Manifold for at least one liquid for a turbine engine of an aircraft

Abstract

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

Description

Technical Field

[0001] This invention relates to the field of manifolds for at least one liquid used in aircraft turbine engines.

[0002] The present invention also relates to a maintenance method for maintaining an aircraft turbine engine. Background Technology

[0003] Turbine engines, particularly those used in aircraft, typically extend along and around a longitudinal axis. In the case of twin-body and twin-flow turbine engines, which include a gas generator, the gas generator typically comprises, from upstream to downstream in the gas flow direction within the turbine engine, 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 a low-pressure compressor is typically connected to the rotor of a low-pressure turbine via a low-pressure shaft. The rotor of a high-pressure compressor is connected to the rotor of a high-pressure turbine via a high-pressure shaft.

[0005] The turbine engine also includes a fan located upstream of the gas generator, which is driven by a fan shaft to rotate about a longitudinal axis. In some types of turbine engines with a high bypass ratio, the fan shaft may be connected to a low-pressure shaft by means of a reduction gear.

[0006] The high-pressure and low-pressure shafts are guided to rotate by means of guide bearings, which must be lubricated with lubricating oil to ensure their proper operation. To protect relevant components of the turbine engine from the lubricating fluid, such as bearings and gear meshing in the reducer, they are typically arranged in lubrication chambers. Each lubrication chamber is connected to a lubrication circuit that allows the chamber to be supplied with lubricating oil. Additionally, each lubrication chamber is defined by a sealing system including gaskets that prevent lubricating fluid leakage.

[0007] In addition, the combustion chamber and certain hydraulic actuators of a turbine engine are supplied with fuel. For this purpose, turbine engines typically include a fuel circuit that allows the combustion chamber and / or hydraulic actuators to be supplied with fuel.

[0008] Lubrication chambers, fuel circuits, and lubrication circuits may be susceptible to fluid leaks, particularly fuel and / or lubricating oil leaks. Although these leaks flow at rates considered normal, they represent a potential source of environmental pollution. Furthermore, fuel from the combustion chamber is typically vented to limit the risk of coking.

[0009] Therefore, turbine engines typically include at least one discharge circuit for these liquids.

[0010] To limit environmental pollution caused by these liquids, turbine engines typically include a manifold for at least one of these liquids, connected to an exhaust circuit. The manifold typically includes a chamber defining an inner cavity for receiving the liquid and a first inlet for the liquid to enter the inner cavity. The manifold also includes a first outlet for the liquid leading to the chamber.

[0011] Leaks also exist, which may be caused by malfunctions in, for example, the fuel circuit or lubrication circuit, or by deterioration or rupture of the sealing system of the lubrication chamber. In this case, the leakage rate of the liquid is abnormal, and the inflow rate of the liquid into the manifold is much greater than the outflow rate, causing liquid to accumulate in the cavity. To collect such abnormal leaks and ensure they are drained from the chamber, the manifold typically includes a liquid drain pipe configured to drain liquid from the chamber when the liquid level in the chamber is above a threshold liquid level in the cavity. Therefore, the drain pipe includes a second liquid inlet located in the cavity and a second liquid outlet leading to the manifold chamber. The second inlet is typically located at a height equal to the threshold liquid level in the cavity, allowing liquid to overflow into the drain pipe.

[0012] Such leaks can reduce the margin for shutting down the turbine engine or the margin for the availability of emergency operating modes for the turbine engine. Therefore, it is important for operators to be able to detect these unusual leaks.

[0013] In this context, to detect and report abnormal fluid leaks in a turbine engine, the manifold typically includes a detection and signaling device for detecting and signaling a first threshold fluid level. This detection and signaling device is, for example, connected to a drain pipe and includes detection and signaling elements, such as a viewing glass or warning light, capable of observing and / or signaling fluid in the drain pipe. Detection of fluid in the drain pipe generally indicates an abnormal fluid leak and thus indicates a failure of seals in the fuel or lubrication circuit or lubrication chamber.

[0014] However, this device for detecting and signaling manifold leaks is not entirely satisfactory. In fact, the detection and signaling device cannot identify the source of the leak, therefore, it is necessary to conduct leak testing activities to pinpoint the source. Only after such testing can the leak problem be addressed and resolved.

