Turbine engine for an aircraft comprising a manifold

Abstract

The invention relates to a turbine engine (1) comprising: - a nozzle (70) comprising a casing (71); - at least one discharge circuit (C1) for discharging 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 discharge 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 a 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), wherein the opening (50) is configured to create a vacuum in the suction duct (42).

Description

Technical Field

[0001] This invention relates to the field of turbine engines for aircraft, the turbine engine comprising a discharge circuit for discharging at least one first liquid and a manifold connected to the discharge circuit. Background Technology

[0002] In particular, turbine engines used in aircraft typically extend along and around a longitudinal axis. In the case of a dual-body and dual-flow turbine engine, the turbine engine includes a gas generator, which typically includes a low-pressure compressor, a high-pressure compressor, a gas combustion chamber, a high-pressure turbine, and a low-pressure turbine from upstream to downstream along the gas flow direction in the turbine engine.

[0003] 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.

[0004] 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 can be connected to a low-pressure shaft via a reduction gear.

[0005] The high-pressure and low-pressure shafts are guided to rotate via guide bearings, which are lubricated by lubricating oil to ensure proper operation. To protect relevant components of the turbine engine from the effects of this lubricant, 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 lubricating oil to be supplied to it. Furthermore, each lubrication chamber is defined by a sealing system including gaskets that prevent lubricating oil leakage to the outside of the chamber.

[0006] In addition, fuel is supplied to the combustion chamber and certain hydraulic actuators of the turbine engine. For this purpose, turbine engines typically include a fuel circuit that enables fuel to be supplied to the combustion chamber and / or hydraulic actuators.

[0007] The lubrication chamber, fuel, and lubrication circuits may be subject to fluid leaks, particularly fuel and / or lubricating oil leaks. Although these leaks occur at rates considered normal, they represent potential sources of environmental pollution. Furthermore, fuel from the combustion chamber is typically vented to limit the risk of coking.

[0008] For this purpose, turbine engines typically include at least one discharge circuit for at least one liquid (such as oil and / or fuel).

[0009] To limit environmental pollution caused by the discharged liquid, turbine engines typically include a manifold for collecting the liquid. The manifold includes a containment portion defining an inner cavity and a first inlet that opens into the inner cavity and connects to a discharge circuit. The manifold also includes a first outlet for the liquid that opens to the outside of the containment portion to discharge the liquid from the manifold.

[0010] The discharge of liquid through the first outlet is usually performed by a Venturi effect ejector.

[0011] For this purpose, the turbine engine also includes an injector comprising an air inlet, a liquid inlet, and an outlet for an air-liquid mixture. The liquid inlet is connected to a first outlet of the manifold, and the air-liquid mixture outlet is connected to a nozzle. The air inlet is typically connected to a high-pressure compressor, thus enabling the creation of a vacuum in the injector to draw liquid from the manifold via the liquid inlet of the injector through the Venturi effect. This drawing performs a discharge of the internal cavity, thereby expelling the liquid from the manifold. The air-liquid mixture is then discharged through the nozzle.

[0012] This configuration of the manifold in a turbocharged engine is not entirely satisfactory. In fact, drawing air from the high-pressure compressor affects the overall performance of the turbocharged engine. The performance reduction is typically between 0.1% and 0.3%. Furthermore, the injectors increase the number of interfaces in the turbocharged engine, making assembly more complex and increasing its weight and cost.

