COLLECTOR OF AT LEAST ONE LIQUID FOR AN AIRCRAFT TURBOMACHINE

Abstract

The invention relates to a collector (20) comprising: - at least one first inlet (22, 23), - a first outlet (24), - a liquid discharge line (33) for evacuating the liquid 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), - 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), - a detection and signaling device (40) for when the liquid level in the internal cavity (27) reaches one or both of the first and second threshold levels (S1, S2). (Shorthand 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 the field of collectors of at least one liquid, for an aircraft turbomachine.

[0002] The invention also relates to maintenance methods for aircraft turbomachinery. Technical background

[0003] 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 includes, 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.

[0004] 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, on the other hand, is connected to the rotor of the high-pressure turbine via a high-pressure shaft.

[0005] The turbomachine further comprises a fan located upstream of the gas generator and driven in rotation about the longitudinal axis by a fan shaft. In certain types of high bypass ratio turbomachines, the fan shaft may be connected to the low-pressure shaft via a speed reducer.

[0006] The high- and low-pressure shafts are guided in rotation by means of guide bearings that must be lubricated with lubricating oil to ensure their proper operation. In order to protect the associated components of the turbomachine from this lubricating fluid, 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 that supplies the chamber with lubricating oil. In addition, each lubrication chamber is delimited by sealing systems comprising seals that limit leakage of lubricating fluid outside the lubrication chambers.

[0007] Furthermore, the combustion chamber and certain hydraulic actuators of the turbomachine are supplied with fuel. For this purpose, the turbomachine includes ty tapping a fuel circuit which allows fuel to be supplied to the combustion chamber and / or hydraulic actuators.

[0008] Lubrication chambers, fuel and lubrication circuits may experience fluid leaks, including fuel and / or lubricating oil leaks. Although these leaks occur at a rate considered normal, they represent potential sources of environmental pollution. Therefore, fuel from the combustion chamber is generally drained to limit the risk of coking.

[0009] The turbomachine therefore generally includes at least one drainage circuit for these liquids.

[0010] In order to limit environmental pollution caused by these liquids, the turbomachine typically includes a manifold for at least one of these liquids connected to the drainage circuit. The manifold typically includes a housing defining an internal cavity for receiving the liquid and a first inlet for this liquid into the internal cavity. The manifold further includes a first outlet for this liquid opening outside the housing.

[0011] Leaks can also result from abnormal operation of the fuel or lubrication circuits, or from degradation or rupture of the sealing systems of the lubrication chambers, for example. In such a case, the fluid leakage rate is abnormal, and the fluid inlet flow rate in the manifold is significantly greater than the outlet flow rate, causing the fluid to accumulate in the internal cavity. To collect such abnormal leaks and ensure their evacuation from the chamber, the manifold typically includes a fluid discharge line configured to discharge the fluid from the chamber when the fluid level in the chamber exceeds a threshold level in the internal cavity. This discharge line thus includes a second fluid inlet located in the internal cavity and a second fluid outlet opening outside the manifold chamber.The second inlet is typically located at a height equal to the liquid threshold level in the internal cavity so that the liquid flows into the drain pipe by overflow.

[0012] Such leaks could reduce the turbomachine's shutdown margin or the availability margin of the turbomachine's emergency operating modes. It is therefore important for operators to be able to detect these abnormal leaks.

[0013] In this context, in order to detect and signal an abnormal fluid leak in the turbomachine, the manifold typically includes a first-level threshold detection and signaling device. Such a detection and signaling device is, for example, connected to the discharge line and includes a detection and signaling element. A device allowing observation and / or detection of liquid in the drain line, such as a sight glass or indicator light. The detection of liquid in this drain line generally indicates an abnormal fluid leak and therefore a failure in a fuel or lubrication circuit, or in the seals of the lubrication chambers.

[0014] However, such a leak detection and reporting device for the manifold is not entirely satisfactory. Indeed, this detection and reporting device does not allow for the identification of the leak's origin, making it necessary to conduct a leak detection campaign to identify the source(s). Only after such a search campaign is it possible to address and resolve the leak.

[0015] However, such a search campaign requires the installation of segregation and leak detection equipment on the turbomachine, followed by ground testing of the turbomachine for several tens of minutes to determine the leakage rates of each seal. Such search campaigns are lengthy and tedious for operators, and require the turbomachine to be out of service. Consequently, the aircraft cannot be put into operation during the campaign, significantly impacting its availability.

