TURBOMACHINE MODULE INCLUDING A DAMPING DEVICE AND CORRESPONDING TURBOMACHINE

Abstract

The invention relates to a turbomachine module, particularly for aircraft, having a longitudinal axis X, comprising: - a stator (11) centered on the longitudinal axis, - a rotor comprising a disk (12) driven in rotation about the longitudinal axis by a shaft (5) and relative to the stator via at least one first bearing (20), - a bearing support (21) carrying the first bearing and fixed to the stator, and - a damping device (35) for the radial movements of the bearing support. According to the invention, the damping device (35) comprises a rigid annular support structure (36) fixed to the stator and extending radially outward from the bearing support, the annular support structure having first damping means (41) arranged opposite a radially external surface (42) of the bearing support and intended to reduce the radial displacement of the bearing support toward the annular support structure. (Shorthand figure: Figure 2)

Description

Title of the invention: TURBOMACHINE MODULE COMPRISING A DAMPING DEVICE AND CORRESPONDING TURBOMACHINE Scope of the invention

[0001] The present invention relates to the general field of turbomachinery. It relates in particular to a damping device for a turbomachine rotor installed in an aircraft turbomachine module, and to an aircraft turbomachine comprising such a module. Technical background

[0002] An aircraft turbomachine generally comprises, from upstream to downstream and following the direction of gas flow within the turbomachine, a compressor section, a combustion chamber, and a turbine section. The compressor section comprises, for example, a low-pressure compressor and a high-pressure compressor, and the turbine section comprises, for example, a high-pressure turbine and a low-pressure turbine. The rotating parts of these compressors and / or turbines, such as shafts and impellers, are driven and / or guided in rotation by means of roller bearings.

[0003] Turbomachinery may include a fan disposed upstream of the compressor section. The fan generates an airflow, part of which supplies the compressors, combustion chamber, and turbines of the turbomachine, forming a primary flow in a primary duct. Another part of the airflow generated by the fan flows into a secondary duct, which extends around the primary duct, forming a secondary airflow that generates a major part of the turbomachine's thrust.

[0004] The compressors, turbines, and blower consist respectively of a first set of fixed parts constituting a stator and a second set of parts which are capable of being rotated relative to the stator and which constitute a rotor.

[0005] During certain phases of aircraft flight, under certain pressure and temperature conditions, typically when the aircraft is flying through clouds with icing conditions, large blocks of ice can form on certain parts of the turbomachine, particularly on the fan blades or the turbomachine inlet cone. Under the action of centrifugal force, pieces of ice can then break off from one or more ice blocks and cause impacts on downstream equipment such as a flow guide vane. secondary stream or acoustic panels of the blower housing. These pieces of ice can even be ingested into the primary stream and reach the blades of a primary stream compressor or the turbine's combustion chamber, potentially leading to combustion failure. In particular, ice detaches heterogeneously across the entire blower, resulting in the blower rotor's axis of rotation no longer coinciding with its axis of inertia. Figure 1 illustrates a blower rotor IA of a turbine comprising a shaft 2A passing through a disk 3A along the longitudinal axis XX. In this Figure 1, the axis of rotation X2A of shaft 2A, located on the right, extends transversely to the longitudinal axis XX. This results in the formation of an imbalance, which offsets the blower while the hub of the intermediate housing 4A maintains its shape.

[0006] Eccentricity implies that, during operation, the fan's suspension mode increases in frequency and amplitude, leading to premature wear of certain turbomachine components, such as the abradable material arranged on the fan housing opposite the fan blades. This degrades the turbomachine's performance and operability within a critical speed range.

[0007] The low-pressure compressor shaft, which is connected to the blower shaft or blower disc, is supported by bearings that serve as an interface with the turbomachine stators. This compressor shaft is radially guided by a first bearing located at the upstream end of the compressor shaft and a second bearing located downstream of the first bearing. The first bearing may comprise a ball bearing, while the second bearing may comprise a roller bearing. Generally, the bearings do not allow for a reduction in blower amplitude in the event of significant imbalance.

