SