereintrittsseite hin (also in der Fig. nach links) enger werdenden Querschnitt aufweisen, wodurch sich im Berstfall eine Verklemmung des Zentrierrings in der Verengung der Auflagefläche am äusseren Verdichtergehäuse ergeben kann. Mit einer solchen Verklemmung kann ein Teil der Berstenergie im Bereich des Zentrierringes 12 abgebaut werden.For centering the housing insert 10 on the outer compressor housing 20, the housing insert comprises a centering ring 12, which rests on the outer compressor housing. Optionally, the bearing surface can be sealed by means of a sealing element (sealing ring). Optionally, like that in the Fig. 2 is indicated, the outer compressor housing 20 in the region of the support surface for centering a closer to the compressor inlet side (ie in the figure to the left) narrowing cross-section, which may result in bursting a jamming of the centering in the constriction of the support surface on the outer compressor housing. With such a jamming part of the rupture energy in the region of the centering ring 12 can be reduced.

Der Zentrierring 12 ist über einen Verbindungssteg 16 mit der inneren Einsatzwandkontur 11 verbunden. Der Verbindungssteg 16 kann, wie in der Fig. 2 angedeutet ist, optional doppelt gekrümmt (S-förmig) ausgeführt sein. Im Berstfall wird der S-förmig gebogene Verbindungssteg 16 stark auf Biegung belastet und dadurch eine hohe axiale Nachgiebigkeit des Gehäuseeinsatzes bei einer berstbedingten Stossbelastung auf die äusseren Gehäuseverbindungen erreichtThe centering ring 12 is connected via a connecting web 16 with the inner insert wall contour 11. The connecting web 16 can, as in the Fig. 2 is indicated, optionally double curved (S-shaped) to be executed. In the event of a burst, the S-shaped connecting web 16 is heavily loaded on bending and thereby achieves a high axial resilience of the housing insert with a burst-related impact load on the outer housing connections

Vom Zentrierring 12 aus führen axial gerichtete Stege 14 zu einem Tragring 13, welcher über ebenfalls axial gerichtete Befestigungsstege 15 an einem Axialanschlag 21 des äusseren Verdichtergehäuses 20 aufliegt. Die Befestigungsstege sind dabei optional mittels Befestigungsmitteln 18 am äusseren Verdichtergehäuse befestigt, beispielsweise können Schrauben oder Schraubenstifte in dafür vorgesehenen Öffnungen in den Befestigungsstegen angeordnet sein. Der Tragring kann optional in mehrere ringsegmentförmige Tragelemente aufgeteilt sein, welche Tragelemente dann auf beiden axialen Stirnseiten jeweils je mindestens einen Steg aufweist, wobei die Stege auf den gegenüberliegenden Stirnseiten zueinander versetzt angeordnete sind.From the centering ring 12 axially directed webs 14 lead to a support ring 13 which rests on likewise axially directed fastening webs 15 on an axial stop 21 of the outer compressor housing 20. The fastening webs are optionally fastened by means of fastening means 18 on the outer compressor housing, for example, screws or screw pins may be arranged in openings provided for this purpose in the fastening webs. The support ring may optionally be divided into a plurality of ring-segment-shaped support elements, which support elements then each have at least one web on both axial end sides, wherein the webs are arranged offset to one another on the opposite end faces.

Die Stege 14 zwischen dem Tragring 13 und dem Zentrierring 12 sind entlang dem Umfang des Tragrings verteilt. Die Befestigungsstege 15 sind ebenfalls entlang dem Umfang des Tragrings verteilt, sind jedoch zu den Stegen 14 versetzt angeordnet. Optional können die Befestigungsstege und die Stege zusätzlich zur oder anstelle der Versetzung in Umfangsrichtung auch in radialer Richtung zueinander versetzt angeordnet sein.The webs 14 between the support ring 13 and the centering ring 12 are distributed along the circumference of the support ring. The fastening webs 15 are also distributed along the circumference of the support ring, but are arranged offset to the webs 14. Optionally, the fastening webs and the webs can be arranged offset from each other in addition to or instead of the offset in the circumferential direction and in the radial direction.

