TURBOMACHINE FOR AN AIRCRAFT COMPRISING A MANIFOLD

Abstract

The invention relates to a turbomachine (1) comprising: - a nozzle (70) comprising a casing (71), - at least one drainage circuit (C1) for at least one liquid, - a manifold (20) comprising: - an enclosure (21) defining an internal cavity (27), - a first inlet (22, 23) (27) connected to the first drainage circuit (C1), - a first outlet (24), - a suction duct (42) connected to the casing (71) and to the manifold (20), the suction duct (42) comprising: - a first open end (43) connected to the casing (71) and opening into the gas flow path (v1), and - a second end (44) connected to the first outlet (24), - an opening opening into the gas flow path (v1) and connected to the first end (43) of the suction duct (42), the opening (50) being configured to create a depression in the suction duct (42). abstract figure: 2

Description

Title of the invention: TURBOMACHINE FOR AN AIRCRAFT COMPRISING A MANIFOLD Technical field of the invention

[0001] The invention relates to the field of turbomachines for aircraft, comprising a drainage circuit for at least a first liquid and a collector connected to the drainage circuit. Technical background

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

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

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

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

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

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

[0008] For this purpose, the turbomachine typically comprises at least one drainage circuit for at least one liquid, such as oil and / or fuel.

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

[0010] The evacuation of the liquid through the first outlet is typically done by emptying through a Venturi effect ejector.

[0011] For this purpose, the turbomachine further comprises an ejector comprising an air inlet, a liquid inlet connected to the first outlet of the manifold and an outlet for the air and liquid mixture connected to the nozzle. The air inlet is typically connected to the high-pressure compressor and thus makes it possible to create a vacuum in the ejector in order to promote the suction of the liquid from the manifold through the liquid inlet of the ejector, by Venturi effect. This suction drains the internal cavity and therefore evacuates the liquid from the manifold. The air and liquid mixture is then expelled through the nozzle.

[0012] Such a configuration of the manifold in the turbomachine is not entirely satisfactory. Indeed, the air sampling within the high pressure compressor impacts the overall performance of the turbomachine. The performance of the turbomachine is typically reduced by a percentage typically between 0.1% and 0.3%. Also, the ejector increases the number of interfaces in the turbomachine, making the assembly of the turbomachine more complex and increasing its mass and cost.

[0013] Therefore, there is a need to provide a turbomachine comprising a collector which allows the drained liquid to be evacuated in a simple and economical manner without reducing the performance of the turbomachine. Summary of the invention

[0014] To this end, the invention proposes a turbomachine for an aircraft, the turbomachine having a longitudinal axis and comprising:

[0015] - a gas exhaust nozzle comprising an annular casing centered on the axis longitudinal and defining a gas flow vein,

[0016] - at least one drainage circuit for at least one liquid,

[0017] - a liquid collector comprising:

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

[0019] - a first liquid inlet opening into the internal cavity and connected to the first drainage circuit,

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

[0021] - a suction duct connected to the casing and the manifold, the suction duct including:

[0022] - a first open end connected to the casing and opening into the vein gas flow, and

[0023] - a second end connected to the first output,

[0024] - an opening opening into the gas flow stream and connected to the first end of the suction duct, the opening being configured to create a vacuum in the suction duct.

[0025] According to the invention, the collector is connected to the nozzle by a suction duct. The first end of the suction duct is furthermore connected to an opening located in the gas flow path.

[0026] Thanks to such an opening, the kinetic energy of the gases flowing in the nozzle is captured by the first end of the suction duct so that a depression is created in this suction duct.

[0027] In accordance with the Venturi effect, thanks to such a depression, the liquid from the internal cavity of the collector is sucked into this suction duct and evacuated by draining outside the collector enclosure. This liquid is then evacuated into the nozzle.

[0028] Thanks to such a configuration, it is possible to do without an ejector and an air bleed in a compressor of the turbomachine.

[0029] It is possible to evacuate the liquid from the collector into the nozzle in a simple and economical manner while minimizing the impact on the performance of the turbomachine.

