ASSEMBLY FOR AN AIRCRAFT TURBOMACHINE, COMPRISING AN EMERGENCY 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 (22) rotating part; - a main device (24) for mechanically coupling the first part (20) with the second part (22), - an emergency device (124) for mechanically coupling the first part (20) with the second part (22), comprising: - a first coupling portion (128), fixed on the first part; - a second coupling portion (132) comprising at least one emergency axial stop (134), and, in the normal operating configuration, the emergency axial stop is axially spaced from a complementary axial stop (136) provided on the first part. In addition, the assembly is configured so that in the event of a failure leading to an unwanted axial separation between the first and second parts, the emergency device switches to an active axial coupling state. Figure for the abstract: Fig. 2.

Description

Title of the invention: ASSEMBLY FOR AN AIRCRAFT TURBOMACHINE, COMPRISING AN EMERGENCY DEVICE FOR MECHANICALLY COUPLING TWO ROTATING PARTS OF THE ASSEMBLY Technical field

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

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

[0003] The invention finds applications in any type of aircraft turbomachine, such as turbojets or turboprops. State of the prior art

[0004] When two rotating parts of a turbomachine are mechanically coupled to each other, in rotation and in translation, the rupture of one of these parts can lead to an unwanted axial displacement of one of these two parts relative to the other. In the case, for example, of a turbine rotor disk, such a rupture can cause this disk to move backwards, while in the case of a compressor rotor disk, this disk is forced to move forwards. In these two examples, the directions of unwanted axial displacement of the disks are determined by the pressure forces applied to the blades carried by these disks.

[0005] Unwanted axial displacement may result in one of the two parts being forced out of the turbomachine. In order to avoid such a situation, and to meet the reliability and certification requirements in this area, the turbomachine must be able to provide an emergency function, preventing the detached part from being extracted from this turbomachine. This emergency function, also known as "Fail Safe", may be achieved by implementing an emergency device for mechanically coupling the two rotating parts, capable of switching from an inactive coupling state to an active coupling state, in the event of a failure consisting of the breakage of one of these two parts which are integral in rotation. The emergency device makes it possible, in its active coupling state, to form an emergency axial restraint of the part likely to move, thus preventing this part from being extracted from the turbomachine.Usually, this backup device also helps to restore the . rotational coupling of these components, when the main coupling is damaged.

[0006] To produce this emergency device, it may be envisaged to associate a massive axial stop structure with the rotating part likely to undergo the unwanted displacement, by placing this stop structure downstream of the part to be retained in the direction of unwanted axial displacement. However, the dense environment in which the rotating parts of the turbomachine are sometimes located does not allow the installation of such a massive and bulky “Fail Safe” structure. And even if this structure is possible to install, it induces a non-negligible impact on the overall mass of the turbomachine, leading to a reduction in performance, as well as an increase in specific fuel consumption.

[0007] Therefore, there remains a need to improve the design of emergency mechanical coupling devices between rotating turbomachine parts. Statement of the invention

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

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

[0010] - a main device for mechanically coupling the first part with the second part, the main device allowing, in a normal operating configuration of the assembly, to mechanically couple in translation the first part with the second part, along the longitudinal central axis of the assembly;

[0011] - an emergency device for mechanically coupling the first part with the second room.

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

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

[0014] - a second coupling portion comprising at least one emergency axial stop, said second coupling portion being 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 said first part;

[0015] the assembly being configured so that in the event of failure leading to an unwanted axial separation 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 the emergency axial stop coming into contact with the complementary axial stop.

[0016] The invention thus provides a simple and reliable solution for ensuring an emergency axial retaining 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 emergency device can advantageously have a low mass. The invention is therefore the result of technological research aimed at significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of these aircraft (decarbonization).

[0018] The invention preferably provides at least any one of the following optional technical features, implemented in isolation 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, one axial face of which forms the emergency axial stop, or an annular row of emergency axial stops.

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

[0022] the assembly being configured so that in the event of a failure leading to an unwanted relative rotation between the first and second parts, the emergency 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 contacting the emergency circumferential stop with the complementary circumferential stop.

