Degassing outlet for an aircraft turbomachine bearing enclosure and its method of use
The degassing outlet with a stator-type fluidic chamber and centrifugal separation mechanism addresses oil consumption and pressure losses in aircraft turbomachine bearings by passively separating oil, enhancing sealing and thrust performance.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2024-05-24
- Publication Date
- 2026-04-17
AI Technical Summary
Existing aircraft turbomachine bearing enclosures face issues with oil consumption due to oil droplets expelled through vent tubes, leading to increased power draw and pressure losses, which compromise the sealing of the bearing housing.
A degassing outlet with a stator-type fluidic chamber and centrifugal separation mechanism that passively separates oil from air without requiring power, positioned at the outlet of the bearing housing to reduce oil conveyance and pressure losses.
The solution effectively reduces oil consumption and pressure losses, maintaining better sealing and preserving thrust performance by integrating a passive oil separator that does not draw power from the shaft, with reduced maintenance costs.
Smart Images
Figure 00000014_0000 
Figure 00000014_0001 
Figure 00000015_0000
Abstract
Description
Title of the invention: Degassing outlet for an aircraft turbomachine bearing housing and its method of use. Technical field
[0001] The present invention relates to the field of aircraft turbomachinery and more specifically aims at a degassing outlet for an aircraft turbomachine bearing enclosure.
[0002] In a known manner, an aircraft turbomachine extends along a longitudinal axis and propels the aircraft by means of an airflow circulating from front to back within the turbomachine during a thrust phase. The aircraft turbomachine comprises, from front to back, one or more compressors, a combustion chamber, and one or more turbines. Each turbine is rotationally connected to a compressor via a shaft extending along the longitudinal axis. The twin-spool aircraft turbomachine typically comprises a low-pressure shaft, connecting a low-pressure compressor and a low-pressure turbine, and a high-pressure shaft, surrounding the low-pressure shaft and connecting a high-pressure turbine and a high-pressure compressor.
[0003] In practice, the low-pressure shaft and the high-pressure shaft are supported at the front and rear by bearings, for example, ball or roller bearings, which must be lubricated and cooled. It is common practice to house the bearings in enclosures to contain the oil. The enclosure is usually filled with an oil mist resulting from the significant contact forces at the bearings.
[0004] In a known manner, each bearing housing comprises a stator wall extending around the rotating shaft and the bearing, as well as seals between the stator wall and the rotating shaft, for example, one at the front and one at the rear. The oil is supplied by a feed line and discharged by gravity at the bottom of the housing. The rotor-stator interfaces, typically sealed by means of gaskets, are generally pressurized with compressed air, notably drawn from the compressor, in order to confine the oil within the bearing housing. For a so-called degassed housing, the air laden with suspended oil droplets is discharged from the top of the housing into a degassing tube.
[0005] In practice, the oil discharged by gravity at the bottom of the enclosure is reinjected into the supply line after passing through an oil deaerator that removes any air bubbles present. The oil consumption of the aircraft turbomachine is thus mainly caused by oil droplets expelled to the outside through the vent tube. To reduce oil consumption and thus reduce the size of the oil reservoir, it is known to mount an air deaerator on the vent tube. which is driven in rotation by a shaft of the aircraft turbomachine to separate the oil droplets by centrifugal effect. The oil separator is typically mounted on the accessory gearbox (AGB) located in the nacelle surrounding the aircraft turbomachine.
[0006] However, such an air oil separator has the disadvantage of drawing some of the power from the aircraft turbomachine shaft and increasing the required length of vent tube piping. Furthermore, the oil droplets conveyed to the oil separator generate pressure drops in the vent tube, which undesirably reduce the sealing of the bearing housing.
[0007] The invention thus aims to eliminate at least some of these drawbacks. PRESENTATION OF THE INVENTION
[0008] The invention relates to a degassing outlet for an aircraft turbomachine bearing housing containing air charged with a cooling and lubricating fluid, the degassing outlet comprising: • a fluidic chamber comprising a frustoconical wall decreasing along a vertical axis oriented from bottom to top in a direction opposite to an axis of gravity of the aircraft turbomachine under nominal flight conditions, the fluidic chamber being stator-like, • an intake duct opening into a lower part of the fluidic chamber and configured to inject air laden with cooling and lubricating fluid in an upward swirling motion, so as to project the cooling and lubricating fluid against the truncated conical wall by centrifugal force, • a receptacle in the lower part of the fluidic chamber configured to collect the cooling and lubricating fluid flowing by gravity over the truncated conical wall, and • an exhaust duct opening into an upper part of the fluidic chamber and configured to guide air out of the fluidic chamber.