[0030] The invention may comprise one or more of the following features, taken in isolation from one another or in combination with one another:

[0031] - a tip located in the vein and at least partially carrying the opening,

[0032] - the tip comprises a cylindrical body extending from the first end to a free end carrying the opening,

[0033] - the free end has a circular section,

[0034] - the free end has a C-shaped section,

[0035] - the tip comprises a cylindrical body carrying the opening and extending from the first end to a closed free end,

[0036] - the cylindrical body comprises a first portion and a second portion connected to the first portion by a shoulder and extending to the free end, the opening being located on the second portion,

[0037] - the tip comprises a semi-annular body delimiting the opening with the casing,

[0038] - the first end and the end piece are connected to the casing by bolting,

[0039] - the suction duct is connected to the casing at a position between 3 o'clock and 9 o'clock,

[0040] - a discharge conduit configured to discharge liquid from the internal cavity by outside the enclosure when the liquid level in the internal cavity is greater than or equal to a threshold liquid level in the internal cavity, the discharge conduit comprising:

[0041] - a second liquid inlet located in the internal cavity, and

[0042] - a second liquid outlet opening outside the enclosure,

[0043] - a ventilation duct comprising a ventilation air inlet opening outside the enclosure and a ventilation air outlet connected to the first outlet to discharge a mixture of air and liquid. Brief description of the figures

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

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

[0046] [Fig.2] [Fig.2] is a schematic representation of a collector connected to a circuit drainage and to a nozzle of the turbomachine by a suction duct,

[0047] [Fig.3] [Fig.3] is a schematic representation in longitudinal section of the collector,

[0048] [Fig.4] [Fig.4] is a perspective representation of the collector connected to the pipe suction,

[0049] [Fig.5] [Fig.5] is a perspective representation of the suction duct connected to the nozzle,

[0050] [Fig.6] [Fig.6] is a perspective representation of a tip according to a first example of realization,

[0051] [Fig.7] [Fig.7] is a perspective representation of a tip according to a second example of realization,

[0052] [Fig.8] [Fig.8] is a perspective representation of a tip according to a third example of realization,

[0053] [Fig.9] [Fig.9] is a perspective representation of a tip according to a fourth example of realization,

[0054] [Fig. 10] [Fig. 10] is a perspective representation of a tip according to a fifth exemplary embodiment. Detailed description of the invention

[0055] An example of an aircraft turbomachine 1 according to the invention is shown in [Fig.l]. The turbomachine 1 is for example a dual-flow turbojet. The turbomachine 1 may have any other architecture and be in the form of a turboprop, for example.

[0056] The turbomachine 1 is modular. It comprises a plurality of modules assembled together.

[0057] The turbomachine 1 extends along a longitudinal axis X. A gas flow F flows in the turbomachine 1.

[0058] For the purposes of the present invention, the terms "upstream" and "downstream" are understood to refer to the direction of flow of the gas flow F in the turbomachine 1. The gas flow F flows in particular from left to right in FIGS. 1 and 2.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] The low pressure 8 and high pressure 9 shafts are centered on the longitudinal axis X and rotatable about the longitudinal axis X. The high pressure shaft 9 is arranged coaxially around the low pressure shaft 8.

[0064] The gas flow F passes through the blower 2 and is divided into a primary air flow F1 passing through a primary vein v1 and into a secondary air flow F2 passing through a secondary vein v2 surrounding the primary vein v1. 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 turbines 6 and low pressure 7. The energy of the gases is transformed by the turbine rotor 7a of the low pressure turbine 7 into mechanical energy enabling the low pressure shaft 8 and consequently the low pressure compressor 3 to rotate. The gases are then ejected into the nozzle 70.

[0065] The fan 2 comprises a mobile disc rotating around the longitudinal axis X and blades 2a carried by the disc and regularly distributed around the longitudinal axis X. In the example of [Fig.l], the fan 2 is surrounded by a fan casing 2b. The fan 2 is of the ducted type. The fan casing 2b carries a nacelle 2c and together define a fan compartment 2d.

[0066] According to another example not shown, the fan 2 is of the non-ducted type.

[0067] 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.

[0068] 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.

