EP1394364B1 - Turbosoufflante et son anneau de guidage - Google Patents

Turbosoufflante et son anneau de guidage Download PDF

Info

Publication number
EP1394364B1
EP1394364B1 EP02018296A EP02018296A EP1394364B1 EP 1394364 B1 EP1394364 B1 EP 1394364B1 EP 02018296 A EP02018296 A EP 02018296A EP 02018296 A EP02018296 A EP 02018296A EP 1394364 B1 EP1394364 B1 EP 1394364B1
Authority
EP
European Patent Office
Prior art keywords
spacers
turbocharger
annular guide
guide conduit
ring
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.)
Expired - Fee Related
Application number
EP02018296A
Other languages
German (de)
English (en)
Other versions
EP1394364A1 (fr
Inventor
Michael Stilgenbauer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP02018296A priority Critical patent/EP1394364B1/fr
Priority to DE50205993T priority patent/DE50205993D1/de
Priority to JP2003297285A priority patent/JP2004084667A/ja
Priority to US10/649,477 priority patent/US7010915B2/en
Publication of EP1394364A1 publication Critical patent/EP1394364A1/fr
Priority to US11/270,738 priority patent/US7533529B2/en
Application granted granted Critical
Publication of EP1394364B1 publication Critical patent/EP1394364B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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 a turbocharger in whose turbine housing at least one turbine rotor is rotatably mounted, to which the exhaust gas is fed via a guide grid of variable turbine geometry.
  • Variable turbine geometry is understood in the prior art, for example according to WO 01/96713, to be a ring of vanes forming variable orientation nozzles. Therefore, the guide grid has an axial boundary of a blade space forming blade bearing ring, on each of which an associated shaft a plurality of adjustable around its shaft blades is mounted in the so-limited blade space around the turbine rotor, the exhaust so over the blades in an adjustable amount can be fed.
  • a further ring a further ring (TG) is provided for axially limiting it.
  • the invention relates to such a trained blade bearing ring.
  • turbomachines such as secondary air pumps.
  • Such a turbocharger and such a blade bearing ring has become known, for example, from EP-A-0 226 444 or DE-A-3 516 738.
  • the axial dimension of the blade space is secured by spacer spacers, which must be inserted screwed into the blade bearing ring, which of course is a relatively complex operation.
  • the invention has for its object to reduce the production cost of a turbocharger or a blade bearing ring of the type mentioned, and this is done according to the invention in that at least one of the two rings circumferentially distributed spacers integrally formed by the axial distance between the two rings is secure.
  • the spacers sit on one or the other ring or alternately on one or the other ring or each half a spacer the one ring is opposite to half a spacer of the other ring.
  • the spacers are formed on the vane bearing ring, in particular cast, because the other ring will generally be part of a larger portion of the housing to which a spacer is more difficult to attach.
  • the spacers are integrally formed so that installation costs are avoided.
  • the tolerance range can be reduced, so that this production brings greater accuracy.
  • a turbocharger 1 in a conventional manner a turbine housing part 2 and an associated compressor housing part 3, which are arranged along an axis of rotation R.
  • the turbine housing part 2 is partially shown in section, so that therein a vane ring 6 a radially outer vane forming, circumferentially distributed vanes 7 rotated about their the vane ring 6 passing through pivot axes 8 so that they form between each nozzle cross-sections, depending on the location the guide vanes 7, namely radially (as shown) or more tangential, larger or smaller and located in the middle of the axis R turbine rotor 4 more or less with the supplied via a supply channel 9 and a central port Apply 10 discharged exhaust gas of a motor to drive via the turbine rotor 4 a seated on the same shaft compressor rotor 21.