[0008] When one of the two bearings, particularly the first bearing, is equipped with a flexible cage and a damping fluid film (known as a "squeeze film"), the formation of an unbalance, if too large, can cause the flexible cage of the bearing to bottom out. Such an example of a turbomachine equipped with a damping fluid film bearing is described in patent application FR2000819. Some damping fluid films can be radially adjusted to increase the damping effect. However, such a solution is insufficient when a large unbalance occurs, because the damping effect of the squeeze film is short-circuited by the bottoming out of the flexible cage. Furthermore, the fan blades can come into contact with the abradable material arranged on the fan housing prematurely, well before the flexible cage bottoms out.

[0009] The invention aims to avoid the aforementioned drawbacks. Summary of the invention

[0010] The objective of the invention is to provide a simple, economical and optimal solution for limiting the eccentricity of a rotor in the event of large imbalances.

[0011] We achieve this objective in accordance with the invention by means of a turbine module, in particular for aircraft, having a longitudinal axis X, comprising: - a stator centered on the longitudinal axis, - a rotor comprising a disk driven in rotation around the longitudinal axis X by a shaft and relative to the stator housing via at least one first bearing, - a bearing support carrying the first bearing and fixed to the stator, and - a device for damping radial movements of the bearing support, the damping device comprising a rigid annular support structure fixed to the stator and extending radially outside the bearing support, the annular support structure having first damping means which are arranged opposite a radially external surface of the bearing support and which are intended to reduce the radial displacement of the bearing support towards the annular support structure.

[0012] Thus, this solution makes it possible to achieve the aforementioned objective. In particular, such a damping device makes it possible to limit the radial amplitudes / displacements of the shaft or rotor and eliminates shaft eccentricity in the event of large imbalances so as not to impair the performance of the turbomachine. These imbalances can result from ice buildup, spontaneous loss of a rotor part (a fan blade, for example), deformation, or even the breakage of a part following the ingestion of a foreign object (bird ingestion, for example), etc. In the case of a fan, the annular structure with the damping means makes it possible to prevent premature wear of an abradable material coating applied to a radially internal wall of a fan casing and opposite the free ends of the fan blades to prevent airflow leaks.Furthermore, such a device is easy to assemble and disassemble for maintenance (part replacement in case of wear or ingestion or icing) thanks to its removable design. In addition, the installation of the annular structure requires little or no structural modifications to the turbomachine module.

[0013] The module comprises one or more of the following features, taken alone or in combination:

[0014] - the stator is formed by a stator housing

[0015] - the shaft passes through the stator housing.

[0016] - the annular support structure is separate from the bearing support and not linked to this one.

[0017] - the first damping means include a damping material such than an elastomer or an abradable material coating.

[0018] - the bearing support includes an axial extension extending upstream and in with regard to the disc, the annular support structure carries secondary damping means arranged opposite a radially external surface of the axial extension and intended to reduce the radial displacement of the bearing support towards the annular support structure.

[0019] - the annular support structure comprises an annular ferrule extending dialement around a part of the disk and comprising a first portion at a distance and opposite a second portion of the disk, the first portion being located upstream of the first bearing and carrying second damping means opposite the second portion which has a complementary shape with the first portion, the second damping means being intended to reduce the radial displacement of the bearing support towards the annular support structure.

[0020] - the second damping means include a damping material such as than an elastomer or equivalent material or a coating of abradable material.

[0021] - the rotor includes a blower and the module includes a blower housing made of developing the blower blades, the blower housing includes a radially internal surface bearing a coating of abradable material which is arranged opposite the free ends of the blades.

[0022] - the annular support structure includes a fixing flange extending ra diamentally outwards and which is configured to be secured to the stator via fusible fastening elements.

