EP1426560A1 - Sealing for a low pressure compressor of turbofan engine - Google Patents

Sealing for a low pressure compressor of turbofan engine Download PDF

Info

Publication number
EP1426560A1
EP1426560A1 EP02447237A EP02447237A EP1426560A1 EP 1426560 A1 EP1426560 A1 EP 1426560A1 EP 02447237 A EP02447237 A EP 02447237A EP 02447237 A EP02447237 A EP 02447237A EP 1426560 A1 EP1426560 A1 EP 1426560A1
Authority
EP
European Patent Office
Prior art keywords
seal
drum
housing
joint
elastomer element
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02447237A
Other languages
German (de)
French (fr)
Other versions
EP1426560B1 (en
Inventor
André Lhoest
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 Aero Boosters SA
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to DE2002613621 priority Critical patent/DE60213621T2/en
Priority to EP20020447237 priority patent/EP1426560B1/en
Publication of EP1426560A1 publication Critical patent/EP1426560A1/en
Application granted granted Critical
Publication of EP1426560B1 publication Critical patent/EP1426560B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the present invention relates to a new seal designed to seal a speaker in the booster or low-pressure compressor of an engine turbofan type single or double flow (turbofan).
  • the invention applies whenever a tightness is required in the speakers of a turbomachine, especially at the level of a record of blower.
  • the assembly of the joint sealing is ensured by bolting a piece of joint metal 5 on a specific flange 4 associated with the drum 2.
  • the deformations to which such a flange is subject in operation involve a great requirement flexibility for it. So is she usually performed "lace".
  • the realization of this flange involves massive piece machining with additional important matter and therefore also cost supplement.
  • the bolted joint involves the realization of holes in the joint, usually made of aluminum and in the flange, which decreases the life of these rooms.
  • the present invention aims to provide a solution that is both free from the disadvantages of state of the art and alternative to the solution already proposed by the Applicant.
  • the present invention relates to a device seal for a pressurized pressure vessel low pressure belonging to a turbomachine engine, preferably a turbojet or turbofan, comprising a seal ensuring a tight contact between the inner part drum supporting the blades of the stages of primary stream compression and rotating disk supporting the rotating vanes of the fan, at the level of a first end of the seal, characterized in that said seal is held at the drum in a housing thereof, an elastomeric member being molded on a second end of the seal to fit the form of said housing.
  • the elastomer element is symmetrical with revolution and concentric with the housing practiced in the drum.
  • the elastomer element is constructed so that it can be compressed by mounting in said housing. The seal is therefore centered without it is subject to constraints.
  • the housing is made in a flange integral with the drum.
  • the elastomeric element is a silicone element.
  • the seal may be made of a metal or an alloy light metal, preferably aluminum.
  • Figure 1 already mentioned above, represents an axial sectional view for a shape of execution of a sealing device according to the state of the technical.
  • Figure 2 shows a perspective view for one embodiment of a sealing device according to the invention.
  • Figure 3 shows a sectional view axis corresponding to the sealing device of the figure 2.
  • the idea behind the present invention is to make a joint that does not play the role of element resilient and therefore not subject to constraints important.
  • the new seal device is shown in FIGS. 2 and 3.
  • the drum 2 comprises a first part of joint 15 shown in Figure 2, which is notched and which has notches 8 allowing the exceeding the fan blades at their level heels 10.
  • the support of the drum 2 on the fan disk 1 is at the level of the excrescences 9 and a second part of joint 5.
  • the second part of joint 5 is metal, for example aluminum. It is maintained place by its position sandwiched between the fan disc 1, at level of its curved end 6 and the drum 2 without a bridle but in which a dwelling 7 has been machined to accommodate the other end 6 'of the seal 5.
  • the metal part 5 of the seal at this end is then trapped in an elastomer such as silicone filling the housing 7.
  • the elastomer is so molded into the drum housing 2, around end 6 'of the metal seal 5 and constitutes the first part of the joint 15.
  • An advantage of the present invention lies in the fact that, given the abandonment of the effect "spring", the metal part of the joint undergoes almost no more constraint and can therefore be made of a common metal such as aluminum.

