EP2140178A2 - Double seal with pressurised lip - Google Patents

Double seal with pressurised lip

Info

Publication number
EP2140178A2
EP2140178A2 EP08788058A EP08788058A EP2140178A2 EP 2140178 A2 EP2140178 A2 EP 2140178A2 EP 08788058 A EP08788058 A EP 08788058A EP 08788058 A EP08788058 A EP 08788058A EP 2140178 A2 EP2140178 A2 EP 2140178A2
Authority
EP
European Patent Office
Prior art keywords
shaft
lip
flow
sealing device
gas
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.)
Withdrawn
Application number
EP08788058A
Other languages
German (de)
French (fr)
Inventor
Monique Fos
Franck Labarthe
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 Helicopter Engines SAS
Original Assignee
Turbomeca 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 Turbomeca SA filed Critical Turbomeca SA
Publication of EP2140178A2 publication Critical patent/EP2140178A2/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/40—Sealings between relatively-moving surfaces by means of fluid
    • F16J15/406—Sealings between relatively-moving surfaces by means of fluid by at least one pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/002—Sealings comprising at least two sealings in succession
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
    • F16J15/3204—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings with at least one lip
    • F16J15/3232—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings with at least one lip having two or more lips

Definitions

  • the present invention relates to the field of seals, in particular that of radial friction seals.
  • the present invention relates more particularly to a sealing device for sealing between a casing and a shaft rotatably mounted in said casing, comprising first and second annular lip seals intended to be arranged side by side axially between the casing and the casing. 'tree.
  • the adjectives "axial” and “radial” refer to the direction of the axis of rotation of the shaft.
  • a pair of lip seals is used to seal a chamber by contact on the shaft.
  • An object of the present invention is to provide a sealing device having a longer life than that of the prior art.
  • the invention achieves its object by the fact that the sealing device according to the invention further comprises means for bringing a stream of pressurized gas into an annular cavity delimited by the first lip seal, the second lip seal and a outer surface of the shaft, such that during the rotation of said shaft, the gas flow is able to take off at least one of the two lip seals of the outer surface of the shaft to flow out of the cavity, said means for causing the flow of pressurized gas further comprise a diaphragm for limiting the flow of gas in case of damage to one of the annular lip seals.
  • At least one of the two lip seals preferably both, take off from the outer surface of the shaft due to the flow of gas flow between the seals. lip and surface external of the shaft, as a result of which the friction between the shaft and the sealing device is advantageously eliminated.
  • the sealing function is advantageously preserved thanks to the flow of gas flowing out of the cavity which tends to maintain the outer particles outside the cavity.
  • the sealing device according to the present invention wears substantially less quickly than the device of the prior art which has the effect of increasing its service life.
  • the diaphragm is disposed in this channel or at one of its ends.
  • the gas flow rate is limited by the separation distance of the lips of the lip seals.
  • the flow of gas is advantageously limited in the event of damage to one of the lip seals.
  • the first lip seal has a first lip while the second lip seal has a second lip, and the first and second lips are intended to extend in the axial direction of the shaft while moving away. one from the other.
  • the first and second lips that take off from the outer surface of the shaft during the flow of the gas flow out of the cavity.
  • the means for bringing the flow of pressurized gas comprise a channel disposed between the first and second lip seals, said channel being connected to a source of pressurized gas.
  • the channel extending radially between the two lip seals.
  • the present invention also relates to a turbine engine for a helicopter comprising a housing and a shaft rotatably mounted in said housing, said turbine engine further comprising a sealing device according to the present invention.
  • the turbine engine according to the invention further comprises a source of pressurized gas for supplying the means for bringing a flow of pressurized gas into the annular cavity.
  • a source of pressurized air is a stream disposed at the outlet of the compression stage.