Die Befestigungsstege 15, der Tragring 13, die Stege 14 zwischen dem Tragring und dem Zentrierring und der Zentrierring 12 bilden zusammen ein Biegeelement 111. Fig. 3 und Fig. 4 zeigen den ausgebauten Gehäuseeinsatz 10 mit der Biegeelementkonstruktion. Die Stege des Biegeelements 111 sind in dieser Ausführung jeweils um eine halbe Teilung in Umfangsrichtung versetzt. Dank dieses Versatzes wird der Kraftfluss zwischen dem Zentrierring 12 und dem Axialanschlag 21 am äusseren Verdichtergehäuse 20 über den Stegen 14 zwischen dem Zentrierring und dem Tragring, den umlaufenden Tragring 13, sowie den Befestigungsstegen 15, zweifach umgelenkt und dadurch eine axial weiche Biegekonstruktion erreicht.The fastening webs 15, the support ring 13, the webs 14 between the support ring and the centering ring and the centering ring 12 together form a bending element 111. Fig. 3 and Fig. 4 show the removed housing insert 10 with the flexure construction. The webs of the bending element 111 are offset in this embodiment in each case by half a pitch in the circumferential direction. Thanks to this offset of the power flow between the centering ring 12 and the axial stop 21 on the outer compressor housing 20 via the webs 14 between the centering ring and the support ring, the peripheral support ring 13, and the fastening webs 15, twice deflected, thereby achieving an axially soft bending construction.

Beim Verdichterbersten kann der Gehäuseeinsatz 10 durch das Auftreffen der Verdichterradbruchstücke in Umfangsrichtung verdreht werden, was zu einem Abscheren der Verbindung 18 zwischen den Befestigungsstegen 15 und dem äusseren Verdichtergehäuse und somit einer teilweisen Dissipation der kinetischen Berstenergie führen kann. Die axialen Berstkräfte werden über den Gehäuseeinsatz 10 in das äussere Verdichtergehäuse 20 und abschliessend in die äussere Gehäuseverbindung 7 eingeleitet. Um ein Austreten der Bruchstücke nach Aussen zu verhindern ist somit immer sicher zu stellen, dass die Gehäuseverbindung 7 intakt bleibt und das Lagergehäuse 80 und das äussere Verdichtergehäuse 20 zusammenhält. Um dies zu erreichen, wird erfindungsgemäss ein grosser Teil der Energie in dem Gehäuseeinsatz abgebaut. Die nach Aussen geschleuderten Bruchstücke können sich zwischen dem Gehäuseeinsatz und dem Lagergehäuse derart verkeilen, dass hohe Axialkräfte neben dem Gehäuseeinsatz auch das äussere Verdichtergehäuse sowie das Lagergehäuse belasten. In erster Linie belasten die Bruchstücke des Verdichterrades jedoch die Einsatzwandkontur 11. Über den Verbindungssteg 16 werden die Axialkräfte auf den Zentrierring 12 übertragen. Vom Zentrierring 12 wiederum werden die Axialkräfte über die Stege 14 auf den Tragring 13 übertragen. Der umlaufende Tragring 13 wird in der Folge im Bereich der Verbindung zu den Stegen 14 plastisch gestaucht, wie dies in der Fig. 4 anhand des gepunkteten Verlaufs des Tragrings 13' angedeutet ist. Durch die plastische Verformung des Tragrings wird kinetische Berstenergie abgebaut. So gelangt nur ein Bruchteil der ursprünglich vorhandenen Berstenergie über die Auflageflächen der Befestigungsstege 15 ins äussere Verdichtergehäuse 20 und schlussendlich in die zu schützende Gehäuseverbindung 7 im radial äusseren Bereich des Verdichtergehäuses.When Verdichterbersten the housing insert 10 can be rotated by the impact of the compressor wheel fragments in the circumferential direction, which can lead to a shearing of the connection 18 between the mounting webs 15 and the outer compressor housing and thus a partial dissipation of the kinetic burst energy. The axial bursting forces are introduced via the housing insert 10 into the outer compressor housing 20 and finally into the outer housing connection 7. In order to prevent leakage of the fragments to the outside is thus always to ensure that the housing connection 7 remains intact and the bearing housing 80 and the outer compressor housing 20 holds together. To this, too reach, according to the invention, a large part of the energy degraded in the housing insert. The fragments thrown outwards may become wedged between the housing insert and the bearing housing in such a way that high axial forces load the outer compressor housing as well as the bearing housing in addition to the housing insert. However, primarily the fragments of the compressor wheel load the insert wall contour 11. Via the connecting web 16, the axial forces are transmitted to the centering ring 12. From the centering ring 12, in turn, the axial forces are transmitted via the webs 14 to the support ring 13. The peripheral support ring 13 is plastically upset in the sequence in the region of the connection to the webs 14, as shown in the Fig. 4 is indicated by the dotted course of the support ring 13 '. Due to the plastic deformation of the support ring kinetic rupture energy is reduced. Thus, only a fraction of the initially existing rupture energy reaches the outer compressor housing 20 via the bearing surfaces of the fastening webs 15 and finally into the housing connection 7 to be protected in the radially outer region of the compressor housing.

