Manifold for at least one liquid for an aircraft turbine engine

Abstract

The invention relates to a manifold (20) comprising: - at least one first inlet (22, 23); - a first outlet (24); - a liquid discharge pipe (33) for discharging the liquid out of the enclosure (21) when the liquid level in the internal cavity (27) is greater than or equal to a first threshold level (S1) of liquid in the internal cavity (27); - a signalling pipe (37) located in the enclosure (21) and configured to collect liquid when the liquid level in the internal cavity (27) is greater than or equal to a second threshold level (S2) of liquid in the internal cavity (27), which is lower than the first threshold level (S1); - a device (40) for detecting and signalling that the liquid level in the internal cavity (27) has reached one and / or the other of the first and second threshold levels (S1, S2).

Description

[0001] DESCRIPTION

[0002] TITLE: COLLECTOR OF AT LEAST ONE LIQUID FOR AN AIRCRAFT TURBOMACHINE

[0003] Technical field of the invention

[0004] The invention relates to the field of collectors of at least one liquid, for an aircraft turbomachine.

[0005] The invention also relates to methods of maintaining aircraft turbomachines.

[0006] Technical background

[0007] A turbomachine, particularly 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.

[0008] The low-pressure compressor rotor is typically connected to the low-pressure turbine rotor via a low-pressure shaft. The high-pressure compressor rotor is connected to the high-pressure turbine rotor via a high-pressure shaft.

[0009] The turbomachine further comprises a fan which is located upstream of the gas generator and which is rotated 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.

[0010] 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 functioning. In order to protect the related 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 supplies the lubrication chamber with lubricating oil. In addition, each lubrication chamber is delimited by sealing systems comprising seals which limit the leakage of lubricating liquid outside the lubrication chambers.

[0011] 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.

[0012] Lubrication chambers, fuel systems, and lubrication systems can experience fluid leaks, including fuel and / or lube oil leaks. Although these leaks flow at a rate considered normal, they represent potential sources of environmental pollution. Therefore, the fuel in the combustion chamber is generally drained to limit the risk of coking.

[0013] The turbomachine therefore generally includes at least one drainage circuit for these liquids.

[0014] In order to limit 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 in the internal cavity. The collector further comprises a first outlet for this liquid opening outside the enclosure.

[0015] There are also leaks that may result from abnormal operation of the fuel or lubrication circuits or from degradation or 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 significantly 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 discharge pipe configured to discharge 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 discharge pipe thus comprises a second liquid inlet located in the internal cavity and a second liquid outlet opening outside the collector enclosure.The second inlet is typically located at a height equal to the threshold liquid level in the internal cavity so that the liquid flows into the overflow drain line.

[0016] Such leaks could reduce the turbomachine's shutdown margin or reduce the turbomachine's emergency operating availability margin. It is therefore important for operators to be able to detect these abnormal leaks.

[0017] In this context, in order to detect and signal an abnormal leak of liquid in the turbomachine, the manifold 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 for observing and / or signaling liquid in the discharge pipe, such as a sight glass 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.

[0018] However, such a manifold leak detection and reporting device is not entirely satisfactory. Indeed, this detection and reporting device does not allow the origin of the leak to be identified, so it is necessary to carry out a search campaign for the leak(s) to identify their origin. It is only after such a search campaign that it is possible to take charge of the leak and resolve it.

[0019] However, such a research 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 determine the leak rates of each seal. Such research 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.

[0020] 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 simple and rapid manner in order to reduce the burden on operators, facilitate maintenance operations and improve the availability of the aircraft.

[0021] Summary of the invention

[0022] To this end, the invention proposes a collector of at least a first liquid for an aircraft turbomachine, the collector comprising:

[0023] - an enclosure delimiting an internal cavity intended to receive at least the first liquid,

[0024] - at least one first inlet of the first liquid opening into the internal cavity,

[0025] - a first liquid outlet opening outside the enclosure,

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

[0027] - a second liquid inlet located in the internal cavity, - a second liquid outlet opening outside the enclosure.

[0028] The collector is remarkable in that it further includes:

[0029] - a signal line located in the enclosure and configured to collect liquid when the liquid level in the internal cavity is greater than or equal to a second threshold level of liquid in the internal cavity, which is lower than the first threshold level, the signal line comprising:

[0030] - a third liquid inlet located in the internal cavity, and

[0031] - a device for detecting and signaling when the liquid level in the internal cavity reaches one and / or the other of the first and second threshold levels.

