Turbomachine module equipped with an electric machine and turbomachine equipped with such a module

Abstract

The invention relates to an aircraft turbomachine module comprising an accessory gearbox (30) and a transmission shaft (34) and a drive shaft (25) which are rotationally connected to each other by a power transmission device (37) housed in a gearbox (50), the module also comprising an electric machine (54) which is rotationally connected to the transmission shaft (34). According to the invention, the electric machine (54) is interposed between the transmission housing (50) and at least one portion (64a) of the transmission shaft (34).

Description

Technical Field

[0001] This invention relates to the field of turbines for aircraft, and more particularly to turbine modules equipped with electric motors. The invention is especially directed to turbines equipped with such modules and an accessory gearbox connected to the electric motor. Background Technology

[0002] Aircraft turbines (such as dual-flow turbines) typically include a ducted fan located at the turbine inlet, which is driven by a low-pressure shaft. In some configurations of turbines with ultra-high bypass ratios (known as UHBRs), a reduction gear can be inserted between the fan and the low-pressure shaft, causing the fan to rotate at a speed lower than that of the low-pressure shaft. This speed reduction also allows for an increase in fan size, enabling the achievement of very high bypass ratios.

[0003] Turbines include an accessory gearbox (AGB) to supply the various equipment or accessories required to operate the turbine or aircraft. One example of an accessory is a permanent magnet alternator (PMA), which typically uses an accessory gearbox to ensure the generation of current. Specifically, the alternator is designed to supply power from idle speed to the turbine computer, such as FADEC (Full Authority Digital Engine Control). Examples of turbines equipped with accessory gearboxes are described in patent documents US-A1-2013 / 098179, US-A1-2018 / 283281, and US-A1-2019 / 146526.

[0004] The accessory gearbox consists of a series of shafts (gear trains) that drive the equipment at different speed ratios. It is typically driven by a radial shaft on the rotor of the high-pressure compressor. The high-pressure compressor is connected to the transmission shaft in the accessory gearbox via a transfer gear box (TGB).

[0005] A motor is known to be equipped in an accessory gearbox. This motor is an electromechanical device based on electromagnetism, enabling the conversion of electrical energy into mechanical energy (generator mode) or, reversibly, the generation of electricity from mechanical energy (motor mode). The motor can operate in either generator mode or motor mode.

[0006] This motor can be used to drive the high-pressure shaft for a limited time, ideally at a very low speed when the turbine is stopped and the aircraft is on the ground. Rotation of the high-pressure shaft can be achieved using a magnet alternator as described in patent application FR2950658. When the turbine is stationary, rotation of the high-pressure shaft prevents the high-pressure body from being supported due to the thermal gradient between the top and bottom of the high-pressure rotor. This thermal gradient is caused by the convection of air flowing through the turbine. Restarting the engine with this thermal gradient on the rotor can lead to increased vibration, thus posing a risk of friction between the rotor blades of the turbine or low-pressure compressor and their respective housings. This phenomenon leads to performance degradation and potentially turbine deterioration. Furthermore, peak rotor deflection can be reached within two hours after the turbine has stopped. Support of the high-pressure body is crucial for all aircraft that perform multiple flights a day. Summary of the Invention

[0007] In particular, the object of the present invention is to provide a solution that enables one or more devices to be integrated into the constrained environment of a turbine to easily drive one of the motor shafts of the turbine's motor shafts, while avoiding disadvantages to turbine quality and manufacturing costs.

[0008] According to the invention, this objective is achieved by a turbine module for an aircraft, the turbine module comprising an accessory gearbox, a drive shaft and a drive shaft, the drive shaft and the drive shaft being rotatably connected to each other by a power transmission device housed in a transmission receiving portion, the module further comprising a motor rotatably connected to the drive shaft, the motor being inserted between at least one portion of the transmission receiving portion and the drive shaft.

