EP1426560B1 - Sealing for a low pressure compressor of turbofan engine - Google Patents

Sealing for a low pressure compressor of turbofan engine Download PDF

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Publication number
EP1426560B1
EP1426560B1 EP20020447237 EP02447237A EP1426560B1 EP 1426560 B1 EP1426560 B1 EP 1426560B1 EP 20020447237 EP20020447237 EP 20020447237 EP 02447237 A EP02447237 A EP 02447237A EP 1426560 B1 EP1426560 B1 EP 1426560B1
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EP
European Patent Office
Prior art keywords
gasket
drum
housing
seal
chamber according
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
EP20020447237
Other languages
German (de)
French (fr)
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EP1426560A1 (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
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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 for sealing a chamber in the booster or low-pressure compressor of a turbofan engine type single or double flow.
  • the invention applies whenever a seal is required in the chambers of a turbomachine, in particular at a fan disk.
  • the mounting of the seal is provided by bolting a piece of metal gasket 5 to a specific flange 4 associated with the drum 2.
  • the deformations to which such a flange is subjected in operation involve a requirement of great flexibility for it. Also it is usually done "lace".
  • the realization of this flange involves machining on massive piece with additional material and therefore also extra cost.
  • the bolted connection involves the making of holes in the joint, usually made of aluminum and in the flange, which reduces the life of these parts.
  • a first solution for producing drum / blower seals has been proposed in European Patent Application No. 01870116 (unpublished).
  • a prestressed seal located between the integral flange of the drum and the rotating disc supporting the rotating blades of the fan is held in place, without mechanical attachment, on the one hand with a heel extending the flange and on the other hand by contact with said disk.
  • the tightening of the support face of the seal on the heel is thus achieved by the elasticity of the seal.
  • the present invention aims to provide a solution that is both free from the disadvantages of the state of the art and alternative to the solution already proposed by the Applicant.
  • the present invention relates to a sealing device for a pressurized chamber of a low-pressure compressor belonging to a turbomachine engine, preferably a turbojet or turbofan, comprising a seal ensuring a sealing contact between the inner part of the drum supporting the blades of the engines. compression stages of the primary flow and the rotating disk supporting the rotating vanes of the fan, at a first end of the seal, characterized in that said seal is held at the drum in a housing thereof, an element elastomer being molded on a second end of the seal to fit the shape of said housing.
  • the elastomer element is symmetrical in revolution and concentric with the housing made in the drum.
  • the elastomeric element is made so that it can be compressed by mounting in said housing.
  • the seal is thereby centered without being subjected to constraints.
  • the housing is made in a flange integral with the drum.
  • the elastomer element is a silicone element.
  • the seal may consist of a metal or a light metal alloy, preferably aluminum.
  • Figure 1 shows an axial sectional view for one embodiment of a sealing device according to the state of the art.
  • FIG. 2 represents a perspective view for one embodiment of a sealing device according to the invention.
  • FIG. 3 represents an axial sectional view corresponding to the sealing device of FIG. 2.
  • the idea underlying the present invention is to provide a seal which does not play the role of resilient element and which is therefore not the seat of significant constraints.
  • the new seal device is shown in Figures 2 and 3.
  • the drum 2 comprises a first seal portion 15 shown in Figure 2, which is notched and has notches 8 for exceeding the blades of the fan at their level. heels 10.
  • the support of the drum 2 on the fan disk 1 is at the level of the protuberances 9 and a second seal portion 5.
  • the second seal portion 5 is metal, for example aluminum. It is held in place by its position sandwiched between the fan disc 1, at its curved end 6 and the drum 2 without a flange but in which a housing 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 molded in the housing of the drum 2, around the end 6 'of the metal gasket 5 and constitutes the first part of the gasket 15.
  • An advantage of the present invention lies in the fact that, given the abandonment of the effect "spring", the metal part of the seal undergoes almost no stress and can be made of a common metal such as aluminum.

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

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 for sealing a chamber in the booster or low-pressure compressor of a turbofan engine type single or double flow.

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.As regards the general field of application, the invention applies whenever a seal is required in the chambers of a turbomachine, in particular at a fan disk.

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, sealing between the different parts of the compressor is necessary to prevent leaks between the 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 represented in FIG. 1, at the level of the first stages of the low-pressure compressor of a turbofan, it is necessary to ensure the seal between the inner part of the drum 2, which serves to support the blades of the primary flow. and the disk 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 inner part of the drum 2 and the ambient air, at the disc level. 1 which supports the blades of the blower. Sealing is effectively provided by a sheet metal gasket 5 having the symmetry of revolution and being placed, at its bent portion 6, against the disk 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 mounting of the seal is provided by bolting a piece of metal gasket 5 to a specific flange 4 associated with the drum 2. The deformations to which such a flange is subjected in operation involve a requirement of great flexibility for it. Also it is usually done "lace". The realization of this flange involves machining on massive piece with additional material and therefore also extra cost. In addition, the bolted connection involves the making of holes in the joint, usually made of aluminum and in the flange, which reduces the life of these parts.