[0016] Therefore, there is a need to provide a manifold for at least one liquid for an aircraft turbomachine, which allows for the simple and rapid detection of abnormal leaks in the turbomachine in order to reduce operator workload, facilitate maintenance operations, and improve aircraft availability. Summary of the invention

[0017] To this end, the invention proposes a manifold for at least one first liquid for an aircraft turbomachine, the manifold comprising:

[0018] - an enclosure defining an internal cavity intended to receive at least the first liquid,

[0019] - at least one first entry of the first liquid opening into the internal cavity,

[0020] - a first liquid outlet opening outside the enclosure,

[0021] - a liquid drain pipe configured to drain liquid from the cavity internal 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 drain line comprising:

[0022] - a second liquid inlet located in the internal cavity,

[0023] - a second liquid outlet opening outside the enclosure.

[0024] The collector is remarkable in that it further comprises:

[0025] - a signaling conduit located within 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 reporting procedure including:

[0026] - a third liquid inlet located in the internal cavity, and

[0027] - a device for detecting and signaling when the liquid level is reached in the internal cavity of one and / or the other of the first and second threshold levels.

[0028] The collector according to the invention thus comprises a signaling conduit which allows the liquid to be collected in the internal cavity when the level of liquid in the internal cavity is greater than a second threshold level of liquid in the internal cavity, this second threshold level being less than the first threshold level.

[0029] It is thus understood that when the second threshold level is reached, the liquid initially flows into the signaling pipe. Then, when the first threshold level is reached, the liquid subsequently flows into the discharge pipe.

[0030] The collector further includes a device for detecting and reporting 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 allows for planning a leak detection campaign, and therefore the shutdown of the turbine and the aircraft's unavailability.

[0031] The first threshold level is detected by safety.

[0032] Thanks to the invention, it is possible to anticipate and plan a leak detection campaign, making it possible to reduce the workload of operators and to limit the unavailability of the turbomachine and therefore of the aircraft.

[0033] The invention may comprise one or more of the following features, taken individually or in combination with each other:

[0034] — the first and second threshold levels correspond to a height of liquid in the internal cavity,

[0035] — the first entrance is located at a first end of the enclosure, called The upper end and the first outlet are located at a second, opposite end of the enclosure, called the lower end.

[0036] — the second liquid inlet is located in a plane perpendicular to the long axis gitudinal of the enclosure and passing through the first threshold level,

[0037] — the third liquid inlet is located in a plane perpendicular to the long axis gitudinal of the enclosure and passing through the second threshold level,

[0038] - the enclosure extends longitudinally along a longitudinal axis between a first one end and a second end closed by a back wall, the third entrance being located axially closer to the back wall than the second entrance,

[0039] - the signaling conduit extends longitudinally into the internal cavity,

[0040] - the second and third liquid inlets are radially offset with respect to the first liquid inlet,

[0041] - the detection and signaling device comprises at least one first component detection and signaling devices including at least one indicator light or window

[0042] - the first detection and signaling device is connected to both the conduit evacuation and emergency response procedures,

[0043] - the detection and signaling device includes a second detection element and a signaling device connected to the signaling pipe, the first detection and signaling device being connected to the evacuation pipe,

[0044] - the signaling conduit includes a third liquid outlet,

[0045] - the collector is produced by additive manufacturing.

[0046] The invention also relates to a method for maintaining an aircraft turbomachine, the maintenance method comprising the following steps:

[0047] (a) provide a turbomachine comprising a manifold according to any one of the previous characteristics,

[0048] (b) fill the internal cavity with the first liquid through the first inlet and Drain the first liquid from the enclosure through the first outlet.