Die Stege und die Ringe des Biegeelementes sind konstruktiv so auszulegen, dass für den normalen Turboladerbetrieb eine ausreichend hohe Steifigkeit erreicht wird und die Einsatzwand als starr anzunehmen ist, womit die Spiele zwischen dem Verdichterrad und dem Gehäuse nicht beeinträchtigt werden. Weiter ist bei der Auslegung des Biegeelementes darauf zu achten, dass die erzielten Eigenfrequenzen der Einsatzwand nicht in den Frequenzbereich des motorinduzierten Anregungsspektrums zu liegen kommen. Der Gehäuseeinsatz kann aus einem Gusswerkstoff (z.B. GGG-40) bestehen.The webs and the rings of the flexure are constructively designed so that for normal turbocharger operation a sufficiently high rigidity is achieved and the insert wall is assumed to be rigid, so that the games between the compressor and the housing are not affected. Furthermore, when designing the bending element, it must be ensured that the natural frequencies of the insert wall obtained do not come within the frequency range of the motor-induced excitation spectrum. The housing insert may be made of a cast material (e.g., GGG-40).

Die Einsatzwandkontur 11 kann optional einen den Strömungskanal 61 radial umgebenden Hohlraum gegen den Strömungskanal abgrenzen, in dem bereits teilweise verdichtete Luft aus dem Bereich der Verdichterradschaufeln zurück in den Ansaugbereich geführt werden kann. Hierzu kann optional in die Einsatzwandkontur ein zumindest teilweise umlaufender Schlitz im Bereich der Verdichterradschaufeln eingelassen sein.The insert wall contour 11 can optionally delimit a cavity surrounding the flow channel 61 radially against the flow channel, in which already partially compressed air from the region of the compressor wheel blades can be guided back into the suction region. For this purpose, an at least partially circumferential slot in the area of the compressor wheel blades can optionally be embedded in the insert wall contour.

