ROTOR FOR AN AIRCRAFT TURBOMACHINE

Abstract

Rotor for an aircraft turbomachine, this rotor comprising: - a rotor disk (14) comprising a first annular flange (24), - rotor blades (16) carried by the disk and each comprising a hook (26), - an annular flange (18) which comprises a second annular flange (28) and a scalloped edge (30) intended to cooperate with the hooks of the blades, and - screws (19) for fixing the first and second annular flanges (24, 28), characterized in that the flange (18) comprises at least one first stop element (40) capable of cooperating by axial stop with at least one second stop element (50) of the disk (14) when the flange and the disk are in an incorrect mounting position. Figure for the abstract: Figure 8

Description

Title of the invention: ROTOR FOR AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The present invention relates in particular to a rotor for an aircraft turbomachine, as well as a method of mounting this rotor. Technical background

[0002] An aircraft turbomachine 1 typically comprises from upstream to downstream, with reference to the flow of gases in the turbomachine in operation (see arrows in [Fig.l]), a fan or propulsion propeller 2, at least one compressor 3, 4, an annular combustion chamber 5, at least one turbine 6, 7, and a nozzle 8 for exhausting the combustion gases.

[0003] The turbine rotor is connected by a shaft to a compressor rotor to form a rotating body.

[0004] In the case of a twin-spool turbojet engine, respectively high pressure and low pressure, the turbojet engine comprises from upstream to downstream a low pressure compressor 3, a high pressure compressor 4, the combustion chamber 5, a high pressure turbine 6 and a low pressure turbine 7.

[0005] The high pressure body comprises the rotors of the high pressure compressor 4 and the high pressure turbine 6, and the high pressure shaft connecting these rotors.

[0006] The low pressure body comprises the rotors of the low pressure compressor 3 and the low pressure turbine 7, and the low pressure shaft connecting these rotors. The low pressure shaft rotates the shaft of the fan or propeller 2, either directly or via a mechanical reducer.

[0007] The bodies and the rotors rotate around the same axis which is generally the longitudinal axis X of the turbomachine 1.

[0008] A rotor generally comprises several annular parts which extend around the same axis and which are fixed to each other by clamping.

[0009] [Fig. 2] illustrates a low-pressure turbine 7 which comprises several successive stages. A turbine stage is formed by a rotor blade 10 followed by a rotor blade 11, or conversely, the turbine 7 comprising four stages in the example shown.

[0010] The rotor blades 10 are integral with each other and form the rotor of the turbine 7. The stator blades 11 are connected to each other and form a stator of the turbine which is carried by a casing 12 of the turbine.

[0011] In the present application, it is considered that a rotor comprises at least one rotor blade. The expressions "rotor" and "rotor blade" can therefore be used to designate the same thing.

[0012] With reference to Figures 2 and 3, a rotor or rotor blade 10 comprises a rotor disk 14, rotor blades 16 carried by the disk 14, an annular flange 18 for axially retaining the blades 18 on the disk 14, and screws 19 for fixing the flange 18 to the disk 14 which can also be used to fix the disk 14 to another disk 20.

[0013] The disc 14 extends around the axis X and comprises at its external periphery axially oriented cells 22. The disc 14 further comprises a first annular flange 24 oriented radially relative to the axis X, here inwards.

[0014] The blades 16 each comprise a blade 16a connected to a root 16b, for example by a platform 16c. The blades 16 have their roots 16b which are engaged in the cells 22 of the disc 14. Each of the blades 16 comprises a hook 26 which is located axially on the side of the first flange 24 and which comprises an opening 26a oriented radially inwards (figures 3 and 4).

[0015] The flange 18 extends around the axis X and comprises at its internal periphery a second annular flange 28 oriented radially relative to the axis X, here inwards, and applied axially to the first flange 24. The flange 18 comprises at its external periphery a scalloped edge 30 which comprises an alternation of solid parts 30a and hollow parts 30b around the axis X ([Fig.4]).

[0016] In practice, the assembly is preferably carried out by orienting the X axis in a vertical direction and by stacking the flange 18 on the disc 20, then the disc 14 on the flange 18.

[0017] The hollow portions 30b are configured to allow axial passage of the hooks 26 of the blades 16 therethrough when the flange 18 is moved axially from a first position in which it is centered on the disc 14, and in which the hollow portions 30b are axially aligned with the hooks 26 of the blades 16, to a second position in which its scalloped edge 30 and the openings 26a of the hooks 26 of the blades 16 are located in the same plane radial to the axis X. This second position is illustrated in [Fig.5b].