[0049] (c) detect the second threshold level of liquid in the internal cavity,

[0050] (d) optionally, detect the first threshold level of liquid in the internal cavity, And

[0051] (e) plan a maintenance operation between the steps. Brief description of the figures

[0052] Other features and advantages will become apparent from the following description of non-limiting embodiments of the invention with reference to the accompanying drawings in which:

[0053] [Fig-1] [Fig.1] is a longitudinal cross-sectional view of an example of a tower aircraft engine according to the invention,

[0054] [Fig.2] [Fig.2] is a longitudinal cross-sectional view of a collector according to the invention,

[0055] [Fig.3] [Fig.3] is a synoptic diagram of a method for maintaining the turbomachine, according to the invention. Detailed description of the invention

[0056] An example of an aircraft turbomachine 1, according to the invention, is shown in [Fig. 1]. The turbomachine 1 is, for example, a turbofan engine. The turbomachine 1 may have any other architecture and may, for example, be in the form of a turboprop engine.

[0057] The turbomachine 1 is modular. It comprises a plurality of assembled modules to each other.

[0058] The turbomachine 1 extends along a longitudinal axis X. A gas flow F flows into the turbomachine 1.

[0059] For the purposes of the present invention, the terms "upstream" and "downstream" are understood in relation 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.

[0060] The turbomachine 1 comprises, from upstream to downstream, a blower 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.

[0061] 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 the turbine rotors 6a, 7a are composed of a plurality of stages, each comprising a bladed wheel.

[0062] 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.

[0063] 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.

[0064] The low pressure shafts 8 and high pressure shafts 9 are centered on the longitudinal axis X and are free to rotate about the longitudinal axis X. The high pressure shaft 9 is arranged coaxially around the low pressure shaft 8.

[0065] The gas flow F passes through the blower 2 and splits into a primary air flow Fl passing through a primary stream v1 and a secondary air flow F2 passing through a secondary stream v2 surrounding the primary stream. The primary air flow Fl passes through the low-pressure compressor 3 and the high-pressure compressor 4. The compressed primary air flow Fl then passes through the combustion chamber 5 where it is mixed with fuel. The combustion gases thus pass through the high-pressure turbine 6 and the low-pressure turbine 7. The energy of the gases is transformed by the turbine rotor 7a of the low-pressure turbine 7 into mechanical energy, which drives the low-pressure shaft 8 and, consequently, the low-pressure compressor 3.

[0066] The fan 2 comprises a rotating disc about the longitudinal axis X and blades 2a carried by the disc and evenly distributed about the longitudinal axis X. In the example of [Fig. 1], the fan 2 is surrounded by a fan housing 2b. The fan 2 is of the enclosed type. The fan housing 2b carries a nacelle 2c and together they define a fan compartment 2d.

[0067] According to another example not shown, the blower 2 is of the non-faired type.

[0068] The fan disk 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.

[0069] The speed reducer 11 allows the blower shaft 10 to be driven at a rotational speed lower than the rotational speed of the low-pressure shaft 8. This makes it possible to increase the dilution ratio of the turbomachine 1.

[0070] The turbomachine 1 further comprises an inter-compressor housing 12 arranged axially between the low-pressure compressor 3 and the high-pressure compressor 4. The inter-compressor housing 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.

[0071] The turbomachine 1 may further include an inlet housing 13. The inlet housing 13 is arranged axially between the fan 2 and the low-pressure compressor 3. The inlet housing 13 includes, 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.

[0072] The turbomachine 1 may further include 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.

[0073] The turbomachine 1 may further include an inter-vein compartment v3 located between the primary vein vl and the secondary vein v2.

[0074] 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 housing 13.

[0075] 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 housing 13 and the low-pressure shaft 8. The fourth bearing 15d is arranged radially between the inter-compressor housing 12 and the low-pressure shaft 8.

[0076] 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 housing 14.

[0077] 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 housing 14 for example.

[0078] Each bearing unit includes, for example, a bearing. The bearing is, for example, at the minus one row of balls or rollers.

[0079] The bearings 15 and the optional speed reducer 11 are lubricated to ensure their proper operation. To prevent oil contamination of related components of the turbomachine 1, the bearings 15 and the speed reducer 11 are arranged in lubrication chambers. The lubrication chambers can also be used to lubricate other components of the turbomachine 1, such as gears and bearings.

[0080] For this purpose, the turbomachine 1 further comprises at least one lubrication chamber, in particular a first upstream chamber 17 in which the first, second and third bearings 15a, 15b, 15c and the speed reducer 11 are arranged, a second upstream lubrication chamber 18 in which the fourth bearing 15d is arranged and a downstream lubrication chamber 19 in which the fifth and sixth bearings 15e, 15f are arranged.