[0015] However, such testing requires installing equipment on the turbine engine to isolate and monitor leaks, followed by operating the turbine engine on the ground for tens of minutes to determine the leak flow rate associated with each seal. This testing activity is lengthy and cumbersome for operators and can tie up the turbine engine, preventing it from being put into operation. Consequently, the aircraft cannot be put into service during the testing activity, severely impacting its availability.

[0016] Therefore, there is a need for a manifold for at least one liquid in an aircraft turbine engine that allows for simple and rapid detection of abnormal leaks in the turbine engine, thereby reducing operator workload, facilitating maintenance operations, and improving aircraft availability. Summary of the Invention

[0017] Therefore, the present invention proposes a manifold for at least one first liquid in an aircraft turbine engine, the manifold comprising: - A chamber, the chamber defining an inner cavity intended to receive at least a first liquid, -At least one first liquid initial inlet leading to the inner cavity, -The first liquid outlet leading to the chamber - A liquid discharge pipe configured to discharge liquid from the inner cavity chamber when the liquid level in the inner cavity is greater than or equal to a first threshold liquid level in the inner cavity, the discharge pipe comprising: - The second liquid inlet is located in the inner cavity. - The second liquid outlet leading to the chamber.

[0018] The manifold is characterized in that it further includes: - A signal transmitting tube, located within a cavity and configured to collect liquid when the liquid level in the cavity is greater than or equal to a second threshold liquid level, the second threshold liquid level being lower than a first threshold liquid level, the signal transmitting tube comprising: -The third liquid inlet located in the inner cavity, and - A detection and signaling device for detecting and sending signals to indicate that the liquid level in the cavity has reached one of a first threshold liquid level and a second threshold liquid level and / or the other.

[0019] Therefore, the manifold according to the invention includes a signal transmitting tube that enables liquid to be collected in the cavity when the liquid level in the cavity is greater than a second threshold liquid level, the second threshold liquid level being lower than a first threshold liquid level.

[0020] Therefore, it should be understood that when the second threshold level is reached, liquid initially flows into the signal transmitting tube. Then, when the first threshold level is reached, the liquid flows out through the discharge tube in the second stage.

[0021] The manifold also includes detection and signaling devices for detecting and signaling first and / or second threshold liquid levels. Therefore, when the second threshold liquid level is reached, the operator is alerted and the first threshold liquid level can be predicted, enabling the planning of leak detection activities and, consequently, the planning of turbine engine shutdown and aircraft unavailability.

[0022] The first threshold liquid level is detected for safety reasons.

[0023] Thanks to this invention, leak testing activities can be predicted and planned, thereby reducing operator workload and limiting turbine engine unavailability, which in turn limits aircraft unavailability.

[0024] The present invention may include one or more of the following features, either individually or in combination thereof: - The first threshold liquid level and the second threshold liquid level correspond to the height of the liquid in the cavity. - The first inlet is located at one end of the chamber, referred to as the upper end, and the first outlet is located at the opposite end of the chamber, referred to as the lower end. - The second liquid inlet is located in a plane perpendicular to the longitudinal axis of the chamber and passing through the first threshold liquid level. - The third liquid inlet is located in a plane perpendicular to the longitudinal axis of the chamber and passing through the second threshold liquid level. - The chamber extends longitudinally along the longitudinal axis between the first end and the second end, which is closed by the bottom wall, and the third inlet is axially closer to the bottom wall than the second inlet. -The signal transmitting tube extends longitudinally within the cavity. - The second and third liquid inlets are radially offset relative to the first liquid inlet. The detection and signal transmission device includes at least one first detection and signal transmission element, which includes at least one indicator light or observation glass. - The first detection and signal transmission element is connected to both the discharge tube and the signal transmission tube. The detection and signal transmission device includes a second detection and signal transmission element connected to a signal transmission tube, and a first detection and signal transmission element connected to a discharge tube. -The signal transmitting tube includes a third liquid outlet. - Use additive manufacturing to manufacture manifolds.