[0023] - the stator includes an intermediate housing mounted downstream of a communication housing low pressure presser along the longitudinal axis.

[0024] The invention also relates to a turbomachine in particular of an aircraft, having a longitudinal axis, comprising a turbomachine module having any of the aforementioned characteristics.

[0025] The invention further relates to an aircraft comprising at least one turbomachine as mentioned above. Brief description of the figures

[0026] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the following detailed explanatory description, of embodiments of the invention given by way of purely illustrative and non-limiting examples, with reference to the accompanying schematic drawings in which:

[0027] Fig. 1 represents a perspective view of an organ of a tur- module aircraft engine, such as a fan, which has a shaft with a longitudinal axis in a normally operating state and a shaft inclined due to an imbalance causing an eccentricity of the component;

[0028] Fig. 2 represents a partial axial cross-sectional view of an example of a turbomachine comprising a first embodiment of a radial damping device according to the invention;

[0029] Fig. 3 is an axial cross-sectional and detailed view of an embodiment of a damping device;

[0030] Figure 4 is a partial axial cross-sectional view of an example of a turbomachine comprising another embodiment of a radial damping device according to the invention; and

[0031] Fig. 5 is an axial and partial view of a variant of the damping device of Fig. 3 which is installed in a turbomachine according to the invention. Detailed description of the invention

[0032] Figure 2 represents a turbomachine intended for mounting on an aircraft. The aircraft (not shown) comprises a fuselage and at least two wings extending from either side of the fuselage along the fuselage axis. At least one turbomachine is mounted, for example, under each wing. The turbomachine shown is a turbojet engine equipped with a shrouded fan (turbofan) that can be offset in case of imbalance. The turbomachine could be a turboprop engine, for example, including "open rotor" or "USF" (Unducted Single Fan) architectures, which would encounter problems with the offset of one of its rotor components. Of course, the invention applies to other types of turbomachines.

[0033] In the present application, the terms "upstream", "downstream", "axial" and "axially" are defined with respect to the direction of gas flow in the turbomachine and also along the longitudinal axis X (and even from left to right in [Fig. 1]). The terms "radial", "radially", "internal" and "external" are also defined with respect to a radial axis Z that is perpendicular to the X axis of the turbomachine.

[0034] Fig. 2 shows that the turbomachine 1 comprises a gas generator 2 upstream of which a blower 3 is mounted. The gas generator 2 typically comprises, from upstream to downstream, a low-pressure compressor 4, a combustion chamber (not shown), a low-pressure turbine and a high-pressure turbine (not shown).

[0035] Each compressor (low or high pressure) and each turbine (low or high pressure) comprises one or more stages, respectively. Each stage comprises a rotating impeller, forming a rotor, which is mounted upstream or downstream of a fixed impeller (or stator blades). The stator blades are supported and so The outer casings form a stator. The outer casings include annular layers of abradable material facing the moving blades to prevent air recirculation. The rotors of the low-pressure compressor and the low-pressure turbine are connected to each other by a low-pressure shaft 5 centered on the longitudinal axis X to form a low-pressure housing. Similarly, the rotors of the high-pressure compressor and the high-pressure turbine are connected to each other by a high-pressure shaft (not shown) centered on the longitudinal axis X to form a high-pressure housing. The low-pressure and high-pressure housings are guided in rotation about the longitudinal axis by roller bearings upstream and downstream. The high-pressure shaft extends radially, at least partially, outside the low-pressure shaft, and they are coaxial.

[0036] With reference to [Fig. 2], the fan 3 is driven in rotation about the longitudinal axis X. It is arranged upstream of the low-pressure compressor 4. The fan 3 compresses an airflow that enters the turbomachine, dividing into a primary airflow Fl and a secondary airflow F2 at a separation nozzle 6. The primary airflow Fl flows in a primary channel 7 that passes through the gas generator 2, and the secondary airflow F2 flows in a secondary channel 8 around the primary channel 7. The separation nozzle 6 is supported by an inlet housing 9 centered on the longitudinal axis X. The inlet housing 9 is located upstream of the low-pressure compressor housing 10. An intermediate housing 11 is arranged between the low-pressure compressor housing 10 and the high-pressure compressor housing (not shown).

