EP0626503A1 - Depressurization device for bearing lubrication chambers - Google Patents

Depressurization device for bearing lubrication chambers Download PDF

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Publication number
EP0626503A1
EP0626503A1 EP94401145A EP94401145A EP0626503A1 EP 0626503 A1 EP0626503 A1 EP 0626503A1 EP 94401145 A EP94401145 A EP 94401145A EP 94401145 A EP94401145 A EP 94401145A EP 0626503 A1 EP0626503 A1 EP 0626503A1
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EP
European Patent Office
Prior art keywords
turbomachine
lubrication
chambers
depressurization device
pumping means
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Granted
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EP94401145A
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German (de)
French (fr)
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EP0626503B1 (en
Inventor
Christian Largillier
Jérôme Friedel
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/20—Lubricating arrangements using lubrication pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/601—Fluid transfer using an ejector or a jet pump

Definitions

  • the invention relates to a device making it possible, under certain conditions, to depressurize the lubrication chambers which surround each of the bearings of a turbomachine such as an aircraft turbojet engine.
  • lubrication liquid supply circuits On turbomachinery such as turbojets fitted to aircraft, the bearings are permanently lubricated by lubrication liquid supply circuits.
  • a circuit usually comprises a reservoir of lubrication liquid, as well as a pump making it possible to convey the liquid to a nozzle situated in the immediate vicinity of each of the bearings.
  • the latter are themselves placed in lubrication chambers closed by seals and at the bottom of which opens a conduit allowing an emulsion formed of the lubrication liquid mixed with air to be recovered.
  • This pipe incorporates a lubricating liquid recovery pump, which conveys the above-mentioned emulsion to a lubricating liquid-air separator, after having cooled it in an appropriate cooling device. At the outlet of the separator, the coolant is returned to the tank, while the air is discharged directly outside through an exhaust port.
  • the lubrication chambers surrounding the bearings are placed in zones which are overpressure relative to the internal pressure of these chambers, under normal operating conditions of the turbomachine.
  • the overpressure is usually provided by the compressor of the turbomachine. This feature normally prevents any escape of the lubrication liquid outside the lubrication chambers.
  • the lubrication system of the turbomachine can be equipped with a device for depressurizing the lubrication chambers of the bearings such as that described in patent FR-A-2 536 120.
  • This device puts each room with the outside and allows to maintain in these rooms a pressure equal to the outside pressure increased only by the pressure drop due to the flow of the air-lubricant emulsion in the device.
  • This device usually comprises a so-called vent pipe, connected to each chamber, at least one air-lubricant separator which is usually that of the turbomachine, as well as an exhaust duct extending the separator.
  • the device remains ineffective at low speeds of the turbomachine, since the compressor no longer provides overpressure around the lubrication chambers.
  • the subject of the invention is precisely a device for depressurizing the lubrication chambers which surround each of the bearings of a turbomachine, under particular pre-established conditions, in order to eliminate any risk of leakage of the lubrication liquid by guaranteeing, in all conditions operating, a pressure in the lubrication chambers, lower than that prevailing outside these chambers.
  • this result is obtained by equipping the depressurization device of the lubrication chambers with auxiliary pumping means supplied with energy by drawing compressed air from the compressor of one or more other turbomachines.
  • the depressurization device also comprises, according to the invention, means for controlling the auxiliary pumping means.
  • control means are actuated when a turbomachine monitoring system detects that the latter is operating at a speed below the idle speed.
  • the auxiliary pumping means are then automatically actuated, which has the effect of establishing a depression in the lubrication chambers avoiding any risk of leakage of the lubrication liquid towards the exterior of these chambers.
  • the auxiliary pumping means consist of a jet pump arranged in the exhaust duct of the air-lubricating separator and supplied with pressurized air through a normally closed valve and constituting the means control.
  • the auxiliary pumping means consist of a jet pump arranged in each vent pipe, all of the jet tubes being supplied with air under pressure through one or more normally closed valves constituting the control means.
  • the external pressure source is constituted by the compressor of the second turbomachine.
  • the device then advantageously comprises a second jet horn placed in the exhaust duct of the air-lubricating separator of the second turbomachine, this second jet horn being supplied by the compressor of the first turbomachine through a second valve normally closed.
  • turbomachines are, for reasons of weight and cost, each equipped with a single air-lubricating separator mechanically driven, but the invention applies in the same way to depressurization devices each comprising a separator specific air-lubricant.
  • the compressors of the first and of the second turbomachine are then connected to the second and to the first jet pump, respectively, by a section of common duct, a non-return valve being placed between each of the compressors and this section .
  • the device which is the subject of the invention has the advantage of being light, which is particularly appreciable on aircraft.
  • the realization is simple and without moving parts other than the valves and means for closing the conduits.
  • the device is therefore reliable and inexpensive.
  • the references 10a and 10b generally designate two turbojets of a multi-engine aircraft.
  • the rotating parts of each of these turbojets 10a and 10b are supported by bearings, the nature and number of which vary according to the type of engine considered.
  • Three of these bearings, located at different points on each of the engines, are designated respectively by the references 12a and 12b in FIG. 1 for each of the turbojets 10a and 10b.
  • each of the circuits 24a, 24b supplies lubrication liquid to all of the bearings of the corresponding turbojet engine 10a, 10b.
  • the bearing 12a, 12b illustrated in FIG. 2 is a ball bearing, it will be understood that the invention applies to any other type of bearing.
  • the bearing 12a, 12b is interposed between a rotary part, constituted here by a shaft 14a, 14b and a non-rotary part 16a, 16b.
  • this non-rotating part 16a, 16b supports a rotating seal 18a, 18b.
  • a lubrication chamber 20a, 20b is thus delimited, in a generally sealed manner, around the bearing 12a, 12b.
  • the lubrication chamber 20a, 20b is itself located in a region 22a, 22b of the turbojet engine which is normally under overpressure relative to atmospheric pressure. This overpressure is produced by the compressor of the turbojet engine.
  • the arrangement which has just been described makes it possible, under normal operating conditions of the turbojet engine, to prevent the lubrication liquid such as oil which is introduced into the lubrication chamber 20a, 20b by the circuit of supply 24a, 24b remains confined in this room due to the pressure difference which exists between the region 22a, 22b and the lubrication chamber 20a, 20b.
  • the supply circuit 24a, 24b comprises a reservoir 26a, 26b filled with lubrication liquid 28.
  • a conduit 30a, 30b for supplying lubrication liquid connects the reservoir 26a, 26b to a nozzle 32a, 32b located in each of the chambers lubrication 20a, 20b surrounding the bearings 12a, 12b of the turbojet engine 10a, 10b.
  • the nozzles 32a, 32b are oriented towards the bearings 12a, 12b, so as to spray the latter permanently with lubrication liquid 28 during operation of the turbojet engine.
  • the pipe 30a, 30b for supplying lubrication liquid comprises a pump 34a, 34b for injecting lubrication liquid.
  • the lubrication liquid injected under pressure into each of the lubrication chambers 20a, 20b falls by gravity into the inclined bottom of this chamber, in which it is taken up by a conduit 36a 36b for recovering a lubrication-air liquid emulsion.