[0025] The present invention also relates to a maintenance method for maintaining an aircraft turbine engine, the maintenance method comprising the following steps: (a) Supplying a turbine engine, said turbine engine comprising a manifold according to any one of the foregoing features, (b) The cavity is filled with a first liquid through the first inlet and the first liquid is discharged from the cavity through the first outlet. (c) Detect the second threshold liquid level of the liquid in the cavity. (d) Optionally, a first threshold liquid level in the lumen is detected, and (e) Plan maintenance operations between steps. Attached Figure Description

[0026] 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: [ Figure 1 ] Figure 1 This is a longitudinal cross-sectional view of an example of an aircraft turbine engine according to the present invention. [ Figure 2 ] Figure 2 This is a longitudinal cross-sectional view of the manifold according to the present invention. [ Figure 3 ] Figure 3 This is a schematic diagram of a turbine engine maintenance method according to the present invention. Detailed Implementation

[0027] Figure 1 An example of an aircraft turbine engine 1 according to the present invention is shown. The turbine engine 1 is, for example, a two-flow turbojet engine. The turbine engine 1 can have any other structure and, for example, take the form of a turboprop engine.

[0028] Turbine engine 1 is modular. The turbine engine consists of multiple modules assembled together.

[0029] Turbine engine 1 extends along the longitudinal axis X. Airflow F flows within turbine engine 1.

[0030] For the purposes of this invention, the terms "upstream" and "downstream" are understood to relate to the flow direction of the airflow F in the turbine engine 1. Figure 1 and Figure 2 In the middle, the airflow F flows from left to right.

[0031] The turbine engine 1 includes a fan 2 and a gas generator from upstream to downstream. The gas generator includes 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 an exhaust nozzle 70 from upstream to downstream.

[0032] Each compressor 3, 4 includes compressor rotors 3a, 4a, and each turbine 6, 7 includes turbine rotors 6a, 7a. The compressor rotors 3a, 4a and the turbine rotors 6a, 7a consist of multiple stages, each stage including an impeller.

[0033] The compressor rotor 3a of the low-pressure compressor 3 is connected to the turbine rotor 7a of the low-pressure turbine 7 via the low-pressure shaft 8. They form a low-pressure body.

[0034] The compressor rotor 4a of the high-pressure compressor 4 is connected to the turbine rotor 6a of the high-pressure turbine 6 via the high-pressure shaft 9. They form a high-pressure body.

[0035] The low-pressure shaft 8 and the high-pressure shaft 9 are centered on the longitudinal axis X and can rotate around the longitudinal axis X. The high-pressure shaft 9 is arranged coaxially around the low-pressure shaft 8.

[0036] Airflow F passes through fan 2 and is split into a main airflow F1 through main duct v1 and a secondary airflow F2 through secondary duct v2 surrounding the main duct. The main airflow F1 passes through low-pressure compressor 3 and high-pressure compressor 4. The compressed main airflow F1 then passes through combustion chamber 5, where it mixes with fuel. The gas produced by combustion passes through high-pressure turbine 6 and low-pressure turbine 7. The energy in the gas is converted into mechanical energy by the turbine rotor 7a of low-pressure turbine 7, thereby allowing the low-pressure shaft 8 to rotate and thus driving the low-pressure compressor 3 to rotate.

[0037] The fan 2 includes a disc rotatable about a longitudinal axis X, and blades 2a carried by the disc and evenly spaced about the longitudinal axis X. Figure 1 In the example shown, fan 2 is surrounded by fan housing 2b. Fan 2 is ducted. Fan housing 2b carries nacelle 2c and together defines fan compartment 2d.

[0038] According to another example not shown, fan 2 is ductless.

[0039] The disk of fan 2 is driven to rotate by fan shaft 10. In this example, and therefore as an alternative, fan shaft 10 is connected to low-pressure shaft 8 by means of reducer 11. Reducer 11 is mechanical. For example, the reducer may have rotary or planetary gears.

[0040] The reducer 11 allows the fan shaft 10 to be driven at a lower speed than the low-pressure shaft 8. This makes it possible to increase the bypass ratio of the turbine engine 1.

[0041] The turbine engine 1 also includes a compressor housing 12 arranged axially between the low-pressure compressor 3 and the high-pressure compressor 4. The compressor housing 12 includes, for example, an inner shroud and an outer shroud centered on a longitudinal axis X. For example, the inner shroud and the outer shroud are connected by an arm.