[0032] The collector according to the invention thus comprises a signaling pipe which makes it possible to collect the liquid in the internal cavity when the liquid level in the internal cavity is higher than a second threshold level of liquid in the internal cavity, this second threshold level being lower than the first threshold level.

[0033] We therefore understand that when the second threshold level is reached, the liquid first flows into the signal pipe. Then, when the first threshold level is reached, the liquid then flows into the discharge pipe.

[0034] The collector further comprises a device for detecting and signaling the first and / or second threshold levels. Thus, when the second threshold level is reached, the operators are alerted and can anticipate the first threshold level, which makes it possible to plan a leak search campaign, and therefore the shutdown of the turbomachine and the unavailability of the aircraft. The first threshold level is detected for safety reasons.

[0035] Thanks to the invention, it is possible to anticipate and plan a leak detection campaign, making it possible to reduce the burden on operators and limit the unavailability of the turbomachine and therefore of the aircraft. The invention may comprise one or more of the following features, taken in isolation from one another or in combination with one another:

[0036] -- the first and second threshold levels correspond to a height of liquid in the internal cavity,

[0037] -- the first inlet is located at a first end of the enclosure, called the upper end and the first outlet is located at a second opposite end of the enclosure, called the lower end,

[0038] -- the second liquid inlet is located in a plane perpendicular to the longitudinal axis of the enclosure and passing through the first threshold level,

[0039] -- the third liquid inlet is located in a plane perpendicular to the longitudinal axis of the enclosure and passing through the second threshold level,

[0040] - the enclosure extends longitudinally along a longitudinal axis between a first end and a second end closed by a bottom wall, the third inlet being located axially closer to the bottom wall than the second inlet,

[0041] - the signal line extends longitudinally in the internal cavity,

[0042] - the second and third liquid inlets are radially offset from the first liquid inlet,

[0043] - the detection and signaling device comprises at least one first detection and signaling member comprising at least one indicator light or a porthole,

[0044] - the first detection and signaling device is connected to both the evacuation pipe and the signaling pipe,

[0045] - the detection and signaling device comprises a second detection and signaling member connected to the signaling pipe, the first detection and signaling member being connected to the discharge pipe,

[0046] - the signal line includes a third liquid outlet,

[0047] - the collector is produced by additive manufacturing. The invention also relates to a method for maintaining an aircraft turbomachine, the maintenance method comprising the following steps:

[0048] (a) provide a turbomachine comprising a manifold according to any of the preceding characteristics,

[0049] (b) filling the internal cavity with the first liquid through the first inlet and discharging the first liquid from the enclosure through the first outlet,

[0050] (c) detecting the second threshold level of liquid in the internal cavity,

[0051] (d) optionally, detecting the first threshold level of liquid in the internal cavity, and

[0052] (e) schedule maintenance between stages.

[0053] Brief description of the figures

[0054] 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:

[0055] [Fig.1] Figure 1 is a longitudinal sectional view of an example of an aircraft turbomachine according to the invention,

[0056] [Fig.2] Figure 2 is a longitudinal sectional view of a collector according to the invention,

[0057] [Fig.3] Figure 3 is a block diagram of a maintenance method for the turbomachine, according to the invention.

[0058] Detailed description of the invention

[0059] An example of an aircraft turbomachine 1 according to the invention is shown in FIG. 1. The turbomachine 1 is, for example, a dual-flow turbojet. The turbomachine 1 may have any other architecture and may, for example, be in the form of a turboprop.

[0060] The turbomachine 1 is modular. It comprises a plurality of modules assembled together. The turbomachine 1 extends along a longitudinal axis X. A gas flow F flows into the turbomachine 1.

[0061] 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 Figures 1 and 2.

[0062] 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.

[0063] 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.

[0064] 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.

[0065] 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.

[0066] The low pressure shaft 8 and high pressure shaft 9 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.

[0067] 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 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.

[0068] 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 figure 1, 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.

[0069] According to another example not shown, the blower 2 is of the unducted type.

[0070] 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.

[0071] 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.

[0072] 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.

[0073] 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.

[0074] 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.

