MODULE FOR AN AIRCRAFT TURBOMACHINE

Abstract

Module (30) for an aircraft turbomachine (10), this module (30) comprising: - a first annular bearing support (32), - a second annular bearing support (34), one of the first and second bearing supports (32, 34) having teeth (90) projecting axially towards the other of the first and second bearing supports (34, 32), these teeth (90) being arranged around the axis (A) and surrounded by the flange (32a, 34a) of this bearing support (32, 34), and said other of the first and second bearing supports (34, 32) having axial openings (92) which are arranged around the axis (A) and surrounded by the flange (34a, 32a) of this bearing support (34, 32). Figure for the abbreviation: Figure 11

Description

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

[0001] The present invention relates to a module for an aircraft turbomachine, as well as a turbomachine comprising such a module. Technical background

[0002] The prior art includes in particular document EP-B1-2 721 260.

[0003] An aircraft turbomachine includes a gas generator which conventionally comprises, from upstream to downstream, with reference to the flow of gases in the turbomachine, at least one compressor, an annular combustion chamber and at least one turbine.

[0004] In the case of a twin-spool turbofan engine, with low-pressure and high-pressure components respectively, the gas generator comprises successively a low-pressure compressor, a high-pressure compressor, the combustion chamber, a high-pressure turbine, and a low-pressure turbine. The gas generator defines a first annular flow path of gas, called the primary flow, which passes through the compressors, the combustion chamber, and the turbines.

[0005] The rotor of the high-pressure compressor is connected to the rotor of the high-pressure turbine by a high-pressure shaft. The rotor of the low-pressure compressor is connected to the rotor of the low-pressure turbine by a low-pressure shaft which passes through the high-pressure shaft and drives a shaft of a propulsion propeller generally located upstream of the gas generator.

[0006] When this propeller is enclosed and therefore surrounded by an annular casing, this propeller is called a blower and generates an airflow, called a secondary flow, which flows around the gas generator.

[0007] The propeller shaft and the low-pressure shaft are guided by bearings housed in a lubrication enclosure. This enclosure is surrounded by the first channel and is at least partially delimited by bearing supports. A first rolling bearing located upstream is supported by a first bearing support, and a second rolling bearing located downstream is supported by a second bearing support. These bearing supports have annular flanges that are radially oriented and axially applied to each other and to an annular flange of a stator housing.

[0008] The lubrication chamber is designed to lubricate the bearings and maintain an oily atmosphere around them. The oil is supplied to the chamber via a supply circuit.

[0009] The propeller includes blades that are susceptible to breakage, although this phenomenon is extremely rare. In such a case, a significant imbalance appears on the propeller shaft, generating cyclic loads and vibrations that the upstream bearing transmits to the stator, with a considerable risk of damage.

[0010] To limit the forces transmitted to the stator in the presence of a large imbalance, a shear screw decoupling device is known from document FR-A1-2 831 624. In practice, the second bearing support is fixed to the stator housing by non-shear screws, and the first bearing support is fixed to the second bearing support by shear screws to form a connection that can be broken. These so-called "fuse" screws, whose operation is fully described in the aforementioned document, have a reduced cross-section portion that is likely to break beyond a predetermined mechanical tensile force and thus achieve the decoupling of the bearing supports. In this situation of breakage of the fusible screws, the first bearing support is no longer held axially or circumferentially around the axis of the bearing supports. The first support moves axially upstream and therefore axially away from the second bearing support. This is especially true when the bearing carried by the first support is a roller bearing, which does not provide axial support to the bearing support when it is disconnected from the second support. The first support can also rotate relative to the second bearing support.

[0011] This phenomenon is problematic because the housing continues to be supplied with oil by the aforementioned circuit, and the oil that accumulates in the housing is likely to pass through the annular passage formed between the bearing support flanges, which have moved axially apart. The oil then spills into the engine, generating contamination. This oil can reach the first air intake from which air is drawn to supply air to the aircraft equipped with the turbomachine. There is therefore a risk that the aircraft will be supplied with polluted air, or even with unpleasant fumes and odors.