  • an actuating device 11 is provided. This may be of any nature in itself, but it is preferred if it has, in a conventional manner, a control housing 12 which controls the control movement of a ram member 14 attached to its movement in a conventional manner to a behind the blade bearing ring 6 (left behind in Fig. 1) located adjusting ring 5 implement the same in a slight rotational movement.
  • the guide vanes 7 are adjusted relative to the turbine rotor 4 with respect to their rotational position via the shafts 8 in such a way that they can be adjusted from an approximately tangentially extending one extreme position into an approximately radially extending other extreme position.
  • the exhaust gas supplied via the supply channel of an internal combustion engine is supplied more or less to the turbine rotor 4, before it exits again at the axial connection piece 10 extending along the axis of rotation R.
  • this blade space 13 may not be much larger than the width of the blades 7, because then the exhaust gas energy would suffer leakage.
  • the blade chamber 13 may not be too tight, because then the blades 7 could jam. This is also particularly significant, because yes must be expected by the hot exhaust gases with a certain thermal expansion of the material.
  • the spacers 16 are arranged at uniform angular intervals in the circumferential direction of the ring 6 around the axis of rotation R, so that the distance to the bearing ring 15 (FIG. 1) over the entire circumference is the same.
  • These spacers 16 are formed with the blade bearing ring 6 in one piece, preferably by a casting, in particular by investment casting, so that they are in direct thermal conduction with the ring 6. It is understood that other manufacturing processes for a one-piece part 6.16 are conceivable, but a casting is preferred.
  • the spacers 16 could of course be arranged at different locations of the radius of the blade bearing ring 6, but it is preferred if they are arranged in the apparent manner at the peripheral edge of the ring 6. Otherwise, they would have to be placed in place of a corresponding vane, as proposed in US-A-4,659,295.
  • the spacers 16 can receive an aerodynamically favorable shape in the context of the invention and in particular themselves are formed like a shovel. In the case of an elongated shape chosen from an aerodynamic point of view, as can also be seen from FIG. 2, it is advantageous if this elongate shape extends approximately tangentially with respect to the ring 6.
  • receding surface 19 is provided along the peripheral edge of the respective ring 15 and / or 6 and in particular of the blade bearing ring 6 itself, in the axial direction of the blade chamber 13 (based on Fig. 2, this is the space through the axial length L of Spacer 16 is determined).
  • This receding surface 19 is preferably tapered in the example of FIG. 2, but may also be discontinued for certain applications, for example in the form of a step with a rounded angle. This has been found for the aerodynamic conditions within the blade space 13 (FIG. 1), which blades 7 (FIG. 1) - as mentioned - sit on adjusting shafts, each having a bore 20 extending from a circumferential direction of the blade bearing ring 6 ring of holes 20 enforce. It is understood that such a receding from the space 13 surface may also be provided on the ring 15, although it is preferably provided only on the blade bearing ring 6.
  • the invention is not limited to the illustrated embodiment; For example, it can also be applied to turbochargers with more than one turbine rotor 2 and / or compressor rotor 21 or with more than one feed channel 9. Moreover, it would be conceivable not to provide all the spacers 16 with bores 18, in particular if, for example, more than three spacers 16 should be provided, for example six.
  • the apparent from Fig. 2 surface could, for example, also are obtained by extrusion, as has already been proposed for other fluid-flow car components.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Claims (10)

