COLLECTOR OF AT LEAST ONE LIQUID FOR AN AIRCRAFT TURBOMACHINE

Abstract

The invention relates to a collector (20) comprising: - an enclosure (21) delimiting an internal cavity (27), - at least a first inlet (22, 23), - a first outlet (24), - a ventilation duct (29) comprising: - a ventilation air inlet (30) located outside the enclosure (21), and - a ventilation air outlet (31) which is connected to the first liquid outlet (24), - a liquid discharge duct (33) configured to discharge the liquid from the internal cavity (27) outside the enclosure (21) when the liquid level in the enclosure (21) is greater than or equal to a threshold level (S1) of liquid in the internal cavity (27), the discharge duct (33) comprising: - a second inlet (34), and - a second outlet (35), the ventilation and liquid discharge ducts (29, 33) being independent of each other. the other. abbreviated figure: 2

Description

Title of the invention: COLLECTOR OF AT LEAST ONE LIQUID FOR AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The invention relates to a collector of at least one liquid, for an aircraft turbomachine. Technical background

[0002] A turbomachine, in particular an aircraft turbomachine, generally extends along and around a longitudinal axis. In the case of a twin-spool, twin-flow turbomachine, it comprises a gas generator which typically comprises, from upstream to downstream, in the direction of gas flow in the turbomachine, a low-pressure compressor, a high-pressure compressor, a gas combustion chamber, a high-pressure turbine and a low-pressure turbine.

[0003] The rotor of the low pressure compressor is typically connected to the rotor of the low pressure turbine via a low pressure shaft. The rotor of the high pressure compressor is connected to the rotor of the high pressure turbine via a high pressure shaft.

[0004] The turbomachine further comprises a fan which is located upstream of the gas generator and which is driven in rotation about the longitudinal axis by a fan shaft. In certain types of turbomachines with a high bypass ratio, the fan shaft may be connected to the low pressure shaft via a speed reducer.

[0005] The high and low pressure shafts are guided in rotation by means of guide bearings which must be lubricated by lubricating oil to ensure their proper operation. In order to preserve the connected components of the turbomachine from this lubricating oil, the bearings and gears of the speed reducer, for example, are typically arranged in lubrication chambers. Each lubrication chamber is connected to a lubrication circuit which makes it possible to supply the lubrication chamber with lubricating oil. In addition, each lubrication chamber is delimited by sealing systems comprising seals which make it possible to limit the leakage of lubricating oil outside the lubrication chambers.

[0006] Furthermore, the combustion chamber and certain hydraulic actuators of the turbomachine are supplied with fuel. For this purpose, the turbomachine typically comprises a fuel circuit which makes it possible to supply fuel to the combustion chamber and / or hydraulic actuators.

[0007] Lubrication chambers, fuel and lubrication circuits may experience liquid leaks, including fuel and / or lubricating oil leaks. Although these leaks flow at a rate considered normal or standard, they represent potential sources of environmental pollution. Also, the fuel in the combustion chamber is generally drained to limit the risk of coking.

[0008] The turbomachine therefore generally comprises at least one drainage circuit for these liquids.

[0009] In order to limit the environmental pollution caused by these liquids, the turbomachine typically comprises a collector of at least one of these liquids connected to the drainage circuit. The collector typically comprises an enclosure defining an internal cavity intended to receive the liquid and a first inlet for this liquid into the internal cavity. The collector further comprises a first outlet for this liquid opening outside the enclosure.

[0010] The liquid is typically evacuated through the first outlet by draining. For this purpose, the turbomachine generally comprises an ejector comprising an air inlet generally connected to the high-pressure compressor, a liquid inlet connected to the first outlet of the manifold and an outlet connected for example to the nozzle for evacuating the liquid.

[0011] The collector further comprises an air ventilation duct comprising an air inlet located outside the enclosure, and an air outlet which is connected to the first liquid outlet.

[0012] Thanks to the pressure difference between the air inlet and the liquid outlet of the collector, a depression is created in the outlet of the collector allowing the liquid to be sucked from the internal cavity to the nozzle.