[0081] Depending on the configuration of the turbomachine 1, the number of bearings 15 and lubrication chambers 16 may vary.

[0082] Each lubrication chamber 16 is annular. Each lubrication chamber 16 is delimited externally by a fixed wall such as a housing and internally by a movable wall such as a shaft.

[0083] For example, the first upstream lubrication chamber 17 is located in the inner shell of the inlet housing 13 and is internally delimited by the blower shaft 10. The second upstream lubrication chamber 18 is located in the inner shell of the inter-compressor housing 12 and is internally delimited by the low-pressure shaft 8 and the downstream lubrication chamber 19 is located in the inner shell of the inter-turbine housing 14 and is internally delimited by the high-pressure shaft 9.

[0084] The lubrication chambers 17, 18, 19 are supplied by at least one lubrication circuit. The lubrication circuit includes 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.

[0085] To limit oil leakage outside the lubrication chambers 17, 18, 19, each lubrication chamber 17, 18, 19 includes sealing gaskets at the terminals of the lubrication chambers 17, 18, 19. The sealing gaskets are each located radially between the fixed wall and the moving wall of the lubrication chambers 17, 18, 19. The sealing gaskets are advantageously of the dynamic type. A dynamic type of gasket is understood as an assembly that limits fluid leakage between the fixed wall and the moving wall. Preferably, the first and second sealing gaskets are labyrinth seals.

[0086] The turbomachine 1 further includes a fuel supply circuit for the combustion chamber 5.

[0087] Despite the sealing of the lubrication chambers 17, 18, 19, lubricating oil leaks may occur. Therefore, the fuel from the combustion chamber 5 must be evacuated to limit the risk of coking.

[0088] In this context, the turbomachine 1 further includes at least one drainage circuit from the combustion chamber 5 and / or the lubrication chambers 17, 18, 19. The drainage circuit Cl thus drains at least one liquid from the combustion chamber 5 and / or the lubrication chambers 17, 18, 19 such as lubricating oil and / or fuel.

[0089] In order to limit the risk of environmental pollution, the turbomachine 1 includes a manifold 20. The manifold 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 manifold 20 is connected to the drainage circuit CL.

[0090] With reference to [Fig. 2], the manifold 20 includes a housing 21, at least a first inlet 22 of the first liquid, optionally an additional inlet 23 of the second liquid and a first outlet 24 of the first liquid and optionally of the second liquid.

[0091] Advantageously, the enclosure 21 is annular and has a longitudinal axis A.

[0092] In the following description, the terms "lower" and "upper" are understood 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.

[0093] In the following description, the terms "longitudinal", "longitudinally", "radial", "radially" are understood with respect to the longitudinal axis A of the collector 20.

[0094] The enclosure 21 has a height h such that it is 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.

[0095] The enclosure 21 may, for example, have a circular or polygonal cross-section. The enclosure 21 advantageously extends between a first end 25, also called the upper end, and a second opposite end 26, also called the lower end. The first and second ends 25, 26 are closed.

[0096] The first end 25 is closed, for example, by a lid or a top wall 25a. The second end 26 is closed by an enclosure bottom 26a.

[0097] 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 in [Fig. 2], the cavity 27 has a liquid level L equal to a predetermined standard level that corresponds to a standard liquid inlet flow rate into the collector. This standard liquid level L in the cavity can be considered normal, since it does not reach the level of an alert threshold that would characterize an abnormal flow rate.

[0098] The inlets 22, 23 open into the internal cavity 27. They are located at the first end 25 and are, for example, formed on the cover 25a. The inlets 22, 23 are thus opposite the second end 25b. The inlets 22, 23 are, for example, annular. They are offset from the longitudinal axis A of the collector 20. According to the example of [Fig.2], the inlets 22, 23 have an axis Al parallel to the longitudinal axis A of the collector 20.

[0099] The inlets 22, 23 are for example connected to the drainage circuit of the turbomachine 1.

[0100] The first outlet 24 opens outside the enclosure 21. The first outlet 24 is thus configured to discharge 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.

[0101] 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.

[0102] The first outlet 24 is, for example, connected to an ejector (not shown) linking 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.