[0075] The turbomachine 1 may further comprise an inter-vein compartment v3 located between the primary vein v1 and the secondary vein v2.

[0076] 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.

[0077] 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.

[0078] 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.

[0079] 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.

[0080] Each bearing includes, for example, a rolling bearing. The rolling bearing is, for example, at least one row of balls or rollers.

[0081] 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.

[0082] 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.

[0083] Depending on the configuration of the turbomachine 1, the number of bearings 15 and lubrication chambers 16 may vary.

[0084] 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.

[0085] 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.

[0086] 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.

[0087] 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.

[0088] The turbomachine 1 further comprises a circuit for supplying fuel to the combustion chamber 5.

[0089] Despite the sealing of the lubrication chambers 17, 18, 19, lubrication oil leaks may occur. Therefore, the fuel from the combustion chamber 5 must be evacuated in order to limit the risk of coking.

[0090] 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.

[0091] In order to limit the risk of environmental pollution, the turbomachine 1 comprises a collector 20. 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.

[0092] With reference to Figure 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.

[0093] Advantageously, the enclosure 21 is annular and has a longitudinal axis A.

[0094] 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.

[0095] In the remainder of the description, the terms “longitudinal”, “longitudinally”, “radial”, “radially” are understood to refer to the longitudinal axis A of the collector 20.

[0096] 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.

[0097] 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.

[0098] 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.

[0099] 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. According to the example of FIG. 2, the cavity 27 has a liquid level L equal to a predetermined standard level which corresponds to a standard flow rate of liquid entering the collector. This standard level L of liquid in the cavity can be considered normal, since it does not reach the level of an alert threshold which would characterize an abnormal flow rate. 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 25b. For example, entries 22, 23 are annular.They are offset relative to the longitudinal axis A of the collector 20. According to the example of figure 2, the inlets 22, 23 have an axis A1 parallel to the longitudinal axis A of the collector 20.

[0100] The inlets 22, 23 are for example connected to the drainage circuit of the turbomachine 1.

[0101] 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.

[0102] According to the example of Figure 2, the first outlet 24 has an axis A2 perpendicular to the longitudinal axis A of the collector 20.

[0103] The first outlet 24 is for example connected to an ejector (not shown) connecting the manifold 20 to the nozzle 70 for example. This allows the liquid to be burned and ejected from the turbomachine 1 through the nozzle 70.

[0104] Preferably, the manifold 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 at a calibrated flow rate of the first and / or second liquid. The nozzle 28 is mounted in the internal cavity 27. It comprises a first inlet end 28a for the first and / or second liquid and an opposite second outlet end 28b for the first and / or second liquid. The second end 28b is connected to the first outlet 24 or forms the first outlet 24.

[0105] 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.

[0106] 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 clogging the nozzle 28. Maintenance of the nozzle 28 is thus facilitated. In order to allow the liquid to be evacuated from the collector 20 by draining, for example through the first outlet 24, preferably, the collector 20 may further comprise a ventilation duct. The ventilation duct is located in the enclosure 21 of the collector 20. It comprises a ventilation air inlet located or opening outside the enclosure 21 and a ventilation air outlet which opens into the first outlet 24.

[0107] The air circulates by the suction effect of the ejector. The air is conveyed in the ventilation duct from the ventilation air inlet to the ventilation air outlet.

[0108] In certain cases, in particular in the event of a 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.

[0109] In this context, the collector 20 further comprises a liquid discharge pipe 33. The discharge pipe 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 first threshold level S1 of liquid in the internal cavity 27. The first threshold level S1 is measured according to the height of the enclosure 21. The first threshold level S1 is greater than the predetermined standard threshold.

[0110] 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.

[0111] The second inlet 34 has an axis 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 first threshold level S1. In particular, the second inlet 34 has an inlet orifice located at a height equal to the height of the first threshold level S1 in the internal cavity 27. Thus, when the liquid level in the internal cavity reaches the first threshold level S1, the liquid overflows into the second inlet 34. 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 with liquid entering the internal cavity 27 while the liquid level in the internal cavity 27 is lower than the first threshold level S1.

[0112] According to the example of Figure 2, the second outlet 35 is connected or opens into the ventilation air inlet 30. The second outlet 35 has an axis A7 perpendicular to the longitudinal axis A of the collector 20. The axis A7 of the second outlet 35 can be confused with the axis A4 of the ventilation air inlet 30.