[0009] The degassing outlet according to the invention advantageously forms a stator air-oil separator suitable for passively de-oiling the air expelled from the bearing housing. Its positioning at the outlet of the bearing housing, namely at the inlet of the degassing circuit, reduces the amount of oil conveyed along the degassing circuit. This reduces pressure losses in the degassing circuit and thus improves the sealing of the bearing housing.
[0010] Such a stator oil separator advantageously requires no power transmission. This avoids drawing power from the shaft of the aircraft turbomachine and frees up positioning constraints, thus allowing It can be integrated directly at the outlet of the bearing housing. Such an oil separator without rotating parts can also prove to be more robust with low maintenance costs.
[0011] According to one aspect of the invention, the degassing outlet comprises a bottom wall configured to be externally fixed to the bearing housing. The fluidic chamber thus extends radially outwards from the bearing housing to limit the space required at the shaft.
[0012] According to one aspect of the invention, the inlet duct passes through the back wall to limit its size. The inlet duct also passes through the wall of the enclosure.
[0013] According to one aspect of the invention, the intake duct comprises an angled portion extending in projection into the fluidic chamber to promote the entrainment of air in an upward vortex motion.
[0014] According to one aspect of the invention, the degassing outlet comprises a return conduit into which the receptacle opens and which is configured to guide the cooling and lubricating fluid into the bearing housing. The collected oil is advantageously drained into the bearing housing by gravity in a simple and practical manner. The direction of reinjection is cleverly positioned in the direction of the oil flow in the housing, that is to say, the direction of rotation of the shaft in the housing (Venturi effect in the rotating oil ring).
[0015] According to one aspect of the invention, the receptacle is in the form of a circumferential gutter facilitating the collection of oil all around the perimeter of the truncated conical wall.
[0016] According to one aspect of the invention, the evacuation conduit opens into the fluidic chamber centered along the vertical axis in continuity with the frustoconical wall to promote the evacuation of air.
[0017] According to one aspect of the invention, the receptacle is inclined relative to a horizontal plane at an angle greater than 5° to guide the cooling and lubrication fluid by gravity towards the return conduit, the angle being preferably greater than 10° and preferably less than 45°.
[0018] The invention also relates to an assembly of a degassing outlet as described above and an aircraft turbomachine bearing enclosure containing air charged with a cooling and lubricating fluid discharged into the inlet duct of the degassing outlet.
[0019] According to one aspect of the invention, the cooling and lubricating fluid circulates in the bearing housing along a longitudinal outer wall, to which a bottom wall of the fluidic chamber is fixed, in a flow direction determined by a direction of rotation of a shaft of the aircraft turbomachine guided by the bearing, the return duct of the degassing outlet being adapted to guide the fluid of cooling and lubrication in the bearing enclosure according to the determined flow direction.
[0020] The invention also relates to an aircraft turbomachine comprising a degassing outlet as described above and an aircraft turbomachine bearing enclosure containing air charged with a cooling and lubricating fluid discharged into the inlet duct of the degassing outlet.
[0021] The invention also relates to a degassing circuit for an aircraft turbomachine bearing enclosure containing air charged with a cooling and lubricating fluid, the degassing circuit comprising a degassing outlet as described above and a separation device supplied with air by the exhaust duct of the degassing outlet and adapted to extract by rotary drive a remainder of cooling and lubricating fluid in the air.
[0022] The invention also relates to an assembly of a degassing circuit as described above and an aircraft turbomachine bearing enclosure containing air charged with a cooling and lubricating fluid discharged into the inlet duct of the degassing outlet.
[0023] The invention also relates to an aircraft turbomachine comprising a degassing circuit as described above and an aircraft turbomachine bearing enclosure containing air charged with a cooling and lubricating fluid discharged into the inlet duct of the degassing outlet.
[0024] The invention also relates to a method of using a degassing outlet as described above to extract the cooling and lubricating fluid in the air from an aircraft turbomachine bearing housing, a method in which the air charged with cooling and lubricating fluid from the bearing housing is injected into the fluidic chamber and driven in an upward vortex motion by means of the inlet duct and the frustoconical wall, the cooling and lubricating fluid being projected against the frustoconical wall by centrifugation and then flowing by gravity into the receptacle, the air being evacuated into the discharge duct.