[0103] Preferably, the manifold 20 further comprises a nozzle 28 that fluidly connects the internal cavity 27 and the first outlet 27. The nozzle 28 is configured to allow the passage of the first and / or second liquid at a calibrated flow rate. 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 a second outlet end 28b opposite the first and / or second liquid. The second outlet 28b is connected to the first outlet 24 or forms the first outlet 24.

[0104] Preferably, the nozzle 28 has an axis A3 perpendicular to the longitudinal axis A of the manifold 20 and parallel to the axis A2 of the first outlet 24.

[0105] Preferably, the nozzle 28 is removably connected to the enclosure 21. This allows the nozzle 28 to be mounted and dismounted for cleaning and to limit the risk of clogging of the nozzle 28. Maintenance of the nozzle 28 is thus facilitated.

[0106] In order to allow the fluid to be evacuated from the manifold 20 by draining, for example through the first outlet 24, preferably the manifold 20 can It also includes a ventilation duct. The ventilation duct is located in enclosure 21 of the manifold 20. It includes a ventilation air inlet located or opening outside enclosure 21 and a ventilation air outlet which opens into the first outlet 24.

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

[0108] In certain cases, particularly in the event of a rupture of the seals in the lubrication chambers 17, 18, 19, the fuel supply circuit, or the lubrication circuit, the fluid inlet flow rate into the manifold 20 through the first inlet 22 exceeds a standard flow rate. In this case, the liquid level in the internal cavity 27 increases, and it is necessary to drain this liquid.

[0109] In this context, the manifold 20 further includes a liquid drain line 33. The drain line 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 SI of liquid in the internal cavity 27. The first threshold level SI is measured according to the height of the enclosure 21. The first threshold level SI is greater than the predetermined standard threshold.

[0110] The discharge conduit 33 includes 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 SL. In particular, the second inlet 34 has an inlet orifice located at a height equal to the height of the first threshold level SI in the internal cavity 27. Thus, when the liquid level in the internal cavity reaches the first threshold level SI, the liquid overflows into the second inlet 34.

[0112] The second inlet 34 is radially offset relative to the first inlet 22 and the additional inlet 23. This prevents contamination of the drain line 33 by liquid entering the internal cavity 27 when the liquid level in the internal cavity 27 is below the first threshold level SL

[0113] According to the example in [Fig.2], the second outlet 35 is connected to or opens into the ventilation air inlet 30. The second outlet 35 has an axis A7 perpendicular to the longitudinal axis A of the manifold 20. The axis A7 of the second outlet 35 can be coincident with the axis A4 of the ventilation air inlet 30.

[0114] 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 cavity internal 27. The overflow tube 36 includes, 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.

[0115] Such leaks can have adverse consequences for the turbomachine 1. It is therefore standard practice to launch a campaign to locate the source of the leak(s). Such a campaign is time-consuming and requires shutting down the turbomachine 1, directly impacting aircraft availability. To limit the consequences of these leaks, and in particular this aircraft unavailability, the manifold 20 also includes a signaling conduit 37 located in the enclosure 21.

[0116] With reference to [Fig. 2], the signaling line 37 is configured to collect liquid when the liquid level in the enclosure 21 is above a second threshold level S2 of liquid in the internal cavity 27. The second threshold level S2 is below the first threshold level SL

[0117] The first and second threshold levels correspond to the height of the 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 the liquid in the internal cavity 27 as measured along a direction parallel to the direction of flow of the liquid in the internal cavity 27.

[0118] The signaling conduit 37 includes 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 manifold 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 from the first inlet 22 and the additional inlet 23.

[0119] 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 lower height in the enclosure 21 than the second inlet 34.

[0120] The third outlet 39 is fluidically connected to the outside of the enclosure 21. For example, it is connected to the drain pipe 33. In order to control the outlet flow rate of the liquid through this third outlet 39, the latter can be equipped with a diaphragm.

[0121] The signaling conduit 37 extends longitudinally within the internal cavity 27. The signaling conduit 37 extends longitudinally within the internal cavity 27 between an upper end 37a having the third inlet 38 and an axially opposite lower end 37b. The signaling conduit 37 further has a fluid passage 37c extending between the upper and lower ends 37a, 37b.

[0122] According to the invention, the collector 20 further comprises a detection and signaling device 40 for the first and / or second threshold levels SI, S2. The detection and signaling device 40 is configured to detect and signal when the first and / or second threshold levels SI, S2 of liquid in the enclosure 21 are reached.