  • FIG. 1 shows a detail of a turbine engine casing of a helicopter in which is mounted a rotary shaft, the turbine engine comprising a sealing device according to the present invention
  • FIG. 2 shows a turbine engine equipped with a sealing device according to the present invention.
  • FIG 1 there is shown a detail of a housing 10 of the speed reducer 11 of a turbine engine 52 for a flying machine, such as a helicopter, in which is mounted a sealing device 12 according to the invention.
  • a shaft 14 having an axis of rotation A is rotatably mounted in the casing 10, in particular via a bearing 16.
  • the housing 10 corresponds to the casing of the gearbox 11 of the turbine engine, that is to say that the end 18 of the shaft 14 on the bearing side is intended to be coupled to gears, while the opposite end 20 is a power take-off intended to be coupled to a shaft transmitting torque to the rotor of the helicopter.
  • the PTO 20 is located outside the turbine engine 52 while the end 18 on the enclosure side 21 of the gear 11 is located inside the turbine engine 52.
  • the sealing device 12 comprises a first annular lip seal 24 and a second annular lip seal 26 which are arranged side by side between the casing 10 and the shaft 14 while being coaxial, it being understood that their common axis corresponds substantially to the axis A of the tree
  • the annular lip seals 24, 26 are radial contact seals and are preferably made of elastomer.
  • the first and second annular lip seals 24, 26 are preferably fixed on a sleeve 28 arranged axially in a bore 30 of the casing 10, the sleeve 28 itself being held integrally with the casing 10 between a flange 32 secured to the casing 10 and the landing 16.
  • first and second annular lip seals 24, 26 respectively comprise a first lip 34 and a second lip 36 which extend in the axial direction of the shaft 14 while moving away from each other. one of the other.
  • the lips 34 and 36 are shaped to have a first position, shown in dashed lines in FIG. 1, in which each of them comes into contact with the outer surface 22 of the shaft 14 in order to ensure the sealing the enclosure 21 of the gearbox 11.
  • the lips 34, 36 are in their first position preferably when the shaft 14 does not rotate.
  • the lips 34,36 in their first position, provide a static seal between the housing 10 and the shaft 14.
  • the first lip 34 prevents the outer particles from entering the the enclosure 21, while the second lip 36 prevents the oil droplets from leaving the enclosure 21 of the gearbox 11.
  • the lips 34 and 36 are able to be in a second position, represented in solid lines in the figure, in which position the lips 34, 36 take off from the outer surface 22 of the shaft 24.
  • the lips 34 and 36 are in their second position when the shaft 14 rotates.
  • an annular cavity 38 delimited by the first lip 34, the second lip 36 and the outer surface 22 of the shaft 14 is pressurized by means 40 to bring a stream of pressurized air F into said cavity 38.
  • Said means comprise a channel 40 formed in a neck 42 of the sleeve 28, said neck 42 extending in a plane orthogonal to the axis A of the shaft 14 so that the channel 40 extending substantially radially.
  • a first end 44 of the channel 40 opens into the annular cavity 38, while a second end 43 of the channel 40 opposite the first end 44 is connected to a connection 46 by the intermediate of a radial pipe 48 formed in the housing 10.
  • the connector 46 is connected via a casing 45 to a pressure source which, in the present case, is a sampling point 49 disposed at the outlet of a compressor 50 of the turbine engine 52 as represented in FIG. 2.
  • the gas corresponds in this case a fraction of air taken from the compressed air by the compressor 50.
  • the gas flow F brought into the cavity 38 has a sufficient pressure to be able to take off the lips 34 and 36 of the outer surface 22 of the shaft 14.
  • the gas flow F detaches the lips 34 and 36 from the outer surface 22 of the shaft 14 to flow out of the cavity 38.
  • the stream of gas leaving the cavity 38 is preferably constituted by a first annular flow Fl flowing axially outwardly of the turbine engine 52 and a second annular flow F2 flowing axially inwardly of the enclosure 21, in a direction opposite to the first annular flow Fl.
  • the first flow Fl prevents the outer particles from entering the enclosure 21 of the reducer
  • the annular lip seals 24,26 wear substantially less because of the absence of friction during the rotation of the tree.
  • the sealing device according to the invention has a longer life than those of the prior art.
  • the sealing device according to the present invention further comprises a diaphragm D to limit the flow of pressurized gas in case of damage to one or other of the lips 34,36.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Sealing Devices (AREA)

