Lubrication / cooling system for an aircraft, and hydraulic enclosure

Abstract

Disclosed is a lubrication / cooling system (100) for an aircraft, comprising: a first circuit (20), a second circuit (30), a third circuit (40) for circulating a lubricating and / or cooling fluid (13), a first pump (50) and a second pump (60) for circulating the lubricating and / or cooling fluid (13), a first heat exchanger (90); the first pump (50) is operationally connected to a gas turbine (9) so as to be actuated during all the operating phases of the gas turbine (9); the second pump (60) is operationally connected to a pusher propeller (3) so as to be actuated during all the operating phases of the pusher propeller (3). Also disclosed are a turbine engine and an aircraft comprising such a system.

Description

[0001] DESCRIPTION

[0002] TITLE OF THE INVENTION

[0003] Aircraft lubrication / cooling system and hydraulic enclosure

[0004] TECHNICAL FIELD

[0005] The invention relates to lubrication / cooling devices for aircraft and more particularly to lubrication / cooling systems intended for the lubrication and cooling of turbomachines provided with an electric generator.

[0006] STATE OF THE PRIOR ART

[0007] Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various carbon emission restrictions have been, are being, or will be adopted by various states. In particular, an ambitious standard applies to both new aircraft types and those already in operation, requiring the implementation of technological solutions to ensure their compliance with current regulations. Civil aviation has been mobilizing for several years now to contribute to the fight against climate change.

[0008] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental consequences with the aim of improving the energy efficiency of aircraft.

[0009] Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

[0010] This sustained research and development work focuses on new generations of aircraft engines, the weight reduction of aircraft, particularly through the materials used and lighter on-board equipment, the development of the use of electrical technologies to ensure propulsion, and, as an essential complement to technological progress, aeronautical biofuels.

[0011] To this end, the invention is the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft.

[0012] In this respect, it should be remembered that conventional propulsion architectures of the turboshaft or turboprop type typically comprise two mechanical systems: the gas turbine and the power reducer. These two systems have technically different limitations concerning the operating temperatures of their respective lubrication circuits. The gas turbine alone contains only bearings and a chain of pinions driving the accessories necessary for its operation (typically: oil pump, fuel pump, FADEC alternator, starter generator, centrifugal oil separator): this assembly can operate with a first lubrication / cooling circuit whose oil temperatures are in the order of one hundred and thirty to one hundred and forty degrees centigrade at the inlet and up to one hundred and eighty degrees centigrade at the outlet.

[0013] The power reducer operates with a second lubrication / cooling circuit with oil temperatures of around 110 to 120 degrees centigrade at the inlet and around 160 degrees centigrade at the outlet.

[0014] The oil pumped from the two lubrication / cooling circuits is directed to an oil / air heat exchanger to be cooled before being discharged into a tank where it will be pumped again to supply the lubrication / cooling circuits. Although the two lubrication / cooling circuits have different supply and outlet temperatures, it is generally accepted to have only one oil-air heat exchanger, because the oversizing generated remains acceptable. This is typically the case on helicopter turbine engines.

[0015] For higher power machines and / or with a power reducer offering a higher reduction ratio, as is generally the case on turboprops, a second cooling system of the oil-fuel heat exchanger type can be added to ensure supercooling of part of the reducer lubrication / cooling circuit.

[0016] In the case of a hybrid engine, a third subsystem appears which is an electric machine composed of power electronics and an electric motor / generator. This third system requires a third lubrication / cooling circuit whose oil temperatures are in the order of sixty to ninety degrees centigrade at the inlet and which then requires a dedicated heat exchanger due to the inlet and outlet temperatures being much lower than those of the other two circuits. Such an exchanger represents an additional cost and excess weight which negatively impacts the aircraft's performance in terms of fuel consumption.