  • This conduit 36a, 36b is equipped with a pump 38a, 38b for recovering lubrication liquid.
  • the pump 38a, 38b discharges this emulsion into a separator 40a, 40b lubricating liquid-air.
  • the conduit 36a, 36b passes through a cooling exchanger 42a, 42b. This cooling exchanger makes it possible to lower the temperature of the lubricating liquid, by heat exchange with the fuel of the aircraft.
  • the separator 40a, 40b lubrication-air liquid is a centrifugal device, of known structure, comprising in particular fins or honeycomb masses whose rotation allows the separation of air and lubrication liquid, under the effect of centrifugal force.
  • the lubrication liquid is taken up in the bottom of the separator 40a, 40b by a conduit 44a, 44b ensuring the return of this liquid in the reservoir 26a, 26b.
  • the overpressure usually prevailing in the region 22a, 22b which surrounds each of the lubrication chambers 20a , 20b may momentarily become lower than the pressure prevailing inside these chambers. Leakage of lubrication liquid then occurs outside the chambers 20a, 20b, and, consequently, internal pollution of the turbojet engine. In some cases, lubrication liquid can also be found in the vein where air circulates for the internal functioning of the aircraft. In addition, a large leak can lead to the depletion of the supply of lubricating liquid, endangering the engine and the aircraft. To eliminate this risk, the lubrication circuit 24a and 24b of each of the turbojets 10a and 10b are usually associated with a device making it possible to depressurize the lubrication chambers 20a, 20b.
  • This depressurization device firstly comprises, for each of the turbojets 10a and 10b, a duct 48a, 48b for venting the lubrication chamber 20a, 20b surrounding each of the bearings of this turbojet.
  • This conduit 48a, 48b opens into the upper part of a lubrication chamber 20a, 20b and connects this lubrication chamber to a separator 40a, 40b lubrication-air liquid itself extended by an exhaust conduit 46a, 46b.
  • the air-lubricant separator 40a, 40b and the exhaust duct 46a, 46b will be common to the device for depressurizing the lubrication chambers 20a, 20b and to the circuit for recovering the lubricant through conduits 36a, 36b and 44a, 44b.
  • the conduits 48a and 48b connect each lubrication chamber 20a, 20b to the common separator 40a, 40b, of the turbomachine 10a, 10b and they thus make it possible to maintain the pressure prevailing in each of the lubrication chambers 20a, 20b at a level close to the atmospheric pressure.
  • the depressurization device further comprises, downstream of the separators 40a, 40b lubrication-air liquid, on the exhaust duct 46a, 46b of this separator, an auxiliary pump.
  • this auxiliary pump is constituted by a jet pump 49a, 49b.
  • This jet horn 49a, 49b comprises a convergent-divergent assembly 50a, 50b placed in the duct 46a, 46b, as well as a nozzle 51a, 51b opening out near the part of the smallest section of the convergent-divergent assembly and oriented downstream, so as to entrain outward the air leaving the separator 40a, 40b through the conduit 46a, 46b.
  • Each of the nozzles 51a, 51b of the jet tubes 49a, 49b is connected to a conduit 52a, 52b for supplying pressurized air ( Figure 1).
  • Each of the conduits 52a and 52b comprises a valve 54a, 54b normally closed when the corresponding turbojet engine is in operating conditions which do not involve any risk of leakage from the lubrication liquid to the outside of the lubrication chambers 20a, 20b.
  • the end of the duct 52a opposite the jet horn 49a opens into the compressor 56b of the turbojet engine 10b and the end of the duct 52b opposite the jet horn 49b opens into the compressor 56a of the turbojet engine 10a.
  • the conduits 52a and 52b have a common section 52.
  • a non-return valve 58a is placed in the part of the conduit 52a between the compressor 56b and the common section 52 and a non-return valve 58b is placed in the part of the duct 52b located between the compressor 56a and the common section 52.
  • the opening of the valve 54a or 54b is automatically controlled by an appropriate circuit 60 fitted to the aircraft, when the information supplied to this circuit by sensors fitted to the turbojet engine 10a or 10b It appears that the operating regime of the latter is insufficient to guarantee the confinement of the lubrication liquid inside the lubrication chambers 20a, 20b which surround each of the bearings of this turbojet engine.
  • the opening of the valve 54a immediately results in the communication of the compressor 56b of the turbojet engine 10b with the air injection nozzle of the jet pump 49a.
  • An air pumping effect located in the lubrication chambers 20a surrounding the bearings 12a of the turbojet engine 10a is immediately obtained. Consequently, these chambers are placed under vacuum and any risk of leakage of the lubrication liquid is avoided.
  • the operation of the part of the depressurization device which is associated with the turbojet engine 10b is completely identical to that of the part of this circuit associated with the turbojet engine 10a. It is also controlled by the opening of the valve 54b and results, here again, in the creation of a vacuum in the lubrication chambers 20b which surround the bearings 12b of the turbojet engine 10b.
  • a second embodiment of the invention is applied to a set of two or more turbomachines.
  • turbomachines 10a and 10b are shown in FIG. 3, but the description which follows will apply in the same way to a greater number of turbomachines.
  • turbomachine being arranged and connected in the same way to the others, let us take the example of the machine 10a.
  • the compressor of the turbomachine 10a is connected to the common duct 52 by the duct 53a, said duct 53a being equipped with a non-return valve 58a which allows the circulation of air only in the direction of the common compressor-duct 52.
  • the venting conduits 48a On the enclosures surrounding the bearings of the turbomachine 10a are connected the venting conduits 48a, the other end of which opens onto an oil separator 40a.
  • the purified air from the oil separator 40a is supplied to the inlet of the jet horn 49a.
  • This jet horn 49a is supplied with pressurized air by a duct 55a connected at its other end to the common duct 52.
  • the duct 55a comprises a shutter means 54a normally closed and controlled automatically by an appropriate circuit 60 of the aircraft.
  • turbomachines 10 can be arranged and connected in the same way to the common duct 52 and receive a command from the circuit 60.
  • the common duct 52 is supplied with pressurized air by the compressors of the turbomachines 10, 10a, 10b which are connected to it, but there is normally no air flow in the common duct 52.
  • auxiliary pumping means 49a, 49b on the depressurization device of the bearing chambers 12a, 12b, in accordance with the invention is advantageous because of the presence of the venting ducts 48a, 48b, said conduits in fact making it possible to transmit to said chambers 20a, 20b the vacuum produced by said pumping means 49a, 49b.
  • the pumping means 49a, 49b of the invention would not have been effective on the lubricant recovery duct 36a, 36b, since the recovery pumps 38a, 38b are usually of the volumetric type, for example with gears, and they would oppose the transmission of the depression between the chambers 12a, 12b and the exterior.
  • the recovery pumps 38a, 38b generate significant variations in pressure which could not have been compensated by the pumping means 49a, 49b of the invention.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

In order to avoid leaks of the fluid for lubricating the bearings (12a, 12b) of a turbomachine such as an aircraft turbojet engine, when the speed of this turbomachine drops below the idling speed, it is proposed to connect the chambers (20a, 20b) surrounding the bearings (12a, 12b) to free air via a pipe (48a, 48b) in which a jet pipe (49a, 49b) has been placed. The nozzle of this jet pipe is connected to a source of compressed air, such as the compressor (56b, 56a) of another turbomachine, via a valve (54a, 54b) which is made to open under the abovementioned conditions. <IMAGE>

Description

L'invention concerne un dispositif permettant, dans certaines conditions, de dépressuriser les chambres de lubrification qui entourent chacun des paliers d'une turbomachine telle qu'un turboréacteur d'aéronef.The invention relates to a device making it possible, under certain conditions, to depressurize the lubrication chambers which surround each of the bearings of a turbomachine such as an aircraft turbojet engine.