Abstract

The invention relates to a sealing device (12) that ensures tightness between a casing (10) and a shaft (14) rotatingly mounted in said casing (10), that comprises first (24) and second (26) seals with an annular lip to be positioned axially side by side between the casing (10) and the shaft (14). The invention is characterised in that the device further includes means (45, 46, 48) for feeding a pressurised gas flow into the annular chamber (38) defined by the first lip seal (24), the second lip seal (26) and an outer surface of the shaft (22) so that, during the rotation of said shaft (22) the gas flow (F, F1, F2) is capable of slightly separating at least one of the lip seals (24, 26) from the outer surface (22) of the shaft (14) in order to flow out of the chamber (38).

Description

Double foint à lèyre pressurisé Double pressurized shoulder joint
La présente invention concerne le domaine des joints d'étanchéité, notamment celui des joints à frottement radial. La présente invention concerne plus particulièrement un dispositif d'étanchéité pour assurer l'étanchéité entre un carter et un arbre monté rotatif dans ledit carter, comprenant des premier et second joints à lèvre annulaires destinés à être disposés côte à côte axialement entre le carter et l'arbre. Dans la suite, les adjectifs « axial » et « radial » se rapportent à la direction de l'axe de rotation de l'arbre.The present invention relates to the field of seals, in particular that of radial friction seals. The present invention relates more particularly to a sealing device for sealing between a casing and a shaft rotatably mounted in said casing, comprising first and second annular lip seals intended to be arranged side by side axially between the casing and the casing. 'tree. In the following, the adjectives "axial" and "radial" refer to the direction of the axis of rotation of the shaft.
Traditionnellement, on utilise un couple de joints à lèvre pour assurer l'étanchéité d'une enceinte par contact sur l'arbre.Traditionally, a pair of lip seals is used to seal a chamber by contact on the shaft.
Du fait du frottement existant entre l'arbre et les lèvres des joints, la rotation de l'arbre entraîne une usure des joints à lèvre qui nécessite le changement des joints, notamment pour éviter les fuites d'huile.Because of the friction existing between the shaft and the lips of the seals, the rotation of the shaft causes wear of lip seals which requires the change of seals, especially to prevent oil leakage.
En effet, les fuites d'huile sont néfastes à l'environnement et peuvent conduire à l'endommagement des pièces rotatives tels les engrenages dont la lubrification n'est plus correctement assurée. Dans le cas où un tel dispositif est monté dans un turbomoteur d'hélicoptère, ce dernier doit être immobilisé afin de procéder au changement des joints, ce qui présente un coût que l'on souhaiterait éviter.Indeed, oil leaks are harmful to the environment and can lead to damage to rotating parts such as gears whose lubrication is no longer properly ensured. In the case where such a device is mounted in a helicopter turbine engine, the latter must be immobilized in order to change the seals, which has a cost that we would like to avoid.
Un but de la présente invention est de proposer un dispositif d'étanchéité ayant une durée de vie plus longue que celui de l'art antérieur. L'invention atteint son but par le fait que le dispositif d'étanchéité selon l'invention comporte en outre des moyens pour amener un flux de gaz pressurisé dans une cavité annulaire délimitée par le premier joint à lèvre, le second joint à lèvre et une surface extérieure de l'arbre, de telle sorte que lors de la rotation dudit arbre, le flux de gaz est apte à décoller au moins l'un des deux joints à lèvre de la surface extérieure de l'arbre pour s'écouler hors de la cavité, lesdits moyens pour amener le flux de gaz pressurisé comportent en outre un diaphragme pour limiter le débit de gaz en cas d'endommagement de l'un des joints à lèvre annulaires.An object of the present invention is to provide a sealing device having a longer life than that of the prior art. The invention achieves its object by the fact that the sealing device according to the invention further comprises means for bringing a stream of pressurized gas into an annular cavity delimited by the first lip seal, the second lip seal and a outer surface of the shaft, such that during the rotation of said shaft, the gas flow is able to take off at least one of the two lip seals of the outer surface of the shaft to flow out of the cavity, said means for causing the flow of pressurized gas further comprise a diaphragm for limiting the flow of gas in case of damage to one of the annular lip seals.
