ROTOR FOR AN AIRCRAFT TURBOMACHINE
The incorporation of stop elements on the flange and disc guides correct assembly of turbomachine rotor flanges, preventing misalignment and ensuring proper fitment without requiring reassembly.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2024-04-23
- Publication Date
- 2026-03-27
AI Technical Summary
The current assembly process for turbomachine rotors is prone to incorrect mounting of flanges due to operators working partly blind, leading to gaps and requiring disassembly for correction.
Incorporating stop elements on the flange and disc to prevent incorrect positioning by ensuring axial alignment and rotationally guided assembly, preventing screws from being mounted until the flanges are correctly aligned.
Ensures correct assembly by preventing fastening when flanges are misaligned, reducing the need for reassembly and ensuring proper fitment of rotor components.
Smart Images
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Abstract
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 operating turbomachine (see arrows in [Fig.1]), a blower or propulsion propeller 2, at least one compressor 3, 4, an annular combustion chamber 5, at least one turbine 6, 7, and a combustion gas exhaust nozzle 8.
[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-body turbojet, respectively high pressure and low pressure, the turbojet 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 includes 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 unit 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 drives the shaft of the blower or propeller 2, either directly or via a mechanical reduction gear.
[0007] The bodies and 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] Figure 2 illustrates a low-pressure turbine 7 comprising several successive stages. A turbine stage is formed by a rotor blade 10 followed by a rotor blade 11, or vice versa, the turbine 7 having four stages in the example shown.
[0010] The rotor blades 10 are fixed together and form the rotor of the turbine 7. The stator blades 11 are connected together and form a stator of the turbine which is carried by a housing 12 of the turbine.
[0011] In the present application, a rotor is considered to comprise at least one rotor blade. The terms "rotor" and "rotor blade" may therefore be used to refer to the same thing.
[0012] With reference to Figures 2 and 3, a rotor or rotor blade 10 comprises a rotor disc 14, rotor blades 16 carried by the disc 14, an annular flange 18 for axially retaining the blades 18 on the disc 14, and screws 19 for fixing the flange 18 to the disc 14 which can also be used to fix the disc 14 to another disc 20.
[0013] The disc 14 extends around the X axis and comprises axially oriented recesses 22 on its outer periphery. The disc 14 further comprises a first annular flange 24 oriented radially with respect to the X axis, here inwards.
[0014] The blades 16 each comprise a blade 16a connected to a foot 16b, for example by a platform 16c. The blades 16 have their feet 16b which are engaged in the recesses 22 of the disk 14. Each of the blades 16 comprises a hook 26 which is located axially on the side of the first flange 24 and which includes an opening 26a oriented radially inwards (figures 3 and 4).
[0015] The flange 18 extends around the axis X and includes at its inner periphery a second annular flange 28 oriented radially with respect to the axis X, here inwards, and applied axially to the first flange 24. The flange 18 includes at its outer periphery a scalloped edge 30 which includes an alternation of solid parts 30a and hollow parts 30b around the axis X ([Fig.4]).
[0016] In practice, the assembly is preferably done by orienting the X axis in a vertical direction and stacking the flange 18 on the disc 20, then the disc 14 on the flange 18.
[0017] The hollow parts 30b are configured to allow axial passage of the hooks 26 of the blades 16 through them when the flange 18 is moved axially from a first position in which it is centered on the disk 14, and in which the hollow parts 30b are aligned axially 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 radial plane to the axis X. This second position is illustrated in [Fig. 5b].
[0018] The solid parts 30a are configured to fit into the openings 26a of the hooks 26 of the blades 16 when the disk 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 serve to fix the flanges 24, 28 to each other or even to the flange 20a of the other disc 20. The screws 19 pass through the first axial holes 24c of the first flange 24 and second axial ports 28a of the second flange 28 (figures 5a). The first and second ports 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 incorrect position, in which the screws 19 can be mounted in the holes 24c, 28c of the flanges 24, 28 even though the flange 14 is not correctly positioned with respect to the disc 14. This incorrect 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 incorrect because during axial movement of the flange 18 towards the disc 14, the solid parts 30a will bear axially on the hooks 26 and prevent the flanges 24, 28 from bearing axially on each other. The orifices 24c, 28c of the flanges 24, 28 are axially aligned in this bad position so the screws 19 can be mounted and tightened in these orifices 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 gap J between the flanges 24, 28. This gap J is generally detected after assembly, which however requires disassembling the rotor and repeating the assembly process.