[0025] The method of use according to the invention advantageously allows the air evacuated from the bearing housing to be de-oiled passively, without rotary drive, directly at the outlet of the bearing housing. This reduces pressure losses in the degassing circuit and thus helps to maintain better sealing in the bearing housing. PRESENTATION OF THE FIGURES
[0026] The invention will be better understood upon reading the following description, given by way of example, and referring to the following figures, given by way of example. non-exhaustive, in which identical references are given to similar objects.
[0027] Fig. 1 is a schematic longitudinal sectional representation of an aircraft turbomachine comprising a bearing housing equipped with a degassing outlet according to a first embodiment of the invention.
[0028] Fig. 2 is a schematic longitudinal sectional representation of an aircraft turbomachine comprising a bearing housing equipped with a degassing outlet according to a second embodiment of the invention.
[0029] Fig. 3 is a schematic longitudinal sectional representation of a bearing enclosure equipped with a degassing outlet according to one embodiment of the invention.
[0030] The [Fig.4] is a schematic representation in truncated perspective of the degassing outlet according to one embodiment of the invention.
[0031] The [Fig.5] is a schematic perspective and transparency representation of the degassing outlet of the [Fig.4].
[0032] The [Fig.6] is a schematic representation in profile view and in transparency of the degassing outlet of the [Fig.4].
[0033] The [Fig.7] is a schematic representation in view from below and in transparency of the degassing outlet of the [Fig.4].
[0034] It should be noted that the figures set out the invention in detail to implement the invention, said figures being of course able to serve to better define the invention where appropriate. DETAILED DESCRIPTION OF THE INVENTION
[0035] With reference to [Fig.1], the invention relates to an aircraft turbomachine 30 comprising one or more bearing enclosures 10 provided with a degassing outlet 1 ensuring passive oil removal from the evacuated air.
[0036] As illustrated in [Fig. 1], the aircraft turbomachine 30 conventionally extends along a longitudinal axis X and propels the aircraft by means of an airflow circulating from front to back within the turbomachine 30 during a thrust phase. The aircraft turbomachine 30 typically comprises, from front to back, one or more compressors 31, 32, a combustion chamber, and one or more turbines 33, 34. Each turbine 33, 34 is rotationally coupled to a compressor 31, 32 via a shaft 39, 40 extending along the longitudinal axis X. In this example, the aircraft turbomachine 30 comprises a low-pressure shaft 40, connecting a low-pressure compressor 31 and a low-pressure turbine 34, and a high-pressure shaft 39, surrounding the low-pressure shaft 40 and connecting a high-pressure turbine 33 and a high-pressure compressor 32.
[0037] As illustrated in [Fig. 1], the low-pressure shaft 40 and the high-pressure shaft 39 are supported at the front and rear by bearings 17, for example, of the ball or roller type. The bearings 17 are housed in enclosures 10 inside which they are immersed in an oil mist to ensure their cooling and lubrication. Only one bearing enclosure 10 at the rear of the aircraft turbomachine 30 is shown in [Fig. 1], but a degassing outlet 1 according to the invention is preferably integrated on each bearing enclosure 10.
[0038] As illustrated in [Fig. 3], the bearing housing 10 extends statorically around the shaft 39, 40 of the aircraft turbomachine 30 and defines an internal volume V in which one or more bearings 17 are located. The bearing housing 10 is conventionally supplied by a supply circuit 13 with cooling and lubrication fluid H, typically oil. Seals 14 connect the bearing housing 10 and the shaft 39, 40, for example, one at the front and one at the rear as illustrated in [Fig. 3]. Passages formed in the seals 14 allow the admission of pressurized air A, notably drawn from the compressor 31, 32, in order to confine the oil H within the bearing housing 10.
[0039] As illustrated in [Fig. 3], the oil H accumulated at the bottom of the bearing housing 10 is discharged by gravity into an oil outlet circuit 15. The oil outlet circuit 15 conventionally includes a separator 16 adapted to remove the air A contained in the oil H, known to those skilled in the art as an "oil deaerator." The air A from the internal volume V is discharged into a degassing circuit 18, where it carries with it suspended oil H and is hereafter referred to as "oil-laden air AH."
[0040] With reference to Figures 3 and 4, according to the invention, the degassing circuit 18 comprises a degassing outlet 1 comprising: • a stator-type fluidic chamber 2 comprising a frustoconical wall 3 decreasing along a vertical axis Y oriented from bottom to top, • an inlet duct 6 opening into a lower part 4 of the fluidic chamber 2 and configured to inject oil-laden air AH according to an upward vortex motion M, so as to project the oil H against the frustoconical wall 3 by centrifugation, • a receptacle 7 in the lower part 4 of the fluidic chamber 2 configured to collect the oil H flowing by gravity over the frustoconical wall 3, and • an exhaust duct 8 opening into an upper part 5 of the fluidic chamber 2 and configured to guide air A out of the fluidic chamber 2.
