EP0789133B1 - Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor - Google Patents

Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor Download PDF

Info

Publication number
EP0789133B1
EP0789133B1 EP97400211A EP97400211A EP0789133B1 EP 0789133 B1 EP0789133 B1 EP 0789133B1 EP 97400211 A EP97400211 A EP 97400211A EP 97400211 A EP97400211 A EP 97400211A EP 0789133 B1 EP0789133 B1 EP 0789133B1
Authority
EP
European Patent Office
Prior art keywords
labyrinth
disc
rim
arch
rotor
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 - Lifetime
Application number
EP97400211A
Other languages
English (en)
French (fr)
Other versions
EP0789133A1 (de
Inventor
Frédéric Chambon
Jacques Henri Mouchel
Patrick Didier Michel Lestoille
Jean-Claude Taillant
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0789133A1 publication Critical patent/EP0789133A1/de
Application granted granted Critical
Publication of EP0789133B1 publication Critical patent/EP0789133B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the invention relates to turbomachinery, such that axial flow turbojets using labyrinth seals for separating enclosures containing air and / or oil. It's the case, in particular, of the labyrinth fixed upstream of the high pressure turbine.
  • the definition technology of turbomachinery involving flows of air at different pressures and temperatures, provides the use of sealing devices between enclosures containing air and / or oil.
  • This is the case with the disc labyrinth 2 existing upstream of the high pressure turbine 1 and placed on the passage of part of the cold flow to the level of the combustion chamber.
  • We add to this a difficult environment because the air flow the surrounding is rather oxidizing and the thermal level is very high.
  • this piece also called front labyrinth of the high pressure turbine, is one of the most difficult parts to size. This operation can also sometimes lead to giving it a duration of insufficient life, or a limitation in its qualities thermal.
  • this disc labyrinth 2 has several parts, including the labyrinth itself lying largely opposite the arrow referenced 2.
  • the lips of this labyrinth are carried by a rim 3 extending upwards by a arch 4 which rests on a downstream surface 5 of the disc 8 of the rotor to which this part is fixed.
  • This fixation is performed, on many current turbojet engines, by through bolts 6 crossing the part interior of this part which ends with a stiffener interior 7.
  • the object of the invention is to optimize the shape of this piece that is the labyrinth disc and its fastening device on the disc 8 of the rotor of the high pressure turbine.
  • US-A-5,236,302 shows that the arch is an upper part of the rim which is fairly radially elongated, downstream surface being placed at the axial level of the end downstream of the main stiffener.
  • the vault is slightly curved
  • the means of mounting include mounting bolts placed in mounting holes in the inner part of the rim, inside and upstream of the stiffener
  • the vault of the labyrinth disk includes ribs placed on the downstream surface of the rim and part of the downstream surface of the vault then acts as an axial abutment surface, via ribs.
  • the labyrinth disk, object of the invention is placed substantially in the same place as where is placed the labyrinth disk of figure 1.
  • rim 13 which constitutes the radial framework of this part.
  • the part inner of this rim 13 ends with a stiffener interior 9 less consistent than that referenced 7 of the figure 1.
  • the labyrinth 10 of the labyrinth disc consists of of two parts each comprising several lips coming tangent with the friction pieces 16 fixed on a fixed part 17 attached to the stator inside and at the exit from combustion chamber 20.
  • FIG. 2 it is by the inner part, i.e. by the flange located above the internal stiffener 9, that the assembly is fixed on the rotor, symbolized by the radial disc 8.
  • the fixing means shown are bolts 6 penetrating holes in the internal stiffener 9.
  • the rim 13 is extended by a central part having passages 11 and lower orifices 15 allowing the passage of the cooling air flow from the upstream part to the downstream part of the labyrinth disk.
  • the outer part of the labyrinth disk 12, according to the invention, is constituted by the arch 14 extending the rim 13 to be supported by a outer end 18 on an upstream surface 19 of the rotor.
  • This vault 14 is slightly less rounded than that of the figure 1.
  • a main stiffener 23 is provided in the middle of the labyrinth disk 12, that is to say on rim 13. Its shape is such that it forms a bead toroid which protrudes from the downstream surface 22 of the disc labyrinth 12, just below the lips labyrinth 10, below passages 11. Its downstream end is at same longitudinal level as the downstream end of the surface downstream 22 of the arch 14. Lower orifices 15 are incidentally planned so that a relatively small part of the cold air flow passing from upstream to downstream relative to the maze disc could pass below and around it main stiffener 23, between the latter and the upstream surface 19 of disc 8 of the rotor.