[0037] The blower 3 includes a disc 12 and a series of blower blades 13 carried by the disc 12. The blower 3 includes a blower housing 14 surrounding or enveloping the blower blades 13. The blower housing 14 includes a radially internal surface 15 which carries, via a support panel (not shown), an annular coating 16 made of abradable material. The coating 16 is arranged opposite and close to the free ends of the blower blades 13. This allows control of the clearance at the free ends of the blades, which can create a pumping effect on the airflow generated by the blower. The free ends of the blower blades are designed to rub against the abradable material to optimize radial clearances during operation and limit airflow leakage at the blade tips.By limiting airflow leaks at the free ends of the fan blades by reducing clearance, the performance of the turbomachine is optimized, with a maximum of the secondary airflow being compressed in the secondary duct 8.

[0038] The abradable material of the coating 16 has a lower hardness than the free ends of the blower blades 13. The coating 16 may be the only part to be replaced in case of significant wear.

[0039] The blower disc 12 3, centered on the longitudinal axis X, includes a flange 17 which is connected to an end portion 18 of the low-pressure shaft 5. The flange 17 of the disc 12 extends along the longitudinal axis and radially around the end portion 18. The flange 17 and the end portion 18 include coupling means such as splines. This configuration reduces the radial bulk in the blower rotor and creates additional space. The disc 12 is driven in rotation by the rotation of the low-pressure turbine via the low-pressure shaft 5.

[0040] The low-pressure shaft 5 is radially guided and axially retained by a first bearing 20. The first bearing 20 is supported by a bearing support 21, which is fixed to the stator of the turbomachine. The first bearing 20 is located near the upstream end 18 of the low-pressure shaft 5. More specifically, the first bearing 20 comprises an inner ring 22, an outer ring 23, and rolling elements 24 mounted between the inner and outer rings 22 and 23. The inner ring 22 is integral with the low-pressure shaft 5. The outer ring 23 is integral with the bearing support 21. In this example, the rolling elements 24 comprise balls. However, the rolling elements may comprise rollers or needles. Advantageously, but not exclusively, the first bearing 20 may include a damping fluid film for damping vibrations of the low-pressure shaft.As is known, the fluid damping film includes oil and is formed at the outer ring and bearing support.

[0041] A second bearing 25 radially guides the low-pressure shaft 5. The second bearing 25 is located downstream of the first bearing 20. Similarly, the second bearing 25 comprises an inner ring 26, an outer ring 27, and rolling elements 28 mounted between the inner and outer rings 26, 27. The inner ring 26 is integral with the low-pressure shaft 5. The outer ring 27 includes a radial flange that is integral with a component 30 connected to the turbomachine stator. In this example, the rolling elements 28 comprise rollers but could also comprise needles or balls. The first bearing 20 and the second bearing 25 are arranged in a lubrication and cooling enclosure 31, which is supplied with lubricant, here oil in the form of a mist, from a lubrication system (not shown). The second bearing 25 can have an axial stop function in case of failure of the low pressure shaft.

[0042] Here, the turbomachine stator is a stator housing. Advantageously, the stator housing is the intermediate housing 11. The bearing support 21 has a shape of revolution extending about an axis that is coaxial with the longitudinal axis X of the turbomachine (in the installed position). The bearing support 21 includes a flange radial 39 annular fixed by fixing members 32 on a lug 33 of the intermediate housing 11. This radial flange 39 is located at a first end 34 of the bearing support 21.