[0009] Therefore, this solution enables the achievement of the aforementioned objectives. In particular, this configuration allows for the avoidance of excessive size and utilizes the available space between the primary power transmission device and the accessory gearbox (typically including gears). The electric motor enables the collection of mechanical power from the motor shaft or the injection of mechanical power into the motor shaft, especially when the aircraft is on the ground, without significantly altering the architecture.

[0010] The turbine module also includes one or more of the following features, individually or in combination:

[0011] - The motor includes a rotor and a stator, the rotor being rotatably fixed to a drive shaft, the stator surrounding the rotor and being fixedly mounted relative to a transmission housing.

[0012] - The stator is supported by the radial inner surface of the cylindrical wall attached to the transmission housing.

[0013] - The drive shaft is enclosed by a first housing, and the motor is housed in a second housing, which is installed between the transmission housing and the first housing, with the cylindrical wall forming the wall of the second housing.

[0014] - The power transmission device includes an output shaft that is coupled to a drive shaft, and a rotor that is mounted radially around the output shaft.

[0015] - The output shaft includes a first section and a second section. The first section is arranged in the annular wall of the transmission receiving portion, and the second section extends outside the annular wall. The diameter of the second section is smaller than that of the first section, so as to form a shoulder at the junction of the first section and the second section.

[0016] - The module includes a bushing that is mounted on the second section of the output shaft and positioned to abut against the shoulder, and the rotor is mounted on the bushing.

[0017] - The module includes at least one fastening device for fastening the bushing against the shoulder of the output shaft.

[0018] - The second section of the output shaft includes a hollow portion that extends axially over all or part of the second section and receives the end of the drive shaft. A coupling device is disposed between the end and the hollow portion, such that the output shaft and the drive shaft are rotatably fixed.

[0019] - The output shaft is rotatably guided in the annular wall by at least one rotary guide bearing, and a sealing element is arranged at an opening in the annular wall and around the first section of the output shaft.

[0020] - An electric motor is of the type of motor and / or generator.

[0021] - The output shaft includes a first spline designed to mate with a second spline on the drive shaft.

[0022] - The first spline is arranged on the radial inner surface at the first end.

[0023] - The second housing is attached to the transfer receiving portion and the first housing, which are fixed.

[0024] - The motor is a permanent magnet AC generator.

[0025] -The toothed gears and wheels are conical.

[0026] - The motor is particularly axially positioned between the first power transmission device and the accessory gearbox.

[0027] - The drive shaft extends to the outside of the accessory gearbox.

[0028] The present invention also relates to an aircraft turbine comprising a high-voltage motor shaft and a turbine module having any of the above features, wherein the power transmission device is a first power transmission device, and the drive shaft is connected to the high-voltage motor shaft via a second power transmission device, such that the drive shaft and the high-voltage motor shaft are rotatably connected.

[0029] The turbine also includes one or more of the following features, individually or in combination:

[0030] - The second power transmission device includes an input wheel mounted on the high-voltage motor shaft, and the input wheel meshes with a second toothed pinion mounted at the second end of the drive shaft.

[0031] - The drive shaft extends inside the housing arm. Attached Figure Description

[0032] The invention will be better understood, and other objects, details, features, and advantages of the invention will become clearer, after reading the following detailed explanatory description of embodiments of the invention given as purely illustrative and non-limiting examples, with reference to the accompanying drawings:

[0033] [ Figure 1 ] Figure 1 This is a schematic axial cross-sectional view of a dual-flow turbine according to the present invention;

[0034] [ Figure 2 ] Figure 2 A schematic diagram of a turbine module according to the present invention having an electric motor installed between a first mechanical transmission device and an accessory gearbox; and

[0035] [ Figure 3 ] Figure 3 This is a detailed view of the rotor of an electric motor according to the invention, which is rotatably connected to the drive shaft of an accessory gearbox. Detailed Implementation

[0036] Figure 1 An axial cross-sectional view along the longitudinal axis X is shown for the turbine 1 to which this invention is applied. The turbine shown is a two-flow, two-shaft turbine, intended for installation on an aircraft. Of course, the invention is not limited to this type of turbine.