[0012] The invention relates to a technical solution aimed at reducing all or part of this phenomenon and problem, in particular with a view to eliminating the risk of oil leakage into the primary channel after decoupling of the bearing supports from the lubrication chamber. Summary of the invention

[0013] The invention relates to a module for an aircraft turbomachine, this module comprising:

[0014] - a first annular bearing support which extends around an axis and which comprises a first annular fixing flange,

[0015] - a second annular bearing support which extends around the axis and which comprises a second annular fixing flange, the first and second flanges being suitable for being applied axially against each other and for being fixed together by shear screws,

[0016] - an annular housing that extends around the axis, the second bearing support being fixed to the crankcase,

[0017] - a lubrication chamber which is at least partly delimited by the first bearing support, this lubrication enclosure containing a first bearing supported by the first bearing support and a second bearing supported by the second bearing support, and

[0018] one of the first and second bearing supports having teeth projecting axially towards the other of the first and second bearing supports, these teeth being arranged around the axis and surrounded by the flange of this bearing support, and

[0019] said other of the first and second bearing supports having axial openings which are arranged around the axis and surrounded by the flange of this bearing support,

[0020] the teeth being axially engaged in at least a part of the openings when the flanges are fixed together and being able to cooperate by circumferential stop with edges of the openings in case of breakage of the fusible screws and axial separation of the flanges from each other.

[0021] In normal operation, the shear screws ensure the axial retention of the first bearing support relative to the second bearing support. If the shear screws break, the bearing supports separate and move axially apart. The teeth are then able to cooperate with the edges of the openings to prevent or limit the rotation of the bearing supports relative to each other around the axis.

[0022] The module according to the invention may comprise one or more of the following features, taken individually or in combination with each other: • The module further includes an annular sealing skirt extending around the first and second flanges. This skirt comprises a first axial end sealed to the first bearing support and a second axial end sealed to the second bearing support. The skirt is made of a deformable material and is designed to provide a seal around the flanges, particularly between the first and second bearing supports, especially in the event of shear bolt failure. Although the skirt provides a seal around the flanges, this sealing is not necessarily required at this stage, as the flanges may be equipped with their own sealing system. In such cases, the skirt provides a seal around the flanges and is deformable to absorb relative movement between the supports. bearing; therefore there is no risk of oil leaking into the engine's oil passage because the oil remains contained by the skirt; • the skirt is made of elastically deformable material; • the skirt is made of elastomer; • the teeth are regularly distributed around the axis and / or the openings are regularly distributed around the axis; • the number of teeth is less than the number of openings; • the number of teeth is between 2 and 10, and preferably between 3 and 8; • The number of openings is between 5 and 40, and preferably between 10 and 30; • each of the teeth has a general L-shape and includes a body oriented parallel to the axis and connected to an internal periphery of the flange by a rim which is perpendicular to the body or inclined with respect to this body; • the teeth are separated from an internal periphery of the flange by an annular groove oriented axially towards the other side of the bearing supports; • the flanges are supported in a plane perpendicular to the axis, and in which the teeth cross axially this plane and / or said groove has its bottom which is axially recessed with respect to this plane; • the other of the bearing supports includes a cylindrical rim which is located radially between the flange and the openings and which is configured to be engaged axially in said groove; • said rim carries an annular sealing gasket suitable for cooperating with the bearing support which includes the teeth; • the teeth are engaged with radial clearances, respectively internal and external, in the openings; • the teeth are located on the first bearing support, and the openings are located on the second bearing support; • each of the teeth has an angular range around the axis, between 10 and 20°; • each of the openings has an angular extent (|3) around the axis, between 11 and 22°;

[0023] — the first end of the skirt is fixed to an annular rib of the first bearing support, this rib extending radially outwards;