[0041] It is specified that the vertical axis Y is defined as parallel to the axis of gravity G of the aircraft turbomachine 30 under nominal conditions and in the opposite direction to it. The terms "down", "up", "horizontal" and "up" are defined with respect to the orientation of the vertical Y axis.
[0042] The degassing outlet 1 according to the invention advantageously forms an air-oil separator suitable for de-oiling the air A evacuated from the bearing enclosure 10. Its positioning at the outlet of the bearing enclosure 10, namely at the inlet of the degassing circuit 18, makes it possible to reduce the quantity of oil H conveyed along the degassing circuit 18. This reduces the pressure losses in the degassing circuit 18 and thus improves the sealing of the bearing enclosure 10.
[0043] The invention is remarkable in that the degassing outlet 1 forms a stator oil separator that does not require any power draw from the shaft 39, 40 of the aircraft turbomachine 30. The separation of oil H and air A is implemented passively, without rotary drive. The thrust performance of the aircraft turbomachine 30 is advantageously preserved. Furthermore, this reduces the positioning constraints of the oil separator, which does not need to be fixed to the shaft 39, 40 of the aircraft turbomachine 30 and can thus be positioned directly at the outlet of the bearing housing 10.
[0044] According to a first embodiment of the invention illustrated in [Fig. 1], the degassing outlet 1 forms a first oil separator, of stator type, and the degassing circuit 18 includes a second oil separator 19, of rotor type. The second oil separator 19 extends downstream of the degassing outlet 1 in the direction of air flow A, and is adapted to extract the remaining oil H in the air A guided in the discharge duct 8 of the degassing outlet 1. In the example of [Fig. 1], the second oil separator 19 is mounted on the accessory gearbox 36 (“accessory gearbox AGB”) housed in the nacelle 35 surrounding the aircraft turbomachine 30 and is driven in rotation by the shaft 39, 40 of the aircraft turbomachine 30. The use of two oil separators in series advantageously improves the recovery of oil H.
[0045] The oil separator formed by the degassing outlet 1 effectively extracts a spectrum of larger, more massive oil droplets from the air by centrifugation. The smaller droplets are not projected onto the wall of the degassing outlet 1 and therefore remain in the outlet air. The presence of a second active oil separator mounted on the accessory gearbox (AGB), driven by high-speed rotation, allows for the recovery of a spectrum of smaller droplets, ultimately resulting in the discharge of more oil-free air.
[0046] According to a second embodiment of the invention illustrated in [Fig.2], the degassing circuit 18 comprises a single oil separator formed by the degassing outlet 1. The air A guided in the exhaust duct 8 is then discharged to the outside, in this example into the air stream 38, typically behind the low-pressure turbine 34.
[0047] With reference to Figures 3 to 5 and as described previously, the degassing outlet 1 comprises a stator-shaped fluidic chamber 2, i.e., free of any rotating parts. The fluidic chamber 2 has a vertical frustoconical wall 3, defining an internal cross-section that decreases from bottom to top, in this circular example. The fluidic chamber 2 is closed at its lower part 4 by a bottom wall 9 and opens at its upper part 5 into the discharge conduit 8.
[0048] According to a preferred aspect illustrated in [Fig. 3], the fluidic chamber 2 is externally and vertically fixed to the bearing housing 10, which is itself stator-shaped. More specifically, the bottom wall 9 of the fluidic chamber 2 is fixed to the longitudinal outer wall 22 of the bearing housing 10. The fluidic chamber 2 thus extends radially outward from the bearing housing 10 to limit the space occupied by the shaft 39, 40 with longitudinal axis X.
[0049] Preferably, as illustrated in [Fig. 7], the bottom wall 9 has a peripheral fixing edge 23 extending outwards from the vertical axis Y, allowing for easy and effective fixing to the bearing housing 10, for example by means of screws, nails, or rivets. The frustoconical geometry of the fluidic chamber 2 gives the bottom wall 9 a large surface area, facilitating its attachment to the bearing housing 10.
