Aircraft turbomachine assembly, including a backup device for mechanically coupling two rotating parts of the assembly

Abstract

The invention relates to an assembly (100) for an aircraft turbomachine, comprising: - a first (20) and a second rotating part (22); - a main device (24) for mechanically coupling the first part (20) with the second part (22); - a backup device (124) for mechanically coupling the first part (20) with the second part (22), comprising: - a first coupling portion (128), fixed to the first part; - a second coupling portion (132) comprising at least one backup axial stop (134), and, in the normal operating configuration, the backup axial stop is axially separated from a complementary axial stop (136) provided on a fastening member (24a) of the main device (24). Furthermore, in the event of a failure leading to an undesired axial separation between the two parts, the backup device switches to an active axial coupling state. Figure for the abstract: Fig. 2.

Description

Title of the invention: AIRCRAFT TURBOMACHINE ASSEMBLY, COMPRISING A MECHANICAL COUPLING BACKUP DEVICE FOR TWO ROTATING PARTS OF THE ASSEMBLY technical field

[0001] The invention relates to the field of aircraft turbomachinery, and more specifically to that of assemblies using rotating parts of the turbomachine, mechanically coupled to each other.

[0002] This may be various rotating parts of the turbomachine, and in particular a drive shaft as well as a disc of a bladed wheel of turbine or compressor rotor, mechanically coupled to the shaft.

[0003] The invention finds applications in all types of aircraft turbomachinery, such as turbojets or turboprops. Prior art

[0004] When two rotating parts of a turbomachine are mechanically coupled together, in rotation and translation, the failure of one of these parts can lead to an undesired axial displacement of one of the two parts relative to the other. In the case, for example, of a turbine rotor disk, such a failure can cause this disk to move backward, while in the case of a compressor rotor disk, this disk is forced to move forward. In both examples, the directions of undesired axial displacement of the disks are determined by the pressure forces acting on the blades carried by these disks.

[0005] Unwanted axial displacement can result in one of the two parts being forced out of the turbomachine. To avoid such a situation, and to meet the relevant reliability and certification requirements, the turbomachine must be able to provide a failsafe function, preventing the detached part from being extracted from the turbomachine. This failsafe function, also known as "Fail Safe," can be implemented by installing a mechanical coupling device for the two rotating parts. This device can switch from an inactive coupling state to an active coupling state in the event of a failure consisting of the breakage of one of the two rotating parts. In its active coupling state, the failsafe device provides an axial restraint for the part that could move, thus preventing it from being extracted from the turbomachine.Usually, this backup system also allows for the restoration of the . rotational coupling of these components when the main coupling is damaged.

[0006] To implement this backup device, it could be considered to associate a massive axial arresting structure with the rotating part likely to undergo the unwanted movement, by placing this arresting structure downstream of the part to be restrained in the direction of the unwanted axial movement. However, the dense environment in which the rotating parts of the turbomachine are sometimes located does not allow for the implementation of such a massive and bulky "fail-safe" structure. And even if such a structure could be implemented, it would have a significant impact on the overall mass of the turbomachine, leading to a decrease in performance, as well as an increase in specific fuel consumption.

[0007] Consequently, there remains a need to improve the design of the backup mechanical coupling devices between the rotating parts of the turbomachine. Description of the invention

[0008] To meet this need, the invention first relates to an assembly for an aircraft turbomachine, comprising:

[0009] - a first turbomachine part and a second turbomachine part, each of the first and second parts being rotatable around a central longitudinal axis of the assembly;

[0010] - a main device for mechanically coupling the first part with the second the main device, which allows, in a normal operating configuration of the assembly, the first part to be mechanically coupled in translation with the second part, along the longitudinal central axis of the assembly, the main device comprising fastening elements spaced circumferentially from each other, and each passing through a first fastening portion of the first part, as well as a second fastening portion of the second part;

[0011] - a backup mechanical coupling device for the first part with the second piece.

[0012] According to the invention, the emergency device comprises:

[0013] - a first coupling portion, fixed to the first part or integrated into it;

[0014] - a second coupling portion comprising at least one emergency axial stop, said second coupling portion being traversed by the fastening members and spaced from the first coupling portion along the longitudinal central axis, and, in the normal operating configuration of the assembly in which the emergency device adopts an inactive axial coupling state, the emergency axial stop is axially spaced from a complementary axial stop provided on one of the fastening members;

[0015] the assembly being configured so that in the event of a failure leading to a If an undesired axial separation occurs between the first and second parts, the emergency device switches to an active axial coupling state in which it ensures the axial retention of one of the first and second parts relative to the other, by bringing the emergency axial stop into contact with the complementary axial stop.