[0013] There are also leaks that can result from abnormal operation of the fuel or lubrication circuits or from a rupture of the sealing systems of the lubrication enclosures, for example. In such a case, the leakage flow rate of the liquid is abnormal and the liquid inlet flow rate into the collector is significantly higher than the outlet flow rate, such that the liquid accumulates in the internal cavity. In order to collect such abnormal leaks and ensure their evacuation outside the enclosure, the collector typically comprises a liquid evacuation pipe configured to evacuate the liquid outside the enclosure when the liquid level in the enclosure is higher than a threshold level of liquid in the internal cavity. This evacuation pipe thus comprises a second liquid inlet located in the internal cavity and a second liquid outlet opening outside the enclosure of the collector.The second liquid outlet is usually common and confused with the ventilation air inlet of the ventilation duct.

[0014] Such abnormal leaks could be such as to reduce the margin for shutdown of the turbomachine or to reduce the margin of availability of the emergency regimes of the turbomachine. It is therefore important for operators to be able to detect these abnormal leaks.

[0015] In this context, in order to detect and signal an abnormal leak of liquid in the turbomachine, the collector typically comprises a device for detecting and signaling the first threshold level. Such a detection and signaling device is for example connected to the discharge pipe and comprises a detection and signaling member making it possible to observe and / or signal liquid in the discharge pipe, such as a window or an indicator light. The detection of liquid in this discharge pipe generally reflects an abnormal leak of liquid and therefore a failure of a fuel or lubrication circuit or of the seals of the lubrication enclosures.

[0016] However, such a collector is not entirely satisfactory. Indeed, since the second liquid outlet is common and coincides with the ventilation air inlet of the ventilation duct, when air is sucked in through the ventilation air inlet, pollutants can enter the discharge duct and accumulate in the internal cavity until they block the first liquid outlet. Such pollution therefore generates leak detections which are not due to a break in the seals or the fuel or lubrication circuits but rather to pollution in the collector.

[0017] Such false failure alerts lead to leak detection campaigns that are long, tedious and costly. Indeed, following the detection of an abnormal leak, it is necessary to carry out a search campaign for the leak(s) to identify their origin. It is only at the end of such a search campaign that it is possible to take charge of the leak and resolve it. Such a search campaign requires the installation of leak segregation and control equipment at the turbomachine, then the training of the turbomachine on the ground for several tens of minutes in order to know the leak flow rates of each seal. Such search campaigns are long, tedious for the operators and mobilize the turbomachine which cannot be put into operation. The aircraft cannot therefore be put into service during the campaign, strongly impacting its availability.

[0018] Therefore, there is a need to provide a collector of at least one liquid for an aircraft turbomachine, which makes it possible to detect abnormal leaks in the turbomachine, in a reliable, simple and rapid manner. Summary of the invention

[0019] To this end, the invention proposes a collector of at least one liquid for an aircraft turbomachine, the collector comprising:

[0020] - an enclosure delimiting an internal cavity intended to receive the liquid,

[0021] - at least one first inlet of the liquid opening into the internal cavity,

[0022] - a first liquid outlet opening outside the enclosure,

[0023] - a ventilation duct comprising:

[0024] - a ventilation air inlet located outside the enclosure, and

[0025] - a ventilation air outlet which is connected to the first liquid outlet,

[0026] - a liquid discharge conduit configured to discharge liquid from the cavity internal outside the enclosure when the liquid level in the enclosure is greater than or equal to a threshold liquid level in the internal cavity, the discharge pipe comprising:

[0027] - a second liquid inlet located in the internal cavity, and

[0028] - a second liquid outlet opening outside the enclosure.

[0029] The collector is remarkable in that the ventilation and liquid discharge pipes are independent of each other.

[0030] Thus, according to the invention, the ventilation and liquid discharge pipes are independent of each other. By "independent", it is understood that these pipes are fluidically separated and therefore do not communicate with each other. In other words, the inlets and outlets of these ventilation and liquid discharge pipes are distinct and non-communicating.

[0031] Thanks to the independence of these pipes, contamination of the discharge pipe is minimized. The risk of detecting false leaks is therefore reduced, which improves the reliability of the collector.

[0032] Thanks to the collector of the invention, it is therefore possible to reduce the number of leak search campaigns.