[0042] The turbine engine 1 may also include an inlet housing 13. The inlet housing 13 is axially arranged between the fan 2 and the low-pressure compressor 3. The inlet housing 13 includes, for example, an inner shroud and an outer shroud centered on a longitudinal axis X. For example, the inner shroud and the outer shroud are connected by an arm.

[0043] The turbine engine 1 may also include a turbine housing 14. The turbine housing 14 is axially arranged between the high-pressure turbine 6 and the low-pressure turbine 7.

[0044] The turbine engine 1 may also include a flow channel compartment v3 located between the main flow channel v1 and the secondary flow channel v2.

[0045] The turbine engine 1 includes at least one bearing 15. In particular, the fan shaft 10 is rotated by a first bearing 15a and advantageously by a second bearing 15b. The first bearing 15a and the second bearing 15b are arranged radially between the fan shaft 10 and the inlet housing 13.

[0046] The low-pressure shaft 8 is rotated by at least a third bearing 15c and a fourth bearing 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 compressor housing 12 and the low-pressure shaft 8.

[0047] The high-pressure shaft 9 is guided to rotate by the fifth bearing 15e. The fifth bearing 15e is arranged, for example, radially between the high-pressure shaft 9 and the turbine housing 14.

[0048] For example, the low-pressure shaft 8 can be guided to rotate downstream by a sixth bearing 15f arranged radially between the downstream end of the low-pressure shaft 8 and the turbine housing 14.

[0049] Each bearing includes, for example, a rolling bearing. A rolling bearing is, for example, at least one row of balls or rollers.

[0050] The bearing 15 and the optional reducer 11 are lubricated to ensure their smooth operation. To prevent oil contamination of related components of the turbine engine 1, the bearing 15 and reducer 11 are arranged in a lubrication chamber. The lubrication chamber can also be used to lubricate other components of the turbine engine 1, such as gears and bearings.

[0051] For this purpose, the turbine engine 1 also includes at least one lubrication chamber, specifically a first upstream chamber 17, a second upstream lubrication chamber 18, and a downstream lubrication chamber 19. The first upstream chamber 17 is provided with a first bearing 15a, a second bearing 15b, a third bearing 15c, and a reducer 11. The second upstream lubrication chamber 18 is provided with a fourth bearing 15d. The downstream lubrication chamber 19 is provided with a fifth bearing 15e and a sixth bearing 15f.

[0052] Depending on the construction of the turbine engine 1, the number of bearings 15 and lubrication chambers 16 can vary.

[0053] Each lubrication chamber 16 is annular. Each lubrication chamber 16 is externally defined by a fixed wall, such as a housing, and internally defined by a movable wall, such as a shaft.

[0054] For example, the first upstream lubrication chamber 17 is located in the inner shroud of the inlet housing 13 and is internally defined by the fan shaft 10. The second upstream lubrication chamber 18 is located in the inner shroud of the compressor housing 12 and is internally defined by the low-pressure shaft 8, and the downstream lubrication chamber 19 is located in the inner shroud of the turbine housing 14 and is internally defined by the high-pressure shaft 9.

[0055] Lubrication chambers 17, 18, and 19 are supplied by at least one lubrication circuit. The lubrication circuit includes an oil outlet leading to lubrication chambers 17, 18, and 19, and an oil inlet connected to, for example, a reservoir for supplying the lubrication circuit.

[0056] To limit oil leakage from lubrication chambers 17, 18, and 19, each lubrication chamber 17, 18, and 19 includes a sealing gasket at its boundary. The sealing gaskets are radially positioned between the fixed wall and the movable wall of each lubrication chamber 17, 18, and 19. Advantageously, the sealing gaskets are of a dynamic type. A dynamic gasket is defined as a component that limits fluid leakage between the fixed wall and the movable wall. Preferably, the first and second sealing gaskets are labyrinth gaskets.

[0057] The turbine engine 1 also includes a fuel supply circuit for the combustion chamber 5.

[0058] Although the lubrication chambers 17, 18, and 19 are sealed, lubricating oil leakage may still occur. Therefore, fuel from combustion chamber 5 must be drained to limit the risk of coking.