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 producing drum / blower seals has been proposed in European Patent Application No. 01870116 (unpublished). According to this invention, a prestressed seal located between the integral flange of the drum and the rotating disc supporting the rotating blades of the fan is held in place, without mechanical attachment, on the one hand with a heel extending the flange and on the other hand by contact with said disk. The tightening of the support face of the seal on the heel is thus achieved by the elasticity of the seal.

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".
Le document EP-A-0 691 455 décrit un joint permettant d'éviter à des particules ingérées par un turboréacteur de venir se glisser entre la surface amont du disque de la turbine haute pression et le labyrinthe fixé sur celui-ci. Ce joint comprend un corps placé dans une cavité du labyrinthe et une lèvre s'appuyant sur la surface amont du disque, tel qu'à l'arrêt il subsiste un petit espace entre le labyrinthe et le joint.Such a prestressed joint must be made of a metal capable of withstanding significant stresses, such as steel or titanium. It is expensive to achieve. In addition, the pressure differences between the speakers are likely to take off the seal which is maintained by its effect "spring".
The document EP-A-0 691 455 describes a seal for preventing particles ingested by a turbojet engine from slipping between the upstream surface of the disc of the high pressure turbine and the labyrinth fixed thereto. This seal comprises a body placed in a cavity of the labyrinth and a lip resting on the upstream surface of the disc, such that when stopped there is a small gap between the labyrinth and the seal.

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 the 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 sealing device for a pressurized chamber of a low-pressure compressor belonging to a turbomachine engine, preferably a turbojet or turbofan, comprising a seal ensuring a sealing contact between the inner part of the drum supporting the blades of the engines. compression stages of the primary flow and the rotating disk supporting the rotating vanes of the fan, at a first end of the seal, characterized in that said seal is held at the drum in a housing thereof, an element elastomer being molded on a second end of the seal to fit the shape 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 in revolution and concentric with the housing made in the drum. The elastomeric element is made so that it can be compressed by mounting in said housing. The seal is thereby centered without being subjected 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.Particularly advantageously, the elastomer 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 preferably emerges from the invention that the seal may consist of a metal or a light metal alloy, 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, shows an axial sectional view for one embodiment of a sealing device according to the state of the art.

La figure 2 représente une vue en perspective pour une forme d'exécution d'un dispositif d'étanchéité selon l'invention.FIG. 2 represents 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.FIG. 3 represents an axial sectional view corresponding to the sealing device of FIG. 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 underlying the present invention is to provide a seal which does not play the role of resilient element and which is therefore not the seat of significant constraints.

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 Figures 2 and 3. The drum 2 comprises a first seal portion 15 shown in Figure 2, which is notched and has notches 8 for exceeding the blades of the fan at their level. heels 10. The support of the drum 2 on the fan disk 1 is at the level of the protuberances 9 and a second seal portion 5. The second seal portion 5 is metal, for example aluminum. It is held in place by its position sandwiched between the fan disc 1, at its curved end 6 and the drum 2 without a flange but in which a housing 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 molded in the housing of the drum 2, around the end 6 'of the metal gasket 5 and constitutes the first part of the gasket 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 seal undergoes almost no stress and can be made of a common metal such as aluminum.

Claims (5)

  1. Pressurised chamber of a low-pressure compressor belonging to the engine of a turbomachine, preferably a turboreactor or turbofan, comprising a sealing device with a gasket (5) ensuring sealed contact between the inner part of the drum (2) supporting the mobile blades of the compression stages of the primary flow and the rotary disc (1) supporting the revolving blades of the blower, at the level of a first end (6) of the gasket (5), said gasket (5) being kept at the level of the drum (2) in a housing (7) of the latter, characterised in that an elastomer element (15) is moulded on a second end (6') of the gasket (5) so as to fit the shape of said housing (7).
  2. Chamber according to Claim 1, characterised in that the elastomer element (15) has rotational symmetry and is concentric with the housing (7) made in the drum, said elastomer element (15) being made in such a way that it can be compressed by being mounted in the housing (7), the gasket (5) thereby being centred without being subjected to stresses.
  3. Chamber according to Claim 1 or 2, characterised in that the housing (7) is made in a collar attached to the drum (2).
  4. Chamber according to any one of the preceding claims, characterised in that the elastomer element (15) is an element made of silicone.
  5. Chamber according to any one of the preceding claims, characterised in that the gasket (5) is made of a light metal or metal alloy, preferably aluminium.
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 EP1426560A1 (en) 2004-06-09
EP1426560B1 true EP1426560B1 (en) 2006-08-02

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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)

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

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3708949A1 (en) * 1986-03-21 1987-09-24 Rolls Royce Plc HOLDING RING FOR LOCATING A COMPONENT
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
FR2695164B1 (en) * 1992-08-26 1994-11-04 Snecma Turbomachine provided with a device preventing a longitudinal circulation of gas around the stages of straightening vanes.
FR2722240B1 (en) * 1994-07-06 1996-08-14 Snecma METAL LIPSTICK AND TURBOMACHINE EQUIPPED WITH THIS SEAL
DE60102217T2 (en) * 2001-05-30 2005-01-13 Techspace Aero, Milmort Sealing connection plate

Also Published As

Publication number Publication date
DE60213621D1 (en) 2006-09-14
DE60213621T2 (en) 2007-03-08
EP1426560A1 (en) 2004-06-09

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