[0037] In this application, the terms "upstream," "downstream," "axial," and "axially" refer to the orientation of the flow of gas within the turbine and along the longitudinal axis (even in...). Figure 1 The terms “radial,” “radially,” “internal,” and “external” are defined relative to the radial axis Z, which is perpendicular to the turbine’s axis X.

[0038] The dual-flow, dual-shaft turbine 1 includes a fan 2 mounted upstream of a gas generator or gas turbine engine 3. The fan 2 includes multiple fan blades 4 extending radially from the periphery of a disk 5, through which a fan shaft 6 passes. The fan 2 is surrounded by a fan housing 7 centered on a longitudinal axis X. The fan housing 7 is supported by a nacelle 8 that surrounds the gas generator 3 and extends along the longitudinal axis X.

[0039] Gas generator 3 comprises, from upstream to downstream, a low-pressure (BP) compressor 9, a high-pressure (HP) compressor 10, a combustion chamber 11, a high-pressure turbine 12, and a low-pressure turbine 13. The rotor of HP compressor 10 is connected to the rotor of HP turbine via an HP shaft 14 centered on the longitudinal axis, forming a first shaft known as the high-pressure body. The rotor of BP compressor 10 is connected to the rotor of BP turbine via a BP shaft 15 centered on the longitudinal axis, forming a second shaft known as the low-pressure body. BP shaft 15 extends inside HP shaft 14. HP shaft 14 is an electric motor shaft that is rotatably driven along the longitudinal axis X within an inner housing 16 centered on the longitudinal axis.

[0040] The airflow F entering the turbine via fan 2 is split into a primary airflow F1 and a secondary airflow F2 by the turbine's splitter nose 17. The primary airflow passes through the gas generator 3, and particularly through the main bypass 18, while the secondary airflow flows around the gas generator 3 in the secondary bypass 19. The main bypass 18 and the secondary bypass 19 are coaxial. The secondary airflow F2 is ejected by the secondary nozzle 20 of the terminal nacelle 8, while the primary airflow F1 is ejected to the outside of the turbine via the injection nozzle 21 located downstream of the gas generator. The main bypass 18 is at least partially radially defined by the inner casing 16 and the inlet casing 22. The secondary bypass 19 is at least partially radially defined by the inlet casing 22 and the fan casing. The inlet casing 22 carries the upstream splitter nose 17 and extends downstream through the inter-duct casing 23 carrying the injection nozzle 21.

[0041] In an optional configuration, reducer 24 can connect BP shaft 15 to fan shaft 6, allowing the speed of fan 2 to be reduced below the speed of BP shaft 15. Reducer 24 also allows for the arrangement of fans with large diameters to increase the bypass ratio. The fan bypass ratio is advantageously higher than 10. Preferably, the bypass ratio is between 15 and 20. The reducer can be a planetary reducer or a cruise reducer.

[0042] The turbine includes a drive shaft 25, which is connected on one side to the high-pressure shaft 14 and on the other side to the turbine's accessory gearbox 30. The drive shaft extends more or less radially relative to the radial axis Z at an angle between 0° and 30° (i.e., an angle between 60° and 90° relative to the longitudinal axis X). This drive shaft allows the motor shaft (in this case, the HP shaft 14) to be rotatably driven, enabling the turbine to be started via a device or accessory that engages with the accessory gearbox described below.

[0043] In this example, drive shaft 25 is referred to as a radial shaft because it is housed within a structural element of the turbine and extends generally radially. This structural element extends generally radially between the inner housing 16 and the fan housing and / or nacelle 8. The structural element is a housing arm 26 that structurally connects the inner housing 16 to the fan housing.

[0044] Reference Figure 2 The accessory gearbox 30 is located in a compartment of the engine room 8 and houses various equipment or accessories for the turbine. These devices mounted on the gearbox 30 may include fuel pumps, generators, lubrication units, starter motors, etc. Typically, the gearbox 30 includes a gear train 31 comprising multiple meshing gears 32, some of which are coupled to rotating parts of the equipment to rotatably drive it. The gear train 31 is housed within a rigid enclosure 33 designed to protect the gears 32.