[0024] — the first end of the skirt is oriented radially outwards from so that a free peripheral edge of this end is oriented radially outwards;

[0025] — the first end of the skirt is pressed against an annular face of the rib thanks to an annular plywood;

[0026] — the plywood is fixed to the rib by screws that pass through holes in the rib, from the end of the skirt and the plywood;

[0027] — the second end of the skirt is fixed to the flange of the second bearing support;

[0028] — the second end of the skirt is radially clamped onto the flange by means of a hose clamp that surrounds the flange;

[0029] — the flange of the second bearing support is axially interposed between the flange of the first bearing support and another flange of the casing;

[0030] — the flange of the second bearing support is fixed to the flange of the housing by screws non-fusible;

[0031] — the skirt has a generally domed shape with a concavity oriented radially towards inside, when the fusible screws are not broken;

[0032] — the skirt defines a free annular cavity around at least part of the first bearing support and / or second bearing support;

[0033] — the skirt is loaded with fibres;

[0034] — the fibers are oriented in the axial direction, which allows the skirt to have a bending deformation capacity and tensile hardness;

[0035] — the module further includes an oil supply circuit for the enclosure.

[0036] The present invention also relates to an aircraft turbomachine, comprising at least one module as described above. Brief description of the figures

[0037] Other features and advantages of the invention will become apparent upon reading the detailed description that follows, for an understanding of which reference should be made to the accompanying drawings in which:

[0038] [Fig-1] [Fig.1] is a schematic half-view in axial section of a part of a aircraft turbomachine,

[0039] [Fig.2] [Fig.2] is a partial schematic axial cross-sectional view of an enclosure bearing lubrication,

[0040] [Fig.3] [Fig.3] is a larger-scale view of part of [Fig.2] and shows a decoupling device with fusible screws, which are shown here unbroken.

[0041] [Fig.4] [Fig.4] is a view similar to that of [Fig.3] and shows the device of decoupling with fusible screws, which are broken here.

[0042] [Fig.5] [Fig.5] is a schematic axial cross-sectional view of a sealing skirt,

[0043] [Fig.6] [Fig.6] is a view similar to that of [Fig.5] and shows the skirt sealing in case of breakage of the fusible screws,

[0044] [Fig.7] [Fig.7] is a schematic perspective view of the first bearing support of a module according to an embodiment of the invention; and

[0045] [Fig.8] [Fig.8] is a larger scale view of part of [Fig.7];

[0046] [Fig.9] [Fig.9] is a schematic perspective view of the first and second bearing supports according to the embodiment of the invention;

[0047] [Fig. 10] [Fig. 10] is a larger-scale view of part of [Fig. 9]; and

[0048] [Fig. 11] [Fig. 11] is a schematic cross-sectional view of a tooth and an opening bearing supports of [Fig.9]. Detailed description of the invention

[0049] Fig. 1 shows a turbomachine 10 for an aircraft, this turbomachine 10 being here a twin-spool turbojet.

[0050] Axis A designates the longitudinal axis of the turbomachine.

[0051] The turbomachine 10 comprises a gas generator 12 which includes, from upstream to downstream with reference to the gas flow along axis A, a low-pressure (LP) compressor 14, a high-pressure (HP) compressor, an annular combustion chamber, a high-pressure (HP) turbine, and a low-pressure (LP) turbine. The turbomachine 10 is partially shown, and only the LP compressor 14 is depicted in the drawing.

[0052] Although not visible in [Fig.1], the HP compressor rotor is connected to the HP turbine rotor by a high-pressure shaft, and the LP compressor rotor 14 is connected to the LP turbine rotor by a low-pressure shaft which passes through the high-pressure shaft and drives a propulsion propeller, called a blower 16, located upstream of the gas generator 12 and which is surrounded by an annular casing called a blower casing 18.

[0053] The blower housing 18 is connected to the gas generator 12 by an intermediate housing 20 which includes a central hub 22 and a series of radial arms 24 connecting the hub 22 to the blower housing 18.