[0016] The invention thus provides a simple and reliable solution to ensure an emergency axial restraint function, in the event of a failure which may take the form of a break in the first rotating part, between the first and second coupling portions of the emergency device.

[0017] Furthermore, with this design, the backup device can advantageously have a low mass. The invention is therefore the result of technological research aimed at significantly improving aircraft performance and, in this respect, contributes to reducing the environmental impact of these aircraft (decarbonization). The low mass results in particular from the compactness of the assembly, achieved in part by using the same fasteners, such as bolts, both in normal operating configuration and in the event of failure.

[0018] The invention preferably provides for at least one of the following optional technical features, implemented individually or in combination.

[0019] Preferably, the mechanical coupling backup device comprises a shaft, preferably centered on the longitudinal central axis.

[0020] Preferably, the second coupling portion of the emergency device comprises a flange whose axial face forms the emergency axial stop, or an annular row of emergency axial stops cooperating respectively with an annular row of complementary axial stops provided on the fastening members.

[0021] Preferably, the main mechanical coupling device also allows, in the normal operating configuration of the assembly, the first part to be mechanically coupled in rotation with the second part, along the longitudinal central axis of the assembly. In addition, the backup device also includes at least one circumferential backup stop, and, in the normal operating configuration of the assembly in which the backup device adopts an inactive state of rotational coupling, the circumferential backup stop is circumferentially spaced from a complementary circumferential stop provided on one of the fastening members;

[0022] the assembly being configured so that in the event of a failure leading to an undesired relative rotation between the first and second parts, the backup device switches to an active rotational coupling state in which it ensures the rotational coupling of one of the first and second parts with the other, by bringing the emergency circumferential stop into contact with the complementary circumferential stop.

[0023] According to a preferred embodiment of the invention, the second coupling portion also includes said circumferential emergency stop, preferably taking the form of a portion of the delimitation surface of a passage orifice through the flange of the emergency device, each passage orifice being traversed by one of the fixing members.

[0024] Thus, with this design, the same backup device is further functionalized, since it is advantageously capable of fulfilling an additional "Fail Safe" function of rotating coupling of the two rotating parts.

[0025] Preferably, the emergency axial stop and the emergency circumferential stop are formed by two surfaces of the flange of the emergency device, and the complementary axial stop and the complementary circumferential stop are formed by two surfaces of the same fastening member.

[0026] Preferably, the additional axial stop and the additional circumferential stop are respectively formed by a spare axial surface of a fastening member and by a lateral surface of the same fastening member, the latter comprising a main axial surface forming a support on the first part to clamp it with the second part in the normal operating configuration of the assembly. This feature simplifies the design of the assembly according to the invention and makes it more compact.

[0027] Preferably, the first fastening portion of the first part is a fastening flange arranged axially between the flange of the emergency device, and the second part.

[0028] The first coupling portion of the backup device is preferably fixed to the first part by means of a threaded or welded connection, preferably centered on the longitudinal central axis. A solution where the backup device is integrated into the first part, i.e., made as a single piece with it, is also conceivable. Preferably, in the case of a threaded connection, the direction in which the first coupling portion of the backup device is tightened onto the first part corresponds to a direction of rotation of the first part about the longitudinal central axis. Thus, in the event of a failure and when the second part is the leading component in rotation within the assembly, the proposed solution prevents the first coupling portion of the backup device from unscrewing.

[0029] Preferably, the second part drives the first part in rotation, in a direction of rotation of the first and second parts.

[0030] Preferably, the first part is a drive shaft of the turbomachine, and the second part is a disc of a bladed rotor wheel, preferably of a turbine or compressor. However, it could be other rotating parts coupled to the turbomachine, without departing from the scope of the invention.

[0031] Finally, the invention relates to an aircraft turbomachine, comprising at least one assembly as described above. It could for example be a turbojet, and preferably a dual-flow, single or dual-body type.