[0033] The invention may comprise one or more of the following features, taken in isolation from one another or in combination with one another:

[0034] - the ventilation duct comprises a sealed air circulation passage vis- with respect to the internal cavity,

[0035] - the ventilation duct comprises an air circulation passage which is connected fluidly to the internal cavity through a venting orifice of the internal cavity,

[0036] - the enclosure extends longitudinally along a longitudinal axis between a first end and a second end closed by a bottom wall, the ventilation air inlet of the ventilation duct being located on the side of the first end,

[0037] - the ventilation air inlet is axially opposite the second outlet,

[0038] - the first and second liquid outlets are located on the side of the second end and are radially opposite with respect to the longitudinal axis,

[0039] - the ventilation air inlet of the suction line is oriented towards the second end,

[0040] - the ventilation duct comprises a ventilation line connecting the inlets and ventilation air outlet and extending longitudinally between the first and second ends,

[0041] - the ventilation line is located in the internal cavity,

[0042] - the collector is monobloc,

[0043] - the collector is produced by additive manufacturing. Brief description of the figures

[0044] Other characteristics and advantages will emerge from the following description of non-limiting embodiments of the invention with reference to the appended drawings in which:

[0045] [Fig-1] [Fig.l] is a longitudinal sectional view of an example of a tur- aircraft machine according to the invention,

[0046] [Fig.2] [Fig.2] is a longitudinal sectional view of a collector according to the invention, when the liquid level in the enclosure is lower than the threshold level,

[0047] [Fig.3] [Fig.3] is a longitudinal sectional view of a collector according to the invention, when the liquid level in the enclosure is higher than or equal to the threshold level. Detailed description of the invention

[0048] An example of an aircraft turbomachine 1 according to the invention is shown in [Fig.l]. The turbomachine 1 is for example a dual-flow turbojet. The turbomachine 1 may have any other architecture and be in the form of a turboprop, for example.

[0049] The turbomachine 1 is modular. It comprises a plurality of modules assembled together.

[0050] The turbomachine 1 extends along a longitudinal axis X. A gas flow F flows in the turbomachine 1.

[0051] For the purposes of the present invention, the terms "upstream" and "downstream" are understood to refer to the direction of flow of the gas flow F in the turbomachine 1. The gas flow F flows in particular from left to right in FIGS. 1 and 2.

[0052] The turbomachine 1 comprises, from upstream to downstream, a fan 2 and a gas generator. The gas generator comprises, from upstream to downstream, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, a low-pressure turbine 7 and a gas exhaust nozzle 70.

[0053] Each compressor 3, 4 comprises a compressor rotor 3a, 4a and each turbine 6, 7 comprises a turbine rotor 6a, 7a. The compressor rotors 3a, 4a and turbine 6a, 7a are composed of a plurality of stages each comprising a bladed wheel.

[0054] The compressor rotor 3a of the low pressure compressor 3 is connected to the turbine rotor 7a of the low pressure turbine 7 by a low pressure shaft 8. They form a low pressure body.

[0055] The compressor rotor 4a of the high-pressure compressor 4 is connected to the turbine rotor 6a of the high-pressure turbine 6 by a high-pressure shaft 9. They form a high-pressure body.

[0056] The low pressure 8 and high pressure 9 shafts are centered on the longitudinal axis X and rotatable about the longitudinal axis X. The high pressure shaft 9 is arranged coaxially around the low pressure shaft 8.

[0057] The gas flow F passes through the blower 2 and is divided into a primary air flow F1 passing through a primary vein v1 and into a secondary air flow F2 passing through a secondary vein v2 surrounding the primary vein. The primary air flow F1 passes through the low pressure 3 and high pressure 4 compressors. The compressed primary air flow F1 then passes through the combustion chamber 5 in which it is mixed with a fuel. The gases resulting from the combustion thus pass through the high pressure 6 and low pressure 7 turbines. The energy of the gases is transformed by the turbine rotor 7a of the low pressure turbine 7 into mechanical energy making it possible to drive the low pressure shaft 8 in rotation and consequently the low pressure compressor 3.

