COLLECTOR OF AT LEAST ONE LIQUID FOR AN AIRCRAFT TURBOMACHINE

Abstract

The invention relates to a collector (20) comprising: - an enclosure (21) extending between a first end (25) and a second end (26), - an internal cavity (27), - at least one first inlet (22, 23) for the liquid opening into the internal cavity (27) and located opposite the first end (25), - a first outlet (24) for liquid opening outside the enclosure (21) and located opposite the first inlet (22, 23), and - a ventilation duct (29) comprising: - a ventilation air inlet (34), and - a ventilation air outlet (31) connected to the first outlet (24), characterized in that the collector (20) further comprises a device (42) for collecting and storing particles (P) arranged opposite the first end (25). abstract 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 protect the connected components of the turbomachine from this lubricating liquid, 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 leaks 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 typically drained to limit the risk of coking.

[0008] In this context, the turbomachine comprises a drainage circuit for these liquids.

[0009] In order to limit environmental pollution caused by these liquids, the tur The machine typically includes a collector for this drained liquid. The collector typically includes an enclosure defining an internal cavity for receiving the liquid and a first inlet for this liquid into the internal cavity. The collector further includes 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 rate of the liquid is abnormal and the liquid inlet rate in the collector is much higher than the outlet 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 air inlet of the air suction line.

[0014] Such abnormal leaks could be of a nature to reduce the margin for extinction. 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 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 pipe, pollutants can enter the discharge pipe 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 the availability of the aircraft.

[0018] Consequently, there is a need to provide a collector of at least a first 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 extending longitudinally along a longitudinal axis between a first end and a second end,

[0021] - an internal cavity located in the enclosure and intended to receive the liquid,

[0022] - at least a first inlet of the liquid opening into the internal cavity and located opposite the first end,

[0023] - a first liquid outlet opening outside the enclosure and located at the opposite of the first entry, and

[0024] - a ventilation duct comprising:

[0025] - a ventilation air inlet, and

[0026] - a ventilation air outlet connected to the first outlet.

[0027] The collector is remarkable in that it further comprises a particle collection and storage device arranged opposite the first end.

[0028] Thanks to the collection and storage device of the collector of the invention, it is possible to recover the particles from the internal cavity and to limit the risk of clogging of the first outlet of the collector.

[0029] Thus, the risks of the liquid accumulating up to the threshold level in the internal cavity are reduced, which makes it possible to limit the risk of detecting false abnormal leaks.

[0030] The detection of collector leaks is therefore more reliable.

[0031] The invention may comprise one or more of the following features, taken in isolation from each other or in combination with each other:

[0032] - the collection and storage device comprises an annular tank,

[0033] - the tank is removably connected to the enclosure,

[0034] - the enclosure comprises at least one internal wall for guiding the particles towards the collection and storage device,

[0035] - the inner wall comprises an annular portion extending around the device of collection and storage,

[0036] - the inner wall comprises a truncated cone-shaped portion which flares out from the portion annular and towards the first end of the enclosure,

[0037] - the truncated portion is asymmetrical,

[0038] - a nozzle connecting the first outlet to the internal cavity, the collection and storage being connected to the nozzle,

[0039] - 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 level, the discharge pipe comprising:

[0040] - a second liquid inlet located in the internal cavity, and

[0041] - a second liquid outlet opening outside the enclosure,

[0042] - the internal wall is located between the threshold level and the bottom of the enclosure. Brief description of the figures

[0043] 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:

[0044] [Fig-1] [Fig.l] is a longitudinal sectional view of an example of a tur- aircraft machine according to the invention,

[0045] [Fig.2] [Fig.2] is a longitudinal sectional view of a collector according to the invention. Detailed description of the invention

[0046] 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.

[0047] The turbomachine 1 is modular. It comprises a plurality of modules assembled together.

[0048] The turbomachine 1 extends along a longitudinal axis X. A gas flow F flows in the turbomachine 1.

[0049] 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.

[0050] 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.

[0051] 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 rotors 6a, 7a are composed of a plurality of stages each comprising a bladed wheel.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] According to another example not shown, the fan 2 is of the non-ducted type.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] The turbomachine 1 may further comprise an inter-vein compartment v3 located between the primary vein v1 and the secondary vein v2.

[0064] 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.

[0065] 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.

[0066] 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.

[0067] 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.

[0068] Each bearing comprises, for example, a rolling bearing. The rolling bearing is, for example, at least one row of balls or rollers.

[0069] 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.

[0070] 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 bearings 15e, 15f are arranged.

[0071] Depending on the configuration of the turbomachine 1, the number of bearings 15 and lubrication chambers 16 may vary.

[0072] 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.

[0073] 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- turbines 14 and is internally delimited by the high pressure shaft 9.