[0043] As shown in [Fig. 1], the turbomachine includes a damping device 35 for the radial movements of the turbomachine stator, configured to reduce rotor eccentricity in the event of large imbalances such as those caused by ice, the ingestion of foreign objects, or the loss of a moving blade. In particular, the device dampens the radial movements of the bearing support connected to the fixed structure of the turbomachine. By damping this stator component, the radial movements of the rotor are reduced accordingly. In this example, the rotor includes the fan disk 12 of the fan 3. The damping device 35 includes a rigid annular support structure 36 that is fixed to the stator, or to the stator housing (intermediate housing 11). The annular support structure 36 has a shape of revolution about an axis coaxial with the longitudinal axis. This axis is conical in shape.Alternatively, the annular structure 36 comprises several arms that can be arranged around the longitudinal axis in a regular pattern. There can be a minimum of eight arms, for example. The arms can be connected to each other by a ring at one of their ends. This results in a squirrel cage-like structure with bars formed by the arms, analogous to an openwork piece of revolution.

[0044] The annular structure 36 extends between the blower disc and the intermediate housing 11 along the longitudinal axis X. The annular structure 36 also extends radially outward from the bearing support 21. Advantageously, the annular structure 36 includes a wall whose shape corresponds to the shape of a radially external surface 42 of the bearing support 21. The bearing support 21 and the annular structure 36 are separate from each other and at a distance from the bearing support 21. The annular arm structure is also not connected to the bearing support. The annular structure 36 is more rigid than the bearing support 21. By the term "rigid," we mean the ability of a part to transmit forces and to undergo little or no structural change or displacement. The bearing support 21 is also rigid with respect to the first bearing 20, which moves radially.

[0045] The annular structure 36 is made of a metallic material. The metallic material may include steel or an equivalent alloy (such as the turbomachine parts surrounding the thrust bearing).

[0046] To this end, the annular structure 36 includes a mounting flange 37 that extends radially outwards. The mounting flange 37 is located at a first end 38. The mounting flange 37 is intended to be fixed to a flange 49 of the intermediate housing. The fixing is achieved using fasteners 40 such as screws, Nuts, bolts, studs, etc. The fasteners 40 are axial fasteners. By "axial fasteners," we mean that the fasteners extend primarily in a direction parallel to the longitudinal axis. Indeed, the mounting flange 37 and the flange 49 include holes and corresponding holes parallel to the longitudinal axis X, through which the screws, for example, pass. Such fasteners 40 allow for quick assembly and disassembly of the annular structure 36.

[0047] The annular structure 36 includes first damping means 41 arranged opposite a radially external surface 42 of the bearing support 21 and intended to reduce the radial displacement of the support bearing 21 towards the annular structure. In the embodiment of [Fig. 1], the damping means are designed to compress when the bearing support 21 moves radially outwards in the event of eccentricity of the blower. The damping means 41 extend along the radially external surface 42 of the bearing support. A substantially radial distance d (clearly shown in the figure) is provided between the damping means 41 and the bearing support 21.

[0048] The first damping means include a damping material. An example of a damping material is an elastomer or an equivalent material. Such a damping material allows itself to be compressed or crushed to provide maximum damping during the displacements or amplitude of the shaft 5 and to prevent the transmission of the displacement of the shaft 5, bearing 20, bearing support 21 assembly to the blower blades (i.e., the blower eccentricity).

[0049] According to an advantageous feature, the fastening elements 40 are fusible. In particular, the fastening elements 40 are configured to break before the first bearing is decoupled. The decoupling of the first bearing 20 takes place via the fusible fastening elements at the interface between the bearing support and the intermediate housing. In particular, the elements 40 are configured to break at a predetermined stress value corresponding to an extreme imbalance (for example, the loss of a blower blade). The loss of a blower blade is considered more significant and severe than ice buildup on the blower blades. It is necessary to be able to shut down the blower and the gas generator as quickly as possible. In this case, the failure of the fastening allows the free ends of the blower blades to rub excessively against the coating 16.In this example, the screws of the fastening elements 40 have a reduced cross-section relative to their axes. Specifically, this fracture occurs under shear and tensile stresses exerted on the screw. In this way, the fastening elements 40 allow the annular structure 36 to separate from the intermediate housing 11. The forces transmitted up into the turbomachine structures via the bearing support are also limited.