[0054] The gas generator 12 defines a main annular flow channel V1 of a first air flow, called primary flow FL. The gas generator 12 is surrounded by a secondary annular flow channel V2 of a second air flow, called secondary flow F2.

[0055] The airflow F entering the blower 16 splits into a portion forming the primary flow FL. The air in this primary flow FL is compressed in the BP 14 and HP compressors, then mixed with fuel and burned in the combustion chamber. The combustion gases of the primary flow are then expanded in the HP and BP turbines and finally flow through an exhaust nozzle.

[0056] The other part of the airflow entering the blower 16 forms the secondary flow F2 and is intended to be mixed with the primary flow Fl downstream of the nozzle.

[0057] Figure 1 further shows a module 30 of the turbomachine, this module 30 comprising annular bearing supports 32, 34, an annular housing 36, a lubrication chamber 38 and an oil supply circuit 40 for the chamber 38.

[0058] A first annular bearing support 32 extends around the axis A and includes a first annular fixing flange 32a, more clearly visible in [Fig.2].

[0059] A second annular bearing support 34 extends around the axis A and includes a second annular fixing flange 34a. The flanges 32a, 34a extend radially outwards and are suitable for being applied axially against each other and fixed together by screws 42 which are shear-off and more clearly visible in figures 2 to 4.

[0060] An annular housing 36 extends around axis A, and the second bearing support 34 is fixed to this housing 36 by screws that are not shear-resistant and are not shown in the drawings. The shear-resistant and non-shear-resistant screws 42 may be located on the same circumference centered on axis A. The housing 36 may be the intermediate housing 20 of [Fig. 1] or another housing fixed to or integral with this intermediate housing 20.

[0061] The housing 36 includes a flange 36a onto which the flange 34a is applied and fixed by the aforementioned non-sheathable screws. The flange 34a of the second bearing support 34 is axially interposed between the flange 32a of the first bearing support 32 and the flange 36a of the housing 36, as illustrated in Figures 2 to 4.

[0062] The lubrication enclosure 38 is at least partly delimited by the first bearing support 32 and contains a first bearing 44, or upstream bearing, carried by the first bearing support 32, and a second bearing 46, or downstream bearing, carried by the second bearing support 34.

[0063] In the example shown, the upstream bearing 44 is a roller bearing and the downstream bearing 46 is a ball bearing.

[0064] Furthermore, in the example shown, the first bearing support 32 has a generally annular and elongated shape along the axis A, and comprises an upstream end carrying the rolling bearing 44, and a downstream end connected to the flange 32a. The second bearing support 34 has a generally annular and radial shape, and comprises a radially internal end carrying the downstream bearing 46, and a radially external end connected to the flange 34a.

[0065] The oil supply circuit 40 of the enclosure 38 is more clearly visible in [Fig.2] and includes an oil distributor 48 and at least one oil line 50. The oil distributor 48 is integral with the housing 36 and includes at least one oil inlet 48a and at least one first oil outlet 48b.

[0066] The oil inlet 48a is suitable for connection to an oil reservoir not shown.

[0067] The oil line 50 is integral with the first bearing support 32 and has an end 40a, here downstream, connected to the first oil outlet 48b of the distributor 48 for the purpose of circulating oil from said inlet 48a to said at least one outlet 48b.

[0068] In the example shown, the distributor 48 comprises two oil outlets 48b, 48c, the first oil outlet 48b mentioned above and a second oil outlet 48c. The second oil outlet 48c can be connected to another line or to an oil nozzle 52 as illustrated in the drawing. The nozzle 52 sprays oil onto the downstream bearing 46, while the line 50 connected to the first outlet 48b of the distributor 48 supplies oil to the upstream bearing 44 for lubrication.

[0069] Preferably, the first outlet 48b is oriented axially, in particular towards the first bearing support 32, i.e. here upstream. The second outlet 48c can be oriented radially inwards.