[0023] According to a preferred embodiment of the invention, the second coupling portion also comprises said emergency circumferential stop.

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

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

[0026] Preferably, the first member is a tooth, a groove or a notch provided radially projecting within the flange of the emergency device, and the second member is a coupling imprint, or vice versa, and the first member is housed in the coupling imprint when the emergency device is in its active and inactive states of axial coupling and rotational coupling. This feature simplifies the design of the assembly according to the invention.

[0027] Preferably, the flange of the emergency device comprises several first radially projecting members, circumferentially spaced from each other, and the first part comprises several coupling impressions each housing one of the first members, the first part comprising a fixing flange crossed by fixing members forming the main mechanical coupling device, the first members of the emergency device being arranged circumferentially alternating with the fixing members of the main device. This particular arrangement further reinforces the compactness of the assembly.

[0028] The first coupling portion of the emergency device is preferably fixed to the first part using, for example, a welded connection, preferably centered on the longitudinal central axis. A solution where the emergency device would be integrated into the first part, namely made in a single piece with it, is also conceivable.

[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 second member is the coupling imprint, and the complementary circumferential stop corresponds to a circumferential delimitation surface of this imprint, and the complementary axial stop corresponds to an axial bottom of this imprint. Also, in the event of failure and when the second part is driving in rotation within the assembly, the proposed solution makes it possible to automatically obtain the entry into contact of the emergency circumferential stop with the complementary circumferential stop, by relative displacement in rotation between the second driving part, and the second coupling portion of the emergency device secured to the first driven rotating part.

[0031] Preferably, the first part is a drive shaft of the turbomachine, and the second part is a disc of a rotor bladed wheel, preferably of a turbine or compressor. However, it could be other coupled rotating parts of the turbomachine, without departing from the scope of the invention.

[0032] Finally, the invention relates to an aircraft turbomachine, comprising at least one assembly as described above. It may for example be a turbojet, and preferably double-flow and single or double-body.

[0033] Other advantages and characteristics of the invention will appear in the detailed non-limiting description below. Brief description of the drawings

[0034] The following detailed description refers to the attached drawings in which:

[0035] [Fig-1] is a schematic view in longitudinal section of a turbomachine aircraft;

[0036] [Fig.2] is a schematic view in longitudinal section of an assembly intended to equip the turbomachine shown in the preceding figure, the assembly being in the form of a preferred embodiment of the invention, shown in normal operating configuration;

[0037] [Fig.3] is a sectional view taken along line III-III of [Fig.2];

[0038] [Fig.3A] is a sectional view taken along line IIIA-IIIA of [Fig.3];

[0039] [Fig.4] is a schematic longitudinal sectional view similar to that of [Fig.2], with the assembly shown in the failure configuration;

[0040] [Fig.5] is a sectional view taken along line VV of [Fig.4]. Detailed description of embodiments

[0041] Referring firstly to [Fig.l], an aircraft turbomachine 1 is shown. This is a double-flow, double-spool turbojet engine. However, it could be a turbomachine of another type, for example a single-spool turbojet engine, or even a turboprop, without departing from the scope of the invention.

[0042] 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 flow of the gases through this turbomachine, a fan 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.

[0043] Conventionally, after passing through the blower, the air divides into a central primary flow 12a and a secondary flow 12b which surrounds the primary flow. The primary flow 12a flows in a main gas circulation vein 14a passing through the compressors 4, 6, the combustion chamber 11 and the turbines 7, 8. The secondary flow 12b flows in a secondary vein 14b delimited radially outwards by a motor casing, surrounded by a nacelle 9.

[0044] Figures 2 to 5 represent an assembly 100 intended to equip the turbomachine shown in [Fig.l], and presented in the form of a preferred embodiment of the invention.