  1. Turbosoufflante présentant les caractéristiques suivantes :
    un carter de turbine (2) avec au moins un canal d'alimentation (9) pour des gaz d'échappement, dans lequel au moins un rotor de turbine (4) est monté à rotation, et auquel sont susceptibles d'être amenés les gaz d'échappement par l'intermédiaire d'une grille de guidage à géométrie de turbine variable, entourant radialement extérieurement le rotor de turbine (4), ladite grille de guidage
    présentant une bague de palier d'aubes (6) sur laquelle, chaque fois sur un arbre (8) associé, sont montées des aubes (7), réglables autour de leur arbre (8), en un espace d'aubes (13) limité autour du rotor de turbine (4), espace d'aubes auquel peuvent être amenés en quantité réglable des gaz d'échappement passant sur les aubes (7), la bague de palier d'aubes (6) formant une délimitation axiale d'un espace d'aubes (13), et avec
    une autre bague (15), axialement opposée à la bague de palier d'aubes (6) et formant l'autre délimitation axiale de l'espace d'aubes (13),

    caractérisée par le fait qu'
    au moins l'une des deux bagues (6, 15) présente des supports d'espacement, répartis en direction périphérique et formés d'un seul tenant en une seule partie, au moyen desquels l'espacement axial des deux bagues (6, 15) peut être assuré.
  2. Turbosoufflante (1) selon la revendication 1, caractérisée en ce que les supports d'espacement (16) sont formés d'un seul tenant sur la bague de palier d'aubes (6).
  3. Turbosoufflante (1) selon la revendication 1 ou 2, caractérisée en ce que les supports d'espacement (16) sont coulés conjointement sur la bague (6 ou 15) respective, moulée.
  4. Turbosoufflante (1) selon l'une des revendications précédentes, caractérisée en ce que les supports d'espacement (16) sont disposés sur le bord périphérique de la bague (6 ou 15) respective.
  5. Turbosoufflante (1) selon l'une des revendications précédentes, caractérisée en ce que le long du bord périphérique de la bague (6 ou 15) respective, en particulier de la bague de palier d'aubes (6), est prévue une surface (19) de déviation de retour en direction axiale de l'espace d'aubes (13).
  6. Turbosoufflante (1) selon l'une des revendications précédentes, caractérisée en ce que les supports d'espacement (16) eux-mêmes ont une forme allongée, de préférence une forme aubes, cette forme étant, de manière appropriée, orientée tangentiellement.
  7. Turbosoufflante (1) selon l'une des revendications précédentes, caractérisée en ce qu'au moins une partie des supports d'espacement (16) sont chacun traversés par un perçage (18) pour des boulons de liaison chaque fois à une partie de palier voisine, en particulier pour assurer la liaison à la bague de palier (15) axialement opposée.
  8. Bague de palier à aubes (6) pour une turbosoufflante (1) selon l'une des revendications précédentes, comprenant des perçages (20), répartis en direction périphérique sur sa surface, pour le passage des arbres (8) d'aubes de guidage (7), caractérisée en ce qu'elle présente des supports d'espacement (16) axiaux, répartis en direction périphérique, en particulier ayant une forme d'aube aérodynamique, formés d'un seul tenant d'une seule pièce, par exemple elle est fabriquée en un procédé de moulage, par exemple un procédé de fonderie de précision, et les supports d'espacement (16) étant alors coulés conjointement.
  9. Bague de palier à aubes (6) selon la revendication 8,
    caractérisée en ce que, le long de son bord périphérique radial, est prévue une surface (19) de déviation de retour, s'étendant en direction axiale depuis l'espace pour les aubes (7), surface (19) sur laquelle sont disposés, de préférence, les supports d'espacement (16).
  10. Bague de palier à aubes (6) selon la revendication 8 ou 9, caractérisée en ce qu'au moins une partie des supports d'espacement (16) sont chacun traversés par un passage (18) pour des boulons de liaison à une partie de palier chaque fois voisine, en particulier pour assurer la liaison à la bague (15) axialement opposée.
EP02018296A 2002-08-26 2002-08-26 Turbosoufflante et son anneau de guidage Expired - Fee Related EP1394364B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP02018296A EP1394364B1 (fr) 2002-08-26 2002-08-26 Turbosoufflante et son anneau de guidage
DE50205993T DE50205993D1 (de) 2002-08-26 2002-08-26 Turbolader und Schaufellagerring hierfür
JP2003297285A JP2004084667A (ja) 2002-08-26 2003-08-21 ターボ加給機及びそのベーン支持リング
US10/649,477 US7010915B2 (en) 2002-08-26 2003-08-26 Turbocharger and vane support ring for it
US11/270,738 US7533529B2 (en) 2002-08-26 2005-11-09 Turbocharger and vane support ring for it

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02018296A EP1394364B1 (fr) 2002-08-26 2002-08-26 Turbosoufflante et son anneau de guidage

Publications (2)

Publication Number Publication Date
EP1394364A1 EP1394364A1 (fr) 2004-03-03
EP1394364B1 true EP1394364B1 (fr) 2006-03-08

Family

ID=31197805

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02018296A Expired - Fee Related EP1394364B1 (fr) 2002-08-26 2002-08-26 Turbosoufflante et son anneau de guidage