[0032] Other advantages and features of the invention will appear in the detailed, non-limiting description below. Brief description of the drawings

[0033] The detailed description that follows refers to the accompanying drawings in which:

[0034] [Fig-1] is a schematic longitudinal cross-sectional view of a turbomachine aircraft;

[0035] [Fig.2] is a schematic longitudinal sectional view of an assembly intended to equip the turbomachine shown in the previous figure, the assembly being in the form of a preferred embodiment of the invention, shown in normal operating configuration;

[0036] [Fig.3] is a cross-sectional view taken along line III-III of [Fig.2];

[0037] [Fig.4] is a schematic longitudinal sectional view similar to that of [Fig.2], with the assembly represented in failure configuration;

[0038] [Fig.5] is a cross-sectional view taken along line VV of [Fig.4]. Detailed description of implementation methods

[0039] With reference first to [Fig. 1], an aircraft turbomachine 1 is shown. This is a twin-spool turbofan engine. However, it could be a turbomachine of another type, for example a single-spool turbofan engine, or even a turboprop, without departing from the scope of the invention.

[0040] The turbomachine 1 has an axis X around which its various components extend, this axis being called the longitudinal central axis of the turbomachine. It comprises, from upstream to downstream along a main direction 5 of gas flow through this turbomachine, a blower 3, a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 11, a high-pressure turbine 7 and a low-pressure turbine 8.

[0041] Conventionally, after passing through the blower, the air splits into a central primary flow 12a and a secondary flow 12b which surrounds the primary flow. The primary flow 12a flows into a main gas circulation channel 14a passing through the compressors 4, 6, the combustion chamber 11 and the turbines 7, 8. The secondary flow 12b, on the other hand, flows into a secondary channel 14b delimited radially outwards by an engine casing, surrounded by a nacelle 9.

[0042] Figures 2 to 5 represent an assembly 100 intended to equip the turbomachine shown in [Fig.1], and presented in the form of a preferred embodiment of the invention.

[0043] This assembly 100 comprises any two rotating parts, coupled me mechanically to each other. The two parts 20, 22 are concentric, with axis X, and are arranged so that the first part 20 is upstream of the second part 22. The two parts 20, 22 are thus rotatable around the axis X, which also corresponds to the longitudinal central axis of the assembly 100. In this preferred embodiment of the invention, the second part 22 is considered to be the driving part, while the first part 20 is driven in rotation by this second part 22. A reverse situation could nevertheless be considered, without departing from the scope of the invention. For the sake of reference, the first part 20 here corresponds to a drive shaft of the turbomachine, for example the low pressure shaft of the turbomachine, while the second part 22 corresponds to a disc of a bladed turbine rotor wheel, for example the rotor disc of the last stage of the low pressure turbine 8, namely the disc located furthest downstream within the turbomachine.Other applications remain possible, however, such as having the second driving part 22 corresponding to the low-pressure shaft, and the first driven part 20 corresponding to a bladed disc of a compressor rotor wheel, for example the rotor disc of the first stage of the low-pressure compressor, namely the disc located furthest upstream within the turbomachine.

[0044] In the case which will be considered below, namely that in which the first driven part 20 corresponds to the low pressure shaft, and the second driving part 22 corresponds to a disc of a bladed rotor wheel of a last stage of the low pressure turbine, the pressure forces resulting from the primary flow and applied to the second part 22 tend to force it axially downstream, relative to the first part 20.

[0045] To ensure axial retention of these two parts 20, 22 relative to each other, the assembly 100 includes a main device 24 for mechanically coupling the first part 20 with the second part 22. This device 24 takes the form of an annular ring of bolt-type fasteners 24a, or similar fasteners, the ring being preferably centered on the X-axis. These fasteners 24a, preferably axially oriented, each first pass through a through hole 23 in a mounting flange 25 provided on a downstream end portion 38 of the shaft 20. After passing through this mounting flange 25, which is radially oriented outwards, each bolt 24a passes through a through hole 23a provided on the disc 22. The bolts 24a, spaced circumferentially from each other around the X axis, therefore axially clamp the fixing flange 25 and the disc 22.

[0046] As a result, the fixing flange 25 forms a first portion of fixing the shaft 20, while the part of the disc which delimits the through orifice 23a, forms a second portion of fixing 22' of this disc 22.

[0047] In the normal operating configuration of the assembly 100, shown in Figures 2 and 3, the main device 24 allows the first part 20 to be mechanically coupled in translation with the second part 22, along the X axis. It also allows these two parts 20, 22 to be mechanically coupled in rotation, again along the longitudinal central axis X, thanks to the axial tightening of the bolts 24a.