[0045] This assembly 100 comprises any two rotating parts, coupled mechanically mechanically to each other. The two parts 20, 22 are concentric, with axis X, and here 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, also corresponding to the longitudinal central axis of the assembly 100. In this preferred embodiment of the invention, it is considered that the second part 22 is driving, while the first part 20 is driven in rotation by this second part 22. An inverse situation could nevertheless be retained, without departing from the scope of the invention. For information purposes, 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 disk of a turbine rotor bladed wheel, for example the rotor disk of the last stage of the low pressure turbine 8, namely the disk 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 disc of a compressor rotor bladed wheel, for example the rotor disc of the first stage of the low pressure compressor, namely the disc located furthest upstream within the turbomachine.

[0046] 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 rotor bladed 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 the latter axially downstream, relative to the first part 20.

[0047] To ensure the axial retention of these two parts 20, 22 relative to each other, the assembly 100 comprises a main device 24 for mechanically coupling the first part 20 with the second part 22. This device 24 here takes the form of an annular ring of fixing members 24a of the bolt type, or similar fixing members, the ring being preferably centered on the axis X. These fixing members 24a, preferably oriented axially, each first pass through a through-orifice 23 of a fixing flange 25 provided on a downstream end portion 38 of the shaft 20. After passing through this fixing flange 25, oriented radially outwards, each bolt 24a passes through a through-orifice 23a provided on the disc 22. The bolts 24a, spaced circumferentially from each other around of the X axis, therefore axially enclose the fixing flange 25 and the disc 22.

[0048] In the normal operating configuration of the assembly 100, shown in Figures 2 and 3, the main device 24 makes it possible to mechanically couple in translation the first part 20 with the second part 22, along the X axis. It makes it possible also to mechanically couple in rotation these two parts 20, 22, always according to the longitudinal central axis X, thanks to the axial tightening of the bolts 24a.

[0049] The assembly 100 also comprises a backup device 124 for mechanically coupling the first part 20 with the second part 22, of a design specific to the present invention. This backup device 124, also called a “Fail Safe” device, makes it possible to deal with a failure case corresponding to a break on the downstream end portion 38 of the first part 20. The backup device 124 in fact makes it possible to deal with any failure case likely to lead to an unwanted axial displacement of the second part 22 downstream relative to the first part 20, and more generally any failure case likely to lead to an unwanted axial separation between these two parts 20, 22.

[0050] More precisely, the emergency device 124 comprises a shaft 126, hollow or solid, centered on the axis X. At its upstream end, the shaft 126 carries a first coupling portion 128, fixed to the first part 20, preferably using a welded connection 130, also centered on the axis X. It may alternatively be a mechanical connection between the two elements, for example made using a pin or similar mechanical elements. This connection 130 is preferably provided inside the hollow engine shaft forming the first turbomachine part 20.

[0051] 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 axis X. Indeed, the first coupling portion 128 is preferably located at the same axial level as a rolling bearing 40 supporting the shaft 20, or close to this bearing 40. This first coupling portion 128 can extend upstream beyond the most downstream rolling bearing 40, as shown in FIGS. 2 and 4. The second coupling portion 132 is, for its part, preferably located at the same axial level as a downstream end of the downstream end portion 38 of the shaft 20, or close to this end.Also, the emergency device 124 is provided to ensure the “Fail Safe” function in the event of breakage of the shaft 20 occurring in an area located axially between the two coupling portions 128, 132 of the emergency device. This amounts to considering, in the preferred embodiment which is described, that the emergency device 124 is capable of ensuring the “Fail Safe” function in the event of breakage of the shaft 20 occurring axially at any location on its downstream end portion 38, i.e. downstream of the bearing 40 or the welded connection 130.

[0052] The emergency device 124 implemented in this preferred embodiment is such that it makes it possible to provide emergency axial retention, as well as emergency rotational coupling between the two parts 20, 22, in the event of breakage of the shaft at its downstream end portion 38.

[0053] At its downstream end, the shaft 126 therefore carries the second coupling portion 132, which comprises a flange 133 extending radially outwards, and an upstream axial face of which forms an annular row of emergency axial stops 134.

[0054] The flange 133 has a general star or toothed wheel shape, in that it comprises a circumferential base 133a from which a plurality of first members 138 of the emergency device 124 extend. These first members 138 are circumferentially spaced from one another, projecting radially outward from the base 133a of the flange. Each first member 138 takes the form of a tooth, a groove or a notch. This first member 138 is intended to cooperate with a second member 238, which is here a coupling imprint provided on a downstream axial end surface of the shaft 20, this imprint 238 opening radially inward, and axially downstream.