[0058] The fan 2 comprises a mobile disc rotating around the longitudinal axis X and blades 2a carried by the disc and regularly distributed around the longitudinal axis X. In the example of [Fig.l], the fan 2 is surrounded by a fan casing 2b. The fan 2 is of the ducted type. The fan casing 2b carries a nacelle 2c and together define a fan compartment 2d.

[0059] According to another example not shown, the fan 2 is of the non-ducted type.

[0060] The fan disc 2 is driven in rotation by a fan shaft 10. In the example described, and therefore optionally, the fan shaft 10 is connected to the low pressure shaft 8 via a speed reducer 11. The speed reducer 11 is of the mechanical type. It is for example an epicyclic or planetary gear train.

[0061] The speed reducer 11 allows the fan shaft 10 to be driven at a rotational speed lower than the rotational speed of the low pressure shaft 8. This allows the bypass ratio of the turbomachine 1 to be increased.

[0062] The turbomachine 1 further comprises an inter-compressor casing 12 arranged axially between the low-pressure compressor 3 and the high-pressure compressor 4. The inter-compressor casing 12 comprises, for example, an inner shell and an outer shell which are centered on the longitudinal axis X. The inner and outer shells are for example connected by arms.

[0063] The turbomachine 1 may further comprise an inlet casing 13. The inlet casing 13 is arranged axially between the fan 2 and the low-pressure compressor 3. The inlet casing 13 comprises, for example, an inner shell and an outer shell which are centered on the longitudinal axis X. The inner and outer shells are, for example, connected by arms.

[0064] The turbomachine 1 may further comprise an inter-turbine casing 14. The inter-turbine casing 14 is arranged axially between the high-pressure turbine 6 and the low-pressure turbine 7.

[0065] The turbomachine 1 may further comprise an inter-vein compartment v3 located between the primary vein v1 and the secondary vein v2.

[0066] The turbomachine 1 comprises at least one bearing 15. In particular, the fan shaft 10 is guided in rotation by a first bearing 15a and advantageously a second bearing 15b. The first and second bearings 15a, 15b are arranged radially between the fan shaft 10 and the inlet casing 13.

[0067] The low pressure shaft 8 is guided in rotation by at least a third and fourth bearing 15c, 15d. The third bearing 15c is arranged radially between the inlet casing 13 and the low pressure shaft 8. The fourth bearing 15d is arranged radially between the inter-compressor casing 12 and the low pressure shaft 8.

[0068] The high pressure shaft 9 is guided in rotation by a fifth bearing 15e. The fifth bearing 15e is for example arranged radially between the high pressure shaft 9 and the inter-turbine casing 14.

[0069] The low pressure shaft 8 can be guided in rotation downstream by a sixth bearing 15f arranged radially between a downstream end of the low pressure shaft 8 and the inter-turbine casing 14 for example.

[0070] Each bearing comprises, for example, a rolling bearing. The rolling bearing is, for example, at least one row of balls or rollers.

[0071] The bearings 15 and the possible speed reducer 11 are lubricated to ensure their proper operation. To avoid contaminating the related components of the turbomachine 1 with oil, the bearings 15 and the speed reducer 11 are arranged in lubrication enclosures. The lubrication enclosures may also be intended for the lubrication of other elements of the turbomachine 1, such as gears, bearings.

[0072] For this purpose, the turbomachine 1 further comprises at least one lubrication enclosure, in particular a first upstream enclosure 17 in which the first, second and third bearings 15a, 15b, 15c and the speed reducer 11 are arranged, a second upstream lubrication enclosure 18 in which the fourth bearing 15d is arranged and a downstream lubrication enclosure 19 in which the fifth and sixth levels 15th, 15f.

[0073] Depending on the configuration of the turbomachine 1, the number of bearings 15 and lubrication chambers 16 may vary.

[0074] Each lubrication enclosure 16 is annular. Each lubrication enclosure 16 is delimited externally by a fixed wall such as a casing and internally by a movable wall such as a shaft.

[0075] For example, the first upstream lubrication enclosure 17 is located in the internal shell of the inlet casing 13 and is delimited internally by the fan shaft 10. The second upstream lubrication enclosure 18 is located in the internal shell of the inter-compressor casing 12 and is delimited internally by the low pressure shaft 8 and the downstream lubrication enclosure 19 is located in the internal shell of the inter-turbine casing 14 and is delimited internally by the high pressure shaft 9.