[0018] The solid parts 30a are configured to be housed in the openings 26a of the hooks 26 of the blades 16 when the disc 14 is moved in rotation on the flange 18 around the axis X, from the second position to a third position in which the solid parts 30a are axially aligned with the hooks 26 of the blades 16. This third position is illustrated in Figures 3, 4 and 6b.

[0019] The screws 19 have the function of fixing the flanges 24, 28 to each other or even to the flange 20a of the other disc 20. The screws 19 pass through first axial orifices 24c of the first flange 24 and second axial holes 28a of the second flange 28 (figures 5a). The first and second holes 24c, 28c are axially aligned to receive the screws 19 when the flange 18 is in the third position ([Fig.6a]) and are not axially aligned when the flange 18 is in the second position ([Fig.5a]).

[0020] It is therefore understood that the screws 19 can be mounted in the orifices 24c, 28c of the flanges 24, 28 when the flange 14 is in its third position on the disc 14.

[0021] In the current technique, there is a position, called the bad position, in which the screws 19 can be mounted in the orifices 24c, 28c of the flanges 24, 28 despite the fact that the flange 14 is not correctly positioned with respect to the disc 14. This bad position is illustrated in [Fig.7] and corresponds to the case where the flange 18 is centered on the disc 14 and its solid parts 30a are axially aligned with the hooks 26 of the blades 16. This position is a bad position because during the axial movement of the flange 18 towards the disc 14, the solid parts 30a will come into axial support on the hooks 26 and prevent the flanges 24, 28 from coming into axial support on each other. The holes 24c, 28c of the flanges 24, 28 are axially aligned in this wrong position so the screws 19 can be mounted and tightened in these holes 14a, 28a.

[0022] This assembly process is carried out by an operator who works partly blind. It can therefore be difficult to detect incorrect assembly of the flange 18 and in particular the presence of a clearance J between the flanges 24, 28. This clearance J is generally detected after assembly, which however requires the rotor to be dismantled and the assembly process to be repeated.

[0023] There is therefore a need to avoid this type of poor mounting of the flange on the disc in a turbomachine rotor.

[0024] The present invention provides a simple, effective and economical solution to this need. Summary of the invention

[0025] The invention relates to a rotor for an aircraft turbomachine, this rotor comprising:

[0026] - a rotor disc extending around an axis and comprising at its outer periphery axially oriented cells, the rotor disk further comprising a first annular flange oriented radially relative to the axis,

[0027] - rotor blades which each comprise a blade connected to a root, the blades having their feet which are engaged in the cells of the disc, each of the blades comprising a hook which is located axially on the side of said first flange and which comprises an opening oriented radially inwards,

[0028] - an annular flange which extends around the axis and which comprises at its periphery internally a second annular flange oriented radially with respect to the axis and applied axially to the first annular flange, the flange comprising at its external periphery a scalloped edge which comprises an alternation of solid parts and hollow parts around the axis, the hollow parts being configured to allow the axial passage of the hooks of the blades through them when the flange is moved axially from a first position in which it is centered on the disc, and in which the hollow parts are axially aligned with the hooks of the blades, to a second position in which its scalloped edge is radially aligned with the openings of the hooks of the blades,and the solid portions being configured to fit into the openings of the hooks of the blades when the flange is rotated on the disc about the axis from the second position to a third position in which the solid portions are axially aligned with the hooks of the blades, and,

[0029] - screws for fixing the first and second annular flanges, these screws passing through first axial orifices of the first flange and second axial orifices of the second flange, the first and second orifices being axially aligned when the flange is in the third position,

[0030] characterized in that the flange comprises at least one first stop element capable of cooperating by axial stop with at least one second stop element of the disc, the first and second stop elements being configured to come into axial stop on each other and to prevent axial contact between the scalloped edge of the flange and the hooks of the blades when the flange is in a bad position in which it is centered on the disc, and its solid parts are axially aligned with the hooks of the blades, and the first and second stop elements being configured not to come into axial stop on each other and thus to allow axial movement of the flange from its first position to its second position when the flange is in its first position.

