LUBRICATION TANK FOR AN AIRCRAFT TURBOMACHINE OR SELF-PROPELLED AIRCRAFT

Description

Technical field of the invention

[0001] The technical field of the present invention is that of lubrication tanks for turbomachines of aircraft or self-propelled aerial vehicles, and more particularly that of tanks which can be subjected to accelerations occurring in a direction and a sense different from the gravitational forces. By lubrication tank is meant a tank capable of containing a lubricating liquid for a lubrication system of the turbomachine. Technical background

[0002] Conventionally, turbomachine lubrication systems include a reservoir of lubricant, such as oil, for their supply. The reservoir typically comprises a casing arranged at a low point of the turbomachine, in a direction and a sense of the gravitational force, and in this casing, a so-called suction strainer, that is to say arranged at the inlet of a device intended to suck the oil.

[0003] In most turbomachines, the oil return is forced by pressurized air. The degassing system, i.e. deaeration, of turbomachine oil tanks generally consists of a rotating deaerator, which is typically located in the center of the tank and which allows excess air to be evacuated from the oil while keeping the oil in the tank and thus avoiding oil loss during operation.

[0004] Document FR 2.687.329-B1 describes and represents a rotating degasser comprising a bowl rotating around an axis and comprising at a first end radial blades onto which the air-laden oil is projected and which communicates at a second end with an oil sump.

[0005] In the normal operating case of the turbomachine, that is to say with a zero trim and the lubrication system subject only to gravity, the oil is located in the oil sump. The oil is sucked into a pump in the lubrication circuit through a suction strainer located at the bottom of the oil sump.

[0006] It is known that aircraft and self-propelled aerial vehicles can experience lateral and / or upward accelerations, corresponding to maneuvers or the crossing of turbulence. The duration of these accelerations is generally limited in time, but the occurrences of these accelerations are multiple.

[0007] Reservoirs have been proposed to ensure the oil supply to the pump when it is subjected to various accelerations. Such reservoirs consist of an enclosure, at least part of which forms an oil sump and receives a feed strainer for the lubrication circuit of the turbomachine. The oil sump may have a suitable shape so that, in the event of lateral acceleration, the suction strainer remains immersed in the oil and thus guarantees the supply of the oil pump. In addition, the rotating degasser is generally located in a central position above the oil sump to prevent the surface of the oil from coming into contact with the rotating degasser, so as not to reduce its efficiency.

[0008] Such tanks may also include a strainer located at a high point in the enclosure to suck up the oil in the event of the tank overturning, or in the event that the oil is subjected to strong vertical acceleration upwards. A valve system, mechanical or electrically controlled, allows the strainer, which is immersed in the oil, to be closed to prevent the introduction of air into the lubrication circuit. The valve may, for example, be a ball that moves with gravity or an electric actuator controlled by a gravity sensor.

[0009] The ability of such lubrication systems to withstand lateral accelerations is therefore conditioned by the depth of the reservoir's oil sump, so that a sufficient quantity of oil is present to ensure the immersion of the strainer. However, certain constraints of integration of the reservoir in its environment do not allow for a sufficiently deep oil sump, which severely limits the reservoir's ability to withstand lateral accelerations.

[0010] Furthermore, when the turbomachine is subjected to purely lateral accelerations, the lubricant may be confined in the enclosure between the two strainers without either of them being submerged. In this case, the only solution is to add additional strainers, and as many corresponding valves or actuators, which increases the complexity of such a reservoir.

[0011] Another disadvantage of such a tank is that it requires a power take-off to operate the rotating deaerator. However, the turbomachine cannot always be equipped with such a power take-off. In this case, the use of a static deaeration device becomes imperative.

[0012] Furthermore, such a tank generally includes at least one vent intended to evacuate the air previously separated from the oil in said tank. This vent is generally placed in an upper part of the tank. It is important that this vent cannot be submerged by lubricating oil in the event of the tank being overturned, in order to prevent a significant quantity of oil from being lost, which would harm the overall operation of the lubrication system, as is the case in GB-1.339825-A.