[0113] 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.

[0114] Such leaks can have harmful consequences on the turbomachine 1 . It is therefore customary to launch a campaign to search for the origin of the leak(s). Such a campaign is tedious and requires shutting down the turbomachine 1 , directly impacting the availability of the aircraft. In order to limit the consequences of these leaks, and in particular this unavailability of the aircraft, the manifold 20 further comprises a signaling pipe 37 located in the enclosure 21 .

[0115] Referring to Figure 2, the signal line 37 is configured to collect liquid when the liquid level in the enclosure 21 is greater than a second threshold level S2 of liquid in the internal cavity 27. The second threshold level S2 is lower than the first threshold level S1. The first and second threshold levels correspond to the height of liquid in the internal cavity 27 as measured according to the height of the enclosure 21. In other words, the first and second threshold levels correspond to the height of liquid in the internal cavity 27 as measured in a direction parallel to the direction of flow of the liquid in the internal cavity 27.

[0116] The signaling pipe 37 comprises a third liquid inlet 38 located in the internal cavity 27 and optionally a third liquid outlet 39. The third inlet 38 has an axis A8 parallel to the longitudinal axis A of the collector 20. The third inlet 38 is located in a plane perpendicular to the longitudinal axis A and passing through the second threshold level S2. In particular, the third inlet 34 has an inlet orifice located at a height equal to the height of the second threshold level S2 in the internal cavity 27. Thus, when the liquid level in the internal cavity 27 reaches the second threshold level S2, the liquid overflows into the third inlet 38. The third inlet 38 is radially offset relative to the first inlet 22 and the additional inlet 23.

[0117] The third inlet 38 is axially offset relative to the second inlet 34. In particular, the third inlet 38 is axially closer to the second end 26 of the enclosure 21 than the second inlet 34 and therefore axially closer to the bottom wall 26a. The third inlet 38 is axially further from the first inlet 22 than the second inlet 34. Indeed, the third inlet 38 is located at a height in the enclosure 21 lower than a height at which the second inlet 34 is located.

[0118] The third outlet 39 is fluidically connected to the outside of the enclosure 21. It is for example connected to the discharge pipe 33. In order to control the flow rate of the liquid exiting through this third outlet 39, the latter can be equipped with a diaphragm.

[0119] The signal line 37 extends in particular longitudinally in the internal cavity 27. The signal line 37 extends longitudinally in the internal cavity 27 between an upper end 37a having the third inlet 38 and an axially opposite lower end 37b. The signal line 37 further has a fluid passage 37c which extends between the upper and lower ends 37a, 37b.

[0120] According to the invention, the collector 20 further comprises a device 40 for detecting and signaling the first and / or second threshold levels S1, S2. The detection and signaling device 40 is configured to detect and signal when the first and / or second threshold levels S1, S2 of liquid in the enclosure 21 are reached.

[0121] The detection and signaling device 40 of the first threshold S1 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 a detection and signaling member configured to independently signal the first and second threshold levels S1, S2.

[0123] The detection and signaling member is, in this example, connected both to the discharge pipe 33 and to the signaling pipe 37.

[0124] The detection and signaling member comprises, for example, a light signaling the first threshold level S1 in the form of a first color and signaling the second threshold level S2 in the form of a second color which is different from the first color.

[0125] According to another example illustrated in FIG. 2, the detection and signaling device 40 comprises a first detection and signaling member

[0126] 41 configured to signal the first threshold level S1 and a second detection and signaling member 42 configured to signal the second threshold level S2. The first detection and signaling member 41 is connected to the discharge pipe 33 and the second detection and signaling member

[0127] 42 is connected to reporting line 37.

[0128] The first and second detection and signaling members 41, 42 comprise, for example, first and second indicator lights.

[0129] According to an alternative, the first and second detection and signaling members 41, 42 each comprise a porthole or a window making it possible to detect and signal the presence of liquid in the evacuation and signaling pipes 36, 37. Each porthole or window is mounted respectively opposite the evacuation and signaling pipes 36, 37. In particular, a first porthole 41 is mounted opposite the axial portion 36a of the overflow pipe 36, opposite the second inlet 34 and a second porthole 42 is mounted opposite the lower end 37b of the signaling pipe 37.