[0031] The invention thus proposes to equip the rotor with stop elements. These stop elements are carried respectively by the flange and the disc and are capable of cooperating together by axial stop to prevent incorrect mounting of the flange on the disc. The invention makes it possible to prevent an operator from being able to fix the flanges together, or to hinder this fixing, when the flange is not correctly positioned on the disc. For this, the scalloped edge of the flange is kept at a distance from the hooks of the blades when the flange is not correctly positioned, which allows the flanges to be kept at a distance from each other. This distance between the flanges must be sufficient to prevent the screws from being mounted in the flanges of the flange and of the disc, or to hinder this assembly for example in the case where the screws are not long enough to pass through the holes of the two flanges at the same time.

[0032] The correct kinematics for mounting the flange on the disc essentially includes the three aforementioned positions:

[0033] - the first position in which the flange is centered on the disc and its parts hollow are axially aligned with the hooks of the blades,

[0034] - the second position in which the scalloped edge of the flange and the openings of the hooks of the blades are located in the same radial plane, the flanges being applied axially one on the other,

[0035] - the third position in which the solid parts are axially aligned with the hooks of the blades, the holes of the flanges being axially aligned.

[0036] It is understood that the transition from the first to the second position is achieved by axial displacement of the flange towards the disc, and that the transition from the second to the third position is achieved by rotational displacement of the flange on the disc around the axis. This displacement is achieved over an angle generally corresponding to half a pitch between two adjacent blades of the disc.

[0037] The aforementioned bad position is in fact a bad “first” position, that is to say that, although the flange is centered on the disk, it is its solid parts (and not its hollow parts) which are axially aligned with the hooks of the blades. It is therefore understood that an axial displacement of the flange towards the disk will not make it possible to reach the second position but on the contrary a bad “second” position in which the solid parts of the flange are in axial support on the hooks of the blades. A rotational displacement of the flange with respect to the disk is then necessary, from its bad position to its first position.

[0038] The rotor according to the invention may comprise one or more of the following characteristics, taken in isolation from one another, or in combination with one another: • at least one of the first and second stop elements is in the form of a first axially oriented tab; • the first leg has a general L or U shape and includes a free end forming a stop; • the other of the first and second stop elements is in the form of a radially oriented tab, in particular inwards; • the second leg has a flat shape and extends in a plane perpendicular to the axis; • said at least one first stop element is located at the second flange of the flange, and said at least one second stop element is located at the first flange of the disc; • the second flange of the flange is scalloped and comprises an alternation of solid parts and hollow parts around the axis, the second orifices being formed in the solid parts and said at least one first stop element being connected to one of these solid parts or to some of these solid parts, and the first flange of the disc is scalloped and comprises an alternation of solid parts and hollow parts around the axis, the first orifices being formed in the solid parts and said at least one second stop element being connected to one of these solid parts or to some of these solid parts; • said at least one first stop element is formed in a single piece with the flange, and said at least one second stop element is formed in a single piece with the disc; • the flange comprises at least two or three first stop elements regularly distributed around the axis, and the disc comprises at least two or three second stop elements regularly distributed around the axis and capable of cooperating by axial stop respectively with said at least two or three first stop elements;

[0039] — the disc comprises as many second stop elements as there are solid parts at the level of its scalloped bridle;

[0040] — the number of solid parts of the scalloped edge of the flange is equal to the number of solid parts of its scalloped bridle;

[0041] — the or each first stop element or the or each tab comprises or delimits a groove which is oriented radially outwards and which may be adapted to receive one of the second stop elements or one of its legs;

[0042] — the or each first stop element or the or each tab comprises or forms a hook at its free end intended to cooperate with one of the second stop elements or one of its legs in order to retain it in the groove for example.

[0043] The present invention also relates to an aircraft turbomachine comprising at least one rotor as described above.

[0044] The present invention also relates to a method of mounting a rotor as described above, comprising the following steps:

[0045] a) axial alignment of the disc on the flange,

[0046] b) axial displacement of the flange from its first position to its second position,

[0047] c) rotational movement of the flange from its second position to its third position,

[0048] d) fixing the first and second flanges by the screws.