Ainsi, lors de la rotation de l'arbre, au moins l'un des deux joints à lèvres, de préférence les deux, décollent de la surface extérieure de l'arbre du fait de l'écoulement du flux de gaz entre les joints à lèvre et la surface extérieure de l'arbre, en conséquence de quoi le frottement entre l'arbre et le dispositif d'étanchéité est avantageusement supprimé.Thus, during the rotation of the shaft, at least one of the two lip seals, preferably both, take off from the outer surface of the shaft due to the flow of gas flow between the seals. lip and surface external of the shaft, as a result of which the friction between the shaft and the sealing device is advantageously eliminated.
Malgré le décollement du ou des joints à lèvre, la fonction d'étanchéité est avantageusement préservée grâce au flux de gaz s'écoulant hors de la cavité qui tend à maintenir les particules extérieures en dehors de la cavité.Despite the detachment of the lip seal (s), the sealing function is advantageously preserved thanks to the flow of gas flowing out of the cavity which tends to maintain the outer particles outside the cavity.
On comprend ainsi que des particules d'huile ou de poussière ne peuvent traverser le dispositif d'étanchéité dans un sens ou dans l'autre.It is thus understood that particles of oil or dust can not pass through the sealing device in one direction or the other.
Il en résulte que le dispositif d'étanchéité conforme à la présente invention s'use sensiblement moins vite que le dispositif de l'art antérieur ce qui a pour effet d'augmenter sa durée de vie.As a result, the sealing device according to the present invention wears substantially less quickly than the device of the prior art which has the effect of increasing its service life.
De surcroit, lorsque l'arbre ne tourne pas, l'étanchéité est simplement réalisée par le fait que les joints à lèvre annulaires viennent en contact contre la surface extérieure de l'arbre. En effet, il n'est en effet pas nécessaire de pressuriser la cavité car à ce moment il n'existe pas de frottement entre l'arbre et le dispositif d'étanchéité.In addition, when the shaft does not rotate, the seal is simply achieved by the fact that the annular lip seals come into contact against the outer surface of the shaft. Indeed, it is indeed not necessary to pressurize the cavity because at this time there is no friction between the shaft and the sealing device.
De préférence, le diaphragme est disposé dans ce canal ou bien à l'une de ses extrémités.Preferably, the diaphragm is disposed in this channel or at one of its ends.
Lors du fonctionnement normal du dispositif d'étanchéité selon l'invention, le débit de gaz est limité par la distance de décollement des lèvres des joints à lèvre.During normal operation of the sealing device according to the invention, the gas flow rate is limited by the separation distance of the lips of the lip seals.
Dans le cas où l'une des deux lèvres venait à être endommager, le débit de gaz pourrait augmenter brutalement engendrant une perte indésirable de gaz.In the case where one of the two lips was to be damaged, the flow of gas could increase suddenly causing an undesirable loss of gas.
Grâce au diaphragme, le débit de gaz est avantageusement limité en cas d'endommagement de l'un des joints à lèvre.Thanks to the diaphragm, the flow of gas is advantageously limited in the event of damage to one of the lip seals.
De manière préférentielle, le premier joint à lèvre comporte une première lèvre tandis que le second joint à lèvre comporte une seconde lèvre, et les première et seconde lèvres sont destinés à s'étendre selon la direction axiale de l'arbre tout en s'éloignant l'une de l'autre. Ainsi, ce sont les première et seconde lèvres qui décollent de la surface extérieure de l'arbre lors de l'écoulement du flux de gaz hors de la cavité.Preferably, the first lip seal has a first lip while the second lip seal has a second lip, and the first and second lips are intended to extend in the axial direction of the shaft while moving away. one from the other. Thus, it is the first and second lips that take off from the outer surface of the shaft during the flow of the gas flow out of the cavity.
Avantageusement, les moyens pour amener le flux de gaz pressurisé comportent un canal disposé entre les premier et second joints à lèvre, ledit canal étant relié à une source de gaz pressurisé. De préférence, le canal s'étendant radialement entre les deux joints à lèvre.Advantageously, the means for bringing the flow of pressurized gas comprise a channel disposed between the first and second lip seals, said channel being connected to a source of pressurized gas. Preferably, the channel extending radially between the two lip seals.
La présente invention concerne également un turbomoteur pour hélicoptère comportant un carter et un arbre monté rotatif dans ledit carter, ledit turbomoteur comportant en outre un dispositif d'étanchéité conforme à la présente invention.The present invention also relates to a turbine engine for a helicopter comprising a housing and a shaft rotatably mounted in said housing, said turbine engine further comprising a sealing device according to the present invention.
