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EP-4117949-B1 - SPEED REDUCER EQUIPPED WITH AN ELECTRIC MACHINE

EP4117949B1EP 4117949 B1EP4117949 B1EP 4117949B1EP-4117949-B1

Inventors

  • LEVISSE, PAUL GHISLAIN ALBERT
  • BARET, Emmanuel Fabrice Marie
  • BOSCO, FRANCK EMMANUEL
  • BECOULET, JULIEN FABIEN PATRICK
  • BRAULT, MICHEL GILBERT ROLAND

Dates

Publication Date
20260513
Application Date
20210303

Claims (10)

  1. A reducer (21) with epicyclic gear train for an aircraft turbomachine (1), the reducer (21) comprising a sun gear (30) and a ring gear (33) which are centred on a longitudinal axis X and a planet carrier (32) which carries at least one planet gear (31) mounted so as to be able to rotate about a planet gear axis A parallel to the longitudinal axis X, the sun gear (30) being able to rotate about the longitudinal axis, the planet gear (31) meshing with both the sun gear (30) and the ring gear (33), the reducer (21) comprises an electric machine (50) integrated therewith, the reducer being characterised in that the planet carrier (32) is movable about the longitudinal axis and the ring gear (33) is stationary in rotation the reducer, and in that the electric machine comprises a rotor (51) mounted on the planet carrier (32) so as to be driven in rotation about the longitudinal axis X and a stator (52) mounted on the ring gear (33), an in that an electric harness (70) extends outside the ring gear (33) and at least one electric cable (71) connected to the stator (52) of the electric machine (50) circulates inside the electric harness (70).
  2. The reducer (21) according to the preceding claim, characterised in that the stator (52) of the electric machine (50) extends around the rotor (51) of the electric machine.
  3. The reducer (21) according to any of the preceding claims, characterised in that the stator (52) comprises a first annular part (53) centred on the longitudinal axis and extending the ring gear (33) downstream along the longitudinal axis.
  4. The reducer (21) according to the preceding claim, characterised in that the first annular part (53) is fitted on the ring gear (33) or formed as an integral part of the ring gear (33).
  5. The reducer (21) according to the preceding claim, characterised in that the rotor comprises a second annular part (55) mounted on a cage (58) of the planet carrier (32).
  6. The reducer (21) according to any of the preceding claims, characterised in that the planet carrier (32) comprises an annular cage (58) carrying a plain bearing (62) on which the planet gear is mounted.
  7. An aircraft turbomachine (1) comprising a drive shaft (14) of longitudinal axis X and a fan (2) having a fan shaft (6) driven in rotation by the drive shaft via a reducer (21) according to any of the preceding claims, the ring gear (33) being attached to a stator casing of the turbomachine and the planet carrier (32) being coupled to the fan shaft (6) in order to drive it in rotation about the longitudinal axis.
  8. The turbomachine according to the preceding claim, characterised in that the reducer (21) and the electric machine (50) are arranged in a lubrication enclosure (22) arranged upstream of an internal casing.
  9. The turbomachine according to any one of claims 7 and 8, characterised in that the sun gear is coupled to the drive shaft (14) for driving it in rotation about the longitudinal axis.
  10. A method of modular assembly for a turbomachine (10) according to the preceding claim, characterised in that it comprises the following steps: - assembling the speed reducer (21) according to any of claims 1 to 6, - integrating the electric machine (50) with the speed reducer (50) by mounting the rotor (51) on the planet carrier and the stator (52) on the ring gear (33), and - mounting the speed reducer and integrated electric machine (50) assembly in the lubrication enclosure (22) of the turbomachine.

Description

Scope of the invention The present invention relates to the field of speed reducers, particularly for aircraft turbomachinery. It specifically concerns a speed reducer equipped with an electric machine and a turbomachine comprising such a speed reducer. Technical background Prior art includes documents US-A1-2019/085714 , which forms the basis of the two-part form, WO-A1-2019/243558 And US-A-4291233 . An aircraft turbomachine, such as a turbofan, generally comprises a shrouded fan located at the turbomachine's inlet, driven by a low-pressure shaft. A reduction gear may be interposed between the fan and the low-pressure shaft to reduce the fan's rotational speed. This speed reduction also allows for an increase in fan size, enabling very high bypass ratios. In addition to aircraft propulsion, the turbomachine generates electrical current, typically using a permanent magnet alternator (PMA) and an accessory gearbox (AGB) to power various systems, such as cabin lighting and the cabin air conditioning and pressurization system. It is known to equip the turbomachine, and in particular the accessory gearbox, of an electric machine. An electric machine is an electromechanical device based on electromagnetism that converts electrical energy, for example, into mechanical energy (generator mode) or, reversibly, produces electricity from mechanical energy (motor mode). The electric machine can also operate in generator mode as well as in motor mode. Faced with the environmental challenge in the aeronautical field and the growing need for electrical power in conjunction with the increasing number of aircraft components and new functions, the question of turbomachine hybridization arises. The machine The electrical system as described above does not provide a significant gain in electrical power for all aircraft functions, and the efficiency of converting mechanical power to electrical power is not optimal. Furthermore, integrating the electric machine into various areas of the turbomachine is complex and constrained by size, the temperature resistance of certain electric machine components, accessibility, the performance of the turbomachine itself, and other factors. Summary of the invention The objective of the present invention is to provide an ease of integration of an electrical machine intended to provide additional electrical power in a turbomachine without significantly modifying the components of the turbomachine. We achieve this objective in accordance with the invention by means of an epicyclic gear reducer for an aircraft turbomachine, the reducer is defined by claim 1. Thus, this solution achieves the aforementioned objective. In particular, this configuration avoids cluttering the turbomachine since the electric machine is integrated into the gearbox, and it also allows the gearbox's design (fixed ring gear and movable planet carrier) to control the position of the rotor and stator to achieve an acceptable air gap. Furthermore, integrating the electric machine into the gearbox provides a modular approach, as the gearbox and electric machine components can be assembled independently of each other and also independently of other turbomachine components. Assembly and disassembly are also simplified because the electric machine and gearbox are located in the same place. The reducer also includes one or more of the following features, as defined by the claims: The stator of the electric machine extends around the rotor of the electric machine. the stator comprises a first annular piece centered on the longitudinal axis and extending the ring downstream along the longitudinal axis. In particular, the rotor and stator downstream of the speed reducer are more accessible, unlike those of the prior art which are located at the heart of the speed reducer, implying that the electrical machine must be mounted at the same time as each component of the speed reducer. the first annular piece is attached to the crown or came from the same material as the crown. the rotor includes a second annular piece mounted on a cage of the satellite carrier. The satellite carrier includes an annular cage carrying a plain bearing on which the satellite is mounted. The invention also relates to an aircraft turbomachine comprising a drive shaft with longitudinal axis X and a fan having a fan shaft driven in rotation by the drive shaft via a reduction gear having any of the above characteristics, the ring being fixed to a stator housing of the turbomachine and the planet carrier being coupled to the fan shaft to drive it in rotation around the longitudinal axis. The turbomachine also includes one or more of the following features, as defined by the claims: The solar panel is coupled with the drive shaft designed to rotate it around the longitudinal axis. the lubrication enclosure is delimited at least in part by a ferrule forming at least in part a radially internal wall of the primary vein and the blower shaft. The reducer and the electr