Country Status (4)

Country Link
US (2) US7010915B2 (fr)
EP (1) EP1394364B1 (fr)
JP (1) JP2004084667A (fr)
DE (1) DE50205993D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008014680A1 (de) 2008-03-18 2010-09-23 Continental Automotive Gmbh Leitgitteranordnung eines Abgasturboladers, Abgasturbolader und Verfahren zur Herstellung einer Leitgitteranordnung

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101184958B1 (ko) * 2001-08-03 2012-10-02 가부시키가이샤 아키타 파인 블랑킹 브이지에스 타입 터보 차저에서의 터빈 프레임의제조방법, 이 방법에 의해 제조된 터빈 프레임, 이 터빈프레임을 적용한 브이지에스 타입 터보 차저의 배기가이드 어셈블리, 및 이 배기 가이드 어셈블리를 장착하여이루어지는 브이지에스 타입 터보 차저
DE502004000984D1 (de) * 2004-03-08 2006-08-31 Borgwarner Inc Strömungsmaschine, Leitgitter und Montagering hierfür
DE102004062564B4 (de) * 2004-12-24 2008-08-07 Mahle Ventiltrieb Gmbh Schaufellagerring eines Turboladers eines Kraftfahrzeug-Verbrennungsmotors
DE102005012048A1 (de) * 2005-03-08 2006-09-14 Dr.Ing.H.C. F. Porsche Ag Turbinengehäuse eines Abgasturboladers mit verstellbarer Turbinengeometrie
EP3150805B1 (fr) * 2005-11-25 2020-09-23 BorgWarner, Inc. Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur
JP4847842B2 (ja) * 2006-10-25 2011-12-28 アイシン高丘株式会社 タービンハウジング
DE102007029004A1 (de) 2007-06-23 2008-12-24 Ihi Charging Systems International Gmbh Abgasturbolader für eine Brennkraftmaschine
CN102597453B (zh) * 2009-11-27 2014-12-10 博格华纳公司 具有可变涡轮几何形状（vtg）的涡轮增压器
US9556882B2 (en) * 2011-05-10 2017-01-31 Borgwarner Inc. Turbocharger with variable turbine geometry
US9945287B2 (en) 2012-12-28 2018-04-17 Borgwarner Inc. Asymmetric actuator pivot shaft bushing for VTG turbocharger
US9873515B2 (en) * 2014-08-13 2018-01-23 Hamilton Sundstrand Corporation Turbine nozzle with relief cut
US10227889B2 (en) * 2015-02-05 2019-03-12 Garrett Transportation I Inc. Variable geometry nozzle for partitioned volute
US9879594B2 (en) 2015-03-09 2018-01-30 Caterpillar Inc. Turbocharger turbine nozzle and containment structure
US9822700B2 (en) 2015-03-09 2017-11-21 Caterpillar Inc. Turbocharger with oil containment arrangement
US9903225B2 (en) 2015-03-09 2018-02-27 Caterpillar Inc. Turbocharger with low carbon steel shaft
US9732633B2 (en) 2015-03-09 2017-08-15 Caterpillar Inc. Turbocharger turbine assembly
US9752536B2 (en) 2015-03-09 2017-09-05 Caterpillar Inc. Turbocharger and method
US10006341B2 (en) 2015-03-09 2018-06-26 Caterpillar Inc. Compressor assembly having a diffuser ring with tabs
US9683520B2 (en) 2015-03-09 2017-06-20 Caterpillar Inc. Turbocharger and method
US9638138B2 (en) 2015-03-09 2017-05-02 Caterpillar Inc. Turbocharger and method
US9650913B2 (en) 2015-03-09 2017-05-16 Caterpillar Inc. Turbocharger turbine containment structure
US9890788B2 (en) 2015-03-09 2018-02-13 Caterpillar Inc. Turbocharger and method
US9777747B2 (en) 2015-03-09 2017-10-03 Caterpillar Inc. Turbocharger with dual-use mounting holes
US10066639B2 (en) 2015-03-09 2018-09-04 Caterpillar Inc. Compressor assembly having a vaneless space
US9915172B2 (en) 2015-03-09 2018-03-13 Caterpillar Inc. Turbocharger with bearing piloted compressor wheel
US9739238B2 (en) 2015-03-09 2017-08-22 Caterpillar Inc. Turbocharger and method
US9810238B2 (en) 2015-03-09 2017-11-07 Caterpillar Inc. Turbocharger with turbine shroud
USD777212S1 (en) 2015-06-20 2017-01-24 General Electric Company Nozzle ring
JP6908472B2 (ja) * 2017-08-31 2021-07-28 三菱重工コンプレッサ株式会社 遠心圧縮機