Sur les turbomachines telles que les turboréacteurs équipant les aéronefs, les paliers sont lubrifiés en permanence par des circuits d'alimentation en liquide de lubrification. Un tel circuit comprend habituellement un réservoir de liquide de lubrification, ainsi qu'une pompe permettant d'acheminer le liquide jusqu'à un gicleur situé à proximité immédiate de chacun des paliers. Ces derniers sont eux-mêmes placés dans des chambres de lubrification fermées par des joints d'étanchéité et dans le fond desquelles débouche un conduit permettant de récupérer une émulsion formée du liquide de lubrification mélangé à de l'air. Ce conduit incorpore une pompe de récupération de liquide de lubrification, qui achemine l'émulsion précitée jusqu'à un séparateur liquide de lubrification-air, après l'avoir refroidie dans un dispositif de refroidissement approprié. A la sortie du séparateur, le liquide de refroidissement est ramené dans le réservoir, alors que l'air est évacué directement à l'extérieur par un orifice d'échappement.On turbomachinery such as turbojets fitted to aircraft, the bearings are permanently lubricated by lubrication liquid supply circuits. Such a circuit usually comprises a reservoir of lubrication liquid, as well as a pump making it possible to convey the liquid to a nozzle situated in the immediate vicinity of each of the bearings. The latter are themselves placed in lubrication chambers closed by seals and at the bottom of which opens a conduit allowing an emulsion formed of the lubrication liquid mixed with air to be recovered. This pipe incorporates a lubricating liquid recovery pump, which conveys the above-mentioned emulsion to a lubricating liquid-air separator, after having cooled it in an appropriate cooling device. At the outlet of the separator, the coolant is returned to the tank, while the air is discharged directly outside through an exhaust port.

Dans une turbomachine, les chambres de lubrification entourant les paliers sont placées dans des zones qui sont en surpression par rapport à la pression interne de ces chambres, dans les conditions normales de fonctionnement de la turbomachine. La surpression est habituellement fournie par le compresseur de la turbomachine. Cette caractéristique empêche normalement tout échappement du liquide de lubrification en dehors des chambres de lubrification.In a turbomachine, the lubrication chambers surrounding the bearings are placed in zones which are overpressure relative to the internal pressure of these chambers, under normal operating conditions of the turbomachine. The overpressure is usually provided by the compressor of the turbomachine. This feature normally prevents any escape of the lubrication liquid outside the lubrication chambers.

Cependant, lorsque le régime de fonctionnement de la turbomachine est inférieur au régime de ralenti, la pression qui règne normalement à l'extérieur des chambres de lubrification peut devenir voisine de la pression régnant à l'intérieur de ces chambres, et même inférieure à cette pression. Ces conditions peuvent notamment se présenter lors d'une forte baisse de régime de la turbomachine, d'origine quelconque, lorsqu'elle subit une extinction et ne tourne plus qu'en autorotation, lors d'essais de redémarrage de la turbomachine à l'arrêt et lors d'un fonctionnement de la turbomachine sans allumage.However, when the operating speed of the turbomachine is lower than the idling speed, the pressure which normally prevails outside the lubrication chambers may become close to the pressure prevailing inside these chambers, and even less than this. pressure. These conditions can in particular arise during a sharp drop in the speed of the turbomachine, of any origin, when it undergoes an extinction and does not turn more than in autorotation, during tests of restarting of the turbomachine with shutdown and during operation of the turbomachine without ignition.

Une telle diminution de la pression qui règne habituellement à l'extérieur des chambres de lubrification des paliers d'une turbomachine, provoque des fuites du liquide de lubrification vers l'extérieur des chambres de lubrification. Ces fuites de liquide de lubrification entraînent une pollution de la turbomachine et de son environnement immédiat, qui peut être visible de l'extérieur. Sur un aéronef, les fuites de liquide de lubrification peuvent conduire à un épuisement de la réserve nécessairement réduite de liquide de lubrification mettant les turbomachines et, par conséquent, l'aéronef en danger. Pour résoudre ce problème, on peut équiper le système de lubrification de la turbomachine d'un dispositif de dépressurisation des chambres de lubrification des paliers tel que celui qui est décrit dans le brevet FR-A-2 536 120. Ce dispositif met en communication chaque chambre avec l'extérieur et permet de maintenir dans ces chambres une pression égale à la pression extérieure augmentée seulement de la perte de charge due à l'écoulement de l'émulsion air-lubrifiant dans le dispositif. Ce dispositif comporte habituellement un conduit dit, de mise à l'air libre, connecté à chaque chambre, au moins un séparateur air-lubrifiant qui est habituellement celui de la turbomachine, ainsi qu'un conduit d'échappement prolongeant le séparateur.Such a reduction in the pressure which usually prevails outside the lubrication chambers of the bearings of a turbomachine, causes leaks of the lubrication liquid towards the exterior of the lubrication chambers. These leaks of lubrication liquid cause pollution of the turbomachine and its immediate environment, which may be visible from the outside. On an aircraft, leaks of lubrication liquid can lead to an exhaustion of the necessarily reduced supply of lubrication liquid, putting the turbomachines and, consequently, the aircraft in danger. To solve this problem, the lubrication system of the turbomachine can be equipped with a device for depressurizing the lubrication chambers of the bearings such as that described in patent FR-A-2 536 120. This device puts each room with the outside and allows to maintain in these rooms a pressure equal to the outside pressure increased only by the pressure drop due to the flow of the air-lubricant emulsion in the device. This device usually comprises a so-called vent pipe, connected to each chamber, at least one air-lubricant separator which is usually that of the turbomachine, as well as an exhaust duct extending the separator.

Le dispositif reste cependant inefficace aux bas régimes de la turbomachine, car le compresseur ne fournit plus de surpression autour des chambres de lubrification.However, the device remains ineffective at low speeds of the turbomachine, since the compressor no longer provides overpressure around the lubrication chambers.

L'invention a précisément pour objet un dispositif permettant de dépressuriser les chambres de lubrification qui entourent chacun des paliers d'une turbomachine, dans des conditions particulières préétablies, afin de supprimer tout risque de fuite du liquide de lubrification en garantissant, dans toutes les conditions de fonctionnement, une pression dans les chambres de lubrification, inférieure à celle qui règne à l'extérieur de ces chambres.The subject of the invention is precisely a device for depressurizing the lubrication chambers which surround each of the bearings of a turbomachine, under particular pre-established conditions, in order to eliminate any risk of leakage of the lubrication liquid by guaranteeing, in all conditions operating, a pressure in the lubrication chambers, lower than that prevailing outside these chambers.

Conformément à l'invention, ce résultat est obtenu en équipant le dispositif de dépressurisation des chambres de lubrification, de moyens de pompage auxiliaires alimentés en énergie par prélèvement d'air comprimé sur le compresseur d'une ou plusieurs autres turbomachines. Le dispositif de dépressurisation comporte aussi selon l'invention des moyens de commande des moyens de pompage auxiliaires.According to the invention, this result is obtained by equipping the depressurization device of the lubrication chambers with auxiliary pumping means supplied with energy by drawing compressed air from the compressor of one or more other turbomachines. The depressurization device also comprises, according to the invention, means for controlling the auxiliary pumping means.