[0017] STATEMENT OF THE INVENTION

[0018] For this purpose, a lubrication / cooling system for an aircraft turbomachine is provided, comprising: a first circuit for circulating a lubricating and / or cooling fluid intended to be connected to a first inlet and a first lubrication and / or cooling outlet of a gas turbine; a second circuit for circulating the lubricating and / or cooling fluid intended to be connected to a second inlet and a second lubrication and / or cooling outlet of a mechanical reducer; a third circuit for circulating the lubricating and / or cooling fluid intended to be connected to a third inlet and a third lubrication and / or cooling outlet of an electrical machine;a fourth circulation circuit for the lubricating and / or cooling fluid intended to be connected to a fourth lubrication and / or cooling inlet and a fourth lubrication and / or cooling outlet of a power electronics module of the electric machine; a first circulation pump for the lubricating and / or cooling fluid comprising a first suction port for the lubricating and / or cooling fluid and a first discharge port for the lubricating and / or cooling fluid; a second circulation pump for the lubricating and / or cooling fluid comprising a second suction port for the lubricating and / or cooling fluid and a second discharge port for the lubricating and / or cooling fluid;a set of reservoirs comprising a first reservoir, called a hot reservoir, of lubricating and / or cooling fluid comprising a first deaeration volume supplied by a fifth lubricating and / or cooling fluid inlet and a first supply volume connected to a fifth lubricating and / or cooling fluid outlet; the reservoir assembly also comprising a second reservoir, called a cold reservoir, of lubricating and / or cooling fluid comprising a second deaeration volume supplied by a sixth lubricating and / or cooling fluid inlet and a second supply volume connected to a sixth lubricating and / or cooling fluid outlet;a first heat exchanger comprising a seventh inlet and a seventh outlet for lubricating and / or cooling fluid, wherein: the first circuit connects the first discharge port and the fifth inlet; the second circuit connects the second discharge port and the fifth inlet; the third circuit connects the second discharge port and the fifth inlet; the fourth circuit connects the seventh outlet and the sixth inlet; the sixth outlet is fluidically connected to the first suction port and the second suction port; the fifth outlet is fluidically connected to the seventh inlet; the first pump is operatively connected to the gas turbine so as to be actuated during all phases of operation of the gas turbine, the second pump is operatively connected to the propeller so as to be actuated during all phases of operation of the propeller.;

[0019] According to other particular, non-exclusive and optional embodiments of the invention: the lubrication / cooling system comprises a third pump for circulating the lubrication and / or cooling fluid comprising a third suction port for the lubrication and / or cooling fluid and a third discharge port for the lubrication and / or cooling fluid, the third pump being located in the fourth circuit or between the fifth outlet and the seventh inlet; the first heat exchanger is a fluid / air exchanger whose first cold source is air and the first circuit comprises a second heat exchanger whose second cold source is a fuel circuit of the turbomachine.; the second circuit comprises a third heat exchanger whose third cold source is a fuel circuit of the turbomachine and / or the third circuit comprises a fourth heat exchanger whose fourth cold source is a fuel circuit of the turbomachine; the first circuit and / or the second circuit and / or the third circuit comprises a device for filtering the lubricating and / or cooling fluid; the first pump and / or the second pump and / or the third pump are connected to mechanical power take-offs of the reducer; the first supply volume and the second supply volume are fluidically connected by a fluid connection; the fluid connection comprises a forcing pump; the first reservoir and the second reservoir are combined in the same interior volume of a hydraulic enclosure.

[0020] The invention also relates to a turbomachine comprising a lubrication / cooling system as described above and an aircraft comprising such a turbomachine.

[0021] Other characteristics and advantages of the invention will appear on reading the following description of a particular non-limiting embodiment of the invention.

[0022] BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Reference will be made to the attached figures, including:

[0024] [Fig.l] Figure 1 is a schematic sectional view of a turbomachine;

[0025] [Fig.2] Figure 2 is a schematic view of a lubrication / cooling circuit according to a first embodiment of the invention; [Fig.3] Figure 3 is a schematic view of a lubrication / cooling circuit according to a second embodiment of the invention;

[0026] [Fig.4] Figure 4 is a schematic view of a lubrication / cooling circuit according to a third embodiment of the invention;

[0027] [Fig.5] Figure 5 is a schematic detail view of a fourth embodiment of the invention.

[0028] DETAILED DESCRIPTION OF SPECIFIC EMBODIMENTS

[0029] In a turbomachine, here a turboprop engine marked 1 in Figure 1 and which equips an aircraft not shown, the air is admitted into an inlet sleeve 2 after having passed through a propulsive propeller 3 comprising a series of rotating blades to then be compressed by compressor stages 4 before reaching a combustion chamber 5 into which fuel is injected and then burned. The pressurized gas flow generated in the combustion chamber 5 expands by passing through turbine stages 6, before being evacuated to the exhaust

[0030] The blades of the compressor stages 4 and the turbine stages 6 are rotationally fixed to a shaft 7 mounted to rotate relative to a casing 8 surrounding the compressor stages 4, the combustion chamber 5, the turbine stages 6, the casing 8 defining an exhaust outlet. The inlet sleeve 2, the compressor stages 4, the combustion chamber 5, the turbine stages 6 and the casing 8 define a gas turbine 9.