[0059] In this configuration, the turbine engine 1 also includes at least one exhaust circuit for the combustion chamber 5 and / or lubrication chambers 17, 18, 19. Therefore, the exhaust circuit C1 discharges at least one liquid, such as lubricating oil and / or fuel, from the combustion chamber 5 and / or lubrication chambers 17, 18, 19.

[0060] To limit the risk of environmental pollution, the turbine engine 1 includes a manifold 20. The manifold 20 is configured to collect at least one liquid from the exhaust circuit C1. The liquid is, for example, lubricating oil and / or fuel for the turbine engine 1. The manifold 20 is connected to the exhaust circuit C1.

[0061] refer to Figure 2 The manifold 20 includes a chamber 21, at least one first inlet 22 for a first liquid, an optional additional inlet 23 for a second liquid, and a first outlet 24 for the first liquid and the optional second liquid.

[0062] Advantageously, chamber 21 is annular and has a longitudinal axis A.

[0063] In the following description, the terms "lower" and "upper" are understood relative to the gravitational flow of the liquid in manifold 20. Therefore, the term "upper" refers to the portion relatively closer to the first inlet 22, and the term "lower" refers to the portion relatively farther from the first inlet 22. Figure 2 In this case, the liquid flows downwards due to gravity.

[0064] In the following description, the terms “longitudinal,” “longitudinal,” “radial,” and “radial” are understood relative to the longitudinal axis A of the manifold 20.

[0065] The chamber 21 has a height h measured along a direction parallel to the flow direction of the liquid in the chamber 21. In this example, the height h is measured along the longitudinal axis A.

[0066] The chamber 21 has, for example, a circular or polygonal cross-section. Advantageously, the chamber 21 extends between a first end 25 (also referred to as the upper end) and an opposing second end 26 (also referred to as the lower end). The first end 25 and the second end 26 are closed.

[0067] The first end 25 is closed, for example, by a cover or upper wall 25a. The second end 26 is closed by a bottom chamber 26a.

[0068] Preferably, chamber 21 defines an inner cavity 27 intended to receive the first and second liquids. Advantageously, the inner cavity 27 is annular and centered on the longitudinal axis A. The first and second liquids flow into the inner cavity 27 by gravity through inlets 22, 23. Figure 2 In the example, the liquid level L in the cavity 27 is equal to a predetermined standard level, which corresponds to the standard inflow rate of liquid entering the manifold. This standard level L of liquid in the cavity can be considered normal because it has not reached the level that would characterize an abnormal flow.

[0069] Inlets 22 and 23 lead to the inner cavity 27. Inlets 22 and 23 are located at the first end 25 and are, for example, disposed on the cover 25a. Therefore, inlets 22 and 23 are opposite to the second end 25b. Inlets 22 and 23 are, for example, annular. Inlets 22 and 23 are offset from the longitudinal axis A of the manifold 20. According to... Figure 2 For example, inlets 22 and 23 have an axis A1 that is parallel to the longitudinal axis A of manifold 20.

[0070] For example, inlets 22 and 23 are connected to the exhaust circuit of turbine engine 1.

[0071] The first outlet 24 leads to the chamber 21. Therefore, the first outlet 24 is configured to discharge liquid from the chamber 21. The first outlet 24 is located, for example, at the second end 26, and thus opposite the first end 25. Therefore, the first outlet 24 is opposite to the inlets 22 and 23.

[0072] according to Figure 2 In the example, the first outlet 24 has an axis A2 that is perpendicular to the longitudinal axis A of the manifold 20.

[0073] The first outlet 24 is connected, for example, to an injector (not shown), which connects, for example, manifold 20 to nozzle 70. This allows the liquid to burn and be ejected from the turbine engine 1 through nozzle 70.

[0074] Preferably, the manifold 20 further includes a metering orifice 28 that fluidly connects the inner cavity 27 to the first outlet 27. The metering orifice 28 is configured to allow the first liquid and / or the second liquid to pass through at a calibrated flow rate. The metering orifice 28 is installed in the inner cavity 27. The metering orifice 28 includes a first inlet end 28a for the first liquid and / or the second liquid and an opposing second outlet end 28b for the first liquid and / or the second liquid. The second end 28b is connected to or forms the first outlet 24.

[0075] Preferably, the metering orifice 28 has an axis A3 that is perpendicular to the longitudinal axis A of the manifold 20 and parallel to the axis A2 of the first outlet 24.