Landscapes

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

Abstract

The seal consists of a light metal or alloy joint (5), preferably of aluminium, providing a sealed contact between the inner part of a drum (2) supporting the mobile blades of the primary flow compression stages and the rotary blade disc (1) of the fan. The joint is held at the drum level by an elastomer element (15) moulded onto one edge (6') of the joint and shaped to fit in a drum cavity (7). The elastomer element has a symmetry of revolution and is concentric with the cavity, which can be in a flange fixed to the drum; it is designed to be compressed to fit in the cavity, leaving the seal unstressed.

Description

Objet de l'inventionObject of the invention

La présente invention se rapporte à un nouveau joint destiné à assurer l'étanchéité d'une enceinte dans le booster ou compresseur basse pression d'un moteur de type turboréacteur simple ou double flux (turbofan).The present invention relates to a new seal designed to seal a speaker in the booster or low-pressure compressor of an engine turbofan type single or double flow (turbofan).

En ce qui concerne le domaine général d'application, l'invention s'applique chaque fois qu'une étanchéité est requise dans les enceintes d'une turbomachine, en particulier au niveau d'un disque de soufflante.With regard to the general area application, the invention applies whenever a tightness is required in the speakers of a turbomachine, especially at the level of a record of blower.

Etat de la techniqueState of the art

Il est connu que, dans les turboréacteurs, l'étanchéité entre les différentes parties du compresseur est nécessaire pour éviter les fuites entre les enceintes maintenues à des pressions différentes.It is known that, in turbojet engines, the seal between the different parts of the compressor is necessary to prevent leaks between speakers maintained at different pressures.

Ainsi, comme représenté à la figure 1, au niveau des premiers étages du compresseur basse pression d'un turbofan, il est nécessaire d'assurer l'étanchéité entre la partie interne du tambour 2, qui sert de support des aubes mobiles du flux primaire et le disque 1 qui supporte les aubes de la soufflante (disque fan). L'étanchéité est assurée au moyen d'un flasque 3 situé entre l'enceinte pressurisée délimitée par la partie interne du tambour 2 et l'air ambiant, au niveau du disque 1 qui supporte les aubes de la soufflante. L'étanchéité est assurée effectivement par un joint en tôle 5 présentant la symétrie de révolution et venant se placer, au niveau de sa partie recourbée 6, contre le disque 1.Thus, as shown in Figure 1, level of the first stages of the low pressure compressor of a turbofan, it is necessary to ensure the tightness between the inner part of the drum 2, which serves as a support moving blades of the primary flow and the disc 1 which Supports the blades of the fan (fan disk). Sealing is ensured by means of a flange 3 located between the pressurized enclosure delimited by the internal drum 2 and ambient air at the disc level 1 which supports the blades of the blower. The seal is actually provided by a sheet metal gasket 5 presenting the symmetry of revolution and coming to stand, at the level of its curved part 6, against the disc 1.

Traditionnellement, le montage du joint d'étanchéité est assuré en boulonnant une pièce de joint métallique 5 sur une bride spécifique 4 associée au tambour 2. Les déformations auxquelles une telle bride est soumise en fonctionnement impliquent une exigence de grande souplesse pour celle-ci. Aussi est-elle généralement réalisée "en dentelle". La réalisation de cette bride implique un usinage sur pièce massive avec supplément de matière important et donc également supplément de coût. De plus, l'assemblage boulonné implique la réalisation de trous dans le joint, réalisé généralement en aluminium et dans la bride, ce qui diminue la durée de vie de ces pièces.Traditionally, the assembly of the joint sealing is ensured by bolting a piece of joint metal 5 on a specific flange 4 associated with the drum 2. The deformations to which such a flange is subject in operation involve a great requirement flexibility for it. So is she usually performed "lace". The realization of this flange involves massive piece machining with additional important matter and therefore also cost supplement. Of Moreover, the bolted joint involves the realization of holes in the joint, usually made of aluminum and in the flange, which decreases the life of these rooms.