  • Such a cold air flow allows to cool this main stiffener 23 and the downstream surface 22 of the labyrinth disk 12.
  • the two fresh air flows passing through the passages 11 and the lower orifices 15 meet behind the labyrinth disc 10 on the downstream surface 22 of the arch 14 to go up between the fixing teeth 24. They cool everything the back of this set of discs labyrinth. They reach the rim of the turbine disc 8 and join the cooling circuits of the blades 21 and the fixing cells of these blades.
  • This main stiffener 23 constitutes the element main mechanical strength of the labyrinth disk 10. It contributes to reducing the internal stiffener 9 and reducing the general dimension of the labyrinth disk 10 and, in particular, of the vault 14. It is noted that this can have a slightly less rounded shape but slightly offset towards the downstream side of the labyrinth disk 12 to come almost tangent with the upstream surface 19 of the disc 8 of the rotor.
  • this stiffener main 23 is a little offset towards downstream.
  • This main stiffener 23 being closer operational elements of the labyrinth disk 12, that is to say the labyrinths themselves 10 it allows to ensure a better mechanical resistance of these.
  • this main stiffener 23 increases the time of thermal response of the labyrinth disk 12, since it is placed in the central part of the latter. It improves the compatibility of radial movements of the labyrinth disc 12 relative to disk 8 of the turbine and thus minimizes the efforts on the upper support means of the disc labyrinth 12.
  • the latter also constitute a part of the means for fixing the labyrinth disk 12 to the rotor.
  • these may consist of fixing teeth 24 placed on the downstream surface 22 of the labyrinth disk 12 and, in particular, on the outside of the vault 14.
  • fixing teeth 25 of a system of bayonet lock in number corresponding to the number fixing teeth 24 of the labyrinth disk 12.
  • the axial positioning of the labyrinth disk 12 is provided relative to the rotor disc 8, by through the downstream surface 22 of the rim 13 and the arch 14.
  • ribs 26 are placed on the downstream surface 22 of the arch 14 to stiffen it. They are based on the downstream surface 22 of the disc 8 of the rotor and thus constitute axial stops.
  • the labyrinth disk 12 can be fixed by a bolt system 6 in its part interior.
  • Radial stops 27 can be provided on the upstream surface 19 of the rotor disk 8, just below bayonet fixing teeth 25, so as to take support on the external surface of the fixing teeth 24 of the labyrinth disk 12.
  • the radial stops 27 do not face each other to the fixing teeth 24 only when the part is in locking position in the bayonet system.
  • part of the charges is absorbed by the radial stops 27, a part being absorbed by the main stiffener 23 and a small part being passed on to the bolts 6.
  • FIG. 3 represents a first variant of the labyrinth disk according to the invention. She shows the use of holes 30 placed on the base 31 of the main stiffener 33 which is unique and which therefore is a little more elongated, but still placed just in below the labyrinth 10.
  • the fixing system by bayonet comes down to a single set of 34 teeth on the labyrinth disk 32, since these are both office fixing teeth by coming to stay behind the 35 teeth for fixing the locking system to rotor disc 38 bayonet and also act as radial stops, thanks to their inclined surfaces combined with the corresponding inclined surfaces of the fixing teeth 35 of the disc 38 of the rotor.
  • These teeth of fixing 34 of labyrinth disc 32 are preferably housed in the upper part of ribs 36.
  • the second variant represented by the figure 4, uses the same holes 30 in the main stiffener 33.
  • the fixing system described in the figure 2 is the same.
  • Radial stops 28 are provided in the part exterior of the ribs 26 and placed in correspondence with stops 27 of the disc 8 of the rotor.
  • Figure 5 shows a third variant always using the single main stiffener 33, extended to provide for the use of holes 32 on either side and on the other side of the stiffening disc 52.
  • the radial stops 58 are placed further outside by in relation to the fixing system. They are placed in look of abutment surfaces 59 of the disc 8 of the rotor.
  • the axial fixing is carried out by means of a system of bayonet attachment at the ribs 56. They use teeth 54 engaging in bayonet locking system teeth 55 of the rotor discs 8.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Claims (1)