Dans un tel dispositif, les moyens de commande sont actionnés lorsqu'un système de surveillance de la turbomachine détecte que celle-ci fonctionne à un régime inférieur au régime de ralenti. Les moyens de pompage auxiliaires sont alors automatiquement actionnés, ce qui a pour effet d'établir dans les chambres de lubrification une dépression évitant tout risque de fuite du liquide de lubrification vers l'extérieur de ces chambres.In such a device, the control means are actuated when a turbomachine monitoring system detects that the latter is operating at a speed below the idle speed. The auxiliary pumping means are then automatically actuated, which has the effect of establishing a depression in the lubrication chambers avoiding any risk of leakage of the lubrication liquid towards the exterior of these chambers.

Dans une forme de réalisation préférée, les moyens de pompage auxiliaires sont constitués par une trompe à jet disposée dans le conduit d'échappement du séparateur air-lubrifiant et alimentée par de l'air sous pression à travers une vanne normalement fermée et constituant les moyens de commande.In a preferred embodiment, the auxiliary pumping means consist of a jet pump arranged in the exhaust duct of the air-lubricating separator and supplied with pressurized air through a normally closed valve and constituting the means control.

Dans une autre forme de réalisation de l'invention, les moyens de pompage auxiliaires sont constitués par une trompe à jet disposée dans chaque conduit de mise à l'air libre, l'ensemble des trompes à jet étant alimentées par de l'air sous pression à travers une ou plusieurs vannes normalement fermées et constituant les moyens de commande.In another embodiment of the invention, the auxiliary pumping means consist of a jet pump arranged in each vent pipe, all of the jet tubes being supplied with air under pressure through one or more normally closed valves constituting the control means.

Dans le cas où le dispositif de dépressurisation conforme à l'invention est utilisé sur un aéronef bimoteur, la source de pression extérieure est constituée par le compresseur de la deuxième turbomachine.In the case where the depressurization device according to the invention is used on a twin-engine aircraft, the external pressure source is constituted by the compressor of the second turbomachine.

Le dispositif comprend alors, avantageusement, une deuxième trompe à jet placée dans le conduit d'échappement du séparateur air-lubrifiant de la deuxième turbomachine, cette deuxième trompe à jet étant alimentée par le compresseur de la première turbomachine au travers d'une deuxième vanne normalement fermée.The device then advantageously comprises a second jet horn placed in the exhaust duct of the air-lubricating separator of the second turbomachine, this second jet horn being supplied by the compressor of the first turbomachine through a second valve normally closed.

Il est aussi possible de remplacer les trompes à jet par des pompes comportant une soufflante entraînée par une turbine alimentée en air comprimé, mais cette solution est plus coûteuse. On peut remarquer aussi que les turbomachines sont, pour des raisons de poids et de coût, équipées chacune d'un seul séparateur air-lubrifiant entraîné mécaniquement, mais l'invention s'applique de la même façon aux dispositifs de dépressurisation comportant chacun un séparateur air-lubrifiant spécifique.It is also possible to replace the jet tubes with pumps comprising a blower driven by a turbine supplied with compressed air, but this solution is more expensive. It can also be noted that the turbomachines are, for reasons of weight and cost, each equipped with a single air-lubricating separator mechanically driven, but the invention applies in the same way to depressurization devices each comprising a separator specific air-lubricant.

De préférence, les compresseurs de la première et de la deuxième turbomachine sont alors reliés à la deuxième et à la première pompe à jet, respectivement, par un tronçon de conduit commun, un clapet anti-retour étant placé entre chacun des compresseurs et ce tronçon.Preferably, the compressors of the first and of the second turbomachine are then connected to the second and to the first jet pump, respectively, by a section of common duct, a non-return valve being placed between each of the compressors and this section .

Le dispositif objet de l'invention présente l'avantage d'être léger, ce qui est particulièrement appréciable sur les aéronefs. La réalisation est simple et sans pièces mobiles autres que les clapets et moyens d'obturation des conduits. Le dispositif est en conséquence fiable et peu coûteux.The device which is the subject of the invention has the advantage of being light, which is particularly appreciable on aircraft. The realization is simple and without moving parts other than the valves and means for closing the conduits. The device is therefore reliable and inexpensive.

On décrira à présent, à titre d'exemples non limitatifs, deux formes de réalisation préférentielles de l'invention, en se référant aux dessins annexés, dans lesquels :

  • la figure 1 représente schématiquement deux turbomachines d'un aéronef multimoteur, auquel est associé un dispositif de dépressurisation conforme à l'invention ;
  • la figure 2 représente plus en détail le circuit permettant d'alimenter en fluide de lubrification les paliers de chacune des turbomachines, ainsi que la partie du dispositif de dépressurisation associée à ce circuit ; et
  • la figure 3, représente schématiquement un ensemble de turbomachines d'un aéronef multimoteurs auquel est associé suivant une variante le dispositif de dépressurisation conforme à l'invention.
Two preferred embodiments of the invention will now be described, by way of non-limiting examples, with reference to the appended drawings, in which:
  • FIG. 1 schematically represents two turbomachines of a multi-engine aircraft, with which is associated a depressurization device according to the invention;
  • Figure 2 shows in more detail the circuit for supplying lubrication fluid to the bearings of each of the turbomachines, as well as the part of the depressurization device associated with this circuit; and
  • FIG. 3 schematically represents a set of turbomachines of a multi-engine aircraft with which, according to a variant, the depressurization device according to the invention is associated.

Sur la figure 1, les références 10a et 10b désignent de façon générale deux turboréacteurs d'un aéronef multimoteur. Les parties tournantes de chacun de ces turboréacteurs 10a et 10b sont supportées par des paliers dont la nature et le nombre varient selon le type des moteurs considérés. Trois de ces paliers, situés en différents points de chacun des moteurs, sont désignés respectivement par les références 12a et 12b sur la figure 1 pour chacun des turboréacteurs 10a et 10b.In FIG. 1, the references 10a and 10b generally designate two turbojets of a multi-engine aircraft. The rotating parts of each of these turbojets 10a and 10b are supported by bearings, the nature and number of which vary according to the type of engine considered. Three of these bearings, located at different points on each of the engines, are designated respectively by the references 12a and 12b in FIG. 1 for each of the turbojets 10a and 10b.

La lubrification des paliers 12a, 12b de chacun des turboréacteurs 10a, 10b est assurée par deux circuits 24a, 24b d'alimentation en liquide de lubrification. Etant donné que ces deux circuits sont identiques, la description qui va à présent en être faite en se référant à la figure 2 s'applique à l'un et à l'autre des circuits 24a, 24b.The lubrication of the bearings 12a, 12b of each of the turbojets 10a, 10b is ensured by two circuits 24a, 24b for supplying lubrication liquid. Since these two circuits are identical, the description which will now be made with reference to FIG. 2 applies to both of the circuits 24a, 24b.

Pour faciliter la lecture de la figure 2, seul un palier 12a, 12b a été représenté. On comprendra, cependant, que chacun des circuits 24a, 24b alimente en liquide de lubrification tous les paliers du turboréacteur 10a, 10b correspondant. En outre, si le palier 12a, 12b illustré sur la figure 2 est un palier à billes, on comprendra que l'invention s'applique à tout autre type de palier.To facilitate the reading of FIG. 2, only a bearing 12a, 12b has been shown. It will be understood, however, that each of the circuits 24a, 24b supplies lubrication liquid to all of the bearings of the corresponding turbojet engine 10a, 10b. In addition, if the bearing 12a, 12b illustrated in FIG. 2 is a ball bearing, it will be understood that the invention applies to any other type of bearing.