[0045] Gearbox 30 includes a gear among a plurality of gears 32 that forms the input gear of gear train 31 and is coupled to a first end 35 of drive shaft 34. The drive shaft typically extends out of gearbox 30 along an axis A angled to the axis of drive shaft 25. It should be understood that drive shaft 34 is coupled to accessory gearbox 30. Drive shaft 34 may, for example, be arranged such that its axis of rotation A is substantially parallel to the longitudinal axis X. Drive shaft 34 includes a second end 45 connected to radial shaft 25 via a first power transmission device 37 (also referred to as a bevel gear or drive gearbox).

[0046] like Figure 2 As shown, the drive shaft 34 is housed within a first annular housing 38 centered on axis A. The housing 38 may include a sheath that serves only a protective function and does not structurally support the drive shaft 34. The first housing 38 includes a first end 39, which is attached to a side wall 40 of the accessory gearbox 30 using an attachment device. The attachment device may be a bolt and / or screw. The drive shaft 34 is hollow and extends along axis A from the side wall 40 of the accessory gearbox 30.

[0047] The first power transmission device 37 includes an output shaft 41 connected to a drive shaft 34. The output shaft 41 is coaxial with the drive shaft 34. The output shaft 41 is also hollow for at least a portion of its axial length. A coupling device is arranged between the output shaft 41 and the drive shaft 34, such that the output shaft and the drive shaft are rotatably fixed. The output shaft includes a first section 51 and a second section 64. The second section 64 of the output shaft includes a hollow portion 64a that extends axially from the first end 42 of the output shaft 41 over all or part of the second section 64. The hollow portion 64a receives the second end 45 of the drive shaft 34, and the coupling device is disposed between the second end 45 and the hollow portion. In particular, the output shaft 41 includes a first spline 43 (shown in dashed lines) toward the first end 42, which is formed on the radially inner surface of the output shaft 41. These first splines 43 engage with corresponding second splines 44 on the drive shaft 34. These second splines 44 are formed on the radially outer surface of the drive shaft 34 and are located at the second end 45 of the drive shaft. In other words, the second end 45 of the drive shaft 34 is mounted inside the output shaft 41. In this way, the output shaft 41 and the drive shaft 34 are rotatably fixed. The direct connection between the output shaft 41 and the drive shaft 34 enables a reduction in the number of parts and weight, simplifies installation, and reduces the overall size. Manufacturing and installation costs are also reduced.

[0048] The output shaft 41 also includes a second end 46 that carries a gear 47 with beveled teeth. The gear with beveled teeth meshes with a first pinion 48 with beveled teeth to form a transmission gearbox, which is carried by the radially outer end 49 of the radial shaft 25. The transmission gearbox enables the transmission of rotational motion between two non-parallel shafts.

[0049] The first power transmission device 37 is housed in a transmission receiving portion 50, which encloses and protects the gear (formed from a pinion and / or wheel).

[0050] The first segment 51 of the output shaft 41 rotates within the transmission housing 50. To achieve this, a rotary guide bearing 52 is arranged around the first segment 51. Advantageously, the guide bearing is a rolling bearing. Each of these guide bearings includes an inner ring and an outer ring, the inner ring being mounted on the first segment of the output shaft 41 and the outer ring being fixed to the annular wall 53 of the transmission housing 50. A rolling member is arranged between the inner and outer rings. The rolling member can be a ball or a roller. The annular wall 53 is centered on axis A. The first segment 51 of the output shaft is arranged within the annular wall of the transmission housing 50, while the second segment 64 extends outside the annular wall 53. The diameter of the second segment 64 of the output shaft 41 is smaller than the diameter of the first segment 51. This diameter difference is marked by a shoulder 65, which defines the junction of the first segment 51 and the second segment 64 of the output shaft 41.