[0013] Therefore, there is a need for a turbine engine that includes a manifold that allows for the discharge of liquids in a simple and economical manner without reducing the performance of the turbine engine. Summary of the Invention

[0014] Therefore, the present invention proposes a turbine engine for an aircraft, the turbine engine having a longitudinal axis and comprising: - A gas discharge nozzle, comprising an annular housing centered on a longitudinal axis, defining a gas flow path for gas flow. - At least one discharge circuit for discharging at least one liquid. - A manifold for liquids, comprising: - Enclosure, which defines an inner cavity for containing liquid. - First liquid inlet, the first liquid inlet leads to the inner cavity and is connected to the first discharge circuit. - First liquid outlet, the first liquid outlet leads to the outside of the enclosure. - Suction tubing, which connects to the housing and manifold, includes: - The first opening end, which is connected to the housing and leads to the gas flow path, and - Second end, the second end is connected to the first outlet. - An opening that leads to the gas flow path and is connected to the first end of the suction pipe is configured to create a vacuum in the suction pipe.

[0015] According to the invention, the manifold is connected to the nozzle via a suction pipe. Furthermore, the first end of the suction pipe is connected to an opening located in the gas flow path.

[0016] Because of this opening, the kinetic energy of the gas flowing in the nozzle is captured at the first end of the suction pipe, thereby creating a vacuum in the suction pipe.

[0017] According to the Venturi effect, due to this vacuum, liquid from the manifold cavity is drawn into the suction pipe and discharged outside the manifold enclosure. Thus, this liquid is discharged into the nozzle.

[0018] This configuration eliminates the need for injectors and the air exhausted from the compressor of the turbine engine.

[0019] It allows for a simple and economical way to drain liquid from the manifold into the nozzle, while minimizing the impact on the performance of the turbine engine.

[0020] This invention may include one or more of the following features, used individually or in combination: - The end component is located in the flow path and has at least a partial opening. - The end component includes a cylindrical body extending from a first end to a free end with an opening. - The free end has a circular cross-section. - The free end has a C-shaped cross section. - The end component includes a cylindrical body with an opening and extends from the first end to a closed free end. - The cylindrical body comprises a first part and a second part, the second part being connected to the first part via a shoulder and extending to a free end, with an opening located on the second part. - The end component includes a semi-annular body, which, together with the housing, defines an opening. - The first end and end components are connected to the housing by bolts. - The suction tube connects to the housing at a position between 3 o'clock and 9 o'clock. - The discharge pipe is configured to discharge liquid from the cavity to the outside of the enclosure when the liquid level in the cavity is greater than or equal to a threshold liquid level in the cavity. The discharge pipe includes: - Second liquid inlet, the second liquid inlet is located in the inner cavity, and - Second liquid outlet, the second liquid outlet leads to the outside of the enclosure. - A ventilation duct, the ventilation duct including a ventilation air inlet and a ventilation air outlet, the ventilation air inlet leading to the outside of the enclosure, and the ventilation air outlet connected to a first outlet to discharge a mixture of air and liquid. Attached Figure Description

[0021] Further 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 schematic diagram of a manifold that connects to the exhaust circuit and the turbine engine nozzles via a suction pipe. [ Figure 3 ] Figure 3 This is a schematic diagram of the longitudinal cross-section of the manifold. [ Figure 4 ] Figure 4 This is a perspective view of the manifold connected to the suction line. [ Figure 5 ] Figure 5 This is a perspective view of the suction pipe connected to the nozzle. [ Figure 6 ] Figure 6 This is a perspective view of the end component according to the first embodiment. [ Figure 7 ] Figure 7 This is a perspective view of the end component according to the second embodiment. [ Figure 8 ] Figure 8 This is a perspective view of the end component according to the third embodiment. [ Figure 9 ] Figure 9 This is a perspective view of the end component according to the fourth embodiment. [ Figure 10 ] Figure 10 This is a perspective view of the end component according to the fifth embodiment. Detailed Implementation

[0022] Figure 1 An example of an aircraft turbine engine 1 according to the present invention is shown. For example, turbine engine 1 is a dual-flow turbojet engine. For example, turbine engine 1 can have any other architecture and take the form of a turboprop engine.

[0023] Turbine engine 1 is modular. Turbine engine 1 comprises multiple modules assembled together.

[0024] Turbine engine 1 extends along the longitudinal axis X. Gas flow F flows in turbine engine 1.