Sur la figure 2, le palier 12a, 12b est interposé entre une partie rotative, constituée ici par un arbre 14a, 14b et une partie non rotative 16a, 16b. De part et d'autre du palier 12a, 12b, cette partie non rotative 16a, 16b supporte un joint d'étanchéité tournant 18a, 18b. Une chambre de lubrification 20a, 20b se trouve ainsi délimitée, d'une manière en principe étanche, autour du palier 12a, 12b. La chambre de lubrification 20a, 20b est elle-même située dans une région 22a, 22b du turboréacteur qui est normalement en surpression par rapport à la pression atmosphérique. Cette surpression est produite par le compresseur du turboréacteur.In FIG. 2, the bearing 12a, 12b is interposed between a rotary part, constituted here by a shaft 14a, 14b and a non-rotary part 16a, 16b. On either side of the bearing 12a, 12b, this non-rotating part 16a, 16b supports a rotating seal 18a, 18b. A lubrication chamber 20a, 20b is thus delimited, in a generally sealed manner, around the bearing 12a, 12b. The lubrication chamber 20a, 20b is itself located in a region 22a, 22b of the turbojet engine which is normally under overpressure relative to atmospheric pressure. This overpressure is produced by the compressor of the turbojet engine.

L'agencement qui vient d'être décrit permet, dans des conditions de fonctionnement normal du turboréacteur, d'éviter que le liquide de lubrification tel que de l'huile qui est introduit dans la chambre de lubrification 20a, 20b par le circuit d'alimentation 24a, 24b reste confiné dans cette chambre du fait de la différence de pression qui existe entre la région 22a, 22b et la chambre de lubrification 20a, 20b.The arrangement which has just been described makes it possible, under normal operating conditions of the turbojet engine, to prevent the lubrication liquid such as oil which is introduced into the lubrication chamber 20a, 20b by the circuit of supply 24a, 24b remains confined in this room due to the pressure difference which exists between the region 22a, 22b and the lubrication chamber 20a, 20b.

Le circuit d'alimentation 24a, 24b comprend un réservoir 26a, 26b rempli de liquide de lubrification 28. Un conduit 30a, 30b d'amenée de liquide de lubrification relie le réservoir 26a, 26b à un gicleur 32a, 32b situé dans chacune des chambres de lubrification 20a, 20b entourant les paliers 12a, 12b du turboréacteur 10a, 10b. Les gicleurs 32a, 32b sont orientés vers les paliers 12a, 12b, de façon à asperger ces derniers en permanence de liquide de lubrification 28 lors du fonctionnement du turboréacteur. A cet effet, le conduit 30a, 30b d'amenée de liquide de lubrification comporte une pompe 34a, 34b d'injection de liquide de lubrification.The supply circuit 24a, 24b comprises a reservoir 26a, 26b filled with lubrication liquid 28. A conduit 30a, 30b for supplying lubrication liquid connects the reservoir 26a, 26b to a nozzle 32a, 32b located in each of the chambers lubrication 20a, 20b surrounding the bearings 12a, 12b of the turbojet engine 10a, 10b. The nozzles 32a, 32b are oriented towards the bearings 12a, 12b, so as to spray the latter permanently with lubrication liquid 28 during operation of the turbojet engine. To this end, the pipe 30a, 30b for supplying lubrication liquid comprises a pump 34a, 34b for injecting lubrication liquid.

Le liquide de lubrification injecté sous pression dans chacune des chambres de lubrification 20a, 20b retombe par gravité dans le fond incliné de cette chambre, dans lequel il est repris par un conduit 36a 36b de récupération d'une émulsion liquide de lubrification-air. Ce conduit 36a, 36b est équipé d'une pompe 38a, 38b de récupération de liquide de lubrification. La pompe 38a, 38b refoule cette émulsion dans un séparateur 40a, 40b liquide de lubrification-air. Entre la pompe 38a, 38b et le séparateur 40a, 40b, le conduit 36a, 36b traverse un échangeur de refroidissement 42a, 42b. Cet échangeur de refroidissement permet d'abaisser la température du liquide de lubrification, par échange thermique avec le carburant de l'aéronef.The lubrication liquid injected under pressure into each of the lubrication chambers 20a, 20b falls by gravity into the inclined bottom of this chamber, in which it is taken up by a conduit 36a 36b for recovering a lubrication-air liquid emulsion. This conduit 36a, 36b is equipped with a pump 38a, 38b for recovering lubrication liquid. The pump 38a, 38b discharges this emulsion into a separator 40a, 40b lubricating liquid-air. Between the pump 38a, 38b and the separator 40a, 40b, the conduit 36a, 36b passes through a cooling exchanger 42a, 42b. This cooling exchanger makes it possible to lower the temperature of the lubricating liquid, by heat exchange with the fuel of the aircraft.

Le séparateur 40a, 40b liquide de lubrification-air est un dispositif centrifuge, de structure connue, comportant notamment des ailettes ou des masses alvéolées dont la rotation permet d'effectuer la séparation de l'air et du liquide de lubrification, sous l'effet de la force centrifuge. Le liquide de lubrification est repris dans le fond du séparateur 40a, 40b par un conduit 44a, 44b assurant le retour de ce liquide dans le réservoir 26a, 26b. Par ailleurs, l'air s'échappe du séparateur 40a, 40b par un conduit d'échappement central 46a, 46b. Lorsque, pour une raison quelconque, le régime de fonctionnement de l'un ou l'autre des turboréacteurs 10a, 10b tombe en dessous du régime de ralenti, la surpression régnant habituellement dans la région 22a, 22b qui entoure chacune des chambres de lubrification 20a, 20b peut devenir momentanément inférieure à la pression qui règne à l'intérieur de ces chambres. Il se produit alors des fuites de liquide de lubrification à l'extérieur des chambres 20a, 20b, et, par conséquent, une pollution interne du turboréacteur. Dans certains cas, du liquide de lubrification peut aussi se retrouver dans la veine où circule l'air pour le fonctionnement interne de l'aéronef. En outre, une fuite importante peut conduire à un épuisement de la réserve de liquide de lubrification mettant en danger le moteur et l'aéronef. Pour supprimer ce risque, on associe habituellement au circuit de lubrification 24a et 24b de chacun des turboréacteurs 10a et 10b un dispositif permettant de dépressuriser les chambre de lubrification 20a, 20b.The separator 40a, 40b lubrication-air liquid is a centrifugal device, of known structure, comprising in particular fins or honeycomb masses whose rotation allows the separation of air and lubrication liquid, under the effect of centrifugal force. The lubrication liquid is taken up in the bottom of the separator 40a, 40b by a conduit 44a, 44b ensuring the return of this liquid in the reservoir 26a, 26b. Furthermore, air escapes from the separator 40a, 40b through a central exhaust duct 46a, 46b. When, for whatever reason, the operating speed of one or other of the turbojets 10a, 10b falls below the idling speed, the overpressure usually prevailing in the region 22a, 22b which surrounds each of the lubrication chambers 20a , 20b may momentarily become lower than the pressure prevailing inside these chambers. Leakage of lubrication liquid then occurs outside the chambers 20a, 20b, and, consequently, internal pollution of the turbojet engine. In some cases, lubrication liquid can also be found in the vein where air circulates for the internal functioning of the aircraft. In addition, a large leak can lead to the depletion of the supply of lubricating liquid, endangering the engine and the aircraft. To eliminate this risk, the lubrication circuit 24a and 24b of each of the turbojets 10a and 10b are usually associated with a device making it possible to depressurize the lubrication chambers 20a, 20b.