[0076] The lubrication chambers 17, 18, 19 are supplied by at least one lubrication circuit. The lubrication circuit comprises an oil outlet opening into the lubrication chambers 17, 18, 19 and an oil inlet connected for example to a reservoir for supplying the lubrication circuit.

[0077] In order to limit oil leaks outside the lubrication chambers 17, 18, 19, each lubrication chamber 17, 18, 19 comprises seals at the terminals of the lubrication chambers 17, 18, 19. The seals are each located radially between the fixed wall and the movable wall of the lubrication chambers 17, 18, 19. The seals are advantageously of the dynamic type. A dynamic type seal is understood as an assembly limiting leaks of a fluid between the fixed wall and the movable wall. Preferably, the first and second seals are labyrinth seals.

[0078] The turbomachine 1 further comprises a circuit for supplying the combustion chamber 5 with fuel.

[0079] Despite the sealing of the lubrication chambers 17, 18, 19, leaks of lubricating oil may occur. Also, the fuel from the combustion chamber 5 must be evacuated in order to limit the risks of coking.

[0080] In this context, the turbomachine 1 further comprises at least one drainage circuit for the combustion chamber 5 and / or the lubrication enclosures 17, 18, 19. The drainage circuit C1 thus drains at least one liquid from the combustion chamber 5 and / or the lubrication enclosures 17, 18, 19 such as lubricating oil and / or fuel.

[0081] In order to limit the risk of environmental pollution, the turbomachine 1 comprises a collector 20.

[0082] The collector 20 is preferably produced by additive manufacturing. The collector 20 is preferably a single piece.

[0083] The collector 20 is configured to collect at least one liquid from the drainage circuit C1. The liquid is for example lubricating oil and / or fuel from the turbomachine 1. The collector 20 is connected to the drainage circuit C1.

[0084] With reference to [Fig.2], the collector 20 comprises an enclosure 21, at least a first inlet 22 for the first liquid, optionally an additional inlet 23 for the second liquid and a first outlet 24 for the first liquid and optionally for the second liquid.

[0085] Advantageously, the enclosure 21 is annular and has a longitudinal axis A.

[0086] In the remainder of the description, the terms "lower" and "upper" are understood to mean relative to the gravity flow of the liquid in the collector 20. Thus, the term "upper" refers to an element relatively closer to the first inlet 22 and the term "lower" refers to an element relatively further from the first inlet 22. In [Fig. 2], the liquid flows by gravity from top to bottom.

[0087] In the remainder of the description, the terms “longitudinal”, “longitudinally”, “radial”, “radially” are understood relative to the longitudinal axis A of the collector 20.

[0088] The enclosure 21 has a height h as measured along a direction parallel to the direction of flow of the liquid in the enclosure 21. In the present example, this height h is measured along the longitudinal axis A.

[0089] The enclosure 21 has, for example, a circular or polygonal cross-section. The enclosure 21 advantageously extends between a first end 25, also called the upper end, and an opposite second end 26, also called the lower end. The first and second ends 25, 26 are closed.

[0090] The first end 25 is closed for example by a cover or an upper wall 25a. The second end 26 is closed by an enclosure bottom 26a.

[0091] The enclosure 21 preferably delimits an internal cavity 27 intended to receive the first and second liquids. The internal cavity 27 is advantageously annular and centered on the longitudinal axis A. The first and second liquids flow into the internal cavity 27 by gravity through the inlets 22, 23.

[0092] The inlets 22, 23 open into the internal cavity 27. They are located at the first end 25 and are for example arranged on the cover 25a. The inlets 22, 23 are thus opposite the second end 26 of the enclosure 21. The inlets 22, 23 are for example annular. According to the example of [Fig.2], the inlets 22, 23 have an axis A1 parallel to the longitudinal axis A of the collector 20. The axis A1 of each inlet 22, 23 is offset relative to the longitudinal axis A of the collector A.

[0093] The inlets 22, 23 are for example connected to the drainage circuit C1 of the turbomachine 1.