Avantageusement, le turbomoteur selon l'invention comporte en outre une source de gaz pressurisé pour alimenter les moyens pour amener un flux de gaz pressurisé dans la cavité annulaire. De manière préférentielle mais non exclusivement, la source d'air pressurisé est une veine disposée en sortie de l'étage de compression.Advantageously, the turbine engine according to the invention further comprises a source of pressurized gas for supplying the means for bringing a flow of pressurized gas into the annular cavity. Preferably, but not exclusively, the source of pressurized air is a stream disposed at the outlet of the compression stage.
On pourrait en effet prévoir une source de gaz pressurisé extérieure sans sortir du cadre de la présente invention.It could indeed provide a source of external pressurized gas without departing from the scope of the present invention.
L'invention sera mieux comprise et ses avantages apparaîtront mieux à la lecture de la description qui suit, d'un mode de réalisation indiqué à titre d'exemple non limitatif. La description se réfère aux figures annexées sur lesquelles : la figure 1 montre un détail d'un carter de turbomoteur d'un hélicoptère dans lequel est monté un arbre rotatif, le turbomoteur comportant un dispositif d'étanchéité conforme à la présente invention ; et la figure 2 représente un turbomoteur muni d'un dispositif d'étanchéité selon la présente invention.The invention will be better understood and its advantages will appear better on reading the description which follows, of an embodiment indicated by way of non-limiting example. The description refers to the appended figures in which: Figure 1 shows a detail of a turbine engine casing of a helicopter in which is mounted a rotary shaft, the turbine engine comprising a sealing device according to the present invention; and FIG. 2 shows a turbine engine equipped with a sealing device according to the present invention.
Sur la figure 1, on a représenté un détail d'un carter 10 du réducteur de vitesse 11 d'un turbomoteur 52 pour un engin volant, tel un hélicoptère, dans lequel est monté un dispositif d'étanchéité 12 conforme à l'invention.In Figure 1, there is shown a detail of a housing 10 of the speed reducer 11 of a turbine engine 52 for a flying machine, such as a helicopter, in which is mounted a sealing device 12 according to the invention.
Evidemment, cette figure ne représente qu'un exemple non limitatif d'utilisation du dispositif selon l'invention.Obviously, this figure represents only a nonlimiting example of use of the device according to the invention.
Comme on le voit sur la figure 1, un arbre 14 présentant un axe de rotation A est monté rotatif dans le carter 10, notamment par l'intermédiaire d'un palier 16.As can be seen in FIG. 1, a shaft 14 having an axis of rotation A is rotatably mounted in the casing 10, in particular via a bearing 16.
En l'espèce, le carter 10 correspond au carter du réducteur 11 du turbomoteur, c'est-à-dire que l'extrémité 18 de l'arbre 14 du côté du palier est destinée à être couplée à des engrenages, tandis que l'extrémité opposée 20 est une prise de mouvement destinée à être couplée à un arbre transmettant le couple au rotor de l'hélicoptère. En d'autres termes, l'extrémité 20 de prise de mouvement est située à l'extérieur du turbomoteur 52 tandis que l'extrémité 18 côté enceinte 21 du réducteur 11 est située à l'intérieur du turbomoteur 52.In this case, the housing 10 corresponds to the casing of the gearbox 11 of the turbine engine, that is to say that the end 18 of the shaft 14 on the bearing side is intended to be coupled to gears, while the opposite end 20 is a power take-off intended to be coupled to a shaft transmitting torque to the rotor of the helicopter. In other words, the PTO 20 is located outside the turbine engine 52 while the end 18 on the enclosure side 21 of the gear 11 is located inside the turbine engine 52.
Afin de lubrifier les éléments tournants situés dans l'enceinte 21 du réducteur 11, on y injecte de l'huile, si bien qu'il règne une ambiance air/huile dans cette partie du turbomoteur 52.In order to lubricate the rotating elements situated in the enclosure 21 of the gearbox 11, oil is injected therein, so that an air / oil atmosphere prevails in this part of the turbine engine 52.
Tant pour des considérations environnementales que mécaniques, il convient d'éviter que l'huile ne sorte du carter 10 du réducteur 11.For both environmental and mechanical considerations, it is necessary to prevent the oil from coming out of the housing 10 of the gearbox 11.
Il convient également d'éviter que des poussières ou toute autre particule indésirable ne pénètrent dans l'enceinte 21 du réducteur 11, qui, dans le cas contraire, risqueraient d'endommager les engrenages 53 du réducteur 11.It is also necessary to prevent dust or any other undesirable particle from entering the enclosure 21 of the gearbox 11, which, otherwise, could damage the gears 53 of the gearbox 11.
Pour ce faire et conformément à l'invention, le dispositif d'étanchéitéTo do this and in accordance with the invention, the sealing device