[0051] Figure 2 A motor 54 is also shown, which is designed to collect power (mechanical or electrical) from or inject power into a motor shaft. The motor shaft may be the low-pressure or high-pressure shaft of a dual-shaft turbine. In this example, the motor 54 is arranged between the first power transmission device 37 and the accessory gearbox 30. More precisely, the motor 54 is inserted between the transmission receiving portion 50 and at least one portion 34a of the drive shaft 34.

[0052] Specifically, motor 54 includes a rotor 54a and a stator 54b. Advantageously, but not limited to, motor 54 operates in generator mode to convert mechanical energy into electrical energy. In this example, motor 30 is reversible, meaning it can alternate between generator mode and motor mode. In motor mode, the motor converts electrical energy into mechanical energy to drive the HP shaft or at least assist in rotating the high-voltage shaft.

[0053] The motor 54 is housed in a second annular housing 55. This second housing 55 is mounted between the transmission receiving portion 50 of the first power transmission device and the first housing 38 of the drive shaft 34. For this purpose, the second housing 55 includes a cylindrical wall 56 having an axis A. At a first end, the cylindrical wall 56 includes a collar 57 that extends at least partially radially outward relative to axis A. At a second end, the cylindrical wall 56 includes an annular base 58 centered on axis A. The annular base 58 is defined in a plane perpendicular to axis A. The collar 57 is attached to an annular flange 59 of the transmission receiving portion 50. The annular flange 59 is centered on axis A and extends radially outward from the distal end of the annular wall 53 of the transmission receiving portion. Attachment devices (such as screws or bolts) enable the second housing to be attached to the transmission receiving portion. The annular wall 53 includes an opening through which the output shaft 41 extends to the outside of the transmission receiving portion 50. The opening is defined by the annular flange 59. Specifically, the second section 64 of the output shaft 41 extends inside the cylindrical wall 59.

[0054] A cylindrical skirt 60 extends generally along axis A from the outer surface 61 of the annular base 58. The cylindrical skirt 60 extends particularly inside the first housing 38. A sealing device (e.g., in the form of an O-ring) can be disposed radially in the space between the cylindrical skirt 60 and the second end 62 of the first housing 38 (axially opposite to the first end 39). In this way, and during operation, ambient air will not enter the first housing 38 and then the second housing 55 via through-holes in the annular base 58. The second end 62 of the first housing 38 can also be fitted around the cylindrical skirt 60, or even attached to the cylindrical skirt 60 by an attachment device.

[0055] Alternatively, not shown, the first housing 38 and the second housing 55 can be combined to form a single housing. To achieve this, a cylindrical skirt 60 can be extended to a fixing device for attaching the skirt to the side wall 40 of the accessory gearbox 30, such that the skirt 60 forms a protective housing for the drive shaft 34. The single housing thus formed between the transmission housing 50 and the accessory gearbox 30 can optionally be provided with sufficient reinforcement (e.g., by increasing wall thickness and / or reinforcing ribs in the longitudinal direction) to provide a structural housing that participates in suspending the accessory gearbox 30 in the turbine. The transmission housing 50 is attached, for example, to the downstream narrow neck of the intermediate housing of the turbine. The accessory gearbox 30 is then cantilevered relative to the narrow neck of the intermediate housing by the structural housing surrounding the drive shaft 34.

[0056] More in detail, Figure 3 In the annular base 58, a through hole 63 is provided, which passes through the annular base on both sides along axis A. The through hole 63 is radially arranged inside the cylindrical skirt 60. The output shaft 41 (particularly the second section 64 of the output shaft) passes through the through hole.

[0057] The rigid enclosure 33 of the first housing 38, the second housing 55, the transmission housing 50, and the accessory gearbox 30 is fixed.