Une première solution pour la réalisation de joints d'étanchéité tambour/soufflante a été proposée dans la demande de brevet européen N° 01870116 (non publiée). Selon cette invention, un joint précontraint situé entre la bride solidaire du tambour et le disque rotatif supportant les aubes tournantes de la soufflante est maintenu en place, sans fixation mécanique, d'une part avec un talon prolongeant la bride et d'autre part par contact avec ledit disque. Le serrage de la face d'appui du joint sur le talon est ainsi réalisé par l'élasticité du joint.A first solution for the realization of drum / blower seals has been proposed in European Patent Application No. 01870116 (unpublished). According to this invention, a prestressed joint located between the integral flange of the drum and the rotating disc supporting the rotating vanes of the blower is maintained in place, without mechanical attachment, on the one hand with a heel extending the flange and secondly by contact with said disk. Clamping the support face of the seal on the heel is thus achieved by the elasticity of the joint.

Un tel joint précontraint doit être réalisé en un métal capable de supporter des contraintes importantes, tel que l'acier ou le titane. Il est coûteux à ,réaliser. De plus, les différences de pression entre les enceintes sont susceptibles de décoller le joint qui n'est maintenu que par son effet "ressort". Such a prestressed joint must be realized in a metal capable of withstanding constraints such as steel or titanium. It is expensive to ,achieve. In addition, the pressure differences between speakers are likely to take off the seal that is not maintained only by its effect "spring".

Buts de l'inventionGoals of the invention

La présente invention vise à fournir une solution qui soit à la fois exempte des inconvénients de l'état de la technique et alternative à la solution déjà proposée par la Demanderesse.The present invention aims to provide a solution that is both free from the disadvantages of state of the art and alternative to the solution already proposed by the Applicant.

Principaux éléments caractéristiques de l'inventionMain characteristic elements of the invention

La présente invention concerne un dispositif d'étanchéité pour enceinte pressurisée d'un compresseur basse pression appartenant à un moteur de turbomachine, de préférence un turboréacteur ou turbofan, comprenant un joint assurant un contact étanche entre la partie interne du tambour supportant les aubes mobiles des étages de compression du flux primaire et le disque rotatif supportant les aubes tournantes de la soufflante, au niveau d'une première extrémité du joint, caractérisé en ce que ledit joint est maintenu au niveau du tambour dans un logement de celui-ci, un élément en élastomère étant moulé sur une seconde extrémité du joint pour s'adapter à la forme dudit logement.The present invention relates to a device seal for a pressurized pressure vessel low pressure belonging to a turbomachine engine, preferably a turbojet or turbofan, comprising a seal ensuring a tight contact between the inner part drum supporting the blades of the stages of primary stream compression and rotating disk supporting the rotating vanes of the fan, at the level of a first end of the seal, characterized in that said seal is held at the drum in a housing thereof, an elastomeric member being molded on a second end of the seal to fit the form of said housing.

Selon l'invention, l'élément en élastomère est à symétrie de révolution et concentrique avec le logement pratiqué dans le tambour. L'élément en élastomère est réalisé de manière à pouvoir être comprimé par montage dans ledit logement. Le joint est par ce fait centré sans qu'il soit soumis à des contraintes.According to the invention, the elastomer element is symmetrical with revolution and concentric with the housing practiced in the drum. The elastomer element is constructed so that it can be compressed by mounting in said housing. The seal is therefore centered without it is subject to constraints.

Avantageusement, le logement est réalisé dans une bride solidaire du tambour.Advantageously, the housing is made in a flange integral with the drum.

De manière particulièrement avantageuse, l'élément en élastomère est un élément en silicone.In a particularly advantageous manner, the elastomeric element is a silicone element.

Il ressort préférentiellement de l'invention que le joint peut être constitué d'un métal ou d'un alliage métallique léger, de préférence l'aluminium. It is preferentially apparent from the invention that the seal may be made of a metal or an alloy light metal, preferably aluminum.

Brève description des figuresBrief description of the figures

La figure 1, déjà mentionnée ci-dessus, représente une vue en coupe axiale pour une forme d'exécution d'un dispositif d'étanchéité selon l'état de la technique.Figure 1, already mentioned above, represents an axial sectional view for a shape of execution of a sealing device according to the state of the technical.