[0048] To achieve this, each bolt 24a comprises a screw with a shank 58 passing through the two orifices 23, 23a. On the downstream end face of the turbine disc 22, the threaded portion of the shank cooperates with a nut 62, axially bearing against this downstream end face. Furthermore, on the side of the mounting flange 25, the shank has an enlarged portion 64 defining an axial shoulder, which forms a main axial surface 66, bearing against the upstream end surface of the mounting flange 25. Thus, in the normal operating configuration of the assembly, the main axial surface 66 of the screw and the nut 62 are under tension so as to axially clamp the two parts 20, 22.

[0049] It is noted that the through orifice 23 is traversed by the shaft 58 of the screw with just a mounting clearance, or without clearance.

[0050] The assembly 100 also includes a failsafe device 124 for mechanically coupling the first part 20 with the second part 22, of a design specific to the present invention. This failsafe device 124, also called the "Fail Safe" device, makes it possible to cope with a failure case corresponding to a break in the downstream end portion 38 of the first part 20. The failsafe device 124 makes it possible to cope with any failure case likely to lead to an undesired axial displacement of the second part 22 downstream relative to the first part 20, and more generally with any failure case likely to lead to an undesired axial separation between these two parts 20, 22.

[0051] More specifically, the backup device 124, arranged around the shaft 20, comprises a shaft 126, hollow or solid, centered on the X-axis. At its upstream end, the shaft 126 carries a first coupling portion 128, fixed to the first part 20, preferably by means of a threaded connection 130 or welded, also centered on the X-axis. This threaded connection 130 is therefore preferably provided outside the hollow drive shaft forming the first turbomachine part 20. In the screwed solution, the screwing direction of the first coupling portion 128, on the first part 20, corresponds to the direction of rotation of the two parts 20, 22 in normal operating configuration. Therefore, in the event of failure, with the second driving part 22 rotating the backup device 124, there is no risk that this rotation will cause the first coupling portion 128 of this backup device 124 to unscrew.

[0052] At its downstream end, the shaft 126 carries a second coupling portion 132 comprising at least one emergency axial stop 134. The second coupling portion 132 is spaced from the first coupling portion 128, along the X axis. Indeed, the first coupling portion 128 is preferably located at the same axial level as a bearing 40 supporting the shaft 20, or close to this bearing 40. Here, the bearing 40 indirectly supports the shaft 20, via the backup device 124, around which the bearing 40 is directly mounted.

[0053] The first coupling portion 128, which is therefore preferably threaded, can extend upstream beyond the most downstream bearing 40. The second coupling portion 132 is, for its part, preferably located near an upstream end of the downstream end portion 38 of the shaft 20, formed by the mounting flange 25. Also, the backup device 124 is provided to ensure the "Fail Safe" function in the event of failure of the shaft 20 occurring in an area located axially between the two coupling portions 128, 132 of the backup device. This amounts to considering, in the preferred embodiment which is described, that the backup device 124 is capable of ensuring the "Fail Safe" function in the event of breakage of the shaft 20 occurring axially at any point on its downstream end part 38, i.e. downstream of the bearing 40 or the threaded connection 130.

[0054] The emergency device 124 implemented in this preferred embodiment is such that it makes it possible to ensure emergency axial restraint, as well as emergency rotational coupling between the two parts 20, 22, in the event of breakage of the shaft at its downstream end part 38.

[0055] At its downstream end, the shaft 126 therefore carries the second coupling portion 132, which comprises a flange 133 extending radially outwards, and whose upstream axial face forms an annular row of emergency axial stops 134. More precisely, the flange 133 has through-holes 68 through which the bolts 24a pass. More precisely, it is the enlarged portion 64 of each shaft 58 that is housed in one of the through-holes 68. Thus, the emergency axial stops 134 are formed on the upstream axial face of the flange by the surfaces at which the through-holes 68 open, these surfaces being able to be considered annular or substantially annular around each hole 68. They are designed to cooperate with an annular row of complementary axial stops 136, provided on the bolts 24a.More specifically, each additional axial stop 136 is formed by a spare axial surface provided on the corresponding fastening member 24a. As can be seen in [Fig.2], this spare axial surface 134 is located between the screw head 72 and the enlarged portion 64 of the shaft, and corresponds more precisely to the downstream axial surface of the screw head 72, from which the enlarged portion extends downstream.

[0056] Furthermore, the flange 133 of the second coupling portion 132 includes an annular row of circumferential emergency stops 234. Each of these stops 234 is formed by a part of the boundary surface of one of the passage orifices 68 through the flange 133. More precisely, this part 234 corresponds to an angular sector of the boundary surface of this passage orifice 68. This is the angular sector located at a circumferential end of the orifice 68, namely that in the direction of rotation 54 of the two parts 20, 22.