[0058] Reference Figure 2 and Figure 3 A tubular bushing 66 is mounted around the output shaft 41 with axis A as its center. For example, a rotor 54a of a motor 54 including a permanent magnet is mounted on the bushing 66 in close contact with the rotor, allowing the rotor to rotate fixedly with the bushing. In other words, the rotor 54a is mounted radially around the output shaft 41. Similarly, the rotor surrounds at least a portion of the second end 45 of the drive shaft, which is received within the hollow portion 64a of the output shaft 41. The bushing 66 includes a tubular body 66a having a first base plate 67 at a first end and a second base plate 68 at a second end. The first base plate 67 and the second base plate 68 extend radially outward relative to the tubular body. The bushing 66 is mounted on the output shaft 41, particularly on the second section 64 of the output shaft 41.

[0059] Once the bushing 66 has been secured by the fastening device 70 described below, it is held abutting the shoulder 65. An axial gap e is provided between the bushing 66 and the transmission receiving portion 50 to prevent any contact between the bushing and the receiving portion, thereby avoiding any friction. The bushing rotates together with the output shaft 41, while the transmission receiving portion is fixed. More specifically, an axial gap e is provided between the first base plate 67 of the bushing 66 and the annular flange 59 of the receiving portion.

[0060] A sealing element 69 (such as a seal, particularly a rotary seal) is installed in an opening in the annular wall 53 of the transmission housing through which the output shaft 41 extends. This seal 69 prevents lubricant from leaking from the guide bearing to the outside of the transmission housing. Once the bushing 66 abuts against the shoulder 65, a gap is maintained between the first base plate 67 and the seal 69, thereby preventing the base plate 67 from axially compressing the seal and affecting its operation. This gap may differ from the gap e, and is particularly smaller than the gap e. Alternatively, as... Figure 2 As shown, the first base plate 67 can be configured to contact the seal 69 to axially retain the seal without compressing the seal and / or affecting its operation.

[0061] The fastening device 70 allows the bushing 66 to be fastened against the shoulder 65, thereby axially holding the bushing onto the output shaft 41. Specifically, the fastening device 70 includes a nut 71 centered on axis A, which is mounted downstream of the second base plate 68 (relative to axis A). Therefore, the radially outer surface of the second segment 64 of the output shaft 41 includes external threads designed to mate with the internal threads of the nut 71. The outer diameter of the nut is smaller than the diameter of the through-hole.

[0062] The stator 54b of the motor 54 is mounted on the radially inner surface of the cylindrical wall 56 of the second housing, which is fixed. The stator 54b is fixedly mounted relative to the transmission receiving portion 50. Therefore, the rotor 54a rotates inside the fixed stator 54b. The rotor 54a is rotatably fixed to the drive shaft 34.

[0063] like Figure 1 As shown, the input wheel 72 is supported by the high-pressure shaft 14. The input wheel 72 is centered on the longitudinal axis X and has a series of teeth on its radially outer surface. Advantageously, the input wheel 72 is tapered. If a speed reducer 24 is provided, it is positioned upstream of the input wheel 72.

[0064] The radial shaft 25 includes a radially inner end that is rotatably connected to the high-pressure shaft 14. The radially inner end carries a toothed second pinion 73, which meshes with an input gear to form a transmission gearbox. These toothed pinions are conical. Specifically, the input gear 72 and the toothed second pinion 73 form a second power transmission device 74, which is arranged between the high-pressure shaft and the radial shaft. When the high-pressure shaft 14 rotates along its longitudinal axis, the engagement between the input gear 72 and the second pinion 73 ensures that the radial shaft 25 also rotates along a generally radial axis of the high-pressure shaft. In this way, the rotation of the radial shaft 25 causes the transmission shaft 34 to rotate along its axis of rotation A.

[0065] In another embodiment of the invention (not shown), the accessory gearbox 30, the first power transmission device 37, and the motor 54 are installed in the "core" region of the turbine, that is, in the duct compartment located between the main duct and the secondary duct of the twin-flow turbine.