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB701557A (en) * 1949-03-25 1953-12-30 Centrax Power Units Ltd Improvements relating to gas turbine power plant
US3232581A (en) * 1963-07-31 1966-02-01 Rotoflow Corp Adjustable turbine inlet nozzles
GB1036485A (en) * 1964-06-05 1966-07-20 Bristol Siddeley Engines Ltd Improvements in or relating to a reversible, inward flow, independent power turbine
CH422214A (de) * 1964-10-01 1966-10-15 Escher Wyss Ag Verstellvorrichtung für einen Kranz von um zur Kranzachse parallele Achsen schwenkbaren Schaufeln
FR1442174A (fr) * 1964-10-01 1966-06-10 Escher Wyss Ag Dispositif de commande d'une couronne d'aubes aptes à pivoter selon des axes parallèles à l'axe de la couronne
EP0111781B1 (fr) * 1979-05-14 1988-01-13 OSBORN, Norbert Lewis Dispositif de contrôle pour turbosuflante
US4504190A (en) * 1983-03-09 1985-03-12 Gas Power Systems, Inc. Flow control apparatus and method
US4659295A (en) * 1984-04-20 1987-04-21 The Garrett Corporation Gas seal vanes of variable nozzle turbine
DE3516738A1 (de) * 1985-05-09 1986-11-13 Mtu Motoren- Und Turbinen-Union Friedrichshafen Gmbh, 7990 Friedrichshafen Stroemungsmaschine
US4804316A (en) * 1985-12-11 1989-02-14 Allied-Signal Inc. Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger
US4679984A (en) * 1985-12-11 1987-07-14 The Garrett Corporation Actuation system for variable nozzle turbine
US5207565A (en) * 1992-02-18 1993-05-04 Alliedsignal Inc. Variable geometry turbocharger with high temperature insert in turbine throat
JPH10103070A (ja) * 1996-09-27 1998-04-21 Toyota Motor Corp 可変容量ターボチャージャ
JP2996927B2 (ja) 1997-03-11 2000-01-11 株式会社東芝 非水電解液二次電池及びその製造方法
US5947681A (en) * 1997-03-17 1999-09-07 Alliedsignal Inc. Pressure balanced dual axle variable nozzle turbocharger
JP2001289050A (ja) * 1999-05-20 2001-10-19 Hitachi Ltd 可変容量ターボ過給機
GB0025244D0 (en) * 2000-10-12 2000-11-29 Holset Engineering Co Turbine
DE10209484B4 (de) * 2002-03-05 2004-06-24 Borgwarner Turbo Systems Gmbh Turbolader für Fahrzeuge mit verbesserter Aufhängung für den Betätigungsmechanismus der variablen Düsen
DE50207509D1 (de) * 2002-09-10 2006-08-24 Borgwarner Inc Leitgitter variabler Geometrie und Turbolader mit einem solchen Leitgitter
EP1418311B1 (fr) * 2002-11-11 2007-01-17 BorgWarner Inc. Ensemble stator pour turbocompresseur à géométrie variable
EP1536103B1 (fr) * 2003-11-28 2013-09-04 BorgWarner, Inc. Turbomachine avec aubes de guidage et agencement de fixation
DE102004057864A1 (de) * 2004-11-30 2006-06-01 Borgwarner Inc.(N.D.Ges.D.Staates Delaware), Auburn Hills Abgasturbolader, Leitapparat für einen Abgasturbolader sowie Schaufelhebel für einen Leitapparat