La figure 2 représente une vue en perspective pour une forme d'exécution d'un dispositif d'étanchéité selon l'invention.Figure 2 shows a perspective view for one embodiment of a sealing device according to the invention.

La figure 3 représente une vue en coupe axiale correspondant au dispositif d'étanchéité de la figure 2.Figure 3 shows a sectional view axis corresponding to the sealing device of the figure 2.

Description d'une forme d'exécution préférée de l'inventionDescription of a preferred embodiment of the invention

L'idée à la base de la présente invention est de réaliser un joint qui ne joue pas le rôle d'élément résilient et qui ne soit donc pas le siège de contraintes importantes.The idea behind the present invention is to make a joint that does not play the role of element resilient and therefore not subject to constraints important.

Le nouveau dispositif de joint est représenté sur les figures 2 et 3. Le tambour 2 comprend une première partie de joint 15 représentée sur la figure 2, qui est crantée et qui présente des encoches 8 permettant le dépassement des aubes de soufflante au niveau de leurs talons 10. L'appui du tambour 2 sur le disque de soufflante 1 se fait au niveau des excroissances 9 et d'une deuxième partie de joint 5. La deuxième partie de joint 5 est métallique, par exemple en aluminium. Elle est maintenue en place par sa position en sandwich entre le disque fan 1, au niveau de son extrémité recourbée 6 et le tambour 2 dépourvu de bride mais dans lequel un logement 7 a été usiné pour pouvoir accueillir l'autre extrémité 6' du joint métallique 5. La partie métallique 5 du joint à cette extrémité est alors emprisonnée dans un élastomère tel que du silicone remplissant le logement 7. L'élastomère est donc moulé dans le logement du tambour 2, autour de l'extrémité 6' du joint métallique 5 et constitue la première partie du joint 15.The new seal device is shown in FIGS. 2 and 3. The drum 2 comprises a first part of joint 15 shown in Figure 2, which is notched and which has notches 8 allowing the exceeding the fan blades at their level heels 10. The support of the drum 2 on the fan disk 1 is at the level of the excrescences 9 and a second part of joint 5. The second part of joint 5 is metal, for example aluminum. It is maintained place by its position sandwiched between the fan disc 1, at level of its curved end 6 and the drum 2 without a bridle but in which a dwelling 7 has been machined to accommodate the other end 6 'of the seal 5. The metal part 5 of the seal at this end is then trapped in an elastomer such as silicone filling the housing 7. The elastomer is so molded into the drum housing 2, around end 6 'of the metal seal 5 and constitutes the first part of the joint 15.

Un avantage de la présente invention réside dans le fait que, vu l'abandon de l'effet "ressort", la partie métallique du joint ne subit quasiment plus aucune contrainte et peut donc être réalisée en un métal courant tel que l'aluminium.An advantage of the present invention lies in the fact that, given the abandonment of the effect "spring", the metal part of the joint undergoes almost no more constraint and can therefore be made of a common metal such as aluminum.

Claims (5)