12 disposé entre le carter 10 et l'arbre 14 permet d'éviter tant la perte d'huile que l'introduction de particules extérieures dans l'enceinte du réducteur 11, tout en présentant une durée de vie plus longue que le dispositif d'étanchéité de l'art antérieur.12 disposed between the housing 10 and the shaft 14 prevents both the loss of oil and the introduction of external particles in the enclosure of the gear 11, while having a longer life than the device of sealing of the prior art.
Pour ce faire, le dispositif d'étanchéité 12 comporte un premier joint à lèvre annulaire 24 et un second joint à lèvre annulaire 26 qui sont disposés côte à côte entre le carter 10 et l'arbre 14 tout en étant coaxiaux, étant entendu que leur axe commun correspond sensiblement à l'axe A de l'arbreTo do this, the sealing device 12 comprises a first annular lip seal 24 and a second annular lip seal 26 which are arranged side by side between the casing 10 and the shaft 14 while being coaxial, it being understood that their common axis corresponds substantially to the axis A of the tree
14.14.
De préférence, les joints à lèvre annulaires 24,26 sont des joints à contact radial et sont préférentiellement réalisés en élastomère. Les premier et second joints à lèvre annulaires 24,26 sont de préférence fixés sur un manchon 28 disposé axialement dans un alésage 30 du carter 10, le manchon 28 étant lui-même maintenu solidairement avec le carter 10 entre un flasque 32 solidaire du carter 10 et le palier 16.Preferably, the annular lip seals 24, 26 are radial contact seals and are preferably made of elastomer. The first and second annular lip seals 24, 26 are preferably fixed on a sleeve 28 arranged axially in a bore 30 of the casing 10, the sleeve 28 itself being held integrally with the casing 10 between a flange 32 secured to the casing 10 and the landing 16.
Comme on le voit sur la figure 1, les premier et second joints à lèvre annulaires 24,26 comportent respectivement une première lèvre 34 et une seconde lèvre 36 qui s'étendent selon la direction axiale de l'arbre 14 tout en s'éloignant l'une de l'autre.As can be seen in FIG. 1, the first and second annular lip seals 24, 26 respectively comprise a first lip 34 and a second lip 36 which extend in the axial direction of the shaft 14 while moving away from each other. one of the other.
Par ailleurs, les lèvres 34 et 36 sont conformées pour présenter une première position, représentée en traits pointillés sur la figure 1, dans laquelle chacune d'elles vient en contact avec la surface extérieure 22 de l'arbre 14 afin d'assurer l'étanchéité de l'enceinte 21 du réducteur 11. Conformément à l'invention, les lèvres 34, 36 sont dans leur première position de préférence lorsque l'arbre 14 ne tourne pas. Autrement dit, les lèvres 34,36, dans leur première position, assurent une étanchéité statique entre le carter 10 et l'arbre 14. On comprend en effet que, dans leur première position, la première lèvre 34 empêche les particules extérieures de rentrer dans l'enceinte 21, tandis que la seconde lèvre 36 empêche les gouttelettes d'huile de sortir de l'enceinte 21 du réducteur 11.Furthermore, the lips 34 and 36 are shaped to have a first position, shown in dashed lines in FIG. 1, in which each of them comes into contact with the outer surface 22 of the shaft 14 in order to ensure the sealing the enclosure 21 of the gearbox 11. According to the invention, the lips 34, 36 are in their first position preferably when the shaft 14 does not rotate. In other words, the lips 34,36, in their first position, provide a static seal between the housing 10 and the shaft 14. In fact, it is understood that, in their first position, the first lip 34 prevents the outer particles from entering the the enclosure 21, while the second lip 36 prevents the oil droplets from leaving the enclosure 21 of the gearbox 11.
De manière particulièrement avantageuse, les lèvres 34 et 36 sont aptes à se trouver dans une seconde position, représentée en traits pleins sur la figure, position dans laquelle les lèvres 34, 36 décollent de la surface extérieure 22 de l'arbre 24.In a particularly advantageous manner, the lips 34 and 36 are able to be in a second position, represented in solid lines in the figure, in which position the lips 34, 36 take off from the outer surface 22 of the shaft 24.
Préférentiellement, les lèvres 34 et 36 sont dans leur seconde position lorsque l'arbre 14 tourne. Pour ce faire, on pressurise une cavité annulaire 38 délimitée par la première lèvre 34, la seconde lèvre 36 et la surface extérieure 22 de l'arbre 14 grâce à des moyens 40 pour amener un flux d'air F pressurisé dans ladite cavité 38.Preferably, the lips 34 and 36 are in their second position when the shaft 14 rotates. To do this, an annular cavity 38 delimited by the first lip 34, the second lip 36 and the outer surface 22 of the shaft 14 is pressurized by means 40 to bring a stream of pressurized air F into said cavity 38.
Lesdits moyens comportent un canal 40 ménagé dans un col 42 du manchon 28, ledit col 42 s'étendant dans un plan orthogonal à l'axe A de l'arbre 14 de telle sorte que le canal 40 s'étendant sensiblement radialement.Said means comprise a channel 40 formed in a neck 42 of the sleeve 28, said neck 42 extending in a plane orthogonal to the axis A of the shaft 14 so that the channel 40 extending substantially radially.