[0025] For the purposes of this invention, the terms "upstream" and "downstream" are understood relative to the flow direction of the gas flow F in the turbine engine 1. Figure 1 and Figure 2 In the middle, the gas flow F flows from left to right.

[0026] 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 a gas exhaust nozzle 70 for exhausting the gas from upstream to downstream.

[0027] 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.

[0028] The compressor rotor 3a of the low-pressure compressor 3 is connected to the turbine rotor 7a of the low-pressure turbine 7 via a low-pressure shaft 8. The compressor rotor of the low-pressure compressor and the turbine rotor of the low-pressure turbine form the low-pressure body.

[0029] The compressor rotor 4a of the high-pressure compressor 4 is connected to the turbine rotor 6a of the high-pressure turbine 6 via a high-pressure shaft 9. The compressor rotor of the high-pressure compressor and the turbine rotor of the high-pressure turbine form a high-pressure body.

[0030] 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.

[0031] The gas flow F passes through fan 2 and is split into a main air flow F1 and a secondary air flow F2. The main air flow passes through a main flow path v1, and the secondary air flow passes through a secondary flow path v2 surrounding the main flow path v1. The main air flow F1 passes through low-pressure compressor 3 and high-pressure compressor 4. The compressed main air flow F1 passes through combustion chamber 5, where it mixes with fuel. The combustion gases pass through high-pressure turbine 6 and low-pressure turbine 7. The energy in the gases is converted into mechanical energy by the turbine rotor 7a of low-pressure turbine 7, thereby driving the low-pressure shaft 8 to rotate and thus driving the low-pressure compressor 3 to rotate. The gases are then ejected from nozzle 70.

[0032] The fan 2 includes a disc and blades 2a. The disc can rotate around a longitudinal axis X, and the blades are supported by the disc and are evenly spaced around the longitudinal axis X. Figure 1In the example shown, fan 2 is surrounded by fan housing 2b. Fan 2 is ducted. Fan housing 2b supports nacelle 2c, and together the fan housing and nacelle define fan compartment 2d.

[0033] According to another example not shown, fan 2 is non-ducted.

[0034] The disk of fan 2 is driven to rotate by fan shaft 10. In the described example, therefore, as an option, fan shaft 10 is connected to low-pressure shaft 8 via reducer 11. Reducer 11 is mechanical. For example, the reducer may have rotary or planetary gears.

[0035] The reducer 11 drives the fan shaft 10 at a lower speed than the low-pressure shaft 8. This allows for an increase in the bypass ratio of the turbine engine 1.

[0036] Nozzle 70 defines the downstream portion of the main flow path v1 for the gas flow generated by combustion. The nozzle includes an annular housing 71 centered on the longitudinal axis X. Housing 71 advantageously includes an inner shroud and an outer shroud arranged coaxially around the inner shroud. The inner and outer shrouds are connected by an arm.

[0037] The turbine engine 1 also includes a compressor housing 12, which is axially arranged between the low-pressure compressor 3 and the high-pressure compressor 4. For example, the compressor housing 12 includes an inner shroud and an outer shroud centered on the longitudinal axis X. For example, the inner shroud and the outer shroud are connected by an arm.

[0038] The turbine engine 1 may also include an intake casing 13. The intake casing 13 is axially arranged between the fan 2 and the low-pressure compressor 3. For example, the intake casing 13 includes an inner shroud and an outer shroud centered on the longitudinal axis X. For example, the inner shroud and the outer shroud are connected by an arm.

[0039] 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.

[0040] The turbine engine 1 may also include a flow path compartment v3, which is located between the main flow path v1 and the secondary flow path v2.

[0041] The turbine engine 1 includes at least one bearing 15. In particular, the fan shaft 10 is guided to rotate 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 intake housing 13.

[0042] The low-pressure shaft 8 is guided to rotate by at least one third bearing 15c and a fourth bearing 15d. The third bearing 15c is arranged radially between the intake 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.