[0069] The nozzle 70 defines a downstream portion of the primary vein vl for the flow of gases resulting from combustion. It comprises an annular casing 71 centered on the longitudinal axis X. The casing 71 advantageously comprises an inner shell and an outer shell arranged coaxially around the inner shell. The inner and outer shells are connected by arms.

[0070] 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.

[0071] 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.

[0072] 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.

[0073] The turbomachine 1 may further comprise an inter-vein compartment v3 located between the primary vein v1 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 casing 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 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.

[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 casing 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 casing 14 for example.

[0078] Each bearing comprises, for example, a rolling bearing. The rolling bearing is, for example, at least one row of balls or rollers.

[0079] 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.

[0080] 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.

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

[0082] 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.

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

[0084] 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.

[0085] 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.

[0086] The turbomachine 1 further comprises a circuit for supplying the combustion chamber 5 with fuel.

[0087] Despite the sealing of the lubrication chambers 17, 18, 19, leaks of lubricating oil may occur. Also, the fuel from the combustion chamber 5 must be evacuated in order to limit the risks of coking. There are also fuel or oil leaks from certain hydraulic actuators of the turbomachine 1.

[0088] In this context, the turbomachine 1 further comprises at least one first drainage circuit C1 connected to the combustion chamber 5 and / or to the lubrication enclosures 17, 18, 19. The first drainage circuit C1 thus drains at least one liquid from the combustion chamber 5 and / or from the lubrication enclosures 17, 18, 19 such as lubricating oil and / or fuel. The turbomachine 1 may comprise a second drainage circuit (not shown) connected to the combustion chamber 5 and / or to the lubrication enclosures 17, 18, 19 for the drainage of at least one liquid such as lubricating oil and / or fuel.

[0089] With reference to [Fig.2], in order to limit the risk of environmental pollution, the turbomachine 1 further comprises a collector 20 connected to the drainage circuit C1 and to the nozzle 70.

[0090] The collector 20 is configured to collect the liquid from the drainage circuit CL. With reference to FIGS. 2 and 3, the collector 20 comprises an enclosure 21, at least a first liquid inlet 22, optionally an additional liquid inlet 23 and a first liquid outlet 24.

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

[0092] In the remainder of the description, with reference to the collector 20, 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 Figures 2 and 3, the liquid flows by gravity from top to bottom.

[0093] In the remainder of the description, with reference to the collector 20, the terms “longitudinal”, “longitudinally”, “radial”, “radially” are understood relative to the longitudinal axis A of the collector 20.

[0094] 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.

[0095] 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.

[0096] The first and second ends 25, 26 are closed. 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.

[0097] The enclosure 21 preferably delimits an internal cavity 27 receiving the liquid. The internal cavity 27 is advantageously annular and centered on the longitudinal axis A. The first and second liquids flow into the internal cavity 27 by gravity through the inlets 22, 23. According to the example of [Fig. 3], the cavity 27 has a liquid level L equal to a predetermined standard threshold.

[0098] The inlets 22, 23 open into the internal cavity 27. They are located at the first end 25 and are for example arranged on the cover 25a. The inlets 22, 23 are thus opposite the second end 26 of the enclosure 21. The inlets 22, 23 are for example annular. According to the example of [Fig. 3], the inlets 22, 23 have an axis A1 parallel to the longitudinal axis A of the collector 20. The axis A1 of each inlet 22, 23 is offset relative to the longitudinal axis A of the collector A.

[0099] The first inlet 22 is connected to the first drainage circuit C1 and the additional inlet 23 can be connected to the second drainage circuit.

[0100] 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.

[0101] According to the example of [Fig.3], the first outlet 24 has an axis A2 perpendicular to the longitudinal axis A of the collector 20.

[0102] Preferably, the collector 20 further comprises a nozzle 28 which fluidly connects the internal cavity 27 and the first outlet 24. The nozzle 28 is configured to allow the passage according to a calibrated flow rate of the first and / or the second liquid. Also, the nozzle 28 is configured to evacuate the liquid in the form of droplets in order to facilitate the evacuation of the liquid.