[0050] With reference to Figures 3 to 6 and as described previously, the degassing outlet 1 includes an inlet duct 6 opening into the lower part 4 of the fluidic chamber 2 and configured to inject pressurized oil-laden air AH from the internal volume V of the bearing housing 10. As illustrated in [Fig. 7], the inlet duct 6 preferably passes through the bottom wall 9 of the fluidic chamber 2 and the longitudinal outer wall 22 of the bearing housing 10 to establish fluidic communication between the internal volume V and the fluidic chamber 2. Preferably also, the inlet duct 6 extends outward into the internal volume V to limit the carryover of oil H, in particular oil H forming a film on the internal wall of the bearing housing 10.
[0051] According to a preferred aspect illustrated in Figures 4 to 6, the inlet duct 6 has an angled portion 11 projecting into the fluidic chamber 2, preferably outwards with respect to the vertical axis Y, allowing tangential injection of the oil-laden air AH. The angled portion 11 of the inlet duct 6 and the frustoconical geometry of the inlet chamber 2 together impart an upward swirling motion M to the oil-laden air AH, also known as a vortex, which promotes the projection of the oil H onto the frustoconical wall 3 by centrifugal effect.
[0052] According to another preferred aspect illustrated in Figures 4 and 5, the intake duct 6 has an orifice 12 having a cross-sectional restriction to increase the speed The injection of oil-laden air (H) promotes centrifugation. The truncated conical geometry of the fluidic chamber (2) also accelerates the oil-laden air (AH) to further promote centrifugation. The inlet duct (6) is stator-type and free of valves or pumps.
[0053] With reference to figures 4 to 6 and as described previously, the degassing outlet 1 includes a receptacle 7 in the lower part of the fluidic chamber 2 adapted to collect by gravity the oil H projected against the frustoconical wall 3. The receptacle 7 is typically formed on the inner face 20 of the bottom wall 9 of the fluidic chamber 2. Preferably, the receptacle 7 is in the form of a circumferential gutter allowing the oil H to be collected over the entire circumference of the frustoconical wall 3 in a simple and practical manner.
[0054] According to a preferred aspect illustrated in figures 4 to 6, the degassing outlet 1 also includes a return conduit 21 opening on one side into the receptacle 7 and on the other side into the bearing enclosure 10. The return conduit 21 advantageously allows the oil H collected in the receptacle 7 to be drained by gravity into the bearing enclosure 10, in a simple and practical manner.
[0055] Preferably, and with reference to Figures 6 and 7, the return conduit 21 comprises an end, such as a scoop, opening into the bearing housing 10 in a direction and sense corresponding to the flow of the oil film H in the bearing housing 10 along the outer longitudinal wall 22. The flow of the oil film H in the bearing housing 10 is defined by the direction of rotation of the shaft 39, 40 guided by the bearing 17. The direction of the oil H flow in the bearing housing 10 is typically circumferential, in a plane transverse to the longitudinal axis X. This promotes the return of the oil H by gravity and the Venturi effect into the bearing housing 10.
[0056] According to a preferred aspect illustrated in Figures 4 and 6, the receptacle 7 is inclined relative to a horizontal plane P at an angle α greater than 5° to guide the cooling and lubrication fluid by gravity towards the return conduit 21 under all stabilized attitudes of the aircraft turbomachine 30. The angle α is preferably greater than 10° and preferably less than 45° to allow efficient gravity drainage.
[0057] With reference to figures 4 to 6 and as described previously, the degassing outlet 1 includes an exhaust conduit 8 in the upper part 5 of the fluidic chamber 2 adapted to evacuate the air A after centrifugation out of the fluidic chamber 2. Preferably, the exhaust conduit 8 opens into the fluidic chamber 2 centered along the vertical axis Y in the extension of the frustoconical wall 3 to promote the evacuation of the air A. The exhaust conduit 8 is stator-type, free of valve or pump.
[0058] With reference to Figures 3, 4 and 6, the invention also relates to a method of using the degassing outlet 1 to de-oil the air AH coming from a bearing enclosure 10, a method in which: • Oil-laden air AH under pressure from bearing housing 10 is injected into fluid chamber 2 through inlet duct 6, • The oil-laden air AH is drawn in an upward vortex motion M into the fluidic chamber 2, thanks to the geometry of the frustoconical wall 3 and the angled portion 11 of the inlet duct 6, • Oil H is projected against the truncated conical wall 3 by centrifugal effect and then flows by gravity into the receptacle 7, while air A is evacuated into the evacuation duct 8.