Anstelle des streng senkrecht zur axialen Richtung ausgerichteten Tragrings kann auch ein in einem Winkel, vorzugsweise in einem Winkel im Bereich zwischen 60° und 90° zur axialen Richtung ausgerichteter Tragring vorgesehen sein, welcher ebenfalls erfindungsgemäss gestaucht werden und dadurch Berstenergie aufnehmen kann.Instead of the support ring which is oriented strictly perpendicular to the axial direction, it is also possible to provide a support ring oriented at an angle, preferably at an angle in the range between 60 ° and 90 ° to the axial direction, which is also compressed according to the invention and can thus absorb rupture energy.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Verdichterradcompressor
77
Befestigung des Verdichtergehäuses am LagergehäuseFixing the compressor housing to the bearing housing
88th
Wellewave
99
Turbinenradturbine
1010
Gehäuseeinsatz (inneres Verdichtergehäuse)Housing insert (inner compressor housing)
1111
EinsatzwandkonturInsert wall contour
1212
Zentrierringcentering
1313
Tragelement, TragringSupporting element, support ring
1414
Stegweb
1515
Befestigungs-StegFastening web
1616
Verbindungs-StegConnecting rib
1717
SollbruchstelleBreaking point
1818
Befestigungsmittel (Bohrung/ Schraube)Fastener (bore / screw)
1919
Diffusorschaufeldiffuser vane
2020
Spiralgehäuse (äusseres Verdichtergehäuse)Spiral housing (outer compressor housing)
2121
Axialanschlagaxial stop
6161
Strömungskanalflow channel
6262
Sammelraum im SpiralgehäuseCollecting space in the spiral housing
8080
Lagergehäusebearing housing
9090
Turbinengehäuseturbine housing
111111
Biegeelementflexure

Claims (11)

  1. Compressor of an exhaust-gas turbocharger, comprising a compressor wheel (1) which is rotatable about an axis, comprising an outer compressor housing (20) and comprising a housing insert (10) arranged radially outside the compressor wheel (1), wherein the housing insert comprises an insert wall contour (11) which, together with a hub of the compressor wheel (1), delimits a flow duct (61),
    characterized in that
    the housing insert (10) bears against an axial stop (21), which is directed towards the compressor wheel, of the outer compressor housing (20), wherein a flexural element (111) is provided to transmit axial forces from the insert wall contour (11) to the outer compressor housing (20), wherein the flexural element (111) comprises at least two axially oriented webs (14, 15) arranged offset relative to one another and comprises a support element (13) which connects the webs (14, 15) to one another, wherein the support element (13) is oriented at an angle with respect to the axial direction and is arranged between the webs (14, 15) as viewed in the axial direction.
  2. Compressor according to Claim 1, wherein the flexural element (111) comprises an ring-segment-shaped support element (13), wherein the support element (13) is oriented in the circumferential direction of the compressor wheel, and wherein the support element (13) has a plurality of axially oriented webs (14) on one axial side, and has at least one axially oriented web (15) on the other axial side.
  3. Compressor according to Claim 1, the flexural element (111) comprising a ring-shaped support element (13), wherein the support element (13) is arranged in the circumferential direction of the compressor wheel, and wherein the support element (13) has a plurality of axially oriented webs (14, 15) on both axial sides.
  4. Compressor according to Claim 1, wherein the support element (13) is oriented perpendicular to the axial direction and is arranged between the webs (14, 15) as viewed in the axial direction.
  5. Compressor according to Claim 4, wherein the flexural element (111) comprises a ring-segment-shaped support element (13), wherein the support element (13) is oriented in the circumferential direction of the compressor wheel, and wherein the support element (13) has a plurality of axially oriented webs (14) on one axial side, and has at least one axially oriented web (15) on the other axial side.
  6. Compressor according to Claim 4, the flexural element (111) comprising a ring-shaped support element (13), wherein the support element (13) is arranged in the circumferential direction of the compressor wheel, and wherein the support element (13) has a plurality of axially oriented webs (14, 15) on both axial sides.
  7. Compressor according to one of Claims 1 to 6, wherein to transmit axial forces from the insert wall contour (11) to the axial stop (21) of the outer compressor housing (20), the flexural element (111) is arranged in the force flow between the insert wall contour (11) and the axial stop (21).
  8. Compressor according to one of Claims 1 to 6, wherein the flexural element (111) is part of the outer compressor housing (20), and, to transmit axial forces from the insert wall contour (11) to the outer compressor housing (20), the axial stop (21) is arranged in the force flow between the insert wall contour (11) and the flexural element (111).
  9. Compressor according to one of Claims 1 to 6, wherein to transmit axial forces from the insert wall contour (11) to the flexural element (111), the flexural element (111) comprises an encircling centring ring (12) which is connected via a connecting web (16) to the insert wall contour (11).
  10. Compressor according to Claim 9, wherein the connecting web (16) between the insert wall contour (11) and the flexural element (111) is of doubly curved form, that is to say S-shaped in axial profile.
  11. Exhaust-gas turbocharger comprising a compressor according to one of Claims 1 to 6.
EP10150616A 2009-02-04 2010-01-13 Burst protection device for radial compressor Active EP2216517B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10150616A EP2216517B1 (en) 2009-02-04 2010-01-13 Burst protection device for radial compressor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP09152067A EP2216516A1 (en) 2009-02-04 2009-02-04 Burst protection device for radial compressor
EP10150616A EP2216517B1 (en) 2009-02-04 2010-01-13 Burst protection device for radial compressor