En se référant à la figure 1, on constate qu'une première extrémité 44 du canal 40 débouche dans la cavité annulaire 38, tandis qu'une seconde extrémité 43 du canal 40 opposé à la première extrémité 44 est reliée à un raccord 46 par l'intermédiaire d'une conduite radiale 48 ménagée dans le carter 10.Referring to FIG. 1, it can be seen that a first end 44 of the channel 40 opens into the annular cavity 38, while a second end 43 of the channel 40 opposite the first end 44 is connected to a connection 46 by the intermediate of a radial pipe 48 formed in the housing 10.
Le raccord 46 est quant à lui connecté via un tubage 45 à une source de pression qui, dans la présente espèce, est un point de prélèvement 49 disposé en sortie d'un compresseur 50 du turbomoteur 52 tel que représenté sur la figure 2.The connector 46 is connected via a casing 45 to a pressure source which, in the present case, is a sampling point 49 disposed at the outlet of a compressor 50 of the turbine engine 52 as represented in FIG. 2.
Autrement dit, le gaz correspond en l'espèce une fraction d'air prélevée sur l'air comprimé par le compresseur 50.In other words, the gas corresponds in this case a fraction of air taken from the compressed air by the compressor 50.
Un intérêt d'utiliser la sortie du compresseur 50 comme source de pression est de pouvoir s'affranchir d'utiliser une source de pression extérieure bien que cela soit tout à fait possible dans le cadre de la présente invention. Conformément à l'invention, le flux de gaz F amené dans la cavité 38 présente une pression suffisante pour pouvoir décoller les lèvres 34 et 36 de la surface extérieure 22 se l'arbre 14.An advantage of using the output of the compressor 50 as a source of pressure is to be able to avoid using an external pressure source, although this is entirely possible within the scope of the present invention. According to the invention, the gas flow F brought into the cavity 38 has a sufficient pressure to be able to take off the lips 34 and 36 of the outer surface 22 of the shaft 14.
Ainsi, comme on le comprend à l'aide des flèches représentées sur la figure 1, le flux de gaz F fait décoller les lèvres 34 et 36 de la surface extérieure 22 de l'arbre 14 pour s'écouler hors de la cavité 38.Thus, as can be understood by means of the arrows shown in FIG. 1, the gas flow F detaches the lips 34 and 36 from the outer surface 22 of the shaft 14 to flow out of the cavity 38.
Plus précisément, le flux de gaz sortant de la cavité 38 est de préférence constitué par un premier flux annulaire Fl s'écoulant axialement vers l'extérieur du turbomoteur 52 et par un second flux annulaire F2 s'écoulant axialement vers l'intérieur de l'enceinte 21, dans un sens opposé au premier flux annulaire Fl.More specifically, the stream of gas leaving the cavity 38 is preferably constituted by a first annular flow Fl flowing axially outwardly of the turbine engine 52 and a second annular flow F2 flowing axially inwardly of the enclosure 21, in a direction opposite to the first annular flow Fl.
On comprend donc que grâce à l'invention, le premier flux Fl empêche les particules extérieures d'entrer dans l'enceinte 21 du réducteurIt is therefore understood that, thanks to the invention, the first flow Fl prevents the outer particles from entering the enclosure 21 of the reducer
11, tandis que le second flux F2 empêche les gouttelettes d'huile de sortir de l'enceinte 21, en conséquence de quoi l'étanchéité est assurée malgré le décollement des lèvres 34 et 36 lorsqu'elles sont dans leur seconde position.11, while the second flow F2 prevents oil droplets from leaving the chamber 21, whereby sealing is ensured despite detachment of the lips 34 and 36 when in their second position.
Comme on l'a déjà mentionné, grâce au décollement avantageux des lèvres 34 et 36 lors de la rotation de l'arbre 14, les joints à lèvre annulaires 24,26 s'usent sensiblement moins du fait de l'absence de frottement lors de la rotation de l'arbre.As already mentioned, thanks to the advantageous detachment of the lips 34 and 36 during the rotation of the shaft 14, the annular lip seals 24,26 wear substantially less because of the absence of friction during the rotation of the tree.
Ainsi le dispositif d'étanchéité conforme à l'invention présente une durée de vie plus longue que ceux de l'art antérieur.Thus the sealing device according to the invention has a longer life than those of the prior art.
De manière avantageuse, le dispositif d'étanchéité selon la présente invention comporte en outre un diaphragme D permettant de limiter le débit de gaz pressurisé en cas d'endommagement de l'une ou l'autre des lèvres 34,36. Advantageously, the sealing device according to the present invention further comprises a diaphragm D to limit the flow of pressurized gas in case of damage to one or other of the lips 34,36.