[0049] The method may comprise, between steps a) and b), the following steps:

[0050] i) axial displacement of the flange towards the disc until the first and second stop elements come into axial abutment, which means that the flange is in its wrong position, and

[0051] ii) rotational movement of the flange around the axis from its incorrect position to its first position. Brief description of the figures

[0052] Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the appended drawings in which:

[0053] [Fig-1] [Fig.l] is a schematic axial sectional view of a turbomachine aircraft,

[0054] [Fig.2] [Fig.2] is a schematic axial sectional view of a turbine of aircraft turbomachine,

[0055] [Fig.3] [Fig.3] is a schematic perspective view of a turbine rotor,

[0056] [Fig.4] [Fig.4] is a larger scale detail view of part of [Fig.3], and illustrates a rotor flange in a third mounting position on a rotor disc,

[0057] [Fig.4] [Fig.4] is a larger scale detail view of part of [Fig.3],

[0058] [Fig.5a] [Fig.5a] is a schematic perspective view of the flanges of the plate and of the rotor disc of [Fig.3], and illustrates a second mounting position of the flange on the disc,

[0059] [Fig.5b] [Fig.5b] is a schematic perspective view of a scalloped edge and rotor blade hooks of [Fig.3], and illustrates the second mounting position of the flange on the disc,

[0060] [Fig.6a] [Fig.6a] is a schematic perspective view of the flanges of the plate and of the rotor disc of [Fig.3], and illustrates the third mounting position of the flange on the disc,

[0061] [Fig.6b] [Fig.6b] is a schematic perspective view of the scalloped edge and the hooks of the rotor blades of [Fig.3], and illustrates the third mounting position of the flange on the disc,

[0062] [Fig.7] [Fig.7] is a schematic axial sectional view of the rotor of [Fig.3], and illustrates an incorrect mounting position of the flange on the disc,

[0063] [Fig.8] [Fig.8] is a partial schematic view in perspective and in axial section of a rotor according to an embodiment of the invention, and illustrates an incorrect mounting position of the flange on the disc,

[0064] [Fig.9] [Fig.9] is a partial schematic view in axial section of the rotor of the [Fig.8], and illustrates the incorrect mounting position,

[0065] [Fig. 10] [Fig. 10] is a schematic perspective view of the flanges of the rotor flange and disc of [Fig.8], and illustrates the second mounting position of the flange on the disc,

[0066] [Fig. 11] [Fig. 11] is a schematic perspective view of the flanges of the rotor flange and disc of [Fig.8], and illustrates the third mounting position of the flange on the disc,

[0067] [Fig. 12] [Fig. 12] is a schematic perspective view of the rotor flange and disc flanges of [Fig.8], and illustrates the third with screws for fixing the flange and disc flanges,

[0068] [Fig. 13] [Fig. 13] is a schematic perspective view of the rotor endshield flange of [Fig.8], and shows a first stop element in accordance with the embodiment of the invention, and

[0069] [Fig. 14] [Fig. 14] is a schematic perspective view of the rotor disc flange of [Fig.8], and shows a second stop member in accordance with the embodiment of the invention. Detailed description of the invention

[0070] Figures 1 to 7 have already been described in the above.

[0071] A preferred but non-limiting embodiment of the invention is illustrated in Figures 8 to 14. These figures essentially illustrate the differences between a rotor according to the invention and a rotor of the prior art.

[0072] The rotor according to the invention comprises all the characteristics of the rotor of the prior art, which are described in the above with reference to Figures 1 to 6b in particular. As will be described in detail in the following, the invention makes it possible to avoid incorrect assembly of the [Fig.7].

[0073] The elements of the invention already described in the above are therefore designated in the following by the same references.

[0074] The flange 18 of the rotor according to the invention comprises at least one first stop element 40 capable of cooperating by axial stop with at least one second stop element 50 of the disc 14 (figures 8 and 9).

[0075] The first and second abutment elements 40, 50 are configured to axially abut one another and to prevent axial contact between the scalloped edge 30 of the flange 18 and the hooks 26 of the blades 16 when the flange 18 is in an incorrect position in which it is centered on the disc 14, and its solid portions 30a are axially aligned with the hooks 26 of the blades 16 ([Fig.9]).

[0076] As seen in [Fig.9], this contact allows the scalloped edge 30 of the flange 18 to remain at an axial distance from the hooks 26 of the blades 16. This axial distance depends in particular on the axial dimension of the first stop elements 40, and in particular of the distance D which separates the flanges 24, 28 when the stop elements 40, 50 cooperate together by stop. Advantageously, this distance D is such that it is not possible to tighten the screws 19 and in particular to screw a nut onto these screws 19.

[0077] The first and second stop elements 40, 50 are further configured not to come into axial abutment on each other and thus to allow axial movement of the flange 18 from its first position ([Fig. 10]) to its second position (Figures 11 and 12) when the flange is in its first position.