Dispositif d'étanchéité pour enceinte pressurisée d'un compresseur basse pression appartenant à un moteur de turbomachine, de préférence un turboréacteur ou turbofan, comprenant un joint (5) assurant un contact étanche entre la partie interne du tambour (2) supportant les aubes mobiles des étages de compression du flux primaire et le disque rotatif (1) supportant les aubes tournantes de la soufflante, au niveau d'une première extrémité (6) du joint (5), caractérisé en ce que ledit joint (5) est maintenu au niveau du tambour (2) dans un logement (7) de celui-ci, un élément en élastomère (15) étant moulé sur une seconde extrémité (6') du joint (5) pour s'adapter à la forme dudit logement (7).Sealing device for a pressurized chamber of a low-pressure compressor belonging to a turbomachine engine, preferably a turbojet or turbofan, comprising a seal (5) ensuring a sealed contact between the inner part of the drum (2) supporting the blades stages of compression of the primary flow and the rotating disc (1) supporting the rotating vanes of the fan, at a first end (6) of the seal (5), characterized in that said seal (5) is maintained at level of the drum (2) in a housing (7) thereof, an elastomeric member (15) being molded on a second end (6 ') of the seal (5) to fit the shape of said housing (7); ). Dispositif selon la revendication 1, caractérisé en ce que l'élément en élastomère (15) est à symétrie de révolution et concentrique avec le logement (7) pratiqué dans le tambour, ledit élément en élastomère (15) étant réalisé de manière à pouvoir être comprimé par montage dans le logement (7), le joint (5) étant par ce fait centré sans qu'il soit soumis à des contraintes.Device according to claim 1, characterized in that the elastomer element (15) is symmetrical in revolution and concentric with the housing (7) formed in the drum, said elastomer element (15) being made in such a way that it can be compressed by mounting in the housing (7), the seal (5) being thereby centered without being subjected to stress. Dispositif selon la revendication 1 ou 2, caractérisé en ce que le logement (7) est réalisé dans une bride solidaire du tambour (2).Device according to claim 1 or 2, characterized in that the housing (7) is formed in a flange integral with the drum (2). Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que l'élément en élastomère (15) est un élément en silicone.Device according to any one of the preceding claims, characterized in that the elastomer element (15) is a silicone element. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que le joint (5) est constitué d'un métal ou d'un alliage métallique léger, de préférence l'aluminium.Device according to any one of the preceding claims, characterized in that the seal (5) consists of a metal or a light metal alloy, preferably aluminum.
EP20020447237 2002-12-03 2002-12-03 Sealing for a low pressure compressor of turbofan engine Expired - Lifetime EP1426560B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE2002613621 DE60213621T2 (en) 2002-12-03 2002-12-03 Seal for the low-pressure compressor of an aircraft engine
EP20020447237 EP1426560B1 (en) 2002-12-03 2002-12-03 Sealing for a low pressure compressor of turbofan engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20020447237 EP1426560B1 (en) 2002-12-03 2002-12-03 Sealing for a low pressure compressor of turbofan engine

Publications (2)

Publication Number Publication Date
EP1426560A1 true EP1426560A1 (en) 2004-06-09
EP1426560B1 EP1426560B1 (en) 2006-08-02

Family

ID=32309545

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20020447237 Expired - Lifetime EP1426560B1 (en) 2002-12-03 2002-12-03 Sealing for a low pressure compressor of turbofan engine

Country Status (2)

Country Link
EP (1) EP1426560B1 (en)
DE (1) DE60213621T2 (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2596115A1 (en) * 1986-03-21 1987-09-25 Rolls Royce Improvement to retention means
US4968854A (en) * 1988-11-10 1990-11-06 Vanguard Products Corporation Dual elastomer gasket shield for electronic equipment
US4982889A (en) * 1989-08-09 1991-01-08 Union Carbide Corporation Floating dual direction seal assembly
CH681043A5 (en) * 1989-07-13 1992-12-31 Balzers Hochvakuum Sealing element with light metal support - has elastomer sealing body forming compound unit with support.
FR2695164A1 (en) * 1992-08-26 1994-03-04 Snecma Turbomachine provided with a device preventing a longitudinal circulation of gas around the stages of straightening vanes.
EP0691455A1 (en) * 1994-07-06 1996-01-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Metallic lip seal and turbomachine fitted with said deal
EP1262695A1 (en) * 2001-05-30 2002-12-04 Techspace aero Sealing joint plate

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2596115A1 (en) * 1986-03-21 1987-09-25 Rolls Royce Improvement to retention means
US4968854A (en) * 1988-11-10 1990-11-06 Vanguard Products Corporation Dual elastomer gasket shield for electronic equipment
CH681043A5 (en) * 1989-07-13 1992-12-31 Balzers Hochvakuum Sealing element with light metal support - has elastomer sealing body forming compound unit with support.
US4982889A (en) * 1989-08-09 1991-01-08 Union Carbide Corporation Floating dual direction seal assembly
FR2695164A1 (en) * 1992-08-26 1994-03-04 Snecma Turbomachine provided with a device preventing a longitudinal circulation of gas around the stages of straightening vanes.
EP0691455A1 (en) * 1994-07-06 1996-01-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Metallic lip seal and turbomachine fitted with said deal
EP1262695A1 (en) * 2001-05-30 2002-12-04 Techspace aero Sealing joint plate