[0103] The nozzle 28 comprises a first liquid inlet end 28a and an opposite second liquid outlet end 28b. The second end 28b is connected to the first outlet 24 or forms the first outlet 24.

[0104] 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.

[0105] 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 to limit the risks of the nozzle 28 becoming blocked. Maintenance of the nozzle 28 is thus made easier.

[0106] The collector 20 further comprises a ventilation duct 29. The ventilation duct 29 is located in the enclosure 21 of the collector 20. It comprises a ventilation air inlet 30 opening outside the enclosure 21 and a ventilation air outlet 31 which is connected to the first outlet 24.

[0107] The ventilation air inlet 30 has, for example, an axis A4 which is perpendicular to the longitudinal axis A of the collector 20.

[0108] The ventilation air outlet 31 has an axis A5 which is parallel to the longitudinal axis A of the collector 20 and perpendicular to the axis A3 of the nozzle 28.

[0109] The air inlet and outlet 30, 31 are advantageously located opposite the first end 25 of the collector 20. Preferably, the air inlet and outlet 30, 31 are radially opposite.

[0110] According to an exemplary embodiment, the ventilation air inlet and outlet 30, 31 are connected by a ventilation line 32. The ventilation line 32 has, for example, in longitudinal section an inverted U shape. The ventilation line 32 thus comprises a first section 32a and a second section 32b connected together by an intermediate section 32c. The first and second sections 32a, 32b extend longitudinally in the enclosure 21 while the intermediate section 32c extends transversely in the enclosure 21.

[0111] In certain cases, in particular in the event of rupture of the seals of the lubrication enclosures 17, 18, 19, of the fuel supply circuit or even 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 advantageous to evacuate this liquid.

[0112] In this context, the collector 20 further comprises a liquid discharge pipe 33. The discharge pipe 33 is configured to discharge the liquid from the internal cavity 27 outside the enclosure 21 when the liquid level in the enclosure 21 is greater than or equal to a threshold level SI of liquid in the internal cavity 27. The level threshold SI is measured according to the height h of the enclosure 21. The threshold level SI is higher than a predetermined standard level. This predetermined standard level typically corresponds to a standard flow rate of liquid entering the collector 20. This standard level of liquid in the internal cavity 27 can be considered normal, since it does not reach the threshold level, that is to say the level of an alert threshold which would characterize an abnormal flow rate.

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

[0114] The second inlet 34 has an axis A6 parallel to the longitudinal axis A of the collector 20. The second inlet 34 is located in a plane perpendicular to the longitudinal axis A and passing through the threshold level SL. In particular, the second inlet 34 has an inlet orifice located at a height equal to the height of the threshold level SI in the internal cavity 27. Thus, when the liquid level in the internal cavity reaches the threshold level SI, the liquid overflows into the second inlet 34.

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

[0116] According to the example of [Fig.3], the second outlet 35 and the ventilation air inlet 30 are merged.

[0117] The second inlet and outlet 34, 35 are connected by an overflow tube 36 which defines a liquid flow passage. The overflow tube 36 extends into the internal cavity 27. The overflow tube 36 comprises, for example, a first axial portion 36a extending longitudinally in the internal cavity 27 and a second transverse portion 36b extending transversely. The first axial portion 36a is connected to the second inlet 34 and the second transverse portion 36b connects the first axial portion 36a to the second outlet 35.

[0118] Such leaks can have harmful consequences on the turbomachine 1. It is therefore preferable to be able to detect such leaks. In this context, preferably, the collector 20 further comprises a device 40 for detecting and signaling the reaching by the liquid level in the internal cavity 27 of the threshold level SL. The detection and signaling device 40 is configured to detect and signal when the threshold level SI of liquid in the enclosure 21 is reached.

[0119] The detection and signaling device 40 of the threshold level SI is preferably located opposite the first end 25 of the enclosure 21.

[0120] According to one example, the detection and signaling device 40 comprises

[0121] a light signaling the SI threshold level in the form of a first color.