[0074] 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.

[0075] 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.

[0076] The turbomachine 1 further comprises a circuit for supplying the combustion chamber 5 with fuel.

[0077] 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.

[0078] In this context, the turbomachine 1 further comprises at least one drainage circuit C1 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.

[0079] In order to limit the risk of environmental pollution, the turbomachine 1 comprises a collector 20.

[0080] The collector 20 is configured to collect at least one liquid from the drainage circuit CL. The liquid is, for example, lubricating oil and / or fuel from the turbomachine 1. The collector 20 is connected to the drainage circuit CL.

[0081] With reference to [Fig.2], the collector 20 comprises an enclosure 21, at least a first inlet 22 for the liquid, optionally an additional inlet 23 for the liquid and a first outlet 24 for the liquid.

[0082] Advantageously, the enclosure 21 is annular and has a longitudinal axis A.

[0083] 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 high down.

[0084] In the remainder of the description, the terms “longitudinal”, “longitudinally”, “radial”, “radially” are understood relative to the longitudinal axis A of the collector 20.

[0085] 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.

[0086] 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.

[0087] 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.

[0088] The enclosure 21 preferably delimits an internal cavity 27 intended to receive the liquid. 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. According to the example of [Fig. 2], the cavity 27 has a liquid level L equal to a predetermined standard level.

[0089] 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. The inlets 22, 23 are for example annular. They are offset relative to the longitudinal axis A of the collector 20. 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.

[0090] The inlets 22, 23 are for example connected to the drainage circuit C1 of the turbomachine 1.

[0091] 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.

[0092] 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.

[0093] 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.

[0094] Preferably, the collector 20 further comprises a nozzle 28 which fluidly connects the internal cavity 27 and the first outlet 27. The nozzle 28 is configured to allow the passage of the liquid at a calibrated flow rate. The nozzle 28 is mounted in the internal cavity 27. It comprises a first end 28a for the inlet of the first and / or second liquid and an opposite second end 28b for the outlet of the first and / or second liquid. The second end 28b is connected to the first outlet 24 or forms the first outlet 24.

[0095] 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.

[0096] 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.

[0097] 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 and a ventilation air outlet 31 which opens into the first outlet 24.

[0098] The ventilation air inlet 30 has, for example, an axis A4 which is perpendicular to the longitudinal axis A of the collector 20.

[0099] The ventilation air outlet 31 has an axis A5 which is parallel to the longitudinal axis A of the collector 20 and perpendicular to the axis A3 of the nozzle 28.

[0100] The ventilation air inlet and outlet 30, 31 are advantageously located opposite the first end 25 of the collector 20. Preferably, the ventilation air inlet and outlet 30, 31 are radially opposite.

[0101] According to an exemplary embodiment, the ventilation air inlet and outlet 30, 31 are connected by a ventilation line 32. The ventilation line 32 has, for example, in longitudinal section an inverted U shape in longitudinal section. The ventilation line 32 thus comprises a first section 32a and a second section 32b connected together by an intermediate section 32c. The first and second sections 32a, 32b extend longitudinally in the enclosure 21 while the intermediate section 32c extends transversely in the enclosure 21.

[0102] 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.

[0103] 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.

[0104] In this context, the collector 20 further comprises an evacuation pipe 33 of liquid. 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 entering 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 rate.

[0105] 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.

[0106] The second inlet 34 has an axis A6 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 equal to the height of the threshold level SI in the internal cavity 27. Thus, when the liquid level in the internal cavity reaches the threshold level SI, the liquid overflows into the second inlet 34.

[0107] 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.

[0108] According to the example of [Fig.2], the second outlet 35 is connected or opens into the ventilation air inlet 30. The second outlet 35 and the ventilation air inlet 30 are the same.

[0109] 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. 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.

[0110] 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 by the liquid level in the internal cavity 27 of the threshold level SL. The detection and signaling device 40 is configured to detect and signal when the SI threshold level of liquid in enclosure 21 is reached.

[0111] 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 26 of the enclosure 21.

[0112] According to one example, the detection and signaling device 40 comprises

[0113] a light signaling the threshold level SI in the form of a first color.

[0114] According to another example illustrated in [Fig.2], 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.

[0115] According to the invention, the collector 20 comprises a device 42 for collecting and storing particles P arranged in the enclosure bottom 26a. The collection and storage device 42 makes it possible to collect and store the polluting particles P which may enter the internal cavity 27, in particular via the air inlet 30. The particles P are in particular solid particles such as sand. These particles P can obstruct the first outlet 24, in particular the nozzle 28 and cause an increase in the liquid level in the enclosure 21 until it reaches the threshold level SL. The threshold level SI being reached, the detection and signaling device 40 signals such a level and a long and tedious leak search campaign is launched. Such a false leak detection mobilizes the operators and immobilizes the turbomachine and the aircraft.