[0076] Preferably, the metering orifice 28 is removably connected to the chamber 21. This allows for the installation and removal of the metering orifice 28 to clean it and limit the risk of clogging. Therefore, maintenance of the metering orifice 28 is facilitated.

[0077] To allow liquid to drain from manifold 20, for example, through first outlet 24, manifold 20 may preferably also include a vent duct. The vent duct is located in chamber 21 of manifold 20. The vent duct includes a ventilation air inlet located in or leading to chamber 21, and a ventilation air outlet leading to first outlet 24.

[0078] Air circulates through the suction effect of the ejector. Air is transported from the ventilation air inlet to the ventilation air outlet through the ventilation duct.

[0079] In some cases, particularly when the seals in the lubrication chambers 17, 18, 19, the fuel supply circuit, or the lubrication circuit rupture, the fluid inlet velocity entering the manifold 20 through the first inlet 22 is greater than the standard velocity. In this situation, the liquid level in the inner cavity 27 rises, requiring the liquid to be drained.

[0080] In this configuration, manifold 20 also includes a liquid discharge pipe 33. The discharge pipe is configured to discharge liquid from cavity 27 into chamber 21 when the liquid level in chamber 21 is greater than or equal to a first threshold liquid level S1 in cavity 27. The first threshold liquid level S1 is measured based on the height of chamber 21. The first threshold liquid level S1 is greater than a predetermined standard threshold.

[0081] The discharge pipe 33 includes a second liquid inlet 34 located in the inner cavity 27 and a second liquid outlet 35 leading to the chamber 21.

[0082] The second inlet 34 has an axis parallel to the longitudinal axis A of the manifold 20. The second inlet 34 is located in a plane perpendicular to the longitudinal axis A and passing through the first threshold liquid level S1. Specifically, the second inlet 34 has an inlet orifice at a height equal to the height of the first threshold liquid level S1 in the inner cavity 27. Therefore, when the liquid level in the inner cavity reaches the first threshold liquid level S1, liquid overflows into the second inlet 34.

[0083] The second inlet 34 is radially offset relative to the first inlet 22 and the additional inlet 23. This prevents liquid entering the inner cavity 27 from contaminating the discharge pipe 33 when the liquid level in the inner cavity 27 is below the first threshold level S1.

[0084] according to Figure 2 In the example, the second outlet 35 is connected to or leads to 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 interchanged with the axis A4 of the ventilation air inlet 30.

[0085] The second inlet 34 and the second outlet 35 are connected by an overflow pipe 36 that defines a liquid flow path. The overflow pipe 36 extends into the cavity 27. The overflow pipe 36 includes, for example, a first axial portion 36a extending longitudinally in the cavity 27 and a second transverse portion 36b extending laterally in the 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.

[0086] Such a leak could have harmful consequences for turbine engine 1. Therefore, testing activities are typically initiated to locate the source of the leak. These activities are cumbersome and require shutting down turbine engine 1, directly impacting the aircraft's availability. To limit the consequences of these leaks, particularly this unavailability of the aircraft, manifold 20 also includes a signal transmission tube 37 located in chamber 21.

[0087] refer to Figure 2 The signal transmitting tube 37 is configured to collect liquid when the liquid level in chamber 21 is greater than a second threshold liquid level S2 in inner cavity 27. The second threshold liquid level S2 is lower than a first threshold liquid level S1.

[0088] The first threshold liquid level and the second threshold liquid level correspond to the height of the liquid in the inner cavity 27 as measured according to the height of the chamber 21. In other words, the first threshold liquid level and the second threshold liquid level correspond to the height of the liquid in the inner cavity 27 as measured along a direction parallel to the direction of liquid flow in the inner cavity 27.

[0089] The signal transmitting tube 37 includes a third liquid inlet 38 and an optional third liquid outlet 39 located within the cavity 27. The third inlet 38 has an axis A8 parallel to the longitudinal axis A of the manifold 20. The third inlet 38 lies in a plane perpendicular to the longitudinal axis A and passing through the second threshold liquid level S2. Specifically, the third inlet 38 has an inlet orifice at a height equal to the height of the second threshold liquid level S2 in the cavity 27. Therefore, when the liquid level in the cavity 27 reaches the second threshold liquid level S2, liquid overflows into the third inlet 38. The third inlet 38 is radially offset from the first inlet 22 and the additional inlet 23.