[0043] The high-pressure shaft 9 is guided to rotate by the fifth bearing 15e. For example, the fifth bearing 15e is arranged radially between the high-pressure shaft 9 and the turbine housing 14.

[0044] For example, the low-pressure shaft 8 can be guided to rotate downstream by a sixth bearing 15f, which is radially arranged between the downstream end of the low-pressure shaft 8 and the turbine housing 14.

[0045] For example, each bearing includes a rolling bearing. For example, a rolling bearing is at least one row of balls or rollers.

[0046] The bearing 15 and the optional reducer 11 are lubricated to ensure 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 rolling bearings.

[0047] 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, with a first bearing 15a, a second bearing 15b, a third bearing 15c and a reducer 11 arranged in the first upstream chamber, a fourth bearing 15d arranged in the second upstream lubrication chamber, and a fifth bearing 15e and a sixth bearing 15f arranged in the downstream lubrication chamber.

[0048] Depending on the configuration of the turbine engine 1, the number of bearings 15 and lubrication chambers 16 can vary.

[0049] Each lubrication chamber 16 is annular. Each lubrication chamber 16 is defined externally by a fixed wall such as a housing and internally by a movable wall such as a shaft.

[0050] For example, the first upstream lubrication chamber 17 is located in the inner shroud of the intake 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.

[0051] Lubrication chambers 17, 18, and 19 are supplied by at least one lubrication circuit. The lubrication circuit includes an oil outlet and an oil inlet, with the oil outlet leading to lubrication chambers 17, 18, and 19, and the oil inlet connected, for example, to an oil reservoir for supplying lubrication to the lubrication circuit.

[0052] To limit oil leakage outside the lubrication chambers 17, 18, and 19, each lubrication chamber 17, 18, and 19 includes a sealing gasket at its boundary. Each sealing gasket is radially positioned between the fixed wall and the movable wall of the lubrication chamber 17, 18, and 19. Advantageously, the sealing gaskets are dynamic. Dynamic gaskets are defined as components that limit fluid leakage between the fixed wall and the movable wall. Preferably, the first and second sealing gaskets are labyrinth gaskets.

[0053] The turbine engine 1 also includes a fuel supply circuit for supplying fuel to the combustion chamber 5.

[0054] Although lubrication chambers 17, 18, and 19 are sealed, lubricating oil leakage may still occur. Therefore, fuel from combustion chamber 5 must be vented to limit the risk of coking. Fuel or oil leakage also exists in some hydraulic actuators of turbine engine 1.

[0055] In this configuration, the turbine engine 1 also includes at least one first exhaust circuit C1 connected to the combustion chamber 5 and / or the lubrication chambers 17, 18, 19. Therefore, the first exhaust circuit C1 discharges at least one liquid, such as lubricating oil and / or fuel, from the combustion chamber 5 and / or from the lubrication chambers 17, 18, 19. The turbine engine 1 may include a second exhaust circuit (not shown) connected to the combustion chamber 5 and / or the lubrication chambers 17, 18, 19 for discharging at least one liquid, such as lubricating oil and / or fuel.

[0056] refer to Figure 2 To limit the risk of environmental pollution, the turbine engine 1 also includes a manifold 20 connected to the exhaust circuit C1 and the nozzle 70.

[0057] Manifold 20 is configured to collect liquid from discharge loop C1. (Reference) Figure 2 and Figure 3 The manifold 20 includes a containment section 21, at least one first liquid inlet 22, an optional additional liquid inlet 23, and a first liquid outlet 24.

[0058] Advantageously, the enclosure 21 is annular and has a longitudinal axis A.

[0059] In the remainder of the specification, regarding manifold 20, the terms "lower" and "upper" are understood in relation to the gravitational flow of the liquid in manifold 20. Therefore, the term "upper" refers to the element relatively closer to the first inlet 22, and the term "lower" refers to the element relatively farther from the first inlet 22. Figure 2 and Figure 3 In this system, the liquid flows from top to bottom due to gravity.