[0013] To overcome this drawback, it was proposed in document US-2011 / 0315484-A1 to equip a tank with two vertically opposed elbow vent pipes, each having an inlet above the oil level and an outlet below the oil level. In the event of the tank being overturned, venting is carried out via one pipe or the other. This design does not take into account the intermediate positions of the tank and may nevertheless allow oil to be evacuated via these pipes, or even a blockage of these pipes by the oil.

[0014] Similarly, a static degassing device is usually placed at the top of the tank with the outlet pointing downwards. Therefore, if the tank is overturned, there is a high risk of the degassing device being submerged through its outlet, which would impair its effectiveness. It is therefore important that the outlet of the degassing device cannot be submerged. Summary of the invention

[0015] The invention overcomes these drawbacks by proposing a reservoir configured to prevent submersion of the vents and the degassing device, regardless of the acceleration to which the lubricant is subjected.

[0016] For this purpose, the invention proposes a lubrication reservoir for a turbomachine of an aircraft or self-propelled aerial vehicle, comprising an enclosure containing a lubricant, said enclosure comprising, with reference to a direction and a sense of the gravitational force: in a lower part of said enclosure, a suction strainer which is located in the vicinity of a bottom of said enclosure and to which a supply line of a lubrication circuit of the turbomachine is capable of being connected, in an upper part of said enclosure, at least one degassing device capable of being supplied with air-laden lubricant by a lubricant return line of the turbomachine and of separating the lubricant from the air in said enclosure, in the upper part of said enclosure, at least one vent configured to evacuate the air separated from the lubricant to the outside of said enclosure, characterized in that it comprises, to allow the strainer to be fed and to prevent the intrusion of lubricant into said at least one vent when the lubricant is subjected to forces produced by lateral accelerations and / or negative gravity: at least one first partition which separates the lower part from the upper part and which is provided with passages capable of allowing a flow of the lubricant between the lower part and the upper part, in the upper part, two vents arranged on either side of a vertical median plane of the enclosure, two vent pipes, which have upper outlet ends communicating with the vents and which extend in the upper part to lower inlet ends opening into the tank below the degassing device, each pipe having an elbow and having said elbow and its upper outlet end located on the other side of said median plane relative to its lower inlet end.

[0017] According to other characteristics of the tank: the lower part is divided into a central compartment and two lateral compartments by two second substantially vertical partitions arranged on either side of the vertical median plane, which extend substantially between a bottom of the lower part of the enclosure and a closed upper end of said lower part of the enclosure, said central compartment receiving the strainer, and the lower part comprising lubricant passages between the central compartment and the lateral compartments, said at least one first partition comprises, at right angles to each lateral compartment, a tube which extends from said first partition, which plunges into said lateral compartment, and which opens out in the vicinity of the bottom of the enclosure, the degassing device is a static degassing device comprising a housing comprising an inlet supplied with air-laden lubricant from the lubricant return pipe, an outlet communicating with the enclosure,and a porous metallic element arranged between said inlet and outlet, the elbow of each vent duct is arranged transversely, relative to the median plane, at a distance greater than a transverse distance separating its upper outlet end from said median plane, the elbow forming substantially an obtuse angle, the degassing device is arranged transversely between the two vents, the tank has a substantially annular tubular shape configured to surround a cylindrical casing of the turbomachine, the annular tank delimits a circular neck and it comprises two first partitions arranged in the tank on either side of said neck, a section of each vent duct between its lower inlet end and its elbow matches the neck of the tank, ,

[0018] The invention also relates to an aircraft turbomachine comprising at least one lubricating oil reservoir and at least one air inlet casing of said turbomachine, characterized in that the reservoir is a reservoir of the type described previously and in that it surrounds said air inlet casing. Brief description of the figures