[0070] Figures 2 to 4 further show that the conduit 50 includes a portion which extends axially and which passes through an axial orifice 54 of the second bearing support 34. The conduit 50 is radially interposed between the downstream bearing 46 and the flanges 32a, 34a of the bearing supports 32, 34.

[0071] Fig. 3 shows the default and normal operating case in which the flanges 32a of the bearing supports 32 are applied axially to each other and fixed together by the shear screws 42.

[0072] As mentioned above, in the event of imbalance and vibrations, the shear screws 42 are liable to break as illustrated in [Fig. 4]. The flange 32a of the first bearing support 32, and in particular the first bearing support 32 as a whole, is then no longer axially restrained and moves axially away from the second bearing support 32. The first bearing support 32 then moves upstream, creating an annular passage 56 between the flanges 32a, 34a of the bearing supports 32, 34.

[0073] The oil supplied by the distributor 48 continues to flow into the enclosure and accumulates there. This oil is then liable to flow by gravity through the passage 56 and can reach the primary vein VI, which is problematic as mentioned above.

[0074] A simple, effective and economical solution to this problem is proposed.

[0075] This solution is intended to contain the oil inside the enclosure, even when the screws 42 break and the bearing supports 32, 34 move axially apart from each other.

[0076] As illustrated in figures 5 and 6, an annular sealing skirt 80 extends around the flanges 32a, 34a and includes a first axial end 80a fixed in a sealed manner to the first bearing support 32 and a second axial end 80b fixed in a sealed manner to the second bearing support 34.

[0077] The skirt 80 is made of a deformable material, preferably elastically deformable such as an elastomer. The skirt 80 is, for example, made of Viton®.

[0078] The skirt 80 is preferably fiber-reinforced. The fibers are preferably oriented in the axial direction so that the skirt 80 has a bending deformation capacity and a tensile strength.

[0079] The skirt 80 is suitable for ensuring a seal around the flanges 32a, 34a, between the first and second bearing supports 32, 34 in particular in the event of breakage of the shear screws 42 ([Fig.6]).

[0080] In the example shown, the skirt 80 has a generally domed shape with a concavity oriented radially inwards when the fusible screws 42 are not broken ([Fig. 5]). The skirt 80 can define a free annular cavity 82 around at least part of the bearing support 32 and / or the bearing support 34.

[0081] In the example shown, the first end 80a of the skirt 80 is fixed to an annular rib 84 of the first bearing support 32. This rib 84 extends radially outwards, here at an axial distance from the flange 32a.

[0082] The first end 80a of the skirt 80 can be oriented radially outwards so that a free peripheral edge 80al of this end 80a is oriented radially outwards.

[0083] The first end 80a of the skirt 80 is clamped against an annular face 84a, here downstream, of the rib 84 by means of an annular plywood 86. This plywood 86 can be sectored to facilitate its assembly.

[0084] The plywood 86 is fixed to the rib 84 by screws 87 which pass through holes in the rib 84, the end 80a of the skirt 80 and the plywood 86.

[0085] The plywood 86 may include a cylindrical rim 86a which surrounds the edge 80a of the end 80a or also a free peripheral edge 84al of the rib 84.

[0086] In the example shown, the second end 80b of the skirt 80 is fixed to the flange 34a of the second bearing support 34.

[0087] The second end 80b of the skirt 80 can be radially clamped onto the flange 34a by means of a clamping collar 88 which surrounds the flange 34a.

[0088] In normal operation, the skirt 80 is in the configuration shown in [Fig. 5] and is not functional. It is in standby mode. When the screws 42 break and the bearing support 32 moves axially away from the bearing support 34, the skirt 80 is in the configuration shown in [Fig. 6] and is functional. The skirt 80 then provides a seal between the flanges 32a and 34a, and any oil that might pass through the passage 56 between the flanges 32a and 34a is retained by the skirt 80 and does not escape from the housing 38.