[0078] Preferably, at least one of the stop elements 40, 50 is in the form of a first axially oriented tab 42. In the example shown, it is the flange 18 which carries this tab 42 ([Fig. 13]).

[0079] The first leg 42 has, for example, a general L or U shape and comprises a free end 42a forming a stop and therefore intended to come into contact with the disc 14 and in particular its second stop element 50.

[0080] The tab 42 may comprise or delimit a groove 42b which is oriented radially outwards and which may be capable of receiving one of the second stop elements 50. This groove 42b has an axial dimension greater than an axial thickness of the stop element 50, as illustrated in particular in [Fig. 12].

[0081] The tab 42 may comprise or form a hook 42c at its free end intended to cooperate with one of the second stop elements 50 in order to retain it in the groove 42b for example.

[0082] Preferably, the other of the stop elements 40, 50 is in the form of a radially oriented lug 52. In the example shown, it is the disc 14 which carries this lug 52 ([Fig. 14]).

[0083] The second leg 52 has for example a planar shape and extends in a radial plane, that is to say perpendicular to the X axis.

[0084] As in the example shown, said at least one first stop element 40 may be located at the level of the second flange 28 of the end plate 18, and said at least one second stop element 50 may be located at the level of the first flange 24 of the disc 14.

[0085] Preferably, the second flange 28 of the plate 18 is scalloped and comprises an alternation of solid parts 28a and hollow parts 28b around the axis X. The second orifices 28c are formed in the solid parts 28a and the first stop element(s) 40 is / are connected to one of these solid parts 28a or to some of these solid parts 28a.

[0086] Preferably, the first flange 24 of the disc 14 is scalloped and comprises an alternation of solid parts 24a and hollow parts 24b around the axis X. The first orifices 24c are formed in the solid parts 24a and the second stop elements is / are connected to one of these solid parts 24a or to some of these solid parts 24a.

[0087] Advantageously, the or each first stop element 40 is formed in a single piece with the flange 18, and the or each second stop element 50 is formed in a single piece with the disc 14.

[0088] For example, the flange 18 may comprise at least two or three first stop elements 40 regularly distributed around the axis X.

[0089] The disc 18 may comprise at least two or three second stop elements 50 regularly distributed around the axis X and capable of cooperating by axial stop respectively with the two or three first stop elements 40.

[0090] It is however preferable for the disc 14 to comprise as many stop elements 50 and in particular tabs 52 as there are solid parts 24a, as is illustrated in particular in FIGS. 8 and 10-12. This makes it possible to have cooperation of the stop elements 40 with stop elements 50 regardless of the incorrect position of the flange 18 with respect to the disc 14. Insofar as such an incorrect position corresponds to an axial alignment of the solid parts 30a with the hooks 26, there are as many incorrect positions of the flange 18 as there are solid parts 30a or hooks 26. Thus, even if the operators are asked to align the discs / flanges with each other, it will not be possible to mount them incorrectly.

[0091] This limits the risk of the flange 18 being skewed on the disc 14 when the flange 18 bears on the disc 14 via the stop elements 40, 50.

[0092] The present invention also relates to a method of mounting the rotor described in the above. The method essentially comprises the following four steps:

[0093] a) axial alignment of the disc 14 on the flange 18,

[0094] b) axial displacement of the flange 18 from its first position to its second position ([Fig. 10]),

[0095] c) rotational movement of the flange 18 from its second position to its third position ([Fig.11]), and

[0096] d) fixing the first and second flanges by the screws ([Fig. 12]).

[0097] In the case where the flange 18 adopts an incorrect position, between steps a) and b), the The process includes the following steps:

[0098] i) axial displacement of the flange 18 towards the disc 14 until the first and second stop elements 40, 50 come into axial abutment, which means that the flange is in its wrong position (figures 8 and 9),

[0099] ii) rotational movement of the flange 18 around the X axis from its incorrect position to its first position.

