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EP-4735745-A1 - LUBRICATION/COOLING SYSTEM FOR AN AIRCRAFT, AND HYDRAULIC ENCLOSURE

EP4735745A1EP 4735745 A1EP4735745 A1EP 4735745A1EP-4735745-A1

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.

Inventors

  • DEBAT, Alexandre Paul Raimond
  • ROBERT, OLIVIER
  • VIVE, Loïs Pierre Denis
  • APOSTIN, Lucie Stéphanie

Assignees

  • Safran Helicopter Engines et aux Energies Alternatives

Dates

Publication Date
20260506
Application Date
20240611

Claims (9)

  1. 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 electric 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 lubricating and/or cooling a power electronics module (12.1) of the electric machine (12); a first pump (50) for circulating the lubricating and/or cooling fluid (13) comprising a first suction port (51) for the lubricating and/or cooling fluid (13) and a first discharge port (52) for the lubricating and/or cooling fluid (13); a second pump (60) for circulating the lubricating and/or cooling fluid (13) comprising a second suction port (61) for the lubricating 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 lubricating and/or cooling fluid (13), a set of tanks comprising a first tank (70), called a hot tank, 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 tank assembly also comprising a second tank (80), called the cold tank, 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 fluidically connected to the first suction port (51) and to the second suction port (61); the fifth outlet (74) is fluidically 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. 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. 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. 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. 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. 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. 7. A lubrication/cooling system (100) according to claim 6, wherein the fluid connection (116) comprises a forcing pump (118).
  8. 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. 9. Turbomachine (1) comprising a lubrication/cooling system (100) according to any one of claims 1 to 8.

Description

DESCRIPTION TITLE OF THE INVENTION Aircraft lubrication/cooling system and hydraulic enclosure TECHNICAL AREA 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. STATE OF THE PRIOR ART Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various restrictions on carbon emissions have been, are being or will be adopted by various states. In particular, an ambitious standard applies both to new types of aircraft as well as those in circulation requiring the implementation of technological solutions in order to make them compliant with current regulations. Civil aviation has been mobilizing for several years now to make a contribution to the fight against climate change. Technological research efforts have already made it possible to significantly improve 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. Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes that minimize emissions. greenhouse gases to the minimum possible to reduce the environmental footprint of its activity. This sustained research and development work covers new generations of aircraft engines, the weight reduction of aircraft, particularly through the materials used and the lighter on-board equipment, the development of the use of electrical technologies to provide propulsion, and, as an essential complement to technological progress, aeronautical biofuels. To this end, the invention is the result of technological research aimed at significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft. In this respect, it should be recalled that conventional propulsion architectures of the turboshaft or turboprop type typically include two mechanical systems, namely 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 of 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. The power reducer operates with a second lubrication/cooling circuit whose oil temperatures are around one hundred and ten to one hundred and twenty degrees centigrade at the inlet and around one hundred and sixty degrees centigrade at the outlet. The oil pumped out of 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 type exchanger, because the oversizing generated remains acceptable. This is typically the case on helicopter turboshaft engines. 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 in order to ensure supercooling of part of the lubrication/cooling circuit of the reducer. 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 of 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. STATEMENT OF THE INVENTION 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 lubrication and/or cooling inlet and outlet of a gas turbine; a second circuit for circulating