[0089] An embodiment of the present invention is illustrated in Figures 7 and following and can be used in combination with the skirt 80 described above.

[0090] The preceding description applies to the embodiment of Figures 7 and following, and the reference numbers already used in the foregoing are used to designate the same elements of the invention.

[0091] The particularity of the module 30 according to the invention is related to the fact that one of the first and second bearing supports 32, 34 has teeth 90 projecting axially towards the other of the first and second bearing supports 34, 32, and this other bearing support has axial openings 92 which are intended to receive by engagement the teeth 90.

[0092] In the example shown, it is the first bearing support 32 which includes or carries the teeth 90. It is therefore the second bearing support 34 which includes the openings 92.

[0093] The teeth 90 are arranged around the axis A and surrounded by the flange 32a of the bearing support 32. In the same way, the openings 92 are arranged around the axis A and surrounded by the flange 34a of the bearing support 34.

[0094] The teeth 90 are axially engaged in at least a portion of the openings 92 when the flanges 32a, 34a are fixed together ([Fig. 11]). The teeth 90 are able to cooperate by circumferential bearing with edges 92a, 92b of the openings 92 in the event of breakage of the shear screws 42 and axial separation of the flanges 32a, 34a from each other so as to prevent the rotation of the bearing supports 32, 34 relative to each other about the axis A, or at least to limit the stroke or angular deflection of the bearing supports 32, 34 relative to each other about the axis A.

[0095] The teeth 90 are preferably regularly distributed around the axis A.

[0096] The openings 92 are preferably regularly distributed around the axis A.

[0097] As in the example shown, the number of teeth 90 may be less than the number of openings 92.

[0098] The number of teeth 90 is for example between 2 and 10, and preferably between 3 and 8.

[0099] The number of openings 92 is for example between 5 and 40, and preferably between 10 and 30.

[0100] Each of the teeth 90 may have a general L-shape and include a body 90a oriented parallel to the axis A and connected to an internal periphery of the flange 32a by a rim 90b which is perpendicular to the body 90a or inclined with respect to this body 90a.

[0101] The teeth 90 are preferably separated from an internal periphery of the flange 32a by an annular groove 94 oriented axially on the side of the bearing support 34.

[0102] The flanges 32a, 34a are supported in a plane P perpendicular to the axis A.

[0103] Advantageously, the teeth 90 cross axially this plane P so as to be able to guide the axial mounting of the bearing supports 32, 34 before their flanges 32a, 34a come into axial contact with each other (figures 10 and 11).

[0104] Advantageously, the groove 94 has its bottom 94a which is axially recessed with respect to this plane P (figures 10 and 11).

[0105] In the example shown, the bearing support 34 includes a cylindrical flange 96 which is located radially between the flange 34a and the openings 92 and which is configured to be engaged axially in the groove 94 (Figures 10 and 11).

[0106] The rim 96 preferably carries an annular sealing gasket 98 suitable for cooperating with the bearing support 32.

[0107] As can be seen in the drawings, the teeth 90 can be engaged with radial clearances, respectively internal J1 and external J2, in the openings 92 ([Fig. 11]). The teeth 90 can also be engaged with circumferential clearances, respectively J3, in the openings 92 ([Fig. 10]).

[0108] Each of the teeth 90 has, for example, an angular range a around the axis A, between 10 and 20°. Each of the openings 92 has, for example, an angular range [3 around the axis A, between 11 and 22°. The difference in angular ranges a, [3 between the openings 92 and the teeth 90 can be on the order of 1 or 2°, for example.