Claims

1. Claims Rotor for an aircraft turbomachine, this rotor comprising: - a rotor disc (14) extending around an axis (X) and comprising at its outer periphery axially oriented cells (22), the rotor disc (14) further comprising a first annular flange (24) oriented radially relative to the axis (X), - rotor blades (16) which each comprise a blade (16a) connected to a root (16b), the blades (16) having their roots (16b) which are engaged in the cells (22) of the disc (14), each of the blades (16) comprising a hook (26) which is located axially on the side of said first flange (24) and which comprises an opening (26a) oriented radially inwards, - an annular flange (18) which extends around the axis (X) and which comprises at its internal periphery a second annular flange (28) oriented radially with respect to the axis (X) and applied axially to the first annular flange (24), the flange (18) comprising at its external periphery a scalloped edge (30) which comprises an alternation of solid parts (30a) and hollow parts (30b) around the axis (X), the hollow parts (30b) being configured to allow the axial passage of the hooks (26) of the blades (16) therethrough when the flange (18) is moved axially from a first position in which it is centered on the disc (14), and in which the hollow parts (30b) are axially aligned with the hooks (26) of the blades (16), to a second position in which its scalloped edge (30) and the openings (26a) hooks (26) of the blades (16) are located in the same radial plane,and the solid parts (30a) being configured to be housed in the openings (26a) of the hooks (26) of the blades (16) when the flange (18) is moved in rotation on the disc (14) around the axis (X) from the second position to a third position in which the solid parts (30a) are axially aligned with the hooks (26a) of the blades (26), and - screws (19) for fixing the first and second annular flanges (24, 28), these screws (19) passing through first axial orifices (24c) of the first flange (24) and second axial orifices (26a) of the second flange (26), the first and second orifices (24c, 28c) being axially aligned when the flange (18) is in the third position, characterized in that the flange (18) comprises at least one first stop element (40) capable of cooperating by axial stop with at least one second stop element (50) of the disc (14), the first and second stop elements (40, 50) being configured to come into axial stop on each other and to prevent axial contact between the scalloped edge (30) of the flange (18) and the hooks (26) of the blades (16) when the flange (18) is in a bad position in which it is centered on the disc (14), and its solid parts (30a) are axially aligned with the hooks (26) of the blades (16), and the first and second stop elements (40, 50) being configured not to come into axial stop on each other and thus to allow axial movement of the flange (18) from its first position to its second position when the flange (18) is in its first position.

2. A rotor according to claim 1, wherein at least one of the first and second stop members (40, 50) is in the form of a first axially oriented tab (42).

3. Rotor according to claim 2, in which the first leg (42) has a general L or U shape and comprises a free end (2a) forming a stop.

4. Rotor according to claim 2 or 3, wherein the other of the first and second stop elements (40, 50) is in the form of a radially oriented, in particular inwardly oriented, tab (52).

5. Rotor according to claim 4, wherein the second leg (52) has a planar shape and extends in a plane perpendicular to the axis (X).

6. Rotor according to one of the preceding claims, wherein said at least one first stop element (40) is located at the second flange (28) of the end plate (18), and said at least one second stop element (50) is located at the first flange (24) of the disc (14).

7. Rotor according to one of the preceding claims, in which the second flange (28) of the end plate (18) is scalloped and comprises an alternation of solid parts (28a) and hollow parts (28b) around the axis (X), the second orifices (28c) being formed in the solid parts (28a) and said at least one first stop element (40) being connected to one of these solid parts (28a) or to some of these solid parts (28a), and the first flange (24) of the disc (14) is scalloped and comprises an alternation of solid parts (24a) and hollow parts (24b) around the axis (X), the first orifices (24c) being formed in the solid parts (24a) and said at least one second stop element (50) being connected to one of these solid parts (24a) or to some of these solid parts (24a).

8. Rotor according to one of the preceding claims, wherein said at least one first stop element (40) is formed in one piece with the flange (18), and said at least one second stop element (50) is formed in one piece with the disc (14).

9. Rotor according to one of the preceding claims, in which the flange (18) comprises at least two or three first stop elements (40) regularly distributed around the axis (X), and the disc (14) comprises at least two or three second stop elements (50) regularly distributed around the axis (X) and capable of cooperating by axial stop respectively with said at least two or three first stop elements (40).

10. Aircraft turbomachine (1), comprising at least one rotor according to one of the preceding claims.

11. Method for mounting a rotor according to one of claims 1 to 9, comprising the following steps: a) axial alignment of the disc (14) on the flange (18), b) axial movement of the flange (18) from its first position to its second position, c) rotational movement of the flange (18) from its second position to its third position, d) fixing the first and second flanges (24, 28) by the screws (19).

12. A method according to claim 11, wherein it comprises, between steps a) and b), the following steps: i) axially moving the flange (18) towards the disc (14) until the first and second stop elements (40, 50) come into axial abutment, which means that the flange (18) is in its wrong position, and ii) rotating the flange (18) around the axis (X) from its wrong position to its first position.

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