[0090] The third inlet 38 is axially offset relative to the second inlet 34. Specifically, the third inlet 38 is axially closer to the second end 26 of the chamber 21 than the second inlet 34, and therefore axially closer to the bottom wall 26a. The third inlet 38 is axially farther away from the first inlet 22 than the second inlet 34. In fact, the height of the third inlet 38 in the chamber 21 is lower than the height of the second inlet 34.

[0091] The third outlet 39 is fluidly connected to the outside of the chamber 21. For example, the third outlet is connected to the discharge pipe 33. In order to control the outflow rate of the liquid flowing out through the third outlet 39, the third outlet 39 may be equipped with a diaphragm.

[0092] Specifically, the signal transmitting tube 37 extends longitudinally within the cavity 27. The signal transmitting tube 37 extends longitudinally within the cavity 27 between an upper end 37a having a third inlet 38 and an axially opposite lower end 37b. The signal transmitting tube 37 also has a fluid passage 37c extending between the upper end 37a and the lower end 37b.

[0093] According to the present invention, the manifold 20 further includes a detection and signal transmission device 40 for detecting and transmitting signals to indicate a first threshold liquid level S1 and / or a second threshold liquid level S2. The detection and signal transmission device 40 is configured to detect and transmit signals when the first threshold liquid level S1 and / or the second threshold liquid level S2 in the chamber 21 are reached.

[0094] The detection and signal transmission device 40 for detecting and sending a signal to inform the first threshold S1 is mounted on the chamber 21 and is preferably positioned opposite to the first end 25 of the chamber 21.

[0095] According to one example, the detection and signaling device 40 includes a detection and signaling element configured to independently send signals to inform a first threshold liquid level S1 and a second threshold liquid level S2.

[0096] In this example, the detection and signal transmission elements are connected to both the discharge tube 33 and the signal transmission tube 37.

[0097] The detection and signal transmission elements include, for example, a lamp that transmits a signal in the form of a first color to indicate a first threshold liquid level S1 and a signal in the form of a second color different from the first color to indicate a second threshold liquid level S2.

[0098] according to Figure 2 In another example shown, the detection and signal transmission device 40 includes a first detection and signal transmission element 41 configured to transmit a signal to a first threshold liquid level S1, and a second detection and signal transmission element 42 configured to transmit a signal to a second threshold liquid level S2. The first detection and signal transmission element 41 is connected to the discharge pipe 33, and the second detection and signal transmission element 42 is connected to the signal transmission pipe 37.

[0099] The first detection and signal transmission element 41 and the second detection and signal transmission element 42 include, for example, a first indicator light and a second indicator light.

[0100] According to an alternative, the first detection and signal transmission element 41 and the second detection and signal transmission element 42 each include an observation glass or window capable of detecting and transmitting signals to indicate the presence of liquid in the discharge pipe 36 and the signal transmission pipe 37. Each observation glass or window is respectively mounted opposite to the discharge pipe 36 and the signal transmission pipe 37. Specifically, the first observation glass 41 is mounted opposite to the axial portion 36a of the overflow pipe 36 and opposite to the second inlet 34, and the second observation glass 42 is mounted opposite to the lower end 37b of the signal transmission pipe 37.

[0101] The operation of the manifold 20 according to the present invention will now be described.

[0102] For example, liquid leaking from lubrication chambers 17, 18, and 19, or fuel from combustion chamber 5, is discharged through discharge circuit C1. The discharged liquid enters manifold 20 through at least first inlet 22 at a standard flow rate. The liquid then flows into inner cavity 27 by gravity. The liquid in inner cavity 27 is discharged through first outlet 24 at a standard outlet flow rate. The discharged liquid can then be discharged into nozzle 70.

[0103] In some cases, such as when a sealing gasket breaks, the fluid flow rate into chamber 21 can exceed the standard flow rate and the outlet flow rate. The fluid level in inner chamber 27 can accumulate and reach a second threshold level S2. The fluid in inner chamber 27 overflows into signal transmitting pipe 37. Then, detection and signal transmitting device 40 detects the second threshold level S2, while the first threshold level S1 has not yet been detected. Once an alarm is issued, the operator can plan maintenance operations without stopping turbine engine 1.