[0122] According to another example illustrated in [Fig. 3], the detection and signaling device 40 comprises a porthole or a window 41 making it possible to detect and signal the presence of liquid in the discharge pipe 33. The porthole or the window 41 is mounted on the enclosure 21 for example. In particular, the porthole or the window 41 is mounted opposite the discharge pipe 33, in particular a lower end of the axial portion 36a of the overflow tube 36.

[0123] In standard conditions, that is to say when the liquid level in the internal cavity 27 is lower than the threshold level SI, the liquid is evacuated by draining according to the Venturi effect principle.

[0124] To this end, with reference to Figures 2 and 4, the turbomachine 1 according to the invention further comprises a suction duct 42 connected to the collector 20 and to the casing 71 of the nozzle 70.

[0125] The suction duct 42 extends between a first end 43 opening into the primary vein vl of the casing 71 and a second end 44 connected to the collector 20.

[0126] The suction duct 42 further comprises a suction pipe 45 which connects the first and second ends 43.

[0127] The second end 44 is connected to the first outlet 24 of the collector 20. In particular, the second end 44 is connected to one end of the first outlet 24 located outside the enclosure 21.

[0128] The first end 43 advantageously comprises a sleeve 47 which connects the suction pipe 45 to the casing 71.

[0129] The sleeve 47 has a cylindrical shape and has an axis extending radially relative to the longitudinal axis X of the turbomachine 1. The sleeve 47 has, for example, an external diameter greater than an external diameter of the suction pipe 45.

[0130] The suction pipe 45 may comprise a portion of pipe of reduced section located between the first and second ends 43, 44.

[0131] Preferably, as best seen in [Fig.5], the first end 43 is connected to the casing 71 at a position between 3 o'clock and 9 o'clock by analogy with the corresponding position of the hands of a clock face.

[0132] The first end 43 is preferably connected to the casing 71 by bolting. For example, the turbomachine 1 comprises an external flange 48 connected to the first end 43 and to the casing 71 and an internal flange 49 fixed on an internal surface of the casing 71 and connected to the external flange 48 by bolts 49a. The external flange 48 is for example fixed to the sleeve 47.

[0133] According to the invention, the first end 43 is connected to an opening 50 located in the primary vein vl. The opening 50 is therefore located in the casing 71 of the nozzle 70. This opening 50 makes it possible to subject the first end 43 of the suction duct 42 to a pressure greater than the pressure in the collector 20 to create a depression in the suction duct 42 and to suck the liquid from the internal cavity 27 through the first outlet 24 by Venturi effect.

[0134] Thanks to the invention, it is possible to do without an ejector and an air sampling in the high pressure compressor.

[0135] The configuration of the turbomachine 1 and its performance are thus significantly improved.

[0136] Preferably, the turbomachine 1 comprises a nozzle 46 located in the primary vein vl and which at least partially carries the opening 50.

[0137] The opening 50 can have different configurations which will now be described.

[0138] According to a first embodiment illustrated in [Fig.6], the nozzle 46 comprises a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. It extends from the suction pipe 45, in particular from the sleeve 47 to the free end 52. The free end 52 carries the opening 50. The opening 50 is annular and has a circular section.

[0139] According to a second embodiment illustrated in [Fig.7], the end piece 46 comprises a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. It extends from the suction pipe 45, in particular from the sleeve 47, to the free end 52. The free end 52 carries the opening 50. The opening has a C-shaped section. The cylindrical body 51 further has a U-shaped notch 51a which extends to the opening 50. According to this embodiment, the cylindrical body 51 may have a length L as measured along its axis greater than or equal to at least three times its diameter.

[0140] According to a third embodiment illustrated in [Fig.8], the end piece 46 comprises a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. It extends from the suction pipe 45, in particular from the sleeve 47, to the free end 52. The free end 52 carries the opening 50. The opening has a C-shaped section. The cylindrical body 51 further has a U-shaped notch 51a which extends to the opening 50. According to this embodiment, the cylindrical body 51 may have a length L as measured along its axis less than or equal to at least three times its diameter. According to this embodiment, the notch 51a extends substantially to the sleeve 47.