[0060] In the remainder of the specification, the terms “longitudinal,” “longitudinal,” “radial,” and “radial” are understood relative to the longitudinal axis A of the manifold 20.

[0061] The enclosure 21 has a height h measured along a direction parallel to the flow direction of the liquid in the enclosure 21. In this example, the height h is measured along the longitudinal axis A.

[0062] For example, the enclosure 21 has a circular or polygonal cross-section. Advantageously, the enclosure 21 extends between a first end 25 (also called the upper end) and an opposing second end 26 (also called the lower end).

[0063] The first end 25 and the second end 26 are closed. For example, the first end 25 is closed by a cover or upper wall 25a. The second end 26 is closed by a sealing base 26a.

[0064] Preferably, the enclosure 21 defines an inner cavity 27 for containing liquid. 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 and 23. Figure 3 For example, cavity 27 has a liquid level L equal to a predetermined standard threshold.

[0065] 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, provided on the cover 25a. Therefore, inlets 22 and 23 are opposite to the second end 26 of the enclosure 21. For example, inlets 22 and 23 are annular. Figure 3 For example, inlets 22 and 23 have an axis A1 parallel to the longitudinal axis A of manifold 20. The axis A1 of each inlet 22 and 23 is offset relative to the longitudinal axis A of the manifold.

[0066] The first inlet 22 is connected to the first discharge loop C1, and the additional inlet 23 can be connected to the second discharge loop.

[0067] The first outlet 24 leads to the outside of the enclosure 21. Therefore, the first outlet 24 is configured to discharge liquid to the outside of the enclosure 21. For example, the first outlet 24 is located at the second end 26 and is thus opposite to the first end 25. Therefore, the first outlet 24 is opposite to the inlets 22 and 23.

[0068] according to Figure 3 For example, the first outlet 24 has an axis A2 perpendicular to the longitudinal axis A of the manifold 20.

[0069] Preferably, the manifold 20 further includes an ejector 28 that fluidly connects the inner cavity 27 and the first outlet 24. The ejector 28 is configured to allow the first liquid and / or the second liquid to pass through at a calibrated flow rate. Furthermore, the ejector 28 is configured to discharge the liquid in droplets to facilitate liquid drainage.

[0070] The injector 28 includes a first inlet end 28a for liquid and an opposing second outlet end 28b for liquid. The second end 28b is connected to or forms the first outlet 24.

[0071] Preferably, the injector 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.

[0072] Preferably, the injector 28 is removably connected to the enclosure 21. This allows the injector 28 to be installed and removed for cleaning and limits the risk of clogging. Therefore, maintenance of the injector 28 is facilitated.

[0073] The manifold 20 also includes a ventilation duct 29. The ventilation duct 29 is located within the enclosure 21 of the manifold 20. The ventilation duct 29 includes a ventilation air inlet 30 leading to the outside of the enclosure 21 and a ventilation air outlet 31 connected to the first outlet 24.

[0074] For example, the ventilation air inlet 30 has an axis A4 that is perpendicular to the longitudinal axis A of the manifold 20.

[0075] The ventilation air outlet 31 has an axis A5 that is parallel to the longitudinal axis A of the manifold 20 and perpendicular to the axis A3 of the injector 28.

[0076] Advantageously, the air inlet 30 and the air outlet 31 are located opposite the first end 25 of the manifold 20. Preferably, the air inlet 30 and the air outlet 31 are radially opposite each other.

[0077] According to an embodiment, the ventilation air inlet 30 and the ventilation air outlet 31 are connected by a ventilation duct 32. For example, the ventilation duct 32 has an inverted U-shaped longitudinal cross-section. Therefore, the ventilation duct 32 includes a first section 32a and a second section 32b connected together by an intermediate section 32c. The first section 32a and the second section 32b extend longitudinally within the enclosure 21, while the intermediate section 32c extends laterally within the enclosure 21.