Publications (2)

Publication Number Publication Date
EP2216517A1 EP2216517A1 (en) 2010-08-11
EP2216517B1 true EP2216517B1 (en) 2012-07-11

Family

ID=40469896

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09152067A Withdrawn EP2216516A1 (en) 2009-02-04 2009-02-04 Burst protection device for radial compressor
EP10150616A Active EP2216517B1 (en) 2009-02-04 2010-01-13 Burst protection device for radial compressor

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09152067A Withdrawn EP2216516A1 (en) 2009-02-04 2009-02-04 Burst protection device for radial compressor

Country Status (5)

Country Link
US (1) US8393851B2 (en)
EP (2) EP2216516A1 (en)
JP (1) JP5074541B2 (en)
KR (1) KR101157440B1 (en)
CN (1) CN101793266B (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009049841B4 (en) * 2009-10-14 2015-01-15 Mtu Friedrichshafen Gmbh Gas turbine engine and internal combustion engine
DE102010064025A1 (en) 2010-12-23 2012-06-28 Abb Turbo Systems Ag Burst protection
DE102010064047A1 (en) * 2010-12-23 2012-06-28 Man Diesel & Turbo Se Fluid flow machine has housing with fluid guiding housing and bearing housing that is connected with fluid guiding housing, where impeller is mounted in fluid guiding housing over central impeller shaft in rotating manner
GB2499627A (en) 2012-02-23 2013-08-28 Napier Turbochargers Ltd Turbocharger casing
DE102013209063A1 (en) * 2012-09-26 2014-03-27 Bosch Mahle Turbo Systems Gmbh & Co. Kg Radial compressor for use with supercharger for internal combustion engine mounted in motor car, has fastening element that is provided to fasten adapter element releasably on outside of compressor housing
US9371835B2 (en) * 2013-07-19 2016-06-21 Praxair Technology, Inc. Coupling for directly driven compressor
FR2997444B1 (en) * 2012-10-31 2018-07-13 Snecma HUB FOR A TURBOMACHINE
DE102014204768A1 (en) * 2013-05-16 2014-11-20 Bosch Mahle Turbo Systems Gmbh & Co. Kg Radial compressor for an exhaust gas turbocharger
DE102013107134A1 (en) * 2013-07-05 2015-01-08 Abb Turbo Systems Ag Air inlet of a compressor of an exhaust gas turbocharger
WO2015098826A1 (en) * 2013-12-24 2015-07-02 三菱重工業株式会社 Compressor and supercharger
CN103925017B (en) * 2014-03-04 2015-06-17 大同北方天力增压技术有限公司 Anti-bursting device for worm gear box of turbosupercharger
GB201404050D0 (en) * 2014-03-07 2014-04-23 Cummins Ltd A turbine
JP6139463B2 (en) * 2014-05-20 2017-05-31 トヨタ自動車株式会社 Internal combustion engine
JP6404082B2 (en) * 2014-10-28 2018-10-10 三菱重工業株式会社 Centrifugal compressor and supercharger provided with the same
US9995179B2 (en) * 2014-12-17 2018-06-12 Progress Rail Locomotive Inc. Compressor assembly for turbocharger burst containment
JP6001707B2 (en) * 2015-02-25 2016-10-05 株式会社オティックス Compressor housing for turbocharger
DE102015003296A1 (en) 2015-03-14 2015-12-03 Daimler Ag Exhaust gas turbocharger for an internal combustion engine and method for operating such an exhaust gas turbocharger
DE102015014550A1 (en) * 2015-11-11 2017-05-11 Man Diesel & Turbo Se Intake system for an exhaust gas turbocharger and turbocharger
DE102016111081A1 (en) * 2016-06-17 2017-12-21 Man Diesel & Turbo Se flow machine
DE102016125143A1 (en) * 2016-12-21 2018-06-21 Man Diesel & Turbo Se Centrifugal compressor and turbocharger
DE102017207173B4 (en) 2017-04-28 2022-12-22 Vitesco Technologies GmbH Turbocharger with predetermined breaking point for an internal combustion engine
DE102018102704A1 (en) * 2018-02-07 2019-08-08 Man Energy Solutions Se centrifugal compressors
JP2021105385A (en) * 2019-12-27 2021-07-26 三菱重工エンジン＆ターボチャージャ株式会社 Compressor cover and centrifugal compressor including compressor cover
WO2021245860A1 (en) * 2020-06-04 2021-12-09 三菱重工マリンマシナリ株式会社 Turbine housing and supercharger
US11519423B1 (en) * 2021-11-11 2022-12-06 Progress Rail Locomotive Inc. Compressor joint