[0094] The first outlet 24 opens outside the enclosure 21. The first outlet 24 is thus configured to evacuate the liquid outside the enclosure 21. The first outlet 24 is for example located at the second end 26 and is therefore opposite the first end 25. The first outlet 24 is therefore opposite the inlets 22, 23.

[0095] According to the example of [Fig.2], the first outlet 24 has an axis A2 perpendicular to the longitudinal axis A of the collector 20.

[0096] The first outlet 24 is for example connected to an ejector (not shown) connecting the collector 20 to the nozzle 70 for example. This allows the liquid to be burned and ejected from the turbomachine 1 through the nozzle 70.

[0097] Preferably, the collector 20 further comprises a nozzle 28 which fluidly connects the internal cavity 27 and the first outlet 24. The nozzle 28 is configured to allow the passage of the liquid at a calibrated flow rate. It comprises a first liquid inlet end 28a and an opposite second liquid outlet end 28b. The second end 28b is connected to the first outlet 24 or forms the first outlet 24.

[0098] Preferably, the nozzle 28 has an axis A3 perpendicular to the longitudinal axis A of the collector 20 and parallel to the axis A2 of the first outlet 24.

[0099] Preferably, the nozzle 28 is removably connected to the enclosure 21. This makes it possible to mount and dismount the nozzle 28 in order to clean it and limit the risks of the nozzle 28 becoming blocked. Maintenance of the nozzle 28 is thus made easier.

[0100] In order to allow the liquid to be evacuated from the collector 20 by draining through the first outlet 24, preferably, the collector 20 further comprises a ventilation duct 29. The ventilation duct 29 is located in the enclosure 21 of the collector 20. It comprises a ventilation air inlet 30 opening outside the enclosure 21 and a ventilation air outlet 31 which is connected to the first outlet 24.

[0101] The ventilation air inlet 30 is preferably located outside the enclosure 21. It is, according to the example of [Fig. 2], oriented towards the second end 26 of the enclosure 21. The ventilation air inlet 30 is for example bent. It thus has a first annular axial portion 30a and an annular radial portion 30b.

[0102] The ventilation air inlet 30 has a first passage section.

[0103] The ventilation air outlet 31 is located in the enclosure 21. It is axially opposite the ventilation air inlet 30. The ventilation air outlet 31 has an axis A4 which is parallel to the longitudinal axis A of the collector 20 and perpendicular to the axis A3 of the nozzle 28 and to the axis A2 of the first outlet 24.

[0104] The ventilation air outlet 31 preferably opens into the first outlet 24.

[0105] Preferably, the ventilation air inlets and outlets 30, 31 are connected by a ventilation line 32 located in the enclosure 21. The ventilation line 32 extends longitudinally in the enclosure 21. Such a configuration makes it possible to limit the pressure losses in the ventilation duct 29. The ventilation line 32 extends projecting outside or inside the enclosure 21.

[0106] The ventilation duct 29 further has an internal air circulation passage 29a which extends from the ventilation air inlet 30 to the ventilation air outlet 31. The internal passage 29a is for example sealed with respect to the internal cavity 27. Thus, according to this example, the air in the ventilation duct 29 cannot circulate in the internal cavity 27 and the fluid in the internal cavity 27 cannot circulate in the ventilation duct 29.

[0107] According to another example not illustrated, the internal passage 29a is fluidically connected to the internal cavity 27 by means of a venting orifice. This venting orifice is for example located on the side of the first end 25 of the enclosure 21. Such a venting orifice connecting the internal cavity 27 to the ventilation duct 29 allows the internal cavity 27 to be ventilated.

[0108] According to this example, the vent orifice has a second passage section smaller than the first passage section of the ventilation air inlet 30. The air flow rate in the ventilation air inlet 30 is thus greater than the air flow rate in the vent orifice.

[0109] The air circulates by suction effect of the ejector. The air is conveyed in the suction line 32 from the ventilation air inlet 30 to the ventilation air outlet 31.

[0110] In certain cases, in particular in the event of rupture of the seals of the lubrication enclosures 17, 18, 19, of the fuel supply circuit or of the lubrication circuit, the flow rate of fluid entering the manifold 20 through the first inlet 22 is greater than a standard flow rate. In this case, the level of liquid in the internal cavity 27 increases and it is necessary to evacuate this liquid.