  1. Labyrinthträgerscheibe (12, 32; 42, 52, 62) für Turbomaschinenrotoren, bestehend aus:
    einem Hauptscheibenkörper (13, 63),
    einem in dem Scheibenkörper (13) eingebauten Labyrinth (10),
    einer Wölbung (14, 64), die in der äußeren Verlängerung des Scheibenkörpers (13, 63) angeordnet ist und an der Vorderseite (19) der Scheibe (8, 38, 58, 68) des Rotors anliegt,
    Mitteln zur Befestigung der Labyrinthträgerscheibe (12, 32; 42, 52, 62) an der Scheibe (8) des Rotors, und
    einer radialen Hauptversteifung (23, 33), die in dem Scheibenkörper (13, 63) direkt innerhalb des Labyrinths (10) eingebaut ist,
    wobei die Wölbung (14, 64) einen oberen, in radialer Richtung relativ langen Teil des Scheibenkörpers (13, 63) bildet und ihre Hinterseite (22) in Achsrichtung auf der Höhe des hinteren Endes der Hauptversteifung (23, 33) angeordnet ist,
       dadurch gekennzeichnet, daß die Wölbung leicht gewölbt ist, daß die Befestigungsmittel im unteren Teil des Scheibenkörpers (13) und vor der Hauptversteifung (23) aus Befestigungslöchern bestehen, die Befestigungsbolzen (6) aufnehmen sollen, daß die Wölbung (14, 64) Rippen (26, 56, 66) aufweist, und daß die Wölbung (14) über die Rippen (26) als axialer Anschlag dient.
EP97400211A 1996-02-08 1997-01-30 Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor Expired - Lifetime EP0789133B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9601527 1996-02-08
FR9601527A FR2744761B1 (fr) 1996-02-08 1996-02-08 Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine