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2607776C2 (en) * 1976-02-26 1982-05-27 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Cover disk split in the meridian plane for radial impellers of turbo machines, in particular gas turbine engines
DE3823978A1 (en) * 1988-07-15 1990-01-18 Skf Linearsysteme Gmbh LINEAR GUIDE FOR PRECISION MACHINES
JPH066240Y2 (en) * 1988-07-19 1994-02-16 三菱重工業株式会社 Centrifugal compressor
GB9027168D0 (en) * 1990-12-14 1991-02-06 Rolls Royce Business Ventures Turbine scroll
DE10050931C5 (en) * 2000-10-13 2007-03-29 Man Diesel Se Turbomachine with radial impeller
TW576886B (en) 2001-05-04 2004-02-21 Abb Turbo Systems Ag Turbocharger having a radial-flow compressor and burst-protection arrangement for a radial-flow compressor of a turbocharger
US6962480B2 (en) * 2003-11-12 2005-11-08 Honeywell International, Inc. Thermally stabilized turbine scroll retention ring for uniform loading application
EP1586745B1 (en) * 2004-04-13 2015-07-29 ABB Turbo Systems AG Compressor casing
DE102004027594B4 (en) 2004-06-05 2006-06-29 Man B & W Diesel Ag Turbomachine with radially flowing compressor wheel
DE102004028133C5 (en) 2004-06-09 2017-10-26 Man Diesel & Turbo Se Turbomachine, in particular exhaust gas turbocharger
EP1719879B1 (en) * 2005-05-03 2008-01-30 ABB Turbo Systems AG Burst protection device for radial compressors
DE102005039820B4 (en) 2005-08-22 2007-06-28 Man Diesel Se Containment safety device for turbomachinery with radial flow compressor wheel
US7871243B2 (en) * 2007-06-05 2011-01-18 Honeywell International Inc. Augmented vaneless diffuser containment

Also Published As

Publication number Publication date
CN101793266A (en) 2010-08-04
US8393851B2 (en) 2013-03-12
JP5074541B2 (en) 2012-11-14
KR101157440B1 (en) 2012-06-22
EP2216516A1 (en) 2010-08-11
EP2216517A1 (en) 2010-08-11
US20100192570A1 (en) 2010-08-05
JP2010180882A (en) 2010-08-19
KR20100089776A (en) 2010-08-12
CN101793266B (en) 2012-07-18

