EP0789133B1 - Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine - Google Patents
Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine Download PDFInfo
- 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
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)
Description
- une jante principale ;
- un labyrinthe incorporé à la jante ;
- une voûte dans le prolongement extérieur de la jante pour prendre appui sur une surface amont du rotor ; et
- des moyens de fixation du disque labyrinthe sur le rotor et
- figure 1, en demi-coupe longitudinale, une partie d'un turboréacteur de l'art antérieur ;
- figure 2, en demi-coupe, une partie d'un turboréacteur dans lequel est installée l'invention ;
- figure 3, en coupe, une première variante du disque labyrinthe selon l'invention ;
- figure 4, en coupe, une deuxième variante du disque labyrinthe selon l'invention et
- figure 5, en coupe, une troisième variante du disque labyrinthe selon l'invention.
Claims (1)
- Disque labyrinthe (12, 32 ; 42, 52, 62) pour rotor de turbomachine, comportant :une jante principale (13, 63) ;un labyrinthe (10) incorporé à la jante (13) ;une voûte (14, 64) placée dans le prolongement extérieur de la jante (13, 63) pour prendre appui sur la surface amont (19) du disque (8, 38, 58, 68) du rotor , etdes moyens de fixation du disque labyrinthe (12, 32, 42, 52, 62) sur le disque (8) du rotor,un raidisseur principal (23, 33) radial, incorporé à la jante (13, 63), juste à l'intérieur du labyrinthe (10), la voûte (14, 64) étant une partie supérieure de la jante (13, 63) assez allongée radialement, sa surface aval (22) étant placée au niveau axial de l'extrémité aval du raidisseur principal (23, 33), caractérisé en ce que la voûte est légèrement bombée, et en ce que les moyens de fixation sont constitués, dans la partie inférieure de la jante (13) et en amont du raidisseur principal (23), de trous de fixation destinés à recevoir des boulons de fixation (6) et en ce que la voûte (14, 64) comprend des nervures (26, 56, 66) de la voûte (14, 64) et la voûte (14) fait office de butée axiale par l'intermédiaire des nervures (26).
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 (fr) | 1997-08-13 |
EP0789133B1 true EP0789133B1 (fr) | 2000-03-01 |
Family
ID=9488969
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97400211A Expired - Lifetime EP0789133B1 (fr) | 1996-02-08 | 1997-01-30 | Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US5816776A (fr) |
EP (1) | EP0789133B1 (fr) |
CA (1) | CA2196642C (fr) |
DE (1) | DE69701332T2 (fr) |
FR (1) | FR2744761B1 (fr) |
Families Citing this family (48)
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 (fr) * | 2003-08-21 | 2005-02-23 | Siemens Aktiengesellschaft | Anneau de fixation segmenté pour une 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 |
US9022727B2 (en) * | 2010-11-15 | 2015-05-05 | 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 (fr) * | 2013-01-29 | 2014-08-07 | United Technologies Corporation | Joint commun pour un brûleur, un diffuseur et un injecteur embarqué tangentiel d'une turbine à gaz |
US10458258B2 (en) * | 2013-01-30 | 2019-10-29 | United Technologies Corporation | Double snapped cover plate for rotor disk |
EP2818643B1 (fr) * | 2013-06-27 | 2018-08-08 | MTU Aero Engines GmbH | Dispositif d'étanchéité et turbomachine |
US9556737B2 (en) | 2013-11-18 | 2017-01-31 | Siemens Energy, Inc. | Air separator for gas turbine engine |
EP2924237B1 (fr) | 2014-03-25 | 2018-07-11 | Industria de Turbo Propulsores S.A. | Rotor de turbine à gaz |
EP2942483B2 (fr) | 2014-04-01 | 2022-09-28 | Raytheon Technologies Corporation | Injecteur de bord tangentiel ventilé pour un moteur à turbine à gaz |
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 |
US20180320522A1 (en) * | 2017-05-04 | 2018-11-08 | Rolls-Royce Corporation | Turbine assembly with auxiliary wheel |
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 |
US10865646B2 (en) | 2017-05-04 | 2020-12-15 | Rolls-Royce Corporation | Turbine assembly with auxiliary wheel |
EP3495611B1 (fr) * | 2017-12-06 | 2020-07-29 | Ansaldo Energia Switzerland AG | Appareil d'administration contrôlée d'air de refroidissement pour aubes de turbine dans une turbine à gaz |
FR3078363B1 (fr) * | 2018-02-23 | 2021-02-26 | Safran Aircraft Engines | Anneau mobile d'etancheite |
EP3564489A1 (fr) * | 2018-05-03 | 2019-11-06 | Siemens Aktiengesellschaft | Rotor à surfaces de contact optimisées au niveau de forces centrifuges |
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)
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 |
US5236302A (en) * | 1991-10-30 | 1993-08-17 | General Electric Company | Turbine disk interstage seal system |
US5275534A (en) * | 1991-10-30 | 1994-01-04 | General Electric Company | Turbine disk forward seal assembly |
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 |
-
1996
- 1996-02-08 FR FR9601527A patent/FR2744761B1/fr not_active Expired - Fee Related
-
1997
- 1997-01-28 US US08/791,051 patent/US5816776A/en not_active Expired - Lifetime
- 1997-01-30 EP EP97400211A patent/EP0789133B1/fr not_active Expired - Lifetime
- 1997-01-30 DE DE69701332T patent/DE69701332T2/de not_active Expired - Lifetime
- 1997-02-03 CA CA002196642A patent/CA2196642C/fr not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US5816776A (en) | 1998-10-06 |
EP0789133A1 (fr) | 1997-08-13 |
DE69701332T2 (de) | 2000-07-27 |
DE69701332D1 (de) | 2000-04-06 |
FR2744761A1 (fr) | 1997-08-14 |
CA2196642A1 (fr) | 1997-08-09 |
CA2196642C (fr) | 2005-11-15 |
FR2744761B1 (fr) | 1998-03-13 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0789133B1 (fr) | Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine | |
CA2520282C (fr) | Module de turbine pour moteur a turbine a gaz | |
EP2009234B1 (fr) | Dispositif de refroidissement des alvéoles d'un disque de rotor de turbomachine | |
EP2893141B1 (fr) | Rotor de turbine refroidi | |
EP1749977B1 (fr) | Systeme d'etancheite de la chambre de lubrification arriere d'un turboreacteur | |
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 (fr) | Virole interieure pour compresseur axial et utilisation | |
WO2020212666A1 (fr) | Reducteur de vitesse d'une turbomachine | |
FR2961249A1 (fr) | Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine | |
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 | |
FR3062682A1 (fr) | Partie de turbomachine comprenant une paroi de separation de deux cavites pourvue de bossages |
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 |