[0023] There is therefore a need to avoid this type of incorrect 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 disk extending around an axis and comprising at its external periphery axially oriented cells, the rotor disc further comprising a first annular flange oriented radially with respect to the axis,
[0027] - rotor blades, each comprising a blade connected to a foot, the blades having their feet which are engaged in the recesses of the disc, each of the blades comprising a hook which is located axially on the side of said first flange and which includes an opening oriented radially inwards,
[0028] - an annular flange extending around the axis and comprising 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 includes an alternation of solid and hollow parts around the axis, the hollow parts being configured to allow the axial passage of the blade hooks through them when the flange is moved axially from a first position in which it is centered on the disk, and in which the hollow parts are aligned axially with the blade hooks, to a second position in which its scalloped edge is aligned radially with the openings of the blade hooks,and the solid parts being configured to fit into the openings of the blade hooks when the flange is rotated on the disk around the axis from the second position to a third position in which the solid parts are axially aligned with the blade hooks, and ,
[0029] - screws for fixing the first and second annular flanges, these screws passing through of the first axial ports of the first flange and the second axial ports of the second flange, the first and second ports 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 against 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 aligned axially with the hooks of the blades, and the first and second stop elements being configured not to come into axial stop against 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 equipping the rotor with stop elements. These stop elements are supported respectively by the flange and the disc and are capable of cooperating by axial thrust to prevent incorrect mounting of the flange on the disc. The invention prevents an operator from being able to fasten the flanges together, or from hindering this fastening, when the flange is not correctly positioned on the disc. To this end, the scalloped edge of the flange is kept away from the blade hooks when the flange is not correctly positioned, which allows the flanges to be kept apart 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 would not be long enough to pass through both flange openings at the same time.
[0032] The correct kinematics for mounting the flange on the disc essentially comprises the three positions mentioned above:
[0033] - the first position in which the flange is centered on the disk and its parts hollows are aligned axially with the blade hooks.
[0034] - the second position in which the scalloped edge of the flange and the openings of the The blade hooks are located in the same radial plane, with the flanges applied axially to one another.
[0035] - the third position in which the solid parts are axially aligned with the blade hooks, the flange openings 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 disk, and that the transition from the second to the third position is achieved by rotational displacement of the flange on the disk around the axis. This displacement is carried out over an angle generally corresponding to half a pitch between two adjacent blades of the disk.
[0037] The aforementioned incorrect position is in fact an incorrect "first" position, meaning that, although the flange is centered on the disk, it is its solid parts (and not its hollow parts) that are axially aligned with the blade hooks. It is therefore understandable that an axial displacement of the flange towards the disk will not allow it to reach the second position but, on the contrary, an incorrect "second" position in which the solid parts of the flange are axially supported by the blade hooks. A rotational displacement of the flange relative to the disk is then necessary, from its incorrect position to its first position.
[0038] The rotor according to the invention may comprise one or more of the following features, taken individually or in combination with each other: • at least one of the first and second stop elements is in the form of a first axially oriented leg; • 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 tab oriented radially, in particular towards the inside; • 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 level of the second flange of the flange, and said at least one second stop element is located at the level of the first flange of the disc; • the second flange of the flange is scalloped and includes an alternation of solid 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 or some of these solid parts, and the first flange of the disc is scalloped and includes an alternation of solid 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 or some of these solid parts; • said at least one first stop element is formed in one piece with the flange, and said at least one second stop element is formed in one piece with the disc; • the flange includes at least two or three first stop elements regularly distributed around the axis, and the disc includes 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 secondary stop elements as solid parts in 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 first or each first stop element or the leg or each leg comprises or delimits a groove which is oriented radially outwards and which may be suitable for receiving one of the second stop elements or one of its legs;
[0042] — the first or each first stop element or the leg or each leg 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 hold 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 for 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 process may include, 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 contact, which means that the flange is in its incorrect position, and
[0051] ii) rotational displacement of the flange around the axis from its incorrect position to its first position. Brief description of the figures
[0052] Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:
[0053] [Fig-1] [Fig.1] is a schematic axial cross-sectional view of a turbomachine aircraft,
[0054] [Fig.2] [Fig.2] is a schematic axial cross-sectional view of a turbine 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 flange 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 of 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 flange 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 rotor blade hooks of [Fig.3], and illustrates the third mounting position of the flange on the disc,
[0062] [Fig.7] [Fig.7] is a schematic axial cross-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 perspective and axial section view 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 axial cross-sectional view 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 disc and the rotor flange 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 disc and the rotor flange 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 flanges of the rotor disc and flange of [Fig. 8], and illustrates the third with screws for fixing the flanges of the flange and the disc,
[0068] [Fig. 13] [Fig. 13] is a schematic perspective view of the rotor flange flange of [Fig. 8], and shows a first stop element according to 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 element according to the embodiment of the invention. Detailed description of the invention
[0070] Figures 1 to 7 have already been described 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 features of the rotor of the prior art, which are described above with reference in particular to Figures 1 to 6b. As will be described in detail below, the invention makes it possible to avoid incorrect assembly of [Fig. 7].
[0073] The elements of the invention already described above are therefore designated in what follows by the same references.
[0074] The flange 18 of the rotor according to the invention comprises at least a first stop element 40 adapted to cooperate by axial stop with at least a second stop element 50 of the disc 14 (figures 8 and 9).
[0075] The first and second stop elements 40, 50 are configured to come into axial contact with 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 disk 14, and its solid parts 30a are aligned axially with the hooks 26 of the blades 16 ([Fig.9]).