[0059] The invention advantageously allows the air AH evacuated from the bearing housing 10 to be passively de-oiled, without rotary drive, directly at the outlet of the bearing housing 10. This reduces pressure losses in the degassing circuit 18 and thus helps to maintain a better seal in the bearing housing 10. Advantageously, such a stator-based oil separator does not require any power transmission. This avoids drawing power from the shaft 39, 40 of the aircraft turbomachine and frees up positioning constraints, allowing it to be integrated directly at the outlet of the bearing housing 10. Furthermore, such an oil separator without rotating parts can prove to be more robust with low maintenance costs.
Claims
Demands
1. A vent outlet (1) for a bearing housing (10) of an aircraft turbomachine (30) containing air charged with a cooling and lubricating fluid (AH), the vent outlet (1) comprising: • a fluidic chamber (2) comprising a frustoconical wall (3) decreasing about a vertical axis (Y) oriented from bottom to top in a direction opposite to an axis of gravity (G) of the aircraft turbomachine (30) under nominal flight conditions, the fluidic chamber (2) being stator-shaped, • an inlet duct (6) opening into a lower part (4) of the fluidic chamber (2) and configured to inject the air charged with the cooling and lubricating fluid (AH) in an upward vortex motion (M), so as to project the cooling and lubricating fluid (H) against the frustoconical wall (3) by centrifugal force,• a receptacle (7) in the lower part (4) of the fluidic chamber (2) configured to collect the cooling and lubricating fluid (H) flowing by gravity over the frustoconical wall (3), and • a discharge conduit (8) opening into an upper part (5) of the fluidic chamber (2) and configured to guide air (A) out of the fluidic chamber (2).
2. Degassing outlet (1) according to claim 1, comprising a bottom wall (9) configured to be externally fixed to the bearing enclosure (10).
3. Degassing outlet (1) according to claim 2, wherein the inlet conduit (6) passes through the bottom wall (9).
4. Degassing outlet (1) according to any one of claims 1 to 3, wherein the inlet conduit (6) has an angled portion (11) extending projecting into the fluidic chamber (2).
5. Degassing outlet (1) according to any one of claims 1 to 4, wherein the receptacle (7) is in the form of a circumferential gutter.
6. Degassing outlet (1) according to any one of claims 1 to 5, comprising a return conduit (21) into which the receptacle (7) and configured to guide the cooling and lubrication fluid (H) into the bearing enclosure (10).
7. A degassing outlet (1) according to claim 6, wherein the receptacle (7) is inclined with respect to a horizontal plane (P) at an angle (a) greater than 5° to guide the cooling and lubricating fluid (H) by gravity towards the return conduit (21), the angle (a) preferably being greater than 10° and preferably less than 45°
8. HJ. Degassing outlet (1) according to any one of claims 1 to 7, wherein the discharge conduit (8) opens into the fluidic chamber (2) centered along the vertical axis (Y).
9. Degassing circuit (18) for a bearing enclosure (10) of an aircraft turbomachine (30) containing air charged with a cooling and lubricating fluid (AH), the degassing circuit (18) comprising a degassing outlet (1) according to any one of claims 1 to 8 and a separation device (19) supplied with air (A) through the exhaust duct (8) of the degassing outlet (1) and adapted to extract by rotary drive a remainder of cooling and lubricating fluid (H) in the air (A).
10. Assembly of a degassing outlet (1) according to claim 6 and a bearing housing (10) of an aircraft turbomachine (30) containing air charged with a cooling and lubricating fluid (AH) discharged into the inlet duct (6) of the degassing outlet (1), the cooling and lubricating fluid (AH) flowing in the bearing housing (10) along an external longitudinal wall (22), on which is fixed a bottom wall (9) of the fluidic chamber (2), in a direction of flow determined by a direction of rotation of a shaft (39, 40) of the aircraft turbomachine (30) guided by the bearing (17), the return duct (21) of the degassing outlet (1) being adapted to guide the cooling and lubricating fluid (H) in the bearing housing (10) in the determined direction of flow.
11. A method of using a degassing outlet (1) according to any one of claims 1 to 8 for extracting the cooling and lubricating fluid (H) in the air (A) from a bearing housing (10) of an aircraft turbomachine (30), a method wherein the air charged with cooling and lubricating fluid (AH) from the bearing housing (10) is injected into the fluidic chamber (2) and driven by an upward swirling motion (M) by means of the inlet conduit (6) and the truncated conical wall (3), the cooling and lubricating fluid (H) is projected against the truncated conical wall (3) by centrifugation and then flows by gravity into the receptacle (7), the air (A) being evacuated into the evacuation conduit (8).