Also Published As

Publication number Publication date
DE60213621T2 (en) 2007-03-08
DE60213621D1 (en) 2006-09-14
EP1426560B1 (en) 2006-08-02

Similar Documents

Publication Publication Date Title
EP2870323B1 (en) Gasket device for the bearing of a turbomachine, comprising two elastic seals
CA2640003C (en) Foil for turbomachine blade
EP1564455B1 (en) Sealing arrangement for the high-pressure turbine of a turbomachine
FR2974593A1 (en) TURBINE ENGINE COMPRISING A METAL PROTECTION OF A COMPOSITE PIECE
FR2902843A1 (en) COMPRESSOR RECTIFIER AREA OR TURBOMACHINE DISTRIBUTOR SECTOR
FR2979663B1 (en) SYSTEM AND METHOD FOR REALIZING THE SEALING OF A FLOW PATH
FR2973440A1 (en) MECHANICAL ASPIRATION TRIM AND METHOD THEREOF
EP1433988B1 (en) Regulation valve
FR2902172A1 (en) SUCTION LABYRINTH SEAL
EP1580402B1 (en) Turbomachine with two sub-assemblies being under axial pressure
FR2467335A1 (en) ANNULAR SEAL FOR OIL SEALING
BE1022576B1 (en) FIXED VOLUTE ELEMENT AND VOLUME FLUID MACHINE.
EP1544481A1 (en) Metal sheet comprising means for fixing to a support and a seal
FR2649463A1 (en) SHEET SEALING DEVICE
EP1426560B1 (en) Sealing for a low pressure compressor of turbofan engine
FR3063777A1 (en) DUAL-STAGE WHEEL ARRANGEMENT FOR A DOUBLE-STAGE CENTRIFUGAL TURBOCHARGER
EP1262696B1 (en) Sealing arrangement for a turbomachine bearing
FR2996474A1 (en) METHOD FOR THE INTEGRATION OF ABRADABLE MATERIAL IN ISOSTATIC COMPRESSION HOUSING
FR2958990A1 (en) ELASTIC CONICAL WASHER AND ENVELOPE SEALING ELEMENT FOR EXERCISING A TARING
FR2619430A1 (en) COUPLING AND BRAKING DEVICE THAT CAN BE SWITCHED BY A COMPRESSIBLE FLUID, ESPECIALLY PNEUMATIC
EP1262695B1 (en) Sealing joint plate
FR3085187A1 (en) A TURBOCHARGER HAVING A FLEXIBLE CONTACT AREA BETWEEN A BEARING SLEEVE AND A FIXED COMPRESSOR PART.
FR3127983A1 (en) Upgraded turbomachine rotor
FR2660973A1 (en) CYLINDER HEAD GASKET OF AN ALTERNATIVE COMPRESSOR.
EP3966477A1 (en) Compact seal for sealing between a rotating shaft and a stationary body of a machine

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 SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

17P Request for examination filed

Effective date: 20040916

AKX Designation fees paid

Designated state(s): BE DE FR GB

17Q First examination report despatched

Effective date: 20050627

RBV Designated contracting states (corrected)

Designated state(s): BE DE FR GB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Owner name: TECHSPACE AERO S.A.

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): BE DE FR GB

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: 60213621

Country of ref document: DE

Date of ref document: 20060914

Kind code of ref document: P

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

Effective date: 20060824

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: 20070503

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

Ref country code: GB

Payment date: 20141126

Year of fee payment: 13

Ref country code: DE

Payment date: 20141121

Year of fee payment: 13

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 60213621

Country of ref document: DE

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

Effective date: 20151203

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: 20160701

Ref country code: GB

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

Effective date: 20151203

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

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

Ref country code: FR

Payment date: 20171121

Year of fee payment: 16

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: 20181231

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

Ref country code: BE

Payment date: 20211122

Year of fee payment: 20

REG Reference to a national code

Ref country code: BE

Ref legal event code: MK

Effective date: 20221203