[0019] Other characteristics and advantages of the invention will appear during the reading of the detailed description which follows for the understanding of which reference will be made to the appended drawings in which: [ Fig. 1 ] there figure 1 is a schematic view of a fixing circuit according to a prior state of the art comprising a reservoir shown subjected to weightlessness and with a zero attitude; [ Fig.2 ] there figure 2 is a view analogous to the figure 1 with the tank shown subjected to lateral acceleration; [ Fig. 3 ] there figure 3 is a view analogous to the figure 1 with the tank shown subjected to a downward vertical acceleration producing negative gravity; [ Fig. 4 ] there figure 4 is a schematic view of a tank according to the invention shown subjected to gravity and with zero attitude; [ Fig. 5 ] there Figure 5 is a view analogous to the figure 4 with the tank shown subjected to lateral acceleration; [ Fig. 6 ] there figure 6 is a view analogous to the figure 4 with the tank shown subjected to a downward vertical acceleration producing negative gravity; [ Fig. 7 ] there figure 7 is a view analogous to the figure 4 with the tank shown subjected to a lateral acceleration combined with a downward vertical acceleration producing negative gravity; Detailed description of the invention

[0020] It has been represented on the figures 1 to 3a lubrication circuit 10 for a turbomachine of an aircraft or self-propelled aerial vehicle.

[0021] As is known, the circuit 10 is intended to ensure the lubrication of a turbomachine 12.

[0022] The circuit 10 essentially comprises a reservoir 14 which supplies, via a first supply line 16, a lubrication pump 18 which itself supplies the turbomachine 12 via a second supply line 20.

[0023] The circuit 10 is a closed-circuit lubricant circuit, such that a return pipe 22 ensures a return of the lubricant from the turbomachine 12 to the tank 14 in order to allow its recycling and reuse in the circuit 10.

[0024] The first supply line 16 is connected at a low point 22 of a casing 24 formed in an enclosure 26 of the tank 14 to a so-called suction strainer (not shown), which in a normal state of the tank 14 as shown in figure 1 , that is to say at zero attitude of the tank 14 and in the absence of acceleration other than that of the forces of gravity, is immersed in the lubricant 28.

[0025] The lubricant coming from the return pipe 22, which has passed through different pressure chambers inside the turbomachine 12, is generally loaded with air bubbles and it is necessary for this to be deaerated by means of a deaerator or degassing device 30.

[0026] Such a degassing device 30 is widely known in the art and essentially comprises an element 32 rotating about an axis X, as illustrated by the arrow in the figures 1 to 3, which separates the lubricant from the air and evacuates the air, represented by an arrow A.

[0027] It is known to equip such a reservoir 14 with means for ensuring the continuous supply of lubricant to the first pipe 16.

[0028] For this, the reservoir 14 is equipped with a second lubricant suction strainer (not shown) arranged at a high point 34 of the enclosure 26 opposite the casing 24.

[0029] The first supply line 16 is also connected to the strainer of this high point 34 via an inversion device 36 which makes it possible to select, between the high point 22 and the high point 34, the source of lubricant supply to the first line 16 as a function of the position of the lubricant in the enclosure 26.

[0030] The reversing device 36 may consist, as shown in the figures 1 to 3, into a valve, ball valve, or an electric actuator controlled by a gravity sensor.

[0031] When the turbomachine is in the absence of lateral or longitudinal acceleration, that is to say when it is subjected only to gravitational acceleration, the force γ which results from the overall acceleration undergone by the turbomachine is entirely gravitational, as represented by the vertical arrow of the figure 1 The lubricant 28 contained in the casing 24 is sucked through the strainer at the low point 22 towards the pump 18, as shown in figure 1 .

[0032] Generally, the casing 24 is sized and has shapes provided so that, when the turbomachine is subjected to a lateral acceleration combined with the gravitational acceleration which produces a resultant force γ as represented in the figure 2, the configuration of the casing 24 allows the low point 22 to be kept immersed in the lubricant 28, which then partially leaves the casing 24 and spreads into the enclosure 26.