Publications (2)

Publication Number Publication Date
EP0789133A1 EP0789133A1 (de) 1997-08-13
EP0789133B1 true EP0789133B1 (de) 2000-03-01

Family

ID=9488969

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97400211A Expired - Lifetime EP0789133B1 (de) 1996-02-08 1997-01-30 Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor

Country Status (5)

Country Link
US (1) US5816776A (de)
EP (1) EP0789133B1 (de)
CA (1) CA2196642C (de)
DE (1) DE69701332T2 (de)
FR (1) FR2744761B1 (de)

Families Citing this family (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5984636A (en) * 1997-12-17 1999-11-16 Pratt & Whitney Canada Inc. Cooling arrangement for turbine rotor
FR2817290B1 (fr) * 2000-11-30 2003-02-21 Snecma Moteurs Flasque de disque aubage de rotor et agencement correspondant
US6464453B2 (en) * 2000-12-04 2002-10-15 General Electric Company Turbine interstage sealing ring
US6761034B2 (en) * 2000-12-08 2004-07-13 General Electroc Company Structural cover for gas turbine engine bolted flanges
US6575703B2 (en) * 2001-07-20 2003-06-10 General Electric Company Turbine disk side plate
FR2831918B1 (fr) 2001-11-08 2004-05-28 Snecma Moteurs Stator pour turbomachine
FR2840351B1 (fr) * 2002-05-30 2005-12-16 Snecma Moteurs Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre
FR2841591B1 (fr) * 2002-06-27 2006-01-13 Snecma Moteurs Circuits de ventilation de la turbine d'une turbomachine
US6749400B2 (en) * 2002-08-29 2004-06-15 General Electric Company Gas turbine engine disk rim with axially cutback and circumferentially skewed cooling air slots
US6779972B2 (en) * 2002-10-31 2004-08-24 General Electric Company Flowpath sealing and streamlining configuration for a turbine
JP2005009382A (ja) * 2003-06-18 2005-01-13 Ishikawajima Harima Heavy Ind Co Ltd タービンロータ、タービンディスク、及びタービン
US20110150640A1 (en) * 2003-08-21 2011-06-23 Peter Tiemann Labyrinth Seal in a Stationary Gas Turbine
EP1508672A1 (de) * 2003-08-21 2005-02-23 Siemens Aktiengesellschaft Segmentierter Befestigungsring für eine Turbine
GB2426289B (en) * 2005-04-01 2007-07-04 Rolls Royce Plc Cooling system for a gas turbine engine
FR2885167B1 (fr) * 2005-04-29 2007-06-29 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
US7341429B2 (en) * 2005-11-16 2008-03-11 General Electric Company Methods and apparatuses for cooling gas turbine engine rotor assemblies
US8708652B2 (en) * 2007-06-27 2014-04-29 United Technologies Corporation Cover plate for turbine rotor having enclosed pump for cooling air
US8444387B2 (en) * 2009-11-20 2013-05-21 Honeywell International Inc. Seal plates for directing airflow through a turbine section of an engine and turbine sections
FR2961249B1 (fr) * 2010-06-10 2014-05-02 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine
FR2961250B1 (fr) * 2010-06-14 2012-07-20 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine a l'aval du cone d'entrainement
US9109457B2 (en) * 2010-09-03 2015-08-18 Siemens Energy, Inc. Axial locking seals for aft removable turbine blade
US9133855B2 (en) * 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
US8740554B2 (en) 2011-01-11 2014-06-03 United Technologies Corporation Cover plate with interstage seal for a gas turbine engine
US8662845B2 (en) 2011-01-11 2014-03-04 United Technologies Corporation Multi-function heat shield for a gas turbine engine
US8840375B2 (en) 2011-03-21 2014-09-23 United Technologies Corporation Component lock for a gas turbine engine
US9080456B2 (en) * 2012-01-20 2015-07-14 General Electric Company Near flow path seal with axially flexible arms
US8827637B2 (en) 2012-03-23 2014-09-09 Pratt & Whitney Canada Corp. Seal arrangement for gas turbine engines
WO2014120124A1 (en) * 2013-01-29 2014-08-07 United Technologies Corporation Common joint for a combustor, diffuser, and tobi of a gas turbine engine
EP2951398B1 (de) * 2013-01-30 2017-10-04 United Technologies Corporation Gasturbine mit doppel-eingerasteter abdeckplatte für rotorscheibe
ES2684775T3 (es) * 2013-06-27 2018-10-04 MTU Aero Engines AG Dispositivo de obturación y turbomáquina
US9556737B2 (en) 2013-11-18 2017-01-31 Siemens Energy, Inc. Air separator for gas turbine engine
EP2924237B1 (de) 2014-03-25 2018-07-11 Industria de Turbo Propulsores S.A. Gasturbinenrotor
EP2942483B2 (de) * 2014-04-01 2022-09-28 Raytheon Technologies Corporation Belüftete bordseitige tangenzialdüse für einen gasturbinenmotor
US10655480B2 (en) * 2016-01-18 2020-05-19 United Technologies Corporation Mini-disk for gas turbine engine
US10329929B2 (en) * 2016-03-15 2019-06-25 United Technologies Corporation Retaining ring axially loaded against segmented disc surface
DE102017205122A1 (de) * 2017-03-27 2018-09-27 MTU Aero Engines AG Turbomaschinen-Bauteilanordnung
US10280842B2 (en) * 2017-04-10 2019-05-07 United Technologies Corporation Nut with air seal
US10968744B2 (en) 2017-05-04 2021-04-06 Rolls-Royce Corporation Turbine rotor assembly having a retaining collar for a bayonet mount
US10774678B2 (en) 2017-05-04 2020-09-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US20180320522A1 (en) * 2017-05-04 2018-11-08 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10865646B2 (en) 2017-05-04 2020-12-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
EP3495611B1 (de) * 2017-12-06 2020-07-29 Ansaldo Energia Switzerland AG Vorrichtung zur kontrollierten abgabe von kühlluft an turbinenschaufeln in einer gasturbine
FR3078363B1 (fr) * 2018-02-23 2021-02-26 Safran Aircraft Engines Anneau mobile d'etancheite
EP3564489A1 (de) * 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor mit fliehkraft-optimierten kontaktflächen
CN109489957B (zh) * 2018-12-10 2020-12-15 中国航发四川燃气涡轮研究院 一种用于轮盘试验的带应力分割槽的转接结构
FR3093541B1 (fr) * 2019-03-08 2021-07-16 Safran Aircraft Engines Turbine à gaz pour aéronef à double rotor
CN110805476B (zh) * 2019-10-17 2022-04-12 南京航空航天大学 一种带有容腔封严结构的涡轮盘
US11313240B2 (en) 2020-02-05 2022-04-26 Raytheon Technologies Corporation Rounded radial snap configuration for a gas turbine engine cover plate