[0123] The detection and signaling device 40 of the first threshold SI is mounted on the enclosure 21 and is preferably located opposite the first end 25 of the enclosure 21.

[0124] According to one example, the detection and signaling device 40 includes a detection and signaling element configured to independently signal the first and second level thresholds SI, S2.

[0125] The detection and signaling device is, according to this example, connected both to the evacuation pipe 33 and to the signaling pipe 37.

[0126] The detection and signaling device includes, for example, a light indicating the first threshold level SI in the form of a first color and indicating the second threshold level S2 in the form of a second color which is different from the first color.

[0127] According to another example illustrated in [Fig. 2], the detection and signaling device 40 comprises a first detection and signaling element 41 configured to signal the first threshold level SI and a second detection and signaling element 42 configured to signal the second threshold level S2. The first detection and signaling element 41 is connected to the evacuation pipe 33 and the second detection and signaling element 42 is connected to the signaling pipe 37.

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

[0129] According to an alternative, the first and second detection and signaling devices 41, 42 each comprise a sight glass or window for detecting and signaling the presence of liquid in the discharge and signaling pipes 36, 37. Each sight glass or window is mounted opposite the discharge and signaling pipes 36, 37, respectively. In particular, a first sight glass 41 is mounted opposite the axial portion 36a of the overflow pipe 36, on the opposite side of the a second inlet 34 and a second porthole 42 is mounted opposite the lower end 37b of the signaling conduit 37.

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

[0131] Fluid leaks from the lubrication chambers 17, 18, 19 or fuel from the combustion chamber 5 are, for example, drained through the drainage circuit CL. The drained fluid enters the manifold 20 through at least the first inlet 22 at a standard flow rate. The fluid then flows into the internal cavity 27 by gravity. The fluid in the internal cavity 27 is discharged through the first outlet 24 at a standard outlet flow rate. The discharged fluid can be expelled into the nozzle 70.

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

[0133] Thanks to the invention, maintenance operations can be planned, reducing the workload for operators. Also, the availability of the turbomachine 1 is improved since the shutdown of the turbomachine 1 can be anticipated and planned.

[0134] A method for maintaining the turbomachine 1 will now be described with reference to [Fig.3].

[0135] The maintenance procedure comprises the following steps:

[0136] (a) supply the turbomachine 1 and the manifold 20 mounted in the turbomachine

[0137] (b) fill the internal cavity 27 with the first liquid through the first inlet 22 and to evacuate the first liquid from enclosure 21 through the first outlet 24,

[0138] (c) detect the second threshold level S2 of liquid in the internal cavity 27,

[0139] (d) optionally, detect the first SI threshold level of liquid in the cavity internal 27, and

[0140] (e) plan a maintenance operation between steps (c) and (d).

Claims

Demands

1. A manifold (20) for at least one first liquid for an aircraft turbomachine (1), the manifold (20) comprising: - a housing (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 housing (21), - a liquid discharge line (33) configured to discharge the liquid from the internal cavity (27) outside the housing (21) when the liquid level in the internal cavity (27) is greater than or equal to a first threshold level (SI) of liquid in the internal cavity (27), the discharge line (33) comprising: - a second liquid inlet (34) located in the internal cavity (27), - a second liquid outlet (35) opening outside the housing (21),characterized in that the collector (20) further comprises: - a signaling conduit (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 (SI), the signaling conduit (37) comprising: - a third liquid inlet (38) located in the internal cavity (27), the collector (20) further comprising: - a detection and signaling device (40) for when the liquid level in the internal cavity (27) reaches one and / or the other of the first and second threshold levels (SI, 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 conduit (37) extends longitudinally in the internal cavity (27).

4. Manifold according to any one of claims 2 or 3, characterized in that the second and third liquid inlets (34, 38) are radially offset with respect 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 a first detection and signaling element (41) comprising at least one indicator light or window.

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

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

8. Manifold according to any one of the preceding claims, characterized in that the signaling conduit (38) includes a third liquid outlet (39).

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

10. A method for 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 evacuating 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 (SI) of liquid in the internal cavity (27), and (e) scheduling a maintenance operation between steps (c) and (d).