[0050] Alternatively, the fasteners 32 between the bearing support 21 and the intermediate housing 11 are fusible. The screws of the fasteners 32 also have a reduced cross-section allowing them to break under a predetermined inverse value. In this example, the fusible screws of the fasteners 40 must break before the fasteners 32 of the fusible bearing support for an unbalance level greater than icing-type unbalances, but less than the extreme unbalance leading to bearing decoupling.

[0051] Figure 3 illustrates another embodiment of the arrangement of the damping device 35 in the turbomachine. In this embodiment, identical or substantially identical elements and / or elements with the same functions are represented by the same reference numerals as those in the embodiment described previously. This embodiment differs from the embodiment of Figure 2 in that the bearing support 21 includes an axial extension 45 that extends upstream of the bearing support 21 along the longitudinal axis X. The axial extension 42 also extends upstream of the first bearing 20. The axial extension 45 is located opposite the disk 12 of the fan 3. The axial extension 45 is an added component. It can be attached by welding or via radial flanges. Alternatively, the axial extension 45 is formed as part of the bearing support 21.As illustrated, the annular structure 36 includes secondary damping means 46 arranged opposite a radially external surface 47 of the axial extension 45. The secondary damping means are arranged at a second end 48 (opposite to the first end along the length or axis of revolution of the supporting annular structure 36). As with the first damping means, the secondary damping means 46 can compress when the axial extension 45 moves radially outwards, following the movement of the bearing support 21 and the bearing 20 in the event of an imbalance. The secondary damping means also include a damping material such as an elastomer or similar material.

[0052] Sealing means 50 are provided upstream of the first bearing 20 to ensure the sealing of the enclosure 31. The sealing means 50 comprise a seal with a degree of flexibility to accommodate the radial movements of the low-pressure shaft in the event of significant imbalances. The sealing means 50 include a flange 51 which is fixed to a flange of the bearing support and which carries the seal. The seal is arranged radially between the flange 51 and the flange 17. The axial extension 45 extends radially outward from the sealing means.

[0053] Figure 4 illustrates another embodiment of the arrangement of the damping device 35 in the turbomachine. In this embodiment, identical or substantially identical elements and / or elements with the same functions are represented by the same reference numerals as those in the embodiment described previously. This embodiment differs from the embodiment of [Fig.3] in that the damping device 35 also includes the first damping means 41 arranged between the annular structure 36 and the radially external surface of the bearing support 21. With such a configuration, the efficiency of the damping device 35 is even better.

[0054] Figure 5 illustrates another embodiment of the arrangement of the damping device 35 in the turbomachine. In this embodiment, identical or substantially identical elements and / or elements with the same functions are represented by the same reference numerals as those in the embodiment described previously. This embodiment differs from the embodiment of Figure 1 in that the annular structure 36 comprises an annular ferrule 55 that extends radially around a portion of the disk 12. The annular ferrule 55 is centered on the longitudinal axis X. The annular ferrule 55 comprises a proximal end that is fixed to the second end 48 of the annular structure 36. The annular ferrule 55 also comprises a distal end that includes a first portion 56 at a predetermined distance and opposite a second portion 57 of the disk 12.The second portion 57 is connected on one side to the rim of the disc 12, downstream, and on the other side to the flange 17. The first portion 56 of the annular ferrule 55 is also located upstream of the first bearing 20. The first portion 56 of the ferrule extends in a direction transverse to the wall of the annular ferrule. The first portion 56 has a complementary shape to the second portion of the disc 12. Here, the second portion of the disc 12 has a frustoconical axial cross-section.