[0055] Each first member 138 is intended to be housed in a corresponding coupling imprint 238, and this regardless of the states of the emergency device 124, that is to say whether it is in its active or inactive states of axial coupling and rotational coupling.

[0056] The circumferential succession of impressions 238, connected to each other at their open internal radial ends by a recess 238a housing the base 133a of the flange 133, also has a general star or toothed wheel shape, of a shape complementary or substantially complementary to that of the flange 133.

[0057] In addition, the first members 138 of the emergency device 124 are arranged circumferentially alternating with the bolts 24a of the main device 24, as best seen in [Fig. 3]. In cross-section such as that shown in this figure, the first members 138 extend radially outwardly at least beyond a center of the bolts 24a and their through-holes 23.

[0058] Concerning these first members 138, they therefore define, with their upstream axial face, the annular row of emergency axial stops 134. At the same time, each first member 138 in the form of a tooth, groove or notch, also defines, with a circumferential flank delimiting this tooth, a circumferential emergency stop 234. Consequently, the flange 133 also defines an annular row of circumferential emergency stops 234, with circumferential flanks of its teeth 138. As is best seen in [Fig.2], the flange 133 is then arranged axially with clearance in an axial space defined between the axial bottom of the impressions 238, and an upstream axial surface of the disc 22.

[0059] One of the particularities of this embodiment therefore lies in the fact that an emergency axial stop 134, and an emergency circumferential stop 234, are formed by two surfaces of the same first member 138 in the form of a tooth or the like.

[0060] Similarly, a complementary axial stop 136 and a circumferential stop complementary circumferential stop 236 are formed by two surfaces of the same coupling imprint 238 of the shaft 20. Indeed, the complementary circumferential stop 236 corresponds to a circumferential delimitation surface of this imprint 238, while the complementary axial stop 136 corresponds to an axial bottom of this imprint, open downstream.

[0061] In the normal operating configuration of the assembly 100, shown in FIGS. 2 and 3, the emergency device 124 adopts inactive states of axial coupling and rotational coupling.

[0062] In these inactive states, each tooth 138 is located in one of the indentations 238. Nevertheless, the axial clearance 137 is retained between the emergency axial stop 134 and the complementary axial stop 136, as well as a circumferential clearance 237 between the emergency circumferential stop 234 and the complementary circumferential stop 236. A radial clearance is also preferably provided between each first portion 138 and the first part 20.

[0063] In a case of failure corresponding to a rupture within the downstream end portion 38 of the shaft 20, shown diagrammatically in [Fig. 4], the pressure forces applied to the rotor of the disc 22 lead to an unwanted axial separation between the two parts 20, 22. More precisely, this separation is caused by the downstream movement of the disc 22. Simultaneously, an unwanted relative rotation occurs between the first and second parts 20, 22, the disc 22 being momentarily no longer able to drive the shaft in rotation in the direction 54.

[0064] After this break, the shaft 20, which remains axially fixed within the assembly 100, is no longer able to ensure the axial retention of the second part 22 via the bolts. The main mechanical coupling device 24 thus passes into an inactive state of coupling between the two parts, while the aforementioned axial clearance 137 is consumed during the parasitic axial displacement towards the 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 has the consequence that the circumferential clearance 237 is also consumed due to the relative rotation with the shaft 20, which is momentarily no longer driven in the direction 54.

[0065] These small axial and circumferential movements are stopped by the emergency axial stop 134 coming into contact with the complementary axial stop 136 in motion, as well as by the emergency circumferential stop 234 coming into contact with the complementary circumferential stop 236 in rotational motion with the disc 22. This forces the emergency device 124 to pass from its inactive states to its active states of emergency axial coupling and emergency rotational coupling, shown in Figures 4 and 5.

[0066] Once these active states have been adopted, the emergency 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.