[0141] According to a fourth embodiment illustrated in [Fig.9], the nozzle 46 comprises a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. It extends from the suction pipe 45, in particular from the sleeve 47 to the end free end 52. The free end 52 is, according to this embodiment, closed. The opening 50 is provided on the cylindrical body 51.

[0142] In particular, the cylindrical body 51 comprises a first portion 53 and a second portion 54 connected to the first portion 53 and extending to the free end 52. The first portion 53 is connected to the first portion 53 by a shoulder 53a for example. Thus, the first portion 53 has an external diameter greater than an external diameter of the second portion 54.

[0143] The opening 50 is for example located on the second portion 54. The opening 50 has for example the shape of an oblong hole.

[0144] According to a fifth embodiment illustrated in [Fig. 10], the end piece 46 comprises a semi-annular body 55. The semi-annular body 55 has an axis for example parallel to the longitudinal axis X of the casing 71 of the nozzle 70. The semi-annular body 55 is for example connected to the internal flange 49 and advantageously forms a single-piece part with the internal flange 49.

[0145] The semi-annular body 55 delimits with the casing 71 of the nozzle 70 the opening 50.

[0146] According to this embodiment, the end piece 46 and the second end 43 are connected to the casing 71 by the external and internal flanges 48, 49.

Claims

Claims

1. Turbomachine (1) for an aircraft, the turbomachine (1) having a longitudinal axis (X) and comprising: - a gas exhaust nozzle (70) comprising an annular casing (71) centered on the longitudinal axis (X) and defining a gas flow path (vl), - at least one drainage circuit (Cl) for at least one liquid, - a liquid collector (20) comprising: - an enclosure (21) defining an internal cavity (27) intended to receive the liquid, - a first liquid inlet (22, 23) opening into the internal cavity (27) and connected to the first drainage circuit (Cl), - a first liquid outlet (24) opening outside the enclosure (21), - a suction duct (42) connected to the casing (71) and to the collector (20), the suction duct (42) comprising: - a first open end (43) connected to the casing (71) and opening into the gas flow vein (vl), and - a second end (44) connected to the first outlet (24),- an opening (50) opening into the gas flow path (vl) and connected to the first end (43) of the suction duct (42), the opening (50) being configured to create a vacuum in the suction duct (42).,

2. Turbomachine according to the preceding claim, characterized in that it comprises a nozzle (46) located in the vein (vl) and at least partly carrying the opening (50).

3. Turbomachine according to the preceding claim, characterized in that the end piece (46) comprises a cylindrical body (51) extending from the first end (43) to a free end (52) carrying the opening (50).

4. Turbomachine according to the preceding claim, characterized in that the free end (52) has a circular section.

5. Turbomachine according to claim 3, characterized in that the free end (52) has a C-shaped section.

6. Turbomachine according to claim 2, characterized in that the end piece (46) comprises a cylindrical body (51) carrying the opening (50) and extending from the first end (43) to a free end (52) closed.

7. Turbomachine according to the preceding claim, characterized in that the cylindrical body (51) comprises a first portion (53) and a second portion (54) connected to the first portion (53) by a shoulder (53a) and extending to the free end (52), the opening (50) being located on the second portion (54).

8. Turbomachine according to claim 2, characterized in that the end piece (46) comprises a semi-annular body (55) delimiting the opening (50) with the casing (71).

9. Turbomachine according to the preceding claim, characterized in that the first end (43) and the end piece (46) are connected to the casing (71) by bolting.

10. Turbomachine according to any one of the preceding claims, characterized in that the suction duct (42) is connected to the casing (71) at a position between 3 o'clock and 9 o'clock.

11. Turbomachine according to any one of the preceding claims, characterized in that the collector (20) comprises a discharge duct (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 threshold level (SI) of liquid in the internal cavity (27), the discharge duct (33) comprising: - a second liquid inlet (34) located in the internal cavity (27), and - a second liquid outlet (35) opening outside the enclosure (21).

12. Turbomachine according to any one of the preceding claims, characterized in that the manifold (20) comprises a ventilation duct (29) comprising a ventilation air inlet (30) opening outside the enclosure (21) and a ventilation air outlet (31) connected to the first outlet (24) to evacuate a mixture of air and liquid.

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