[0031] The shaft 7 of the gas turbine 9 is connected by a mechanical reducer 10 to a drive shaft 3.1 of the propeller 3. The reducer 10 is also provided with an output shaft 11 connected to an electric machine comprising an electric motor / generator 12 controlled by a power electronics module 12.1. The connection of the motor / generator 12 to the reducer 10 allows the motor / generator 12 to generate electricity during operation of the turboprop 1 in 100% thermal mode, to drive the propeller 3 in 100% electric mode and to assist the turbine 9 in driving the propeller 3 in hybrid mode. In the present text, the terms “upstream” and “downstream” are used in reference to the position or orientation of an element according to the direction of flow of the fluid in the pipes.

[0032] The aircraft is equipped with a lubrication / cooling system 100 comprising a first circuit 20 for circulating a lubricating and / or cooling fluid—here oil 13—, a second circuit 30 for circulating oil 13, a third circuit 40 for circulating oil 13 and a fourth circuit 150 for circulating oil 13.

[0033] The circuit 20 is connected to a first inlet 14 of the turbine 9 by a first supply pipe 21 and to a first outlet 15 of the turbine 9 by a first drainage pipe 22.

[0034] The circuit 30 is connected to a second inlet 16 of the reducer 10 by a second supply pipe 31 and to a second outlet 17 of the reducer 10 by a second drainage pipe 32.

[0035] The circuit 40 is connected to a third input 18 of the motor / generator 12 by a third supply line 41 and to a third output 19 of the motor / generator 12 by a third drainage line 42.

[0036] The circuit 150 is connected to a fourth input 12.2 of the module 12.1 by a fourth supply line 151 and to a fourth output 12.3 of the module 12.1 by a fourth drainage line 152.

[0037] A first pump 50 for circulating the oil 13 comprises a first suction port 51 for oil 13 and a first discharge port 52 for oil 13.

[0038] A second oil 13 circulation pump 60 comprises a second oil 13 suction port 61 and a second oil 13 discharge port 62.

[0039] A third pump 160 for circulating the oil 13 comprises a third suction port 161 for oil 13 and a third discharge port 162 for oil 13.

[0040] The system 100 also comprises a hydraulic enclosure 110 which forms a set of reservoirs comprising a first reservoir 70 and a second reservoir 80 and which are joined together in the same interior volume 111 of the hydraulic enclosure 110. The hydraulic enclosure 110 is defined by a wall 120 and the reservoirs 70 and 80 are separated by a partition 112 extending into the interior volume 111. In order to limit the heat exchanges between the reservoirs 70 and 80, the partition 112 is a double-skin partition comprising a first skin 113 and a second skin 114 separated by a thermal insulator 115.

[0041] The first tank 70, called the hot tank, comprises a first deaeration volume 71 supplied by a fifth inlet 72 of oil 13 as well as a first supply volume 73 connected to a fifth outlet 74 of oil 13. A second tank 80, called the cold tank, comprises a second deaeration volume 81 supplied by a sixth inlet 82 of oil 13 as well as a second supply volume 83 connected to a sixth outlet 84 of oil 13.

[0042] A vent - here a pipe 116 which passes through the partition 112 - extends between the volumes 73 and 83 to ensure the fluid connection. The portions 121 and 122 of the wall 120 which define respectively with the partition 112 the tanks 70 and 80, are separated by thermal bridge breaker devices 117.

[0043] Finally, a first fluid / air heat exchanger 90 comprises a seventh inlet 91 for oil 13 and a seventh outlet 92 for oil 13. The first cold source of the exchanger 90 is air coming from the immediate environment of the aircraft.

[0044] The circuit 20 connects the first discharge port 52 and the fifth inlet 72 via a connection from the upstream end 21.1 of the pipe 21 to the first discharge port 52 and a connection from the downstream end 22.1 of the pipe 22 to the fifth inlet 72.