[0130] The operation of the collector 20 according to the invention will now be described.

[0131] Liquid leaks from the lubrication chambers 17, 18, 19 or the fuel from the combustion chamber 5 are for example drained through the drainage circuit C1. 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.

[0132] In certain cases, for example during a rupture of the seals for example, the flow rate of liquid entering the enclosure 21 may be higher than the standard flow rate and the outlet flow rate. The liquid level in the internal cavity 27 may accumulate and may reach the second threshold level S2. The liquid in the internal cavity 27 overflows into the signaling pipe 37. The detection and signaling device 40 then detects this second threshold level S2 while the first threshold level S1 has not yet been detected. The operator(s) being alerted can then plan a maintenance operation without stopping the turbomachine 1.

[0133] Thanks to the invention, the maintenance operation can be planned, reducing the burden on operators. Also, the availability of the turbomachine 1 is improved since the shutdown of the turbomachine 1 can be anticipated and planned. A maintenance method of the turbomachine 1 will now be described with reference to FIG. 3.

[0134] The maintenance method comprises the following steps: (a) providing the turbomachine 1 and the manifold 20 mounted in the turbomachine

[0135] (b) filling the internal cavity 27 with the first liquid through the first inlet 22 and discharging the first liquid from the enclosure 21 through the first outlet 24, (c) detecting the second threshold level S2 of liquid in the internal cavity 27,

[0136] (d) optionally, detecting the first threshold level S1 of liquid in the internal cavity 27, and

[0137] (e) schedule a maintenance operation between steps (c) and (d).

Claims

CLAIMS 1. Collector (20) of at least a first liquid for an aircraft turbomachine (1), the collector (20) comprising: - an enclosure (21) delimiting an internal cavity (27) intended to receive at least the first liquid, - at least one first inlet (22, 23) of the first liquid opening into the internal cavity (27), - a first outlet (24) of liquid opening outside the enclosure (21), - 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 internal cavity (27) is greater than or equal to a first threshold level (S1) of liquid in the internal cavity (27), the discharge pipe (33) comprising: - a second liquid inlet (34) located in the internal cavity (27), - a second liquid outlet (35) opening outside the enclosure (21), characterized in that the collector (20) further comprises: - a signaling line (37) located in the enclosure (21) and configured to collect liquid when the liquid level in the internal cavity (27) is greater than or equal to a second threshold level (S2) of liquid in the internal cavity (27), which is lower than the first threshold level (S1), the signaling line (37) comprising: - a third liquid inlet (38) located in the internal cavity (27), the collector (20) further comprising: - a device (40) for detecting and signaling the reaching by the liquid level in the internal cavity (27) of one and / or the other of the first and second threshold levels (S1, S2).

2. Collector according to the preceding claim, 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 third inlet (38) being located axially closer to the bottom wall (26a) than the second inlet (34).

3. Collector according to the preceding claim, characterized in that the signaling pipe (37) extends longitudinally in the internal cavity (27).

4. Collector according to one of claims 2 or 3, characterized in that the second and third liquid inlets (34, 38) are radially offset relative to the first liquid inlet (22, 23).

5. Collector according to any one of the preceding claims, characterized in that the detection and signaling device (40) comprises at least one first detection and signaling member (41) comprising at least one indicator light or a porthole.

6. Collector according to the preceding claim, characterized in that the first detection and signaling member (41) is connected both to the evacuation pipe (33) and to the signaling pipe (37).

7. Collector according to claim 5, characterized in that the detection and signaling device comprises a second detection and signaling member (42) connected to the signaling pipe (37), the first detection and signaling member (41) being connected to the discharge pipe (33).

8. Collector according to any one of the preceding claims, characterized in that the signaling pipe (38) comprises a third liquid outlet (39).

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

10. Method of maintaining an aircraft turbomachine (1), the maintenance method comprising the following steps: (a) providing a turbomachine (1) comprising a manifold (20) according to any one of the preceding claims, (b) filling the internal cavity (27) with the first liquid through the first inlet (22, 23) and discharging the first liquid from the enclosure (21) through the first outlet (24), (c) detecting the second threshold level (S2) of liquid in the internal cavity (27), (d) optionally, detecting the first threshold level (S1) of liquid in the internal cavity (27), and (e) schedule a maintenance operation between steps (c) and (d).

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