[0033] In the event of the tank 14 overturning, or when it is subjected to a vertical acceleration in the opposite direction to gravity, as represented by the arrow on the figure 3 symbolizing the direction of the resultant force γ, the lubricant is no longer present in the casing 24 but occupies the opposite part of the enclosure 26 and the high point 34 is then immersed in the lubricant 28. The reversing device 36 is then actuated to supply the first pipe 16 from the high point 34.

[0034] This configuration makes it possible to partially avoid the interruption of the lubricant supply to the first pipe 16. However, it has numerous drawbacks.

[0035] The capacity of the reservoir 14 to support lateral accelerations is conditioned by the depth and the shapes of the oil sump 24, in order to ensure that a sufficient quantity of lubricant is present to ensure the immersion of the strainer of the low point 22. However, certain constraints of integration of the reservoir 14 in its environment do not allow for a sufficiently deep oil sump 24, which greatly limits the capacity of the reservoir 14 to support lateral accelerations.

[0036] Furthermore, when the turbomachine 12 is subjected to purely lateral accelerations, the lubricant 28 may find itself confined in an intermediate part of the enclosure 26 between the two strainers at the low 22 and high 34 points without either of these strainers being immersed in the lubricant 28. In this case, the only solution to avoid the interruption of the lubricant supply consists of adding additional strainers on the side walls of the enclosure 26, and as many corresponding valves or actuators, which increases the complexity of such a reservoir 14.

[0037] Another disadvantage of such a tank 14 is that it requires a power take-off to actuate the rotating degassing device 30. However, depending on the type of turbomachine 12, the turbomachine 12 cannot always be equipped with such a power take-off. In this case, the use of a static degassing device becomes imperative.

[0038] Furthermore, the evacuation of the air separated from the oil is here carried out by means of a vent passing through the rotating degassing device 30. In the case where the lateral acceleration to which the lubricant 28 is subjected causes it to submerge the rotating degassing device 30, the lubricant 28 may be caused to leave the enclosure 26 and this loss of lubricant may be detrimental to the proper functioning of the lubrication circuit 10.

[0039] The invention overcomes this drawback by proposing a reservoir 14 preventing breaks in the oil supply and submersion of its vent(s). Such a reservoir 14 has been shown in figures 4 to 7 .

[0040] The lubrication reservoir 14 according to the invention comprises, as previously, an enclosure 26 receiving a lubricant 28. This reservoir 14 comprises, with reference to a direction and a sense of the gravitational force, that is to say from the top to the bottom of the figure 4, in a lower part 38 of the enclosure 26, a suction strainer 40 which is located in the vicinity of a bottom 41 of the enclosure 26. To this strainer 40 is likely to be connected a supply pipe 16 of the lubrication circuit of the turbomachine supplying a pump 18.

[0041] In an upper part 44 of the enclosure 26, the reservoir 14 comprises, as previously, at least one degassing device 30 capable of being supplied with air-laden lubricant by a lubricant return pipe 22 from the turbomachine in order to separate the lubricant from the air in the enclosure 26.

[0042] In the upper portion of the enclosure 26, the reservoir 14 comprises at least one vent 42 configured to evacuate the air separated from the lubricant outside the enclosure 26.

[0043] In accordance with the invention, the reservoir 14 comprises, to allow the strainer 40 to be supplied and to prevent the intrusion of lubricant 28 into the vent 42 when the lubricant 28 is subjected to accelerations producing lateral forces or vertical accelerations γ in the opposite direction to gravity, as shown in figures 5 to 7 , at least a first partition 46 which separates the lower part 38 from the upper part 44 and which comprises passages 48. These passages 48 are capable of slowing down the flow of the lubricant when it passes through the first partition 46 having been subjected to a lateral and / or vertical force γ in the opposite direction to gravity, as shown in figures 5 to 7The passages 48, which in normal operation allow participation in the return of the lubricant separated from the air from the upper part 44 to the lower part 38, allow lubricant to pass only at a reduced flow rate, which guarantees the presence of lubricant 28 around the strainer 40 in all positions of the reservoir 14.