[0076] As can be 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 separating the flanges 24, 28 when the stop elements 40, 50 cooperate by means of a 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 so as not to come into axial contact with 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 that carries this tab 42 ([Fig. 13]).
[0079] The first leg 42 has for example a general L or U shape and includes a free end 42a forming a stop and therefore intended to come into contact with the disc 14 and in particular with its second stop element 50.
[0080] The leg 42 may include or delimit a groove 42b which is oriented radially outwards and which may be suitable for 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 leg 42 may include 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 tab 52. In the example shown, it is the disc 14 which carries this tab 52 ([Fig. 14]).
[0083] The second leg 52, for example, has 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 can be located at the level of the second flange 28 of the flange 18, and said at least one second stop element 50 can be located at the level of the first flange 24 of the disc 14.
[0085] Preferably, the second flange 28 of the flange 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 or some of these solid parts 28a.
[0086] Preferably, the first flange 24 of the disc 14 is scalloped and comprises alternating solid portions 24a and hollow portions 24b around the X axis. The first orifices 24c are formed in the solid portions 24a and the second one or more stop elements is / are connected to one or some of these solid parts 24a.
[0087] Advantageously, the first stop element or each first stop element 40 is formed in one piece with the flange 18, and the second stop element or each second stop element 50 is formed in one piece with the disc 14.
[0088] For example, the flange 18 may include at least two or three first stop elements 40 regularly distributed around the X axis.
[0089] The disc 18 can include at least two or three second stop elements 50 regularly distributed around the X axis and capable of cooperating by axial stop respectively with the first two or three stop elements 40.
[0090] However, it is preferable for the disc 14 to include as many stop elements 50, and in particular tabs 52, as solid parts 24a, as illustrated in Figures 8 and 10-12. This allows for cooperation between the stop elements 40 and stop elements 50 regardless of the incorrect position of the flange 18 relative to the disc 14. Since 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 operators are required 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 misaligned on the disc 14 when the flange 18 rests on the disc 14 via the stop elements 40, 50.
[0092] The present invention also relates to a method for mounting the rotor described 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 displacement 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 event that 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 contact, which means that the flange is in its wrong position (figures 8 and 9),
[0099] ii) rotational displacement of the flange 18 around the X axis from its incorrect position to its first position.
Claims
1. Demands Rotor for an aircraft turbomachine, this rotor comprising: - a rotor disk (14) extending around an axis (X) and comprising at its outer periphery axially oriented cavities (22), the rotor disk (14) further comprising a first annular flange (24) oriented radially with respect to the axis (X), - rotor blades (16) each comprising a blade (16a) connected to a foot (16b), the blades (16) having their feet (16b) which are engaged in the cavities (22) of the disk (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) extending around the axis (X) and comprising at its inner 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 outer periphery a scalloped edge (30) comprising 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) through them when the flange (18) is moved axially from a first position in which it is centered on the disk (14), and in which the hollow parts (30b) are aligned axially 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 fit into the openings (26a) of the hooks (26) of the blades (16) when the flange (18) is rotated on the disk (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 the first axial holes (24c) of the first flange (24) and the second axial holes (26a) of the second flange (26), the first and second holes (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) adapted to cooperate by axial abutment with at least one second stop element (50) of the disk (14), the first and second stop elements (40, 50) being configured to axially abut 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 an incorrect position in which it is centered on the disk (14), and its solid portions (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 axially abut 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. Rotor according to claim 1, wherein at least one of the first and second stop elements (40, 50) is in the form of a first axially oriented leg (42).
3. Rotor according to claim 2, wherein the first leg (42) has a general L or U shape and includes 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 tab (52) oriented radially, in particular inwards.
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 any one of the preceding claims, wherein said at least one first stop element (40) is located at the level of the second flange (28) of the flange (18), and said at least one second stop element (50) is located at the level of the first flange (24) of the disc (14).
7. Rotor according to any one of the preceding claims, wherein the second flange (28) of the flange (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 thrust element (40) being connected to one or 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 or some of these solid parts (24a).
8. Rotor according to any one of the preceding claims, wherein said at least one first thrust element (40) is formed in one piece with the flange (18), and said at least one second thrust element (50) is formed in one piece with the disc (14).
9. Rotor according to any one of the preceding claims, wherein the flange (18) comprises at least two or three first thrust elements (40) regularly distributed around the axis (X), and the disc (14) comprises at least two or three second thrust elements (50) regularly distributed around the axis (X) and capable of cooperating by axial thrust respectively with said at least two or three first thrust elements (40).
10. Aircraft turbomachine (1), comprising at least one rotor according to one of the preceding claims.
11. Method of mounting a rotor according to any one of claims 1 to 9, comprising the following steps: a) axial alignment of the disc (14) on the flange (18), b) axial displacement of the flange (18) from its first position to its second position, c) rotational displacement of the flange (18) from its second position to its third position, d) fixing of 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) axial displacement of the flange (18) towards the disk (14) until the first and second stop elements (40, 50) come into axial contact, which means that the flange (18) is in its wrong position, and ii) rotational displacement of the flange (18) around the axis (X) from its wrong position to its first position.