[0078] In some cases, particularly in the event of a rupture in the seals of 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 is greater than the standard flow rate. In this situation, the liquid level in the inner cavity 27 rises, thereby advantageously draining the liquid.

[0079] In this configuration, manifold 20 also includes a liquid discharge line 33. The discharge line 33 is configured to discharge liquid from the cavity 27 to the outside of the enclosure 21 when the liquid level in the enclosure 21 is greater than or equal to a threshold liquid level S1 in the cavity 27. The threshold liquid level S1 is measured based on the height h of the enclosure 21. The threshold liquid level S1 is greater than a predetermined standard liquid level. This predetermined standard liquid level typically corresponds to a standard liquid inlet flow rate entering the manifold 20. This standard liquid level in the cavity 27 can be considered normal because it does not reach the threshold liquid level; that is, the alarm threshold liquid level will characterize an abnormal flow rate.

[0080] The discharge line 33 includes a second liquid inlet 34 located in the inner cavity 27 and a second liquid outlet 35 leading to the outside of the enclosure 21.

[0081] The second inlet 34 has an axis A6 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 threshold liquid level S1. In particular, the second inlet 34 has an inlet orifice located at the same height as the threshold liquid level S1 in the inner cavity 27. Therefore, when the liquid level in the inner cavity reaches the threshold liquid level S1, liquid flows into the second inlet 34 through overflow.

[0082] The second inlet 34 is radially offset relative to the first inlet 22 and the additional inlet 23. This prevents liquid entering the cavity 27 from contaminating the discharge line 33 when the liquid level in the cavity 27 is below the threshold level S1.

[0083] according to Figure 3 In the example, the second outlet 35 and the ventilation air inlet 30 are combined.

[0084] 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. For example, the overflow pipe 36 includes a first axial portion 36a extending longitudinally in the cavity 27 and a second transverse portion 36b extending laterally. 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.

[0085] Such a leak could have harmful consequences for the turbine engine 1. Therefore, it is preferable to be able to detect such a leak. In this case, the manifold 20 preferably also includes a detection and signaling device 40, which is configured to send a signal when the liquid level in the inner cavity 27 has reached a threshold liquid level S1. The detection and signaling device 40 is configured to detect and send a signal when the threshold liquid level S1 in the enclosure 21 is reached.

[0086] Preferably, the detection and signal transmission device 40 for the threshold liquid level S1 is located opposite to the first end 25 of the enclosure 21.

[0087] According to one example, the detection and signal transmission device 40 includes a light indicator that transmits a signal about the threshold liquid level S1 in the form of a first color.

[0088] according to Figure 3 In another example shown, the detection and signal transmission device 40 includes a viewing aperture or window 41 that enables the detection and signal transmission of the presence of liquid in the discharge line 33. For example, the viewing aperture or window 41 is mounted on the enclosure 21. In particular, the viewing aperture or window 41 is mounted facing the discharge line 33, and specifically facing the lower end of the axial portion 36a of the overflow pipe 36.

[0089] Under standard conditions, that is, when the liquid level in the inner cavity 27 is lower than the threshold liquid level S1, the liquid is discharged by discharge according to the Venturi effect principle.

[0090] Therefore, refer to Figure 2 and Figure 4 The turbine engine 1 according to the invention also includes a suction pipe 42, which is connected to the housing 71 of the manifold 20 and the nozzle 70.

[0091] The suction pipe 42 extends between a first end 43 and a second end 44, with the first end leading to the main flow path v1 of the housing 71 and the second end connecting to the manifold 20.

[0092] The suction pipe 42 also includes a suction pipe 45 that connects the first end 43 and the second end.