[0044] The passages 48 can for this purpose be produced in the form of calibrated holes or orifices formed in the first partition 46. They can also consist of clearances formed between all or part of the edges of the first partition 46 and an adjacent wall of the enclosure 26. These clearances are calibrated and delimit between the first partition 46 and the adjacent wall lubricant passage windows which allow lubricant to pass only at a reduced flow rate.

[0045] Thus, when the tank 14 is subjected to an acceleration which produces a resultant force γ having a vertical component oriented upwards as shown in figures 5 to 7 , there remains sufficient lubricant 28 around the strainer 40 to ensure the supply of the lubrication circuit.

[0046] The tank 14 also comprises in the upper part 44, two vents 42 arranged on either side of a vertical median plane P of the enclosure 26.

[0047] Advantageously, the tank 14 also comprises two vent pipes 50, which comprise in the upper part 44 upper outlet ends 52 communicating with the vents 42. These vent pipes 50 extend in the upper part 44 to lower inlet ends 54 free from these pipes 50, which open into the tank 14 below the degassing device 30.

[0048] This configuration makes it possible in particular to prevent, in the event of the tank 14 overturning, the lower inlet ends 54 of the pipes 50 from being submerged by the lubricant 28, as shown in figure 6 , which allows ventilation of the reservoir 14 without risk of loss of the lubricant 28.

[0049] Advantageously, each pipe 50 comprises an elbow 56. Each elbow 56 and the upper outlet end 52 of the vent pipe 50 are located on the other side of the median plane P relative to its lower free inlet end 54 of the same pipe 50.

[0050] This configuration is particularly advantageous, because when the lubricant 28 is subjected to an acceleration having a lateral component causing the accumulation of the lubricant 28 on one side of the enclosure 26 as shown in figure 7, it is thus guaranteed that the venting of the reservoir 26 through the vent 42 which is located on the side of the lubricant accumulation 28 is nevertheless ensured since the free end 54 of the vent pipe 50 is located on the opposite side.

[0051] These characteristics correspond to a basic configuration of the 14 tank which can however be improved.

[0052] Thus advantageously, the lower part 38 is divided into a central compartment 56 and two lateral compartments 58 by two second substantially vertical partitions 60 arranged on either side of the vertical median plane P. These second partitions 60 extend substantially vertically between the bottom 41 of the lower part 38 of the enclosure 26 and a closed upper end of this lower part 38 of the enclosure 26.

[0053] In the specific case shown here, the reservoir 14 has a substantially annular tubular shape configured to surround a cylindrical casing of a turbomachine, for example an air inlet casing of the turbomachine. The annular reservoir 14 therefore delimits a circular neck 62, which may be formed by this air inlet casing, and the closed upper end of the lower part 38 of the enclosure 26 is closed by the circular neck 62 and the first two partitions 46 which form a continuity.

[0054] The first two partitions 46 are here preferably arranged in the reservoir 26 on either side of the neck 62 in order to guarantee an adequate volume of lubricant 28.

[0055] It will be understood that the shape of the reservoir 14 is not limiting of the invention here and that the reservoir could not have an annular shape and be without a neck 62. In this case, the reservoir 14 would only have a single first partition 46 which would extend transversely along the entire width of the reservoir 14 and would close the entire upper end of the lower part 38 of the enclosure 26.

[0056] The lower part 38 is divided so that the central compartment 56 and the two compartments 58 which are arranged on either side of the central compartment 58 can exchange with a reduced flow rate of the lubricant 28 with the central compartment 56.