Similar Documents

Publication Publication Date Title
EP2216517B1 (en) Burst protection device for radial compressor
EP2218878B1 (en) Seal device of an exhaust gas turbocharger
EP2635781B1 (en) Exhaust gas turbocharger with means for axially securing the shaft in the event of a compressor wheel burst
EP2181268B1 (en) Radial compressor with a diffuser for use in a turbocharger
EP2655805B1 (en) Burst protection in the compressor housing of an exhaust gas turbocharger
CH698497B1 (en) Turbomachine with radial compressor and perfused with holding device.
EP3047125B1 (en) Exhaust gas turbocharger
DE102016002722A1 (en) Turbocharger turbine nozzle and safety structure
EP1260677B2 (en) Axial turbine with containment
EP1586745B1 (en) Compressor casing
DE19618313B4 (en) Axial turbine of an exhaust gas turbocharger
EP2054595B1 (en) Compressor housing
WO2009101167A1 (en) Turbocharger housing
EP2526263B1 (en) Housing system for an axial turbomachine
EP2730744B1 (en) Exhaust gas turbo charger
EP2772652B1 (en) Partition for sealing the rear section of a radial compressor
EP3034788A2 (en) Compressor blade of a gas turbine
WO2015169509A1 (en) Compressor housing
EP1992789A1 (en) Exhaust gas turbine casing comprising a support element
EP3309360A1 (en) Blade assembly for a gas turbine engine
EP2792855B1 (en) Inner bearing block of an exhaust gas turbocharger
WO2019137854A1 (en) Filter muffler for an exhaust gas turbocharger of an internal combustion engine
EP3795805A1 (en) Concentric introduction of waste-gate mass flow into a flow-optimized axial diffuser
WO2008056002A2 (en) Radial bearing
EP3153671A1 (en) Protection device for a turbomachine

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

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): 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 SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

17P Request for examination filed

Effective date: 20110209

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 25/24 20060101ALI20120321BHEP

Ipc: F01D 21/04 20060101AFI20120321BHEP

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): 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 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

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 566250

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120715

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: DE

Ref legal event code: R096

Ref document number: 502010001006

Country of ref document: DE

Effective date: 20120906

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20120711

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

Effective date: 20120711

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

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: 20120711

Ref country code: FI

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: 20120711

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: 20120711

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: 20121111

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: 20120711

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: 20121011

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

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: 20120711

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: 20120711

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: 20120711

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: 20121012

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: 20120711

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: 20121112

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

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: 20120711

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

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: 20120711

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: 20121022

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: 20120711

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: 20120711

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

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

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: 20120711

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: 20120711

26N No opposition filed

Effective date: 20130412

BERE Be: lapsed

Owner name: ABB TURBO SYSTEMS A.G.

Effective date: 20130131

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

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: 20121011

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010001006

Country of ref document: DE

Effective date: 20130412

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 NON-PAYMENT OF DUE FEES

Effective date: 20130131

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20130930

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: 20130131

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: 20130131

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

Ref country code: IE

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

Effective date: 20130113

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

Ref country code: MT

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: 20120711

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20140131

Ref country code: CH

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

Effective date: 20140131

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: 20120711

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

Ref country code: TR

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: 20120711

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: 20100113

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: 20120711

Ref country code: LU

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

Effective date: 20130113

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 566250

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150113

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: 20150113

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502010001006

Country of ref document: DE

Owner name: TURBO SYSTEMS SWITZERLAND LTD., CH

Free format text: FORMER OWNER: ABB TURBO SYSTEMS AG, BADEN, CH

Ref country code: DE

Ref legal event code: R082

Ref document number: 502010001006

Country of ref document: DE

Representative=s name: ZIMMERMANN & PARTNER PATENTANWAELTE MBB, DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 502010001006

Country of ref document: DE

Owner name: ABB SCHWEIZ AG, CH

Free format text: FORMER OWNER: ABB TURBO SYSTEMS AG, BADEN, CH

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20210225 AND 20210303

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20210304 AND 20210310

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: DE

Ref legal event code: R081

Ref document number: 502010001006

Country of ref document: DE

Owner name: TURBO SYSTEMS SWITZERLAND LTD., CH

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

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

Ref country code: DE

Payment date: 20240119

Year of fee payment: 15

Ref country code: CZ

Payment date: 20240108

Year of fee payment: 15

Ref country code: GB

Payment date: 20240123

Year of fee payment: 15