[0111] In this context, the collector 20 further comprises a liquid discharge pipe 33. The discharge pipe 33 is configured to discharge the liquid from the internal cavity 27 outside the enclosure 21 when the liquid level in the enclosure 21 is greater than or equal to a threshold level SI of liquid in the internal cavity 27. The threshold level SI is measured according to the height of the enclosure 21. The threshold level SI is greater than a predetermined standard level. This predetermined standard level typically corresponds to a standard flow rate of liquid inlet into the collector 20. This standard level of liquid in the internal cavity 27 can be considered normal, since it does not reach the threshold level, that is to say the level of an alert threshold which would characterize an abnormal flow.

[0112] According to the invention, the discharge pipe 33 and the ventilation pipe 29 are independent. By "independent", it is understood that the discharge pipe 33 and the ventilation pipe 29 are not fluidically connected to each other.

[0113] The discharge pipe 33 comprises a second liquid inlet 34 located in the internal cavity 27 and a second liquid outlet 35 opening outside the enclosure 21.

[0114] The second inlet 34 has an axis A5 parallel to the longitudinal axis A of the collector 20. The second inlet 34 is located in a plane perpendicular to the longitudinal axis A and passing through the threshold level SL. In particular, the second inlet 34 has an inlet orifice located at a height less than or equal to the height of the threshold level SI in the internal cavity 27. Thus, when the liquid level in the internal cavity 27 reaches the threshold level SI, the liquid overflows into the second inlet 34.

[0115] The second inlet 34 is radially offset relative to the first inlet 22 and the additional inlet 23. This makes it possible to avoid contaminating the discharge pipe 33 by liquid entering the internal cavity 27 while the liquid level in the internal cavity 27 is below the threshold level SL.

[0116] According to the example of [Fig.2], the second outlet 35 has an axis A6 perpendicular to the longitudinal axis A of the collector 20.

[0117] Preferably, the second outlet 35 is radially opposite the first outlet A2. Also, preferably, the second outlet 35 is located on the side of the second end 26 of the enclosure 21 and is therefore axially opposite the air inlet 30.

[0118] The second inlet and outlet 34, 35 are connected by an overflow tube 36 which defines a liquid flow passage. The overflow tube 36 extends into the internal cavity 27. The overflow tube 36 comprises, for example, a first axial portion 36a extending longitudinally in the internal cavity 27 and a second transverse portion 36b extending transversely in the internal cavity 27. The first axial portion 36a is connected to the second inlet 34 and the second transverse portion 36b connects the first axial portion 36a to the second outlet 35.

[0119] The discharge pipe 33 has a diameter for example between 2 mm and 10 mm. Such a diameter of the discharge pipe makes it possible to minimize the risk of pollutants being sucked in, in particular when the ventilation pipe 29 is in fluid communication with the internal cavity 27. Also, thanks to the different air flow rates of the air inlet 30 and the vent orifice, the risk of pollutants being sucked in from outside the enclosure 21 through the discharge pipe 33 and contamination of the internal cavity 27 is limited.

[0120] Furthermore, such leaks can have harmful consequences on the turbomachine 1. It is therefore preferable to be able to detect such leaks. In this context, preferably, the collector 20 further comprises a device 40 for detecting and signaling the reaching of the threshold level SI by the liquid level in the internal cavity 27. The detection and signaling device 40 is configured to detect and signal when the threshold level SI of liquid in the enclosure 21 is reached.

[0121] The detection and signaling device 40 of the threshold level SI is mounted on the enclosure 21 and is preferably located opposite the first end 25 of the enclosure 21.

[0122] According to one example, the detection and signaling device 40 comprises

[0123] a light signaling the threshold level SI in the form of a first color.

[0124] According to another example illustrated in [Fig. 3], the detection and signaling device 40 comprises a porthole or a window 41 making it possible to detect and signal the presence of liquid in the discharge pipe 33. The porthole or the window 41 is mounted opposite the discharge pipe 33, in particular opposite a lower end of the axial portion 36a of the overflow tube 36. The detection and signaling device 40 is therefore mounted opposite the second inlet 34.

[0125] The operation of the collector 20 according to the invention will now be described with reference to FIGS. 2 and 3.