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB610314A (en) * 1945-01-16 1948-10-14 Power Jets Res & Dev Ltd Improvements relating to the construction of rotors for compressors and turbines
US3832090A (en) * 1972-12-01 1974-08-27 Avco Corp Air cooling of turbine blades
FR2607866B1 (fr) * 1986-12-03 1991-04-12 Snecma Axes de fixation de rotors de turbomachine, procede de montage et rotors ainsi montes
GB2244100A (en) * 1990-05-16 1991-11-20 Rolls Royce Plc Retaining gas turbine rotor blades
FR2663997B1 (fr) * 1990-06-27 1993-12-24 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
US5143512A (en) * 1991-02-28 1992-09-01 General Electric Company Turbine rotor disk with integral blade cooling air slots and pumping vanes
US5275534A (en) * 1991-10-30 1994-01-04 General Electric Company Turbine disk forward seal assembly
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
US5310319A (en) * 1993-01-12 1994-05-10 United Technologies Corporation Free standing turbine disk sideplate assembly
US5333993A (en) * 1993-03-01 1994-08-02 General Electric Company Stator seal assembly providing improved clearance control
US5402636A (en) * 1993-12-06 1995-04-04 United Technologies Corporation Anti-contamination thrust balancing system for gas turbine engines

Also Published As

Publication number Publication date
EP0789133A1 (de) 1997-08-13
CA2196642C (en) 2005-11-15
DE69701332D1 (de) 2000-04-06
FR2744761B1 (fr) 1998-03-13
FR2744761A1 (fr) 1997-08-14
CA2196642A1 (en) 1997-08-09
US5816776A (en) 1998-10-06
DE69701332T2 (de) 2000-07-27

Similar Documents

Publication Publication Date Title
EP0789133B1 (de) Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor
CA2520282C (fr) Module de turbine pour moteur a turbine a gaz
EP2009234B1 (de) Kühlvorrichtung der Hohlräume einer Rotorscheibe einer Strömungsmaschine
EP2893141B1 (de) Gekühlter turbinenrotor
EP1749977B1 (de) Dichtungssystem des hinteren lagergehäuses eines strahltriebwerks
FR2914009A1 (fr) Joints retractables actifs pour turbomachines
CA2931044C (fr) Dispositif pour le centrage et le guidage en rotation d'un arbre de turbomachine comprenant des moyens de retention de bague exterieure de palier
CA2520069C (fr) Module de turbine pour moteur a turbine a gaz avec rotor comportant un corps monobloc
FR2851010A1 (fr) Dispositif de ventilation d'un rotor de turbine a haute pression d'une turbomachine
CA2970715C (fr) Ensemble de turbine de turbomachine d'aeronef
CA2838919A1 (fr) Dispositif d'arbre d'entrainement d'une turbomachine
FR2859002A1 (fr) Dispositif abradable sur carter de soufflante d'un moteur de turbine a gaz
FR2961250A1 (fr) Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine a l'aval du cone d'entrainement
FR3005099A1 (fr) Structure de turbomachine comportant une bague de ventilation
EP1426559B1 (de) Innerer Mantelring eines axialen Kompressors sowie dessen Verwendung
WO2020212666A1 (fr) Reducteur de vitesse d'une turbomachine
FR2961249A1 (fr) Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine
FR2983909A1 (fr) Enceinte lubrifiee logeant un palier inter-turbine et fermee par un joint a labyrinthe a faible usure
FR2971004A1 (fr) Procede d'assemblage d'une turbine basse-pression de turboreacteur a double corps
FR2606071A1 (fr) Etage de stator et compresseur de turbomachine le comportant
BE1029074B1 (fr) Ensemble redresseur pour compresseur de turbomachine d'aeronef
FR3005098A1 (fr) Support de palier d'une turbomachine comportant une ouverture d'acces pour l'assemblage de servitudes
FR3073560A1 (fr) Roue monobloc de turbomachine d'aeronef
FR3094028A1 (fr) Turbine comprenant un anneau d’etancheite rivete
WO2023166266A1 (fr) Cône d'éjection pour turbomachine d'aéronef

Legal Events

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

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19970217

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19990428

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

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

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

Effective date: 20000301

REF Corresponds to:

Ref document number: 69701332

Country of ref document: DE

Date of ref document: 20000406

EN Fr: translation not filed
EN4 Fr: notification of non filing translation in an earlier bopi is erroneous
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
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120517 AND 20120523

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

Ref country code: GB

Payment date: 20141219

Year of fee payment: 19

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

Ref country code: DE

Payment date: 20141218

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

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

Ref country code: FR

Payment date: 20160111

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69701332

Country of ref document: DE

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

Effective date: 20160130

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: 20160802

Ref country code: GB

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

Effective date: 20160130