[0104] As a result of this invention, maintenance operations can be planned, thereby reducing the workload of operators. Furthermore, the availability of turbine engine 1 is improved because the shutdown of turbine engine 1 can be anticipated and planned.

[0105] Reference Figure 3 This describes a maintenance method for maintaining turbine engine 1.

[0106] The maintenance method includes the following steps: (a) Supplying the turbine engine 1 and the manifold 20 installed in the turbine engine, (b) The inner cavity 27 is filled with the first liquid through the first inlet 22, and the first liquid is discharged from the chamber 21 through the first outlet 24. (c) Detect the second threshold liquid level S2 of the liquid in the inner cavity 27. (d) Optionally, a first threshold liquid level S1 of the liquid in the cavity 27 is detected, and (e) Plan maintenance operations between steps (c) and (d).

Claims

1. A manifold (20) for at least one first liquid in an aircraft turbine engine (1), said manifold (20) comprising: - Chamber (21), which defines an inner cavity (27) designed to receive at least the first liquid. - At least one first inlet (22, 23) of the first liquid, the first inlet leading to the inner cavity (27). - First liquid outlet (24) leading to the chamber (21). - A liquid discharge pipe (33) configured to discharge liquid from the inner cavity (27) to the chamber (21) when the liquid level in the inner cavity (27) is greater than or equal to a first threshold liquid level (S1) in the inner cavity (27), the discharge pipe (33) comprising: - A second liquid inlet (34) located in the inner cavity (27). - A second liquid outlet (35) leading to the chamber (21). The manifold (20) is characterized in that it further includes: - A signal transmitting tube (37), located in the chamber (21) and configured to collect liquid when the liquid level in the chamber (27) is greater than or equal to a second threshold liquid level (S2) in the chamber (27), the second threshold liquid level being lower than a first threshold liquid level (S1), the signal transmitting tube (37) comprising: - A third liquid inlet (38) located in the inner cavity (27). The manifold (20) also includes: - Detection and signal transmission device (40) for detecting and transmitting signals to inform that the liquid level in the cavity (27) has reached one of the first threshold liquid level and the second threshold liquid level (S1, S2) and / or the other.

2. The manifold according to the preceding claim, characterized in that, The chamber (21) extends longitudinally along the longitudinal axis (A) between the first end (25) and the second end (26) which is closed by the bottom wall (26a), and the third inlet (38) is closer to the bottom wall (26a) in the axial direction than the second inlet (34).

3. The manifold according to the preceding claim, characterized in that, The signal transmitting tube (37) extends longitudinally within the inner cavity (27).

4. The manifold according to claim 2 or 3, characterized in that, The second liquid inlet and the third liquid inlet (34, 38) are radially offset relative to the first liquid inlet (22, 23).

5. The manifold according to any one of the preceding claims, characterized in that, The detection and signal transmission device (40) includes at least one first detection and signal transmission element (41), which includes at least one indicator light or observation glass.

6. The manifold according to the preceding claim, characterized in that, The first detection and signal transmission element (41) is connected to both the discharge tube (33) and the signal transmission tube (37).

7. The manifold according to claim 5, characterized in that, The detection and signal transmission device includes a second detection and signal transmission element (42) connected to the signal transmission tube (37), and the first detection and signal transmission element (41) is connected to the discharge tube (33).

8. The manifold according to any one of the preceding claims, characterized in that, The signal transmitting tube (38) includes a third liquid outlet (39).

9. The manifold according to any one of the preceding claims, characterized in that, The manifold is manufactured using additive manufacturing.

10. A maintenance method for maintaining an aircraft turbine engine (1), the maintenance method comprising the following steps: (a) Supplying a turbine engine (1), said turbine engine comprising a manifold (20) according to any one of the preceding claims. (b) The cavity (27) is filled with the first liquid through the first inlet (22, 23), and the first liquid is discharged from the chamber (21) through the first outlet (24). (c) Detect the second threshold liquid level (S2) of the liquid in the inner cavity (27). (d) Optionally, the first threshold liquid level (S1) of the liquid in the inner cavity (27) is detected, and (e) Plan maintenance operations between steps (c) and (d).

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