Claims

1. A turbine module for an aircraft, the turbine module comprising an accessory gearbox (30), a drive shaft (34), and a drive shaft (25), the drive shaft and the drive shaft being rotatably connected to each other via a power transmission device (37), the drive shaft (34) being coupled to the accessory gearbox (30), the power transmission device (37) being housed in a transmission receiving portion (50), the turbine module further comprising a motor (54) rotatably connected to the drive shaft (34), and the motor being arranged in... Between the power transmission device (37) and the accessory gearbox (30), the motor (54) includes a rotor (54a) and a stator (54b), the module is characterized in that the motor (54) is inserted between the transmission receiving portion (50) and at least one portion (34a) of the drive shaft (34), the power transmission device (37) includes an output shaft (41) connected to the drive shaft (34), and the rotor (54a) is radially mounted around the output shaft, characterized in that, The output shaft (41) includes a first section (51) and a second section (64), the first section being disposed in the annular wall (53) of the transmission receiving portion (50), the second section extending outside the annular wall (53), and the diameter of the second section (64) being smaller than the diameter of the first section, so as to form a shoulder (65) at the junction of the first section and the second section (51, 64).

2. The turbine module according to claim 1, characterized in that, The rotor (54a) is rotatably fixed to the drive shaft (34), and the stator (54b) surrounds the rotor (54a) and is fixedly mounted relative to the transmission receiving portion (50).

3. The turbine module according to claim 2, characterized in that, The stator (54b) is supported by the radial inner surface of the cylindrical wall (56) attached to the transmission receiving portion (50).

4. The turbine module according to claim 3, characterized in that, The drive shaft (34) is enclosed by a first housing (38), the motor (54) is housed in a second housing (55), the second housing is installed between the transmission accommodating part (50) and the first housing (38), and the cylindrical wall (56) forms the wall of the second housing (55).

5. The turbine module according to any one of claims 1 to 4, characterized in that, The first segment (51) is connected to the output shaft.

6. The turbine module according to claim 5, characterized in that, The turbine module includes a bushing (66) mounted on the second section (64) of the output shaft (41) and positioned to abut against the shoulder (65), and the rotor (54a) mounted on the bushing (66).

7. The turbine module according to claim 6, characterized in that, The turbine module includes at least one fastening device (70) for fastening the bushing (66) against the shoulder (65) of the output shaft (41).

8. The turbine module according to claim 5, characterized in that, The second section (64) of the output shaft (41) includes a hollow portion (64a) that extends axially over all or part of the second section (64) and receives the end (45) of the drive shaft (34). Coupling devices (43, 44) are disposed between the end (45) and the hollow portion, such that the output shaft (41) and the drive shaft (34) are rotatably fixed.

9. The turbine module according to claim 5, characterized in that, The output shaft (41) is rotatably guided in the annular wall (53) by at least one rotary guide bearing (52), and a sealing element (69) is arranged at an opening in the annular wall (53) and around the first section (51) of the output shaft (41).

10. The turbine module according to any one of claims 1 to 4, characterized in that, The motor (54) is of the type of electric motor and / or generator.

11. The turbine module according to any one of claims 1 to 4, characterized in that, The drive shaft (34) extends to the outside of the accessory gearbox.

12. The turbine module according to any one of claims 1 to 4, characterized in that, The first section (51) of the output shaft (41) rotates inside the transmission receiving portion (50), and the rotation guide bearing (52) is arranged around the first section (51).

13. The turbine module according to any one of claims 1 to 4, characterized in that, The transmission housing (50) is fixed to the downstream flange of the intermediate housing of the turbine, and the accessory gearbox (30) is cantilevered relative to the intermediate housing flange by a structural housing surrounding the drive shaft (34).

14. A turbine (1) for an aircraft, the turbine comprising a high-voltage electric motor shaft (14) and a turbine module according to any one of claims 1 to 13, wherein, The power transmission device is a first power transmission device, and the drive shaft (25) is connected to the high-voltage motor shaft (14) through a second power transmission device (74), so that the transmission shaft (34) and the high-voltage motor shaft (14) are rotatably connected.

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