[0093] The second end 44 is connected to the first outlet 24 of the manifold 20. Specifically, the second end 44 is connected to the end of the first outlet 24 located outside the enclosure 21.

[0094] Advantageously, the first end 43 includes a sleeve 47 that connects the suction line 45 to the housing 71.

[0095] Sleeve 47 has a cylindrical shape and an axis extending radially relative to the longitudinal axis X of turbine engine 1. For example, the outer diameter of sleeve 47 is larger than the outer diameter of suction line 45.

[0096] The suction line 45 may include a tube section with a reduced cross-section located between the first end 43 and the second end 44.

[0097] Preferably, such as Figure 5 As shown in the best example, analogous to the corresponding position of the hands on a clock face, the first end 43 is connected to the housing 71 at a position between 3 o'clock and 9 o'clock.

[0098] Preferably, the first end 43 is bolted to the housing 71. For example, the turbine engine 1 includes an outer flange 48 and an inner flange 49, the outer flange being connected to the first end 43 and the housing 71, and the inner flange being fixed to the inner surface of the housing 71 and connected to the outer flange 48 by bolts 49a. For example, the outer flange 48 is fixed to a sleeve 47. According to the invention, the first end 43 is connected to an opening 50 located in the main flow path v1. Thus, the opening 50 is located in the housing 71 of the nozzle 70. This opening 50 allows the first end 43 of the suction conduit 42 to withstand a pressure higher than that in the manifold 20, to create a vacuum in the suction conduit 42, and to draw liquid from the inner cavity 27 via the first outlet 24 through the Venturi effect.

[0099] Thanks to this invention, the injector and the air discharged from the high-pressure compressor can be eliminated.

[0100] Therefore, the configuration and performance of the turbine engine 1 were significantly improved.

[0101] Preferably, the turbine engine 1 includes an end member 46 located in the main flow path v1 and having at least a partial opening 50.

[0102] Opening 50 can have different configurations, which will now be described.

[0103] according to Figure 6 In the first embodiment shown, the end member 46 includes a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. The cylindrical body 51 extends from the suction line 45, particularly from the sleeve 47, to the free end 52. The free end 52 has an opening 50. The opening 50 is annular and has a circular cross-section.

[0104] according to Figure 7 In the second embodiment shown, the end member 46 includes a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. The cylindrical body 51 extends from the suction line 45, particularly from the sleeve 47, to the free end 52. The free end 52 has an opening 50. The opening has a C-shaped cross-section. The cylindrical body 51 also has a U-shaped notch 51a extending to the opening 50. According to this embodiment, the cylindrical body 51 may have a length L measured along its axis, the length L being greater than or equal to at least three times the diameter of the cylindrical body.

[0105] according to Figure 8In the third embodiment shown, the end member 46 includes a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. The cylindrical body 51 extends from the suction line 45, particularly from the sleeve 47, to the free end 52. The free end 52 has an opening 50. The opening has a C-shaped cross-section. The cylindrical body 51 also has a U-shaped notch 51a extending to the opening 50. According to this embodiment, the cylindrical body 51 may have a length L measured along its axis, the length L being less than or equal to at least three times the diameter of the cylindrical body. According to this embodiment, the notch 51a extends substantially to the sleeve 47.

[0106] according to Figure 9 In the fourth embodiment shown, the end member 46 includes a cylindrical body 51 and a free end 52. The cylindrical body 51 is hollow. The cylindrical body 51 extends from the suction line 45, particularly from the sleeve 47, to the free end 52. According to this embodiment, the free end 52 is closed. An opening 50 is provided on the cylindrical body 51.

[0107] Specifically, the cylindrical body 51 includes a first portion 53 and a second portion 54, the second portion 54 being connected to the first portion 53 and extending to a free end 52. The first portion 53 is connected to the first portion 53, for example, via a shoulder 53a. Therefore, the outer diameter of the first portion 53 is larger than the outer diameter of the second portion 54.