[0045] The second circuit 30 connects the second discharge port 62 and the fifth inlet 72 via a connection from the upstream end 31.1 of the pipe 31 to the second discharge port 62 and a connection from the downstream end 32.1 of the pipe 32 to the fifth inlet 72.

[0046] The third circuit 40 connects the second discharge port 62 and the fifth inlet 72 via a connection from the upstream end 41.1 of the pipe 41 to the second discharge port 62 and a connection from the downstream end 32.1 of the pipe 42 to the fifth inlet 72.

[0047] The fourth circuit 150 connects the seventh outlet 92 and the sixth inlet 82 via a connection from the upstream end 151.1 of the conduit 151 to the seventh outlet port 92 and a connection from the downstream end 152.1 of the conduit 152 to the sixth inlet 82.

[0048] The fifth outlet 74 is fluidically connected to the third suction port 161 by a fourth suction line 165.

[0049] The sixth outlet 84 is fluidically connected to the first suction port 51 by a fifth suction line 55 and to the second suction port 61 by a sixth suction line 65.

[0050] The seventh inlet 91 is fluidically connected to the third discharge port 162 by a fourth discharge pipe 166.

[0051] The pump 50 is connected to the gas turbine 9 by a first transmission shaft 53 - shown in dotted lines - so as to be actuated during all phases of operation of the gas turbine 9.

[0052] The pump 60 and the pump 160 are respectively connected to the propeller 3 by a second transmission shaft 63 and a third transmission shaft 163 so as to be actuated during all phases of operation of the propeller 3, whether the propeller 3 is driven by the turbine 9, by the motor / generator 12 or by other means such as the circulation of air through the propeller in a wind turbine mode also known as RAT mode for "Ram Air Turbine". The shafts 63 and 163 constitute direct mechanical connections between the propeller and the pump.

[0053] In thermal operating mode, the gas turbine 9 drives the propeller 3 via the reduction gear 10. The pump 160, the actuation of which is linked to a rotation of the propeller 3, transfers the hot and deaerated oil 13 from the supply volume 73 of the hot reservoir 70 to the heat exchanger 90, the oil 13 thus cooled passes through the module 12.1 and is discharged into the deaeration volume 81 of the cold reservoir 80. The pump 50, the actuation of which is linked to the operation of the gas turbine 9, transfers the deaerated oil 13 from the supply volume 83 to the turbine 9. The pump 60, the actuation of which is linked to a rotation of the propeller 3, transfers, for its part, the deaerated oil 13 from the supply volume 83 to the reduction gear 10, the oil 13 is then recovered at the outlet of the turbine 9 and the reducer 10 to be discharged into the deaeration volume 71 of the tank 70.

[0054] Turbine 9 provides all the motive power and motor / generator 12 produces electricity.

[0055] The vent 116 is arranged to maintain identical oil levels in the volumes 83 and 73 according to the principle of "communicating vessels". Thus, during the operating phases of the turbomachine 1 in which the cumulative flow rates of the pumps 50 and 60 are different from the flow rate of the pump 160, the vent 116 makes it possible to compensate for the difference in flow rates.

[0056] The hybrid operating mode (driving the propulsive propeller 3 by both the engine / generator 12 and the gas turbine 9) is similar to the thermal operating mode with regard to the driving of the pumps 50, 60 and 160.

[0057] In electric operating mode, it is the motor / generator 12 which drives the propeller 3 via the reduction gear 10 and the gas turbine 9 is stopped. The pump 160, the actuation of which is linked to a rotation of the propeller 3, transfers the hot oil 13 from the supply volume 73 of the hot tank 70 to the heat exchanger 90, the oil 13 thus cooled passes through the module 12.1 and is discharged into the deaeration volume 81 of the cold tank 80. The pump 50, the actuation of which is linked to the operation of the gas turbine 9, is not operational. The pump 60, the actuation of which is linked to a rotation of the propeller 3, transfers, for its part, the deaerated oil 13 from the supply volume 83 to the reducer 10, the oil 13 is then recovered at the outlet of the reducer 10 to be discharged into the deaeration volume 71 of the reservoir 70.