[0067] To facilitate this rotation, one or more centerings 56 may be provided between the shaft 20 and the emergency device 124, preferably located here inside the shaft.

[0068] This reliable, space-saving 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.

[0069] Finally, it is noted that the solution proposed by the present invention is also advantageous in the sense that the emergency device 124 does not require, for its installation in the assembly 100, any modification of the disc 22. In addition, the mounting of the emergency device 124 on the shaft 20 remains easy, in the sense that the latter can be inserted axially into the hollow of the shaft from downstream, in the upstream direction, before mounting the disc 22 on this same shaft 20.

[0070] Various modifications may be made by a person skilled in the art to the invention which has just been described, solely by way of non-limiting examples, and the scope of which is defined by the appended claims. For example, the translational emergency coupling function could alternatively be performed solely by the circumferential base 133a of the flange 133 in cooperation with the complementary-shaped recess 238a on the shaft 20, without departing from the scope of the invention. In the latter case, the teeth 138 and the complementary-shaped indentations 238 would then be used solely for the rotational emergency coupling function, still thanks to the stops 234, 236.

Claims

Claims

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 making it possible, in a normal operating configuration of the assembly, to mechanically couple in translation the first part (20) with the second part (22), along the longitudinal central axis (X) of the assembly; - an emergency device (124) for mechanically coupling the first part (20) with the second part (22), characterized in that the emergency device (124) comprises: - a first coupling portion (128), fixed to the first part (20) or integrated therein;- a second coupling portion (132) comprising at least one emergency axial stop (134), said second coupling portion being 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 said first part (20); the assembly being configured so that in the event of a failure leading to an unwanted axial separation between the first and second parts (20, 22), the emergency device (124) 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 the emergency axial stop (134) coming into contact with the complementary axial stop (136).;

2. Assembly according to claim 1, characterized in that the emergency mechanical coupling device (124) comprises a shaft (126), preferably centered on the longitudinal central 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 one axial face forms the axial stop of emergency (134), or an annular row of emergency axial stops (134).

4. Assembly according to any one of the preceding claims, characterized in that the main mechanical coupling device (24) also makes it possible, in the normal operating configuration of the assembly, to mechanically couple in rotation the first part (20) with the second part (22), along the longitudinal central axis of the assembly (X), and in that the emergency device (124) also comprises at least one emergency circumferential 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 emergency circumferential stop (234) is circumferentially spaced from a complementary circumferential stop (236) provided on the first part (20);the assembly being configured so that in the event of a failure leading to an unwanted relative rotation between the first and second parts (20, 22), the emergency device (124) 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 contacting the emergency circumferential stop (234) with the complementary circumferential stop (236).;

5. Assembly according to claim 4, characterized in that the second coupling portion (132) comprises the emergency circumferential stop (234).

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 same first member (138) of the emergency device (124), and in that the complementary axial stop (136) and the complementary circumferential stop (236) are formed by two surfaces of the same second member (238) of the first part (20).

7. An assembly according to claim 6 combined with claim 3, characterized in that the first member (138) is a tooth, a groove or a notch provided to project radially within the flange of the emergency device, and in that the second member (238) is a coupling imprint, or vice versa, and the first member (138) is housed in the coupling imprint (238) when the emergency device backup (124) is in its active and inactive states of axial coupling and rotational coupling.

8. Assembly according to claim 7, characterized in that the flange (133) of the emergency device (124) comprises several first members (138) projecting radially, spaced circumferentially from each other, and in that the first part (20) comprises several coupling impressions (238) each housing one of the first members (138), the first part (20) comprising a fixing flange (25) crossed by fixing members (24a) forming the main mechanical coupling device (24), the first members (138) of the emergency device (124) being arranged circumferentially alternately with the fixing members (24a) of the main device (24).

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) using a welded connection (130), preferably centered on 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. Assembly according to claim 10 combined with claim 7, characterized in that the second member (238) is the coupling imprint, and in that the complementary circumferential stop (236) corresponds to a circumferential delimitation surface of this imprint (238), and in that the complementary axial stop (136) corresponds to an axial bottom of this imprint (238).

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

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