[0108] For example, opening 50 is located on the second part 54. For example, opening 50 has the shape of an elliptical hole.

[0109] according to Figure 10 In the fifth embodiment shown, end member 46 includes a semi-annular body 55. The semi-annular body 55 has an axis, for example, parallel to the longitudinal axis X of the housing 71 of the nozzle 70. The semi-annular body 55 is connected to, for example, an inner flange 49 and advantageously forms an integral part with the inner flange 49. The semi-annular body 55 and the housing 71 of the nozzle 70 define an opening 50.

[0110] According to this embodiment, the end member 46 and the second end 43 are connected to the housing 71 via an outer flange 48 and an inner flange 49.

Claims

1. A turbine engine (1) for an aircraft, the turbine engine (1) having a longitudinal axis (X) and comprising: - Gas discharge nozzle (70), the gas discharge nozzle includes an annular housing (71) centered on the longitudinal axis (X) and defines a gas flow path (v1) for gas flow. - At least one discharge circuit (C1) for discharging at least one liquid. - A manifold (20) for the liquid, the manifold comprising: - Enclosure (21), which defines an inner cavity (27) for containing the liquid. - First liquid inlet (22, 23), the first liquid inlet leads to the inner cavity (27) and is connected to the first discharge circuit (C1). - First liquid outlet (24), the first liquid outlet leads to the outside of the enclosure (21), - Suction pipe (42), the suction pipe being connected to the housing (71) and the manifold (20), the suction pipe (42) comprising: - First opening end (43), the first opening end is connected to the housing (71) and leads to the gas flow path (v1), and - Second end (44), the second end is connected to the first outlet (24). - An opening (50) leading to the gas flow path (v1) and connected to the first end (43) of the suction pipe (42), the opening (50) being configured to create a vacuum in the suction pipe (42).

2. The turbine engine according to the preceding claim, characterized in that, The turbine engine includes an end component (46) located in the flow path (v1) and having at least partially the opening (50).

3. The turbine engine according to the preceding claim, characterized in that, The end component (46) includes a cylindrical body (51) extending from the first end (43) to a free end (52) with the opening (50).

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

5. The turbine engine according to claim 3, characterized in that, The free end (52) has a C-shaped cross section.

6. The turbine engine according to claim 2, characterized in that, The end component (46) includes a cylindrical body (51) with the opening (50) and extends from the first end (43) to a closed free end (52).

7. The turbine engine according to the preceding claim, characterized in that, The cylindrical body (51) includes a first part (53) and a second part (54), the second part being connected to the first part (53) via a shoulder (53a) and extending to the free end (52), and the opening (50) being located on the second part (54).

8. The turbine engine according to claim 2, characterized in that, The end component (46) includes a semi-annular body (55) that defines the opening (50) with the housing (71).

9. The turbine engine according to the preceding claim, characterized in that, The first end (43) and the end component (46) are bolted to the housing (71).

10. The turbine engine according to any one of the preceding claims, characterized in that, The suction pipe (42) is connected to the housing (71) at a position between 3 o'clock and 9 o'clock.

11. The turbine engine according to any one of the preceding claims, characterized in that, The manifold (20) includes a discharge pipe (33) configured to discharge liquid from the cavity (27) to the outside of the enclosure (21) when the liquid level in the cavity (27) is greater than or equal to a threshold liquid level (S1) in the cavity (27), the discharge pipe (33) comprising: - A second liquid inlet (34), the second liquid inlet being located within the inner cavity (27), and - Second liquid outlet (35), the second liquid outlet leads to the outside of the enclosure (21).

12. The turbine engine according to any one of the preceding claims, characterized in that, The manifold (20) includes a ventilation duct (29) with a ventilation air inlet (30) and a ventilation air outlet (31). The ventilation air inlet leads to the outside of the enclosure (21), and the ventilation air outlet is connected to the first outlet (24) to discharge a mixture of air and liquid.

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