[0058] Elements identical or similar to those previously described will bear a numerical reference identical to this in the following description of a second, third and fourth embodiment of the invention. As visible in Figure 3, and according to a second embodiment of the invention, the first circuit 20 comprises a second heat exchanger 23 whose second cold source is a fuel circuit 170 of the turbomachine 1. The second circuit 30 comprises a third heat exchanger 33 whose third cold source is a fuel circuit 170 of the turbomachine 1. The third circuit 40 comprises a fourth heat exchanger 43 whose fourth cold source is a fuel circuit 170 of the turbomachine 1.

[0059] As visible in Figure 4, and according to a third embodiment of the invention, the first circuit 20, the second circuit 30 and the third circuit 40 respectively comprise a first oil 13 filtration device 24, a second oil 13 filtration device 34 and a third oil 13 filtration device 44.

[0060] As visible in Figure 5, and according to a fourth embodiment of the invention, the first supply volume 73 and the second supply volume 83 are fluidically connected by a fourth forcing pump 118.

[0061] Of course, the invention is not limited to the embodiments described but encompasses any variant falling within the scope of the invention as defined by the claims. In particular, although here the lubrication / cooling system comprises a third pump which fluidically connects the fifth outlet of the hot reservoir to the seventh inlet of the heat exchanger, the invention also applies to a fluid connection from the fifth outlet to the seventh inlet comprising an arrangement of controlled or uncontrolled valves and bypasses which connect the first and second pumps;

[0062] - although here the third pump is located between the fifth outlet and the seventh inlet, the invention also applies to other locations of the third pump such as for example an location in the fourth circuit;

[0063] - although here the first pump is mechanically connected to the gas turbine, the invention applies to other means of functionally connecting the first pump and the gas turbine so that the first pump is actuated during all phases of operation of the gas turbine, such as for example a connection of the first pump to a mechanical power take-off of the reducer;

[0064] - although here the second and third pumps are mechanically connected to the propulsion propeller, the invention applies to other means of functionally connecting the second and / or the third pump and the propulsion propeller so that the first pump is actuated during all phases of operation of the propulsion propeller, such as for example a connection of the second pump and the third pump to a mechanical power take-off of the reducer;

[0065] - although here the first and second reservoirs are combined within the same enclosure and separated by a partition, the invention also applies to other configurations such as for example a combination of the two reservoirs in the same enclosure without being separated by a partition and in which the fifth inlet and outlet as well as the sixth inlet and outlet are located so as to take the lubricating and / or cooling fluid from the relevant volumes;

[0066] - although here the first and second tanks are combined within the same enclosure and separated by a partition, the invention also applies to two tanks defined by distinct, physically separate envelopes.

[0067] - although here the deaeration volume is not physically separated from the feed volume (the deaeration being carried out by natural settling), the invention also applies to other configurations of the deaeration and feed volumes such as for example a deaeration volume and a feed volume physically separated by a stilling wall or even by a deaerator;

[0068] - although here the exchanger is a fluid / air type exchanger, the invention also applies to other types of heat exchanger such as for example a fluid / fluid exchanger whose cold circuit would be supplied with fuel or coolant such as water;

[0069] - although here the first and second supply volumes are connected by a vent, the invention also applies to other types of fluid connection such as for example a pipe in the case of two separate tanks, a controlled or uncontrolled valve, or a forcing pump; - although here the first heat exchanger is a fluid / air heat exchanger, the invention also applies to other types of first heat exchanger such as for example a fluid / fluid exchanger in which the cooling fluid may be a fuel circuit of the aircraft; - although here the tanks comprise deaeration and supply volumes, this is a purely functional designation and these volumes are not necessarily physically segregated;

[0070] -although here the connections between the pumps and the propeller are direct mechanical connections by transmission shaft, the functional connection between the pumps and the propeller can be made according to other kinematic chains such as for example shafts connected to the reducer or to a power take-off coupled to the output shaft of the electric machine.