[0057] For this purpose, the lower part 38 has calibrated lubricant passages 64 allowing the passage of lubricant between the central compartment 56 and the lateral compartments 58.

[0058] These passages 64 may be arranged, by way of example and in a non-limiting manner of the invention, at the upper and lower ends of the second partitions 60.

[0059] Alternatively, the upper and lower ends of the second partitions 60 could be joined with the neck 62 and the bottom 41 of the enclosure 26 and the passages could be delimited between the reservoir and axial ends of the second partitions 60.

[0060] The role of these passages 64 is twofold. They allow, on the one hand, to ensure the return of the lubricant 28 freed from the air from the upper part 44 to the central compartment 56 after having passed through the lateral compartments 58, and on the other hand, to limit the losses of lubricant 28 from the central compartment 56 to the compartments 58 when the reservoir is subjected to forces γ of vertical orientation in the opposite direction to gravity or lateral as shown in figures 5 to 7. Indeed, the interposition of the lateral compartments 58 between the central compartment 56 and the upper part 44 forms baffles capable of slowing the flow of the lubricant 28.

[0061] Advantageously, whatever the shape of the tank 14, each first partition 46 comprises at right angles to each lateral compartment 58 a tube 66 which extends from this first partition 46, which plunges into the lateral compartment 58, and which opens out in the vicinity of the bottom 41 of the enclosure 26. In the case which has been represented here, the tank 14 therefore comprises two tubes 66, i.e. one tube 66 at right angles to each lateral compartment 58.

[0062] The role of each tube 66 is to allow the return of the lubricant 28 separated by the degassing device 30 while preventing the passage of lubricant from the lateral compartments 58 to the upper part 44 of the enclosure 26 in the event of overturning, since the free end of the tubes 66 is then above the level of the lubricant 28 in the lateral compartments 58 as shown in figures 6 And 7 .

[0063] Another particularly advantageous configuration of the invention is that the degassing device 30 is a static degassing device which does not require any movement on the turbomachine which is supplied by the reservoir 14. For this purpose, the degassing device 30 comprises a housing 68 comprising an inlet 70 supplied with air-laden lubricant from the lubricant return pipe 22, an outlet 72 communicating with the enclosure 26, and a porous metal element 74 arranged between these inlets 70 and outlets 72.

[0064] By way of example, and in a non-limiting manner of the invention, the metal element 74 may be made of a metal foam. The degassing device 30 is here arranged transversely between the two vents 42.

[0065] Advantageously, to absolutely avoid the intrusion of lubricant 28 into the vent ducts 50, the elbow 56 of each vent duct 50 is arranged transversely, relative to the median plane P, at a distance D greater than a transverse distance d separating its upper outlet end 52 from said median plane P. In this configuration, the elbow 56 substantially forms an obtuse angle in the shape of a hairpin which slows down any passage of the lubricant towards the vents 42.

[0066] In the annular tank configuration 14 which has been shown here, a section 76 of each vent conduit 50 between its lower free inlet end 54 and its elbow 56 fits the neck 62 of the tank 14.

[0067] The particular shape of the annular reservoir 14 which has been shown here is particularly applicable to an arrangement of the reservoir 14 around a turbomachine comprising an air inlet casing (not shown) which is by definition a cold zone of the turbomachine. Thus the neck 62 provides an exchange surface with the air inlet casing of the turbomachine, which allows the cooling of the reservoir 14 and consequently that of all the lubricant 28.

[0068] It should be noted that the neck 62 of the tank 14 could be made directly from the casing of the turbomachine.

[0069] It may also be envisaged that the neck 62 is provided inside the enclosure 26 with exchange surfaces such as fins allowing the interior of the enclosure 26 to be cooled.

[0070] The invention therefore makes it possible to significantly improve the performance of a lubrication reservoir comprising a degassing device.