[0057] One of the particularities of this embodiment therefore lies in the fact that an axial emergency stop 134, and a circumferential emergency stop 234, are formed by two surfaces of the flange 133. The latter is arranged in such a way that the fixing flange 25 of the shaft 20 is located axially between this flange 133 of the emergency device 124, and the upstream end surface of the turbine disc 22.

[0058] Similar to that described above, a complementary axial stop 136 and a complementary circumferential stop 236 are formed by two surfaces of the same bolt 24a. Indeed, the complementary axial stop 136 corresponds to the downstream surface of the screw head 72 as previously indicated, while the complementary circumferential stop 236 corresponds to a portion of a lateral surface delimiting the enlarged portion 64 of the screw shank. More precisely, this portion 236 corresponds to an angular sector of the lateral surface delimiting the enlarged portion 64. This is the angular sector located at a circumferential end of the shank, namely the end in the direction of rotation 54 of the two parts 20, 22.

[0059] In the normal operating configuration of the assembly 100, shown in Figures 2 and 3, the backup device 124 adopts inactive states of axial coupling, and rotational coupling.

[0060] In these inactive states, the axial play 137 is maintained between the emergency axial stop 134 and the complementary axial stop 136, as well as a circumferential play 237 between the circumferential emergency stop 234, and the complementary circumferential stop 236. A radial play is also preferably provided between the enlarged portion 64 of each screw shank 58, and its corresponding passage orifice 68.

[0061] In the event of a failure corresponding to a break within the downstream end portion 38 of the shaft 20, shown schematically in [Fig. 4], the pressure forces applied to the rotor of the disc 22 lead to an undesired axial separation between the two parts 20, 22. More precisely, this separation is caused by the downstream displacement of the disc 22. Simultaneously, an undesired relative rotation occurs between the first and second parts 20, 22, the disc 22 being momentarily unable to drive the shaft in rotation in the direction 54.

[0062] After this break, the shaft 20, which remains axially fixed within the assembly 100, is no longer able to provide axial retention of the second part 22 via the bolts. The main mechanical coupling device 24 thus enters an inactive coupling state between the two parts, while the aforementioned axial play 137 is consumed. during the parasitic axial displacement downstream of the disc 22, taking with it the broken part of the downstream end of the shaft 20. In addition, the pressure forces applied to the rotor cause its disc 22 to continue its rotation, which results in the circumferential clearance 237 also being consumed due to the relative rotation with the shaft 20, which is momentarily no longer driven in the direction 54.

[0063] These small axial and circumferential displacements are stopped by the contact of the emergency axial stop 134 with the moving complementary axial stop 136, as well as by the contact of the emergency circumferential stop 234 with the rotating complementary circumferential stop 236 with the disc 22. This forces the emergency device 124 to move from its inactive states to its active states of emergency axial coupling and emergency rotational coupling, shown in Figures 4 and 5.

[0064] Once these active states are adopted, the backup device 124 allows the axial retention of the disc 22 by the shaft 20, as well as the rotational driving of the second by the first.

[0065] To facilitate this rotation, one or more centering points 56 may be provided between the shaft 20 and the backup device 124, located here preferably outside the shaft.

[0066] This reliable, compact and low-mass solution thus avoids excessive axial displacement of the second part 22 in the event of failure, and above all prevents this part from escaping axially outside the turbomachine.

[0067] Finally, it is noted that the solution proposed by the present invention is also advantageous in that the backup device 124 does not require any modification of the disc 22 for its installation in the assembly 100. Furthermore, mounting the backup device 124 on the shaft 20 remains straightforward. In addition, using the bolts 24a for both the normal operating configuration and the failure configuration further enhances the compactness of the assembly.

[0068] Various modifications can be made by a person skilled in the art to the invention just described, solely by way of non-limiting examples, and the scope of which is defined by the attached claims.