Claims

REVENDICATIONS
1. Dispositif d'étanchéité (12) pour assurer l'étanchéité entre un carter (10) et un arbre (14) monté rotatif dans ledit carter (10), comprenant des premier (24) et second (26) joints à lèvre annulaires destinés à être disposés axialement côte à côte entre le carter (10) et l'arbre (14), ledit dispositif étant caractérisé en ce qu'il comporte en outre des moyens (45,46,48) pour amener un flux de gaz (F) pressurisé dans une cavité annulaire (38) délimitée par le premier joint à lèvre (24), le second joint à lèvre (26) et une surface extérieure de l'arbre (22), de telle sorte que lors de la rotation dudit arbre (14), le flux de gaz (F,F1,F2) est apte à faire légèrement décoller au moins l'un des deux joints à lèvre (24,26) de la surface extérieure (22) de l'arbre (14) pour s'écouler hors de la cavité (38), et en ce que les moyens (45,46,48) pour amener le flux de gaz pressurisé (F) comportent en outre un diaphragme (D) pour limiter le débit d'air pressurisé en cas d'endommagement de l'une des lèvres (34,36) des joints à lèvre annulaires.A sealing device (12) for sealing between a housing (10) and a shaft (14) rotatably mounted in said housing (10), comprising first (24) and second (26) annular lip seals intended to be arranged axially side by side between the casing (10) and the shaft (14), said device being characterized in that it further comprises means (45, 46, 48) for feeding a flow of gas ( F) pressurized in an annular cavity (38) delimited by the first lip seal (24), the second lip seal (26) and an outer surface of the shaft (22), so that during the rotation of said shaft (14), the gas flow (F, F1, F2) is able to slightly lift off at least one of the two lip seals (24,26) from the outer surface (22) of the shaft (14). ) to flow out of the cavity (38), and in that the means (45,46,48) for supplying the pressurized gas flow (F) further comprises a diaphragm (D) to limit the flow rate of air pr essurisé in case of damage to one of the lips (34,36) of the annular lip seals.
2. Dispositif d'étanchéité selon la revendication 1, caractérisé en ce que le premier joint à lèvre (24) comporte une première lèvre (34) tandis que le second joint à lèvre (26) comporte une seconde lèvre (36), et en ce que première et seconde lèvres (34,36) sont destinés à s'étendre selon la direction axiale de l'arbre (14) tout en s'éloignant l'une de l'autre.Sealing device according to claim 1, characterized in that the first lip seal (24) has a first lip (34) while the second lip seal (26) has a second lip (36), and what first and second lips (34,36) are intended to extend in the axial direction of the shaft (14) while moving away from each other.
3. Dispositif d'étanchéité selon la revendication 2, caractérisé en ce que les moyens (45,46,48) pour amener le flux de gaz (F) pressurisé comportent un canal (48) disposé entre les premier et second joints à lèvre, ledit canal (48) étant relié à une source de gaz pressurisé3. Sealing device according to claim 2, characterized in that the means (45,46,48) for bringing the stream of gas (F) pressurized comprises a channel (48) disposed between the first and second lip seals, said channel (48) being connected to a source of pressurized gas
(49,50).(49,50).
4. Turbomoteur (52) pour hélicoptère comportant un carter (10) et un arbre (14) monté rotatif dans ledit carter, caractérisé en ce qu'il comporte en outre un dispositif d'étanchéité (12) selon l'une quelconque des revendications 1 à 3. 4. Turbomotor (52) for helicopter having a housing (10) and a shaft (14) rotatably mounted in said housing, characterized in that it further comprises a sealing device (12) according to any one of the claims 1 to 3.
5. Turbomoteur pour hélicoptère selon la revendication 4, caractérisé en ce qu'il comporte en outre une source de gaz pressurisé (49,50) pour alimenter les moyens (45,46,48) pour amener un flux de gaz pressurisé (F) dans la cavité annulaire (38).5. Turbomotor for helicopter according to claim 4, characterized in that it further comprises a source of pressurized gas (49,50) for supplying the means (45,46,48) to bring a flow of pressurized gas (F) in the annular cavity (38).
6. Turbomoteur pour hélicoptère ayant un étage de compression selon la revendication 5, caractérisé en ce que la source de gaz pressurisé est une veine (49) disposée en sortie de l'étage de compression (50).6. Helicopter for a helicopter having a compression stage according to claim 5, characterized in that the source of pressurized gas is a stream (49) disposed at the output of the compression stage (50).
7. Turbomachine caractérisée en ce qu'elle comporte un dispositif selon l'une quelconque des revendications 1 à 3. 7. Turbomachine characterized in that it comprises a device according to any one of claims 1 to 3.
EP08788058A 2007-03-27 2008-03-27 Double seal with pressurised lip Withdrawn EP2140178A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0754050A FR2914384B1 (en) 2007-03-27 2007-03-27 DOUBLE JOINT WITH PRESSURIZED LIP.
PCT/FR2008/050532 WO2008132410A2 (en) 2007-03-27 2008-03-27 Double seal with pressurised lip

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EP2140178A2 true EP2140178A2 (en) 2010-01-06

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US (1) US20100119368A1 (en)
EP (1) EP2140178A2 (en)
JP (1) JP2010522857A (en)
CN (1) CN101652590A (en)
BR (1) BRPI0809521A2 (en)
CA (1) CA2682004A1 (en)
FR (1) FR2914384B1 (en)
RU (1) RU2009139645A (en)
WO (1) WO2008132410A2 (en)
ZA (1) ZA200906987B (en)

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WO2008132410A2 (en) 2008-11-06
CA2682004A1 (en) 2008-11-06
CN101652590A (en) 2010-02-17
RU2009139645A (en) 2011-05-10
ZA200906987B (en) 2010-06-30
FR2914384B1 (en) 2009-08-21
FR2914384A1 (en) 2008-10-03
US20100119368A1 (en) 2010-05-13
BRPI0809521A2 (en) 2014-10-14
WO2008132410A3 (en) 2008-12-24
JP2010522857A (en) 2010-07-08

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