Claims

Demands

1. A module (30) for an aircraft turbomachine (10), said module (30) comprising: - a first annular bearing support (32) extending about an axis (A) and including a first annular mounting flange (32a), - a second annular bearing support (34) extending about the axis (A) and including a second annular mounting flange (34a), the first and second flanges (32a, 34a) being adapted to be axially pressed against each other and to be fastened together by shear screws (42), - an annular housing (36) extending about the axis (A), the second bearing support (34) being fixed to the housing (36), - a lubrication chamber (38) which is at least partially delimited by the first bearing support (32), this lubrication chamber (38) containing a first bearing support (44) carried by the first bearing support (32) and a second bearing support (46) carried by the second bearing support (34),one of the first and second bearing supports (32, 34) having teeth (90) projecting axially towards the other of the first and second bearing supports (34, 32), these teeth (90) being arranged around the axis (A) and surrounded by the flange (32a, 34a) of this bearing support (32, 34), and said other of the first and second bearing supports (34, 32) having axial openings (92) which are arranged around the axis (A) and surrounded by the flange (34a, 32a) of this bearing support (34, 32), the teeth (90) being axially engaged in at least a part of the openings (92) when the flanges (32a, 34a) are fixed together and being able to cooperate by circumferential bearing with edges (92a) of the openings (92) in case of breakage of the shear screws (42) and axial spacing of the flanges (32a, 34a) from each other.

2. Module (30) according to claim 1, wherein it further comprises an annular sealing skirt (80), preferably of elastically deformable material, which extends around the first and second flanges (32a, 34a) and which comprises a first axial end (80a) fixed in a hermetic manner to the first bearing support (32) and a second axial end (80b) fixed in a sealed manner to the second bearing support (34), this skirt (80) being made of a deformable material and being able to ensure a seal around the flanges (32a, 34a), between the first and second bearing supports (32, 34) in particular in the event of breakage of the shear screws (42).

3. Module (30) according to claim 1 or 2, wherein the teeth (90) are regularly distributed around the axis (A) and / or the openings (92) are regularly distributed around the axis (A).

4. Module (30) according to any one of the preceding claims, wherein the number of teeth (90) is less than the number of openings (92).

5. Module (30) according to any one of the preceding claims, wherein the number of teeth (90) is between 2 and 10, and preferably between 3 and 8.

6. Module (30) according to any one of the preceding claims, wherein the number of openings (92) is between 5 and 40, and preferably between 10 and 30.

7. Module (30) according to any one of the preceding claims, wherein each of the teeth (90) has a general L-shape and comprises a body (90a) oriented parallel to the axis (A) and connected to an internal periphery of the flange (32a, 34a) by a rim (90b) which is perpendicular to the body (90a) or inclined with respect to this body (90a).

8. Module (30) according to any one of the preceding claims, wherein the teeth (90) are separated from an internal periphery of the flange (32a, 34a) by an annular groove (92) oriented axially on the side of the other of the bearing supports (34, 32).

9. Module (30) according to claim 8, wherein the flanges (32a, 34a) are supported in a plane (P) perpendicular to the axis (A), and wherein the teeth (90) axially traverse this plane (P), and / or said groove (94) has its bottom (94a) which is axially recessed with respect to this plane (P).

10. Module (30) according to claim 8 or 9, wherein the other of the bearing supports (34) comprises a cylindrical rim (96) which is located radially between the flange (34a) and the openings (92) and which is configured to be axially engaged in said groove (94).

11. Module (30) according to claim 10, wherein said rim (96) carries an annular sealing gasket (98) adapted to cooperate with the bearing support (32) which includes the teeth (90).

12. Module (30) according to any one of the preceding claims, wherein the teeth (90) are engaged with radial clearances, respectively internal (J1) and external (J2), in the openings (92).

13. Module (30) according to any one of the preceding claims, wherein the teeth (90) are located on the first bearing support (32), and the openings (92) are located on the second bearing support (34).

14. Module (30) according to any one of the preceding claims, wherein each of the teeth (90) has an angular range (a) about the axis (A) of between 10 and 20°, and / or each of the openings (92) has an angular range (|3) about the axis (A) of between 11 and 99°

15. Turbomachine (10) for an aircraft, comprising at least one module (30) according to any one of the preceding claims.

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