Ce dispositif de dépressurisation comprend tout d'abord, pour chacun des turboréacteurs 10a et 10b, un conduit 48a, 48b de mise à l'air libre de la chambre de lubrification 20a, 20b entourant chacun des paliers de ce turboréacteur. Ce conduit 48a, 48b débouche dans la partie supérieure d'une chambre de lubrification 20a, 20b et relie cette chambre de lubrification à un séparateur 40a, 40b liquide de lubrification-air lui-même prolongé par un conduit d'échappement 46a, 46b.This depressurization device firstly comprises, for each of the turbojets 10a and 10b, a duct 48a, 48b for venting the lubrication chamber 20a, 20b surrounding each of the bearings of this turbojet. This conduit 48a, 48b opens into the upper part of a lubrication chamber 20a, 20b and connects this lubrication chamber to a separator 40a, 40b lubrication-air liquid itself extended by an exhaust conduit 46a, 46b.

D'une façon générale et pour des raisons évidentes d'économie, le séparateur air-lubrifiant 40a, 40b et le conduit d'échappement 46a, 46b seront communs au dispositif de dépressurisation des chambres de lubrification 20a, 20b et au circuit de récupération du lubrifiant par les conduits 36a, 36b et 44a, 44b.In general and for obvious reasons of economy, the air-lubricant separator 40a, 40b and the exhaust duct 46a, 46b will be common to the device for depressurizing the lubrication chambers 20a, 20b and to the circuit for recovering the lubricant through conduits 36a, 36b and 44a, 44b.

Les conduits 48a et 48b relient chaque chambre de lubrification 20a, 20b au séparateur commun 40a, 40b, de la turbomachine 10a, 10b et ils permettent ainsi de maintenir la pression régnant dans chacune des chambre de lubrification 20a, 20b à un niveau proche de la pression atmosphérique. Afin que la pression régnant dans les chambres de lubrification 20a, 20b puisse encore être abaissée lorsque des conditions particulières de fonctionnement de l'un ou l'autre des turboréacteurs 10a et 10b amènent la pression dans la région 22a, 22b à une valeur voisine de la pression atmosphérique, le dispositif de dépressurisation conforme à l'invention comprend de plus, en aval des séparateurs 40a, 40b liquide de lubrification-air, sur le conduit 46a, 46b d'échappement de ce séparateur, une pompe auxiliaire.The conduits 48a and 48b connect each lubrication chamber 20a, 20b to the common separator 40a, 40b, of the turbomachine 10a, 10b and they thus make it possible to maintain the pressure prevailing in each of the lubrication chambers 20a, 20b at a level close to the atmospheric pressure. So that the pressure prevailing in the lubrication chambers 20a, 20b can be lowered further when particular operating conditions of one or the other of the turbojets 10a and 10b bring the pressure in the region 22a, 22b to a value close to atmospheric pressure, the depressurization device according to the invention further comprises, downstream of the separators 40a, 40b lubrication-air liquid, on the exhaust duct 46a, 46b of this separator, an auxiliary pump.

Dans la forme de réalisation illustrée sur les figures 1 et 2, cette pompe auxiliaire est constituée par une trompe à jet 49a, 49b. Cette trompe à jet 49a, 49b comprend un ensemble convergent-divergent 50a, 50b placé dans le conduit 46a, 46b, ainsi qu'une buse 51a, 51b débouchant à proximité de la partie de plus petite section de l'ensemble convergent-divergent et orientée vers l'aval, de façon à entraîner vers l'extérieur l'air sortant du séparateur 40a, 40b par le conduit 46a, 46b.Chacune des buses 51a, 51b des trompes à jet 49a, 49b est reliée à un conduit 52a, 52b d'amenée d'air sous pression (figure 1).In the embodiment illustrated in Figures 1 and 2, this auxiliary pump is constituted by a jet pump 49a, 49b. This jet horn 49a, 49b comprises a convergent-divergent assembly 50a, 50b placed in the duct 46a, 46b, as well as a nozzle 51a, 51b opening out near the part of the smallest section of the convergent-divergent assembly and oriented downstream, so as to entrain outward the air leaving the separator 40a, 40b through the conduit 46a, 46b. Each of the nozzles 51a, 51b of the jet tubes 49a, 49b is connected to a conduit 52a, 52b for supplying pressurized air (Figure 1).

Chacun des conduits 52a et 52b comporte une vanne 54a, 54b normalement fermée lorsque le turboréacteur correspondant se trouve dans des conditions de fonctionnement qui n'entraînent pas de risques de fuite du liquide de lubrification vers l'extérieur des chambres de lubrification 20a, 20b.Each of the conduits 52a and 52b comprises a valve 54a, 54b normally closed when the corresponding turbojet engine is in operating conditions which do not involve any risk of leakage from the lubrication liquid to the outside of the lubrication chambers 20a, 20b.

Dans la forme de réalisation illustrée sur la figure 1, l'extrémité du conduit 52a opposée à la trompe à jet 49a débouche dans le compresseur 56b du turboréacteur 10b et l'extrémité du conduit 52b opposée à la trompe à jet 49b débouche dans le compresseur 56a du turboréacteur 10a. Entre les compresseurs 56a et 56b et les vannes 54a et 54b, les conduits 52a et 52b comportent un tronçon commun 52. En outre, un clapet anti-retour 58a est placé dans la partie du conduit 52a comprise entre le compresseur 56b et le tronçon commun 52 et un clapet anti-retour 58b est placé dans la partie du conduit 52b située entre le compresseur 56a et le tronçon commun 52.In the embodiment illustrated in FIG. 1, the end of the duct 52a opposite the jet horn 49a opens into the compressor 56b of the turbojet engine 10b and the end of the duct 52b opposite the jet horn 49b opens into the compressor 56a of the turbojet engine 10a. Between the compressors 56a and 56b and the valves 54a and 54b, the conduits 52a and 52b have a common section 52. In addition, a non-return valve 58a is placed in the part of the conduit 52a between the compressor 56b and the common section 52 and a non-return valve 58b is placed in the part of the duct 52b located between the compressor 56a and the common section 52.

Dans la forme de réalisation illustrée sur la figure 1, l'ouverture de la vanne 54a ou 54b est commandée automatiquement par un circuit approprié 60 équipant l'aéronef, lorsque les informations fournies à ce circuit par des capteurs équipant le turboréacteur 10a ou 10b font apparaître que le régime de fonctionne- ment de ce dernier est insuffisant pour garantir le confinement du liquide de lubrification à l'intérieur des chambres de lubrification 20a, 20b qui entourent chacun des paliers de ce turboréacteur.In the embodiment illustrated in FIG. 1, the opening of the valve 54a or 54b is automatically controlled by an appropriate circuit 60 fitted to the aircraft, when the information supplied to this circuit by sensors fitted to the turbojet engine 10a or 10b It appears that the operating regime of the latter is insufficient to guarantee the confinement of the lubrication liquid inside the lubrication chambers 20a, 20b which surround each of the bearings of this turbojet engine.