Claims

Demands

1. Assembly (100) for an aircraft turbomachine (1), comprising: - a first turbomachine part (20) and a second turbomachine part (22), each of the first and second parts being rotatable about a longitudinal central axis (X) of the assembly; - a main device (24) for mechanically coupling the first part (20) with the second part (22), the main device enabling, in a normal operating configuration of the assembly, the first part (20) to be mechanically coupled in translation with the second part (22), along the longitudinal central axis (X) of the assembly, the main device (24) comprising fastening members (24a) spaced circumferentially from each other, and each passing through a first fastening portion (133) of the first part, as well as a second fastening portion (22') of the second part (22); - a backup device (124) for mechanically coupling the first part (20) with the second part (22), characterized in that the backup device (124) comprises: - a first coupling portion (128), fixed on the first part (20) or integrated into it; - a second coupling portion (132) comprising at least one emergency axial stop (134), said second coupling portion being traversed by the fastening members (24a) and spaced from the first coupling portion along the longitudinal central axis (X), and, in the normal operating configuration of the assembly in which the emergency device adopts an inactive axial coupling state, the emergency axial stop (134) is axially spaced from a complementary axial stop (136) provided on one of the fastening members (24a); the assembly being configured so that in the event of a failure leading to an undesired axial separation between the first and second parts (20, 22), the backup device (124) goes into an active axial coupling state in which it ensures the axial retention of one of the first and second parts relative to the other, by bringing the backup axial stop (134) into contact with the complementary axial stop (136).

2. Assembly according to claim 1, characterized in that the mechanical coupling backup device (124) comprises a shaft (126), of preference centered on the central longitudinal axis (X).

3. Assembly according to claim 1 or 2, characterized in that the second coupling portion (132) of the emergency device (124) comprises a flange (133) of which an axial face forms the emergency axial stop (134), or an annular row of emergency axial stops (134) cooperating respectively with an annular row of complementary axial stops (136) provided on the fastening members (24a).

4. Assembly according to any one of the preceding claims, characterized in that the main mechanical coupling device (24) also allows, in the normal operating configuration of the assembly, the first part (20) to be mechanically coupled in rotation with the second part (22), along the longitudinal central axis of the assembly (X), and in that the emergency device (124) also includes at least one circumferential emergency stop (234), and, in the normal operating configuration of the assembly in which the emergency device (124) adopts an inactive state of rotational coupling, the circumferential emergency stop (234) is circumferentially spaced from a complementary circumferential stop (236) provided on one of the fastening members (24a);the assembly being configured so that in the event of a failure leading to an undesired relative rotation between the first and second parts (20, 22), the backup device (124) goes into an active state of rotational coupling in which it ensures the rotational coupling of one of the first and second parts with the other, by bringing the emergency circumferential stop (234) into contact with the complementary circumferential stop (236).

5. Assembly according to claim 4, combined with claim 3, characterized in that the second coupling portion (132) comprises the circumferential emergency stop (234), preferably taking the form of a portion of the delimiting surface of a passage orifice (68) through the flange (133) of the emergency device (124), each passage orifice (68) being traversed by one of the fastening members (34a).

6. Assembly according to claim 5, characterized in that the emergency axial stop (134) and the emergency circumferential stop (234) are formed by two surfaces of the flange (133) of the emergency device (124), and in that the supplementary axial stop (136) and the supplementary circumferential stop (236) are formed by two surfaces of the same fastening element (24a).

7. Assembly according to claim 6, characterized in that the additional axial stop (136) and the additional circumferential stop (236) are respectively formed by an emergency axial surface of a fastening member (24a), and by a lateral surface of the same fastening member, the latter comprising a main axial surface (66) forming a support on the first part (20) to clamp it with the second part (22) in the normal operating configuration of the assembly.

8. Assembly according to any one of the preceding claims combined with claim 3, characterized in that the first fastening portion of the first part (20) is a fastening flange arranged axially between the flange (133) of the emergency device (124), and the second part (22).

9. Assembly according to any one of the preceding claims, characterized in that the first coupling portion (128) of the emergency device (124) is fixed to the first part (20) by means of a threaded (130) or welded connection, preferably centered on the longitudinal central axis (X), and in that in the case of a threaded connection, the screwing direction of the first coupling portion (128) of the emergency device (124), on the first part (20), corresponds to a direction of rotation (54) of the first part (20), about the longitudinal central axis (X).

10. Assembly according to any one of the preceding claims, characterized in that the second part (22) drives the first part (20) in rotation, in a direction of rotation (54) of the first and second parts (20, 22).

11. Aircraft turbomachine (1), comprising at least one assembly (100) according to any one of the preceding claims, the first part (20) being preferably a drive shaft of the turbomachine, and the second part (22) being preferably a disc of a bladed rotor wheel, preferably of a turbine (7, 8) or compressor (4, 6).

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