[0126] Liquid leaks from the lubrication enclosures 17, 18, 19 or the fuel from the combustion chamber 5 are for example drained through the drainage circuit CL. The drained liquid enters the collector 20 through at least the first inlet 22 at a standard flow rate. The liquid then flows into the internal cavity 27 by gravity. The liquid in the internal cavity 27 is drained through the first outlet 24 at a standard outlet flow rate. The drained liquid can be discharged into the nozzle 70.

[0127] In certain cases, for example during degradation or even rupture of the seals for example, the flow rate of liquid entering the enclosure 21 may be greater than the standard flow rate and the outlet flow rate. The liquid level in the internal cavity 27 may accumulate and may reach the threshold level SI as illustrated in [Fig. 3]. The liquid in the internal cavity 27 overflows into the discharge pipe 33 and is discharged through the second outlet 35. The detection and signaling device 40 then detects this threshold level SL. The operator(s) being alerted can then carry out a leak search campaign and a maintenance operation.

[0128] Thus, thanks to the invention, the circulation of air in the ventilation duct 29 is independent of the evacuation of liquid via the evacuation duct 33. This makes it possible to reduce the pollution of the evacuation duct 33 during the circulation of air and therefore to limit the risk of detection of false abnormal leaks.

[0129] Also, thanks to the independence of these ducts, it is possible to position the air inlet 30 independently of the second liquid outlet 35. The second liquid outlet 35 is generally dependent on the aircraft installations. Thanks to the configuration of the invention, the air inlet 30 can be positioned independently of the aircraft installations, further reducing the risk of pollution of the discharge duct 33 by pollutants sucked in by the ventilation duct 29.

Claims

Claims

1. Collector (20) of at least one liquid for an aircraft turbomachine (1), the collector (20) comprising: - an enclosure (21) delimiting an internal cavity (27) intended to receive the liquid, - at least a first inlet (22, 23) of the liquid opening into the internal cavity (27), - a first outlet (24) of liquid opening outside the enclosure (21), - a ventilation duct (29) comprising: - a ventilation air inlet (30) located outside the enclosure (21), and - a ventilation air outlet (31) which is connected to the first outlet (24) of liquid, - a liquid discharge duct (33) configured to discharge the liquid from the internal cavity (27) outside the enclosure (21) when the liquid level in the enclosure (21) is greater than or equal to a threshold level (SI) of liquid in the internal cavity (27), the discharge pipe (33) comprising: - a second liquid inlet (34) located in the internal cavity (27),and - a second liquid outlet (35) opening outside the enclosure (21), characterized in that the ventilation and liquid evacuation pipes (29, 33) are independent of each other.,

2. Collector according to the preceding claim, characterized in that the ventilation duct (29) comprises an air circulation passage (29a) sealed with respect to the internal cavity (27).

3. A manifold according to claim 1, characterized in that the ventilation duct (29) comprises an air circulation passage (29a) which is fluidically connected to the internal cavity (27) by a venting orifice of the internal cavity (27).

4. Collector according to any one of the preceding claims, characterized in that the enclosure (21) extends longitudinally along a longitudinal axis (A) between a first end (25) and a second end (26) closed by a bottom wall (26a), the ventilation air inlet (30) of the ventilation duct (29) being located on the side of the first end (25).

5. Collector according to the preceding claim, characterized in that the ventilation air inlet (30) is axially opposite the second outlet (35).

6. Collector according to the preceding claim, characterized in that the first and second liquid outlets (24, 35) are located on the side of the second end (26) and are radially opposite relative to the longitudinal axis (A).

7. Collector according to the preceding claim, characterized in that the ventilation air inlet (30) of the suction pipe (29) is oriented towards the second end (26).

8. Collector according to one of claims 4 to 7, characterized in that the ventilation duct (29) comprises a ventilation line (32) connecting the ventilation air inlet and outlet (30, 31) and extending longitudinally between the first and second ends (25, 26).

9. Collector according to the preceding claim, characterized in that the ventilation line (32) is located in the internal cavity (27).

10. Collector according to any one of the preceding claims, characterized in that it is a single-piece.

11. Collector according to any one of the preceding claims, characterized in that it is produced by additive manufacturing.

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