[0116] Thanks to this collection and storage device 42, the risk of detecting false leaks is therefore reduced.

[0117] The collection and storage device 42 comprises an annular tank 43. The tank 43 has a U-shape in longitudinal section. The tank 43 thus comprises a cylindrical portion 44 having an open upper end and a lower end closed by an annular transverse wall 45.

[0118] Preferably, the collection and storage device 42 is connected to the nozzle 28. For example, the nozzle 28 is mounted by screwing onto the tank 43, in particular onto the cylindrical portion 44 of the tank 43.

[0119] To promote the collection of particles P, the enclosure 21 of the collector 20 advantageously comprises an internal wall 46 for guiding the particles P towards the collection and storage device 42. The internal wall 46 delimits the internal cavity 27. The internal wall 46 comprises an upper annular portion 47, a portion lower annular portion 48 and a frustoconical portion 49 connecting the upper and lower annular portions 47, 48.

[0120] The upper annular portion 47 has an internal diameter greater than the internal diameter of the lower annular portion 48. The lower annular portion 48 is arranged around the tank 43, in particular around the cylindrical portion 44.

[0121] Preferably, the tank 43 is removably mounted inside the lower annular portion 48. This makes it easier to maintain the tank 43, in particular the disassembly and reassembly of the tank 43.

[0122] The truncated portion 49 widens from the lower annular portion 48 towards the first end 25 of the enclosure 21, and therefore towards the upper annular portion 47.

[0123] Furthermore, the frustoconical portion 49 is asymmetrical relative to the longitudinal axis A of the enclosure 21. Thus, the frustoconical portion 49 has an axis A7 offset relative to the longitudinal axis A. The frustoconical portion 49 has a first inclined surface 49a and a second inclined surface 49b. The first inclined surface 49a extends in a plane forming an angle a1 of between 5° and 80° with the longitudinal axis A. The second inclined surface 49b extends in a plane forming an angle a2 of between 5° and 80° with the longitudinal axis A. Such slopes promote the guidance of the particles P in the collection and guidance device 42.

[0124] The operation of the collector 20 according to the invention will now be described.

[0125] 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.

[0126] In certain cases, for example when the seals break, 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 SL. 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.

[0127] Thanks to the collector 20 according to the invention, the particles P are collected by the collection and storage device 42, thus reducing the risk of these particles penetrating and blocking the first liquid outlet 24 of the collector 20.

[0128] The risk of blockage of this first outlet 24 being reduced, the threshold level SI is reached mainly because of at least one abnormal leak.

[0129] The collector 20 thus has an improved and therefore more reliable detection of abnormal leaks.

Claims

Claims

1. Collector (20) of at least one liquid for an aircraft turbomachine (1), the collector (20) comprising: - an enclosure (21) extending longitudinally along a longitudinal axis (A) between a first end (25) and a second end (26), - an internal cavity (27) located in the enclosure (21) and intended to receive the liquid, - at least a first inlet (22, 23) of the liquid opening into the internal cavity (27) and located opposite the first end (25), - a first outlet (24) of liquid opening outside the enclosure (21) and located opposite the first inlet (22, 23), and - a ventilation duct (29) comprising: - a ventilation air inlet (34), and - a ventilation air outlet (31) connected to the first outlet (24), characterized in that the collector (20) further comprises a device (42) for collecting and storing particles (P) arranged opposite the first end (25).

2. Collector according to the preceding claim, characterized in that the collection and storage device (42) comprises an annular tank (43).

3. Collector according to the preceding claim, characterized in that the tank (43) is removably connected to the enclosure (21).

4. Collector according to any one of the preceding claims, characterized in that the enclosure (21) comprises at least one internal wall (46) for guiding the particles (P) towards the collection and storage device (42).

5. Collector according to the preceding claim, characterized in that the internal wall (46) comprises an annular portion (48) extending around the collection and storage device (42).

6. Collector according to the preceding claim, characterized in that the internal wall (46) comprises a frustoconical portion (49) which flares from the annular portion (48) and in the direction of the first end (25) of the enclosure (25).

7. Collector according to the preceding claim, characterized in that the frustoconical portion (49) is asymmetrical.

8. A collector according to any preceding claim, ca- characterized in that it comprises a nozzle (28) connecting the first outlet (24) to the internal cavity (27), the collection and storage device (42) being connected to the nozzle (28).

9. Collector according to any one of the preceding claims, characterized in that it comprises a liquid discharge pipe (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), 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).

10. Collector according to claims 9 and any one of claims 2 to 4, characterized in that the internal wall (46) is located between the threshold level (SI) and the enclosure bottom (26a).

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