[0055] The second portion 57 of the disc 12 is designed to radially abut against the first portion 56 of the annular ferrule 55 in the event of rotor movement. This limits the radial displacements of the disc 12 and the eccentricity of the fan in the event of significant imbalances, and also reduces the clearance between the fan housing and the free ends of the fan blades. In this embodiment, the device 35 also includes secondary damping means 46 which are supported by the first portion 56 and opposite the second portion of the disc 12. The secondary damping means 46 may comprise a damping material such as an elastomer.

[0056] Alternatively, the second damping means 46 comprise a coating made from an abradable material. The arrangement of the coating made of abradable material limits the heating of the materials of the disc 12 and the annular ferrule in case of contact, but also provides damping when the predetermined distance (clearance) between the ferrule 55 and the disc 12 is consumed due to imbalance during an icing event and is less than the metal-to-metal clearance of this annular ferrule. This abradable material can be identical to the re Clothing 16 applied to the inner wall of the blower housing. Other materials with similar properties may be considered.

[0057] Abradable materials may include a polymer, metallic fibers and / or a honeycomb.

[0058] With the first and second means of damping, the efficiency of the damping device 35 of this embodiment is even better.

Claims

Claims

1. A turbomachine module, in particular an aircraft module, having a longitudinal axis (X), comprising: - a stator (11) centered on the longitudinal axis (X), - a rotor comprising a disc (12) driven in rotation about the longitudinal axis (X) by a shaft (5) and relative to the stator via at least one first bearing (20), - a bearing support (21) carrying the first bearing (20) and fixed to the stator, and - a device (35) for damping the radial movements of the bearing support (21), the damping device (35) comprising a rigid annular support structure (36) fixed to the stator (11) and extending radially outside the bearing support (21), the annular support structure (36) comprising first damping means (41) which are arranged opposite a radially external surface (42) of the bearing support (21) and which are intended to reduce the radial displacement of the support from bearing (21) to the annular support structure (36),characterized in that the first damping means (41) comprise a damping material such as an elastomer or a coating of abradable material.,

2. Module according to the preceding claim, characterized in that the annular support structure (36) is separate from the bearing support (21) and not linked to it.

3. Module according to one of the preceding claims, characterized in that the bearing support (21) comprises an axial extension (45) extending upstream and opposite the disc (12), the annular support structure (36) comprising second damping means (46) arranged opposite a radially external surface (47) of the axial extension (45) and intended to reduce the radial displacement of the bearing support (21) towards the annular support structure (36).

4. Module according to any one of claims 1 to 3, characterized in that the annular support structure (36) comprises an annular ferrule (55) extending radially around a part of the disc (12) and comprising a first portion (56) at a distance from and opposite a second portion (57) of the disc, the first portion (56) being located in upstream of the first bearing (20) and carrying second damping means (46) opposite the second portion (57) which has a complementary shape with the first portion (56), the second damping means (46) being intended to reduce the radial displacement of the bearing support (21) towards the annular support structure (36).

5. Module according to claim 3 or claim 4, characterized in that the second damping means (46) comprise a damping material such as an elastomer or a material equivalent to the elastomer or a coating of abradable material.

6. Module according to one of the preceding claims, characterized in that the rotor comprises a fan (3) and in that it comprises a fan casing (14) enveloping the blades (13) of the fan (3), the fan casing (14) comprising a radially internal surface (15) carrying a coating (16) of abradable material which is arranged opposite the free ends of the blades (13).

7. Module according to any one of the preceding claims, characterized in that the annular support structure (36) comprises a fixing flange (37) extending radially outwards and which is configured to be secured to the stator (11) via fusible fixing members (40).

8. Module according to any one of the preceding claims, characterized in that the stator comprises an intermediate casing mounted downstream of a low pressure compressor casing (4) along the longitudinal axis.

9. Turbomachine (1) in particular of an aircraft, having a longitudinal axis (X) and comprising a turbomachine module according to any one of the preceding claims.

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