L'ouverture de la vanne 54a se traduit immédiatement par la mise en communication du compresseur 56b du turboréacteur 10b avec la buse d'injection d'air de la trompe à jet 49a. Un effet de pompage de l'air situé dans les chambres de lubrification 20a entourant les paliers 12a du turboréacteur 10a est immédiatement obtenu. Par conséquent, ces chambres sont mises en dépression et tout risque de fuite du liquide de lubrification est évité.The opening of the valve 54a immediately results in the communication of the compressor 56b of the turbojet engine 10b with the air injection nozzle of the jet pump 49a. An air pumping effect located in the lubrication chambers 20a surrounding the bearings 12a of the turbojet engine 10a is immediately obtained. Consequently, these chambers are placed under vacuum and any risk of leakage of the lubrication liquid is avoided.

Le fonctionnement de la partie du dispositif de dépressurisation qui est associé au turboréacteur 10b est totalement identique à celui de la partie de ce circuit associée au turboréacteur 10a. Il est également commandé par l'ouverture de la vanne 54b et se traduit, ici encore, par la création d'une dépression dans les chambres de lubrification 20b qui entourent les paliers 12b du turboréacteur 10b.The operation of the part of the depressurization device which is associated with the turbojet engine 10b is completely identical to that of the part of this circuit associated with the turbojet engine 10a. It is also controlled by the opening of the valve 54b and results, here again, in the creation of a vacuum in the lubrication chambers 20b which surround the bearings 12b of the turbojet engine 10b.

Un deuxième mode de réalisation de l'invention est appliqué à un ensemble de deux ou plusieures turbomachines. Par mesure de clarté, ne sont représentées sur la figure 3, que deux turbomachines 10a et 10b, mais la description qui va suivre s'applique de la même façon à un nombre supérieur de turbomachines.A second embodiment of the invention is applied to a set of two or more turbomachines. For the sake of clarity, only two turbomachines 10a and 10b are shown in FIG. 3, but the description which follows will apply in the same way to a greater number of turbomachines.

Chaque turbomachine étant agencée et raccordée de la même façon aux autres, prenons l'exemple de la machine 10a. Le compresseur de la turbomachine 10a est raccordé au conduit commun 52 par le conduit 53a, ledit conduit 53a étant équipé d'un clapet anti-retour 58a qui n'autorise la circulation de l'air que dans le sens compresseur-conduit commun 52.Each turbomachine being arranged and connected in the same way to the others, let us take the example of the machine 10a. The compressor of the turbomachine 10a is connected to the common duct 52 by the duct 53a, said duct 53a being equipped with a non-return valve 58a which allows the circulation of air only in the direction of the common compressor-duct 52.

Sur les enceintes entourant les paliers de la turbomachine 10a sont raccordés les conduits de mise à l'air libre 48a dont l'autre extrémité débouche sur un deshuileur 40a. L'air épuré issu du deshuileur 40a est amené à l'entrée de la trompe à jet 49a. Cette trompe à jet 49a est alimentée en air pressurisé par un conduit 55a raccordé à son autre extrémité au conduit commun 52. Le conduit 55a comporte un moyen d'obturation 54a normalement fermé et commandé automatiquement par un circuit approprié 60 de l'aéronef.On the enclosures surrounding the bearings of the turbomachine 10a are connected the venting conduits 48a, the other end of which opens onto an oil separator 40a. The purified air from the oil separator 40a is supplied to the inlet of the jet horn 49a. This jet horn 49a is supplied with pressurized air by a duct 55a connected at its other end to the common duct 52. The duct 55a comprises a shutter means 54a normally closed and controlled automatically by an appropriate circuit 60 of the aircraft.

D'autre turbomachines 10 peuvent être agencées et raccordées de la même façon au conduit commun 52 et reçoivent une commande du circuit 60.Other turbomachines 10 can be arranged and connected in the same way to the common duct 52 and receive a command from the circuit 60.

Le fonctionnement est le suivant :The operation is as follows:

Le conduit commun 52 est alimenté en air pressurisé par les compresseurs des turbomachines 10, 10a, 10b qui lui sont connectées, mais il n'y a normalement aucun débit d'air dans le conduit commun 52.The common duct 52 is supplied with pressurized air by the compressors of the turbomachines 10, 10a, 10b which are connected to it, but there is normally no air flow in the common duct 52.

Lorsqu'une turbomachine, par exemple la turbomachine 10a tombe en dessous de son régime de ralenti, cette situation est détectée par le circuit 60 de l'aéronef qui commande alors l'ouverture du moyen d'obturation 54a. L'air préssurisé du conduit 52 en provenance des autres moteurs vient alimenter la trompe à jet 49a par l'intermédiaire du conduit 55a, provoquant ainsi une dépression qui est transmise aux enceintes entourant les paliers du moteur 10a par l'intermédiaire du déshuileur 40a et du conduit 48a.When a turbomachine, for example the turbomachine 10a falls below its idling speed, this situation is detected by the circuit 60 of the aircraft which then controls the opening of the shutter means 54a. The pressurized air in the duct 52 from the other engines feeds the jet horn 49a via the duct 55a, thus causing a vacuum which is transmitted to the enclosures surrounding the bearings of the engine 10a via the oil separator 40a and of conduit 48a.

Les modes de réalisation qui viennent d'être décrits en se référant aux figures 1 à 3 s'appliquent uniquement à des aéronefs multimoteur. Dans le cas plus général de la prévention des fuites du liquide de lubrification hors des chambres de lubrification qui entourent les paliers d'une turbomachine de nature quelconque, il est possible de relier la buse de la trompe à jet placée dans le conduit de mise à l'air libre à une source d'air comprimé extérieure.The embodiments which have just been described with reference to FIGS. 1 to 3 apply only to multi-engine aircraft. In the more general case of preventing the lubrication liquid from leaking out of the lubrication chambers which surround the bearings of a turbomachine of any kind, it is possible to connect the nozzle of the jet pump placed in the delivery pipe. free air to an external compressed air source.

On peut remarquer que la mise en oeuvre de moyens de pompage auxiliaires 49a, 49b sur le dispositif de dépressurisation des chambres de palier 12a, 12b, conformément à l'invention est avantageuse du fait de la présence des conduits de mise à l'air libre 48a, 48b, lesdits conduits permettant en effet de transmettre auxdites chambres 20a, 20b la dépression produite par lesdits moyens de pompage 49a, 49b.It can be noted that the use of auxiliary pumping means 49a, 49b on the depressurization device of the bearing chambers 12a, 12b, in accordance with the invention is advantageous because of the presence of the venting ducts 48a, 48b, said conduits in fact making it possible to transmit to said chambers 20a, 20b the vacuum produced by said pumping means 49a, 49b.

Au contraire, les moyens de pompage 49a, 49b de l'invention n'auraient pas été efficaces sur le conduit de récupération de lubrifiant 36a, 36b, car les pompes de récupération 38a, 38b sont habituellement du type volumétrique, par exemple à engrenages, et elles s'opposeraient à la transmission de la dépression entre les chambres 12a, 12b et l'extérieur.On the contrary, the pumping means 49a, 49b of the invention would not have been effective on the lubricant recovery duct 36a, 36b, since the recovery pumps 38a, 38b are usually of the volumetric type, for example with gears, and they would oppose the transmission of the depression between the chambers 12a, 12b and the exterior.