Claims

1. A lubrication reservoir (14) for a turbine engine for an aircraft or self-propelled flying machine, comprising an enclosure (26) containing a lubricant (28), said enclosure (26) comprising, with reference to a direction and an orientation of the gravitational force: - in a lower part (38) of said enclosure (26), a suction strainer (40) which is located in the vicinity of a bottom (41) of said enclosure (26) and to which a supply duct (16) of a lubrication circuit of the turbine engine can be connected, - in an upper part (44) of said enclosure (26), at least one degassing device (30) capable of being supplied with air-laden lubricant (28) via a lubricant return duct (22) from the turbine engine and of separating the lubricant from the air in said enclosure (26), - in the upper part (44) of said enclosure (26), at least one vent (42) configured to evacuate the air separated from the lubricant outside said enclosure (26), characterised in that it comprises, to allow the strainer (40) to be supplied and to prevent the intrusion of lubricant (28) into said at least one vent (42) when the lubricant is subjected to forces (γ) produced by lateral accelerations and / or a negative gravity: - at least one first partition (46) which separates the lower part (38) from the upper part (44) and which is equipped with passages (48) capable of allowing the lubricant (28) to flow between the lower part (38) and the upper part (44), - in the upper part (44), two vents (42) arranged on either side of a vertical median plane (P) of the enclosure (26), - two vent pipes (50), which comprise upper outlet ends (52) communicating with the vents (42) and which extend in the upper part (44) as far as lower inlet ends (54) opening into the reservoir (14) below the degassing device (30), each pipe (50) comprising a bend (56) and having said bend (56) and its upper outlet end (52) located on the other side of said median plane (P) relative to its lower inlet end (54).

2. The reservoir (14) according to the preceding claim, characterised in that the lower part (38) is divided into a central compartment (56) and two lateral compartments (58) by two second substantially vertical partitions (60) arranged on either side of the vertical median plane (P), which extend substantially between a bottom (41) of the lower part of the enclosure (44) and a closed upper end of said lower part (38) of the enclosure (26), said central compartment (56) receiving the strainer, and the lower part (38) comprising lubricant passages between the central compartment (56) and the lateral compartments (58).

3. The reservoir (14) according to the preceding claim, characterised in that said at least one first partition (46) comprises, in line with each lateral compartment (58), a tube (66) which extends from said first partition (46), which dips into said lateral compartment (58), and which opens out in the vicinity of the bottom (41) of the enclosure (26).

4. The reservoir (14) according to one of the preceding claims, characterised in that the degassing device (30) is a static degassing device comprising a housing (68) comprising an inlet (70) supplied with air-laden lubricant from the lubricant return duct, an outlet (72) communicating with the enclosure (44), and a porous metallic element (74) arranged between said inlet and outlet.

5. The reservoir (14) according to one of the preceding claims, characterised in that the bend (56) of each vent duct (50) is arranged transversely, with respect to the median plane (P), at a distance (D) greater than a transverse distance (d) separating its upper outlet end (52) from said median plane (P), the bend (56) forming substantially an obtuse angle.

6. The reservoir (14) according to one of the preceding claims, characterised in that the degassing device (30) is arranged transversely between the two vents (42).

7. The reservoir (14) according to one of the preceding claims, characterised in that it has a substantially annular tubular shape configured to surround a cylindrical casing of the turbine engine.

8. The reservoir (14) according to the preceding claim, characterised in that the annular reservoir defines a circular neck (62) and in that it comprises two first partitions (46) arranged in the reservoir on either side of said neck (62).

9. The reservoir (14) according to the preceding claim, characterised in that a stretch (76) of each vent duct (50) between its lower inlet end (54) and its bend (56) matches the neck (62) of the reservoir.

10. A turbine engine for an aircraft or self-propelled flying machine, comprising at least one lubricating oil reservoir and at least one air inlet casing of said turbine engine, characterised in that the reservoir (14) is a reservoir according to one of claims 7 to 9 and in that it surrounds said air inlet casing.