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008014680A1 (de) 2008-03-18 2010-09-23 Continental Automotive Gmbh Leitgitteranordnung eines Abgasturboladers, Abgasturbolader und Verfahren zur Herstellung einer Leitgitteranordnung

Also Published As

Publication number Publication date
US20050005603A1 (en) 2005-01-13
JP2004084667A (ja) 2004-03-18
DE50205993D1 (de) 2006-05-04
EP1394364A1 (fr) 2004-03-03
US20060053787A1 (en) 2006-03-16
US7533529B2 (en) 2009-05-19
US7010915B2 (en) 2006-03-14

Similar Documents

Publication Publication Date Title
EP1394364B1 (fr) Turbosoufflante et son anneau de guidage
EP1528225B1 (fr) Turbomachine et méthode de fabrication pour un anneau de guidage
DE60019264T2 (de) Abgasmischvorrichtung und gerät mit einer solchen vorrichtung
DE2948811C2 (fr)
EP1536103B1 (fr) Turbomachine avec aubes de guidage et agencement de fixation
EP1460237B1 (fr) Carter pour une turbosoufflante
EP2733311B1 (fr) Couronne directrice
EP1398463B1 (fr) Aubes de guidage variables et turbosoufflante avec ces aubes
DE2953333C1 (de) Turbinenabdampfstutzen
DE19518203C2 (de) Einrichtung zur Aufnahme eines inneren Leitschaufelendes in einem Axialverdichter
DE60212760T2 (de) Turbine mit variabler Einlassgeometrie
DE3912348C2 (fr)
DE3506733A1 (de) Turbinenleitradring
DE4028329A1 (de) Radialverstellvorrichtung fuer eine laufschaufelspitzenspaltbreitensteuervorrichtung
DE4028328A1 (de) Vorrichtung zum steuern der spaltbreite zwischen den laufschaufelspitzen und einem stationaeren gehaeusemantelring eines gasturbinentriebwerks
DE2914501A1 (de) Gasturbine mit verstellbaren leitschaufeln
EP2536922A1 (fr) Dispositif d'entraînement destiné à faire pivoter les aubes réglables d'une turbomachine
EP0433560A1 (fr) Turbochargeur à gaz pour un moteur à combustion interne
DE2061425A1 (de) Geblaseanordnung fur ein Mantel strom Gasturbinentriebwerk
EP1656493A1 (fr) Anneau de fixation segmente pour une turbine
DE2333274A1 (de) Geblaeserad
EP2182172A1 (fr) Turbomachine comprimante avec injection de fluide
EP2617947B1 (fr) Turbine à gaz d'avion avec soufflante ajustable
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
WO2000009861A2 (fr) Dispositif d'appui pour pales de groupes moteurs

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 IE IT LI LU MC NL PT SE SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

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

Owner name: BORGWARNER, INC.

17P Request for examination filed

Effective date: 20040421

AKX Designation fees paid

Designated state(s): DE FR GB IT NL

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

Owner name: BORGWARNER INC.

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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): DE FR GB IT NL

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 50205993

Country of ref document: DE

Date of ref document: 20060504

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20060606

ET Fr: translation filed
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: 20061211

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

Ref country code: GB

Payment date: 20120726

Year of fee payment: 11

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

Ref country code: FR

Payment date: 20120809

Year of fee payment: 11

Ref country code: IT

Payment date: 20120809

Year of fee payment: 11

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

Ref country code: NL

Payment date: 20120813

Year of fee payment: 11

REG Reference to a national code

Ref country code: NL

Ref legal event code: V1

Effective date: 20140301

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20130826

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 NON-PAYMENT OF DUE FEES

Effective date: 20140301

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20140430

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 NON-PAYMENT OF DUE FEES

Effective date: 20130826

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

Ref country code: GB

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

Effective date: 20130826

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: 20130902

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

Ref country code: DE

Payment date: 20190715

Year of fee payment: 18

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50205993

Country of ref document: DE

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

Ref country code: DE

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

Effective date: 20210302