Claims

CLAIMS 1. Lubrication / cooling system (100) for an aircraft turbomachine comprising: a first circuit (20) for circulating a lubricating and / or cooling fluid (13) intended to be connected to a first inlet (14) and to a first outlet (15) for lubricating and / or cooling a gas turbine (9); a second circuit (30) for circulating the lubricating and / or cooling fluid (13) intended to be connected to a second inlet (16) and to a second outlet (17) for lubricating and / or cooling a mechanical reducer (10); a third circuit (40) for circulating the lubricating and / or cooling fluid (13) intended to be connected to a third inlet (18) and to a third outlet (19) for lubricating and / or cooling an electrical machine (12); a fourth circuit (150) for circulating the lubricating and / or cooling fluid (13) intended to be connected to a fourth inlet (12.2) and to a fourth outlet (12.3) for lubrication and / or cooling of a power electronics module (12.1) of the electric machine (12); a first pump (50) for circulating the lubrication and / or cooling fluid (13) comprising a first suction port (51) for the lubrication and / or cooling fluid (13) and a first discharge port (52) for the lubrication and / or cooling fluid (13); a second pump (60) for circulating the lubrication and / or cooling fluid (13) comprising a second suction port (61) for the lubrication and / or cooling fluid. (13) and a second discharge port (62) for lubricating and / or cooling fluid (13); a third pump (160) for circulating the lubricating and / or cooling fluid (13) comprising a third suction port (161) for the lubricating and / or cooling fluid (13) and a third discharge port (162) for the lubricating and / or cooling fluid (13), a set of reservoirs comprising a first reservoir (70), called the hot reservoir, for lubricating and / or cooling fluid (13) comprising a first deaeration volume (71) supplied by a fifth inlet (72) for lubricating and / or cooling fluid (13) as well as a first supply volume (73) connected to a fifth outlet (74) for lubricating and / or cooling fluid (13);the set of reservoirs also comprising a second reservoir (80), called cold reservoir, of lubricating and / or cooling fluid (13) comprising a second deaeration volume (81) supplied by a sixth inlet (82) of lubricating and / or cooling fluid (13) as well as a second supply volume (83) connected to a sixth outlet (84) of lubricating and / or cooling fluid (13); a first heat exchanger (90) comprising a seventh inlet (91) and a seventh outlet (92) of lubricating and / or cooling fluid (13), in which: the first circuit (20) connects the first discharge port (52) and the fifth inlet (72); the second circuit (30) connects the second discharge port (62) and the fifth inlet (72); the third circuit (40) connects the second discharge port (62) and the fifth inlet (72); the fourth circuit (150) connects the seventh outlet (92) and the sixth inlet (82); the sixth outlet (84) is fluidly connected to the first suction port (51) and to the second suction port (61); the fifth outlet (74) is fluidly connected to the seventh inlet (91); the third pump (160) being located in the fourth circuit (150) or between the fifth outlet (74) and the seventh inlet (91); the first pump (50) is operatively connected to the gas turbine (9) so as to be actuated during all phases of operation of the gas turbine (9); the second pump (60) is operatively connected to the propeller (3) so as to be actuated during all phases of operation of the propeller (3); the fourth inlet is located downstream of the seventh outlet.

2. Lubrication / cooling system (100) according to claim 1, in which the first heat exchanger (90) is a fluid / air exchanger whose first cold source is air and the first circuit (20) comprises a second heat exchanger (23) whose second cold source is a fuel circuit of the turbomachine (1).

3. Lubrication / cooling system (100) according to any one of the preceding claims, in which the second circuit (30) comprises a third heat exchanger (33) whose third cold source is a fuel circuit of the turbomachine (1) and / or the third circuit (40) comprises a fourth heat exchanger (43) whose fourth cold source is a fuel circuit of the turbomachine (1).

4. Lubrication / cooling system (100) according to any one of the preceding claims, wherein the first circuit (20) and / or the second circuit (30) and / or the third circuit (40) comprises a filtration device (24, 34, 44) for the lubricating and / or cooling fluid (13).

5. Lubrication / cooling system (100) according to any one of the preceding claims, wherein the first pump (50) and / or the second pump (60) and / or the third pump (160) are connected to mechanical power take-offs of the reducer (10).

6. A lubrication / cooling system (100) according to any preceding claim, wherein the first supply volume (73) and the second supply volume (83) are fluidically connected by a fluid connection (116).

7. The lubrication / cooling system (100) of claim 6, wherein the fluid connection (116) comprises a forcing pump (118).

8. Lubrication / cooling system (100) according to any one of the preceding claims, in which the first reservoir (70) and the second reservoir (80) are combined in the same interior volume (111) of a hydraulic enclosure (110).

9. Turbomachine (1) comprising a lubrication / cooling system (100) according to any one of claims 1 to 8.

Images