De plus, et quelque soit leur type, les pompes de récupération 38a, 38b engendrent des variations importantes de pression qui n'auraient pu être compensées par les moyens de pompage 49a, 49b de l'invention.In addition, and whatever their type, the recovery pumps 38a, 38b generate significant variations in pressure which could not have been compensated by the pumping means 49a, 49b of the invention.

Claims (9)

Dispositif de dépressurisation des chambres de lubrification (20a) entourant chacun des paliers (12a) d'une turbomachine (10a), ledit dispositif comportant des conduits dits de mise à l'air libre (48a) mettant en communication lesdites chambres (20a) avec l'extérieur, lesdites chambres (20a) étant alimentées en liquide de lubrification sous pression par un circuit d'alimentation (24a), caractérisé en ce que le dispositif de dépressurisation comporte aussi des moyens de pompage auxiliaires (49a), lesdits moyens de pompage (49a) étant alimentés par une source de pression extérieure (56b) constituée par le compresseur d'une seconde turbomachine (10b)Device for depressurizing the lubrication chambers (20a) surrounding each of the bearings (12a) of a turbomachine (10a), said device comprising so-called vent pipes (48a) putting said chambers (20a) into communication with the exterior, said chambers (20a) being supplied with pressurized lubricating liquid by a supply circuit (24a), characterized in that the depressurization device also comprises auxiliary pumping means (49a), said pumping means (49a) being supplied by an external pressure source (56b) constituted by the compressor of a second turbomachine (10b) Dispositif de dépressurisation conforme à la revendication 1, caractérisé en ce que le moyen de pompage auxiliaire (49a) est placé dans ledit conduit de mise à l'air libre (48a).A depressurization device according to claim 1, characterized in that the auxiliary pumping means (49a) is placed in said vent pipe (48a). Dispositif de dépressurisation conforme à la revendication 1, ledit dispositif de dépressurisation comportant un conduit de mise à l'air libre (48a) débouchant dans un séparateur air-lubrifiant (40a), ledit séparateur (40a) comportant lui-même un circuit d'échappement de l'air (46a), caractérisé en ce que le moyen de pompage auxiliaire (49a) est placé dans ledit conduit d'échappement (46a).A depressurization device according to claim 1, said depressurization device comprising a vent pipe (48a) opening into an air-lubricating separator (40a), said separator (40a) itself comprising a circuit for air exhaust (46a), characterized in that the auxiliary pumping means (49a) is placed in said exhaust duct (46a). Dispositif de dépressurisation conforme à l'une quelconque des revendications 1 à 3, caractérisé en ce que le moyen de pompage auxiliaire (49a) est une trompe à jet.A depressurization device according to any one of claims 1 to 3, characterized in that the auxiliary pumping means (49a) is a jet pump. Dispositif de dépressurisation conforme à l'une quelconque des revendications 1 à 4, caractérisé en ce qu'il comporte aussi un moyen de commande des moyens de pompage auxiliaires (49a).Depressurization device according to any one of claims 1 to 4, characterized in that it also comprises means for controlling the auxiliary pumping means (49a). Dispositif de dépressurisation conforme à la revendication 5, caractérisé en ce que le moyen de commande est une vanne (54a) disposée sur le conduit (52a) d'amenée d'air sous pression.Depressurization device according to claim 5, characterized in that the control means is a valve (54a) disposed on the duct (52a) for supplying pressurized air. Dispositif de dépressurisation conforme à la revendication 6, caractérisé en ce que la vanne (54a) est normalement fermée, et en ce qu'elle est ouverte lorsque le régime de la turbomachine (10a) est insuffisant.A depressurization device according to claim 6, characterized in that the valve (54a) is normally closed, and in that it is open when the speed of the turbomachine (10a) is insufficient. Dispositif de dépressurisation conforme à l'une quelconque des revendications 1 à 7, caractérisé en ce que le dispositif de dépressurisation de la seconde turbomachine (10b) comporte des moyens de pompage auxiliaires (49b), lesdits moyens de pompage auxiliaires (49b) étant alimentés par une source de pression extérieure (56a) constituée par le compresseur de la première turbomachine (10a).Depressurization device according to any one of Claims 1 to 7, characterized in that the depressurization device of the second turbomachine (10b) comprises auxiliary pumping means (49b), said auxiliary pumping means (49b) being supplied by an external pressure source (56a) constituted by the compressor of the first turbomachine (10a). Dispositif de dépressurisation conforme à la revendication 8, caractérisé en ce que les conduits d'amenée d'air sous pression (52a) et (52b) comportent un tronçon commun (52), un clapet anti-retour (58a) et (58b) étant placé entre chacun des compresseurs et ce tronçon respectivement sur les conduits (52a) et (52b).Depressurization device according to claim 8, characterized in that the pressurized air supply ducts (52a) and (52b) have a common section (52), a non-return valve (58a) and (58b) being placed between each of the compressors and this section respectively on the conduits (52a) and (52b).
EP94401145A 1993-05-25 1994-05-25 Depressurization device for bearing lubrication chambers Expired - Lifetime EP0626503B1 (en)

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FR9306206 1993-05-25
FR9306206A FR2705733B1 (en) 1993-05-25 1993-05-25 Device for depressurizing the lubrication chambers surrounding the bearings of a turbomachine.

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EP0626503A1 true EP0626503A1 (en) 1994-11-30
EP0626503B1 EP0626503B1 (en) 1996-07-03

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EP (1) EP0626503B1 (en)
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WO2014060656A1 (en) * 2012-10-19 2014-04-24 Snecma Jet pump for depressurizing lubrication chambers of a turbomachine, having independent double injectors
US9790856B2 (en) 2012-10-19 2017-10-17 Snecma Jet pump for depressurizing lubrication chambers of a turbomachine, having independent double injectors
US9644487B2 (en) 2013-01-30 2017-05-09 Snecma Fixed turbine engine receiver part comprising an assembly for holding ancillary systems in position inside a fixed hollow shaft
EP2781704A1 (en) * 2013-03-01 2014-09-24 Rolls-Royce plc Chamber fluid removal system
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FR3034752A1 (en) * 2015-04-10 2016-10-14 Snecma DEVICE FOR DEDUCTION OF AN OIL ENCLOSURE BY AN AIRCRAFT AIR SUPPLY CIRCUIT
CN109211581B (en) * 2017-07-06 2021-08-17 腓特烈斯港齿轮工厂股份公司 Method for detecting the leak tightness of a main pump and corresponding device
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WO2020008156A1 (en) * 2018-07-05 2020-01-09 Safran Part for a turbomachine centrifugal breather having a filtering mesh
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WO2020008153A1 (en) 2018-07-05 2020-01-09 Safran Helicopter Engines Integral centrifugal degasser
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FR3096402A1 (en) * 2019-05-24 2020-11-27 Safran Part for turbomachine centrifugal degasser with filtering mesh
EP3951139A1 (en) * 2020-08-03 2022-02-09 ABB Schweiz AG Shaft bearing assembly having a pressure reduction device and method of reducing a pressure inside a bearing housing supporting a shaft
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Also Published As

Publication number Publication date
DE69400274D1 (en) 1996-08-08
US5429208A (en) 1995-07-04
EP0626503B1 (en) 1996-07-03
DE69400274T2 (en) 1997-01-30
FR2705733B1 (en) 1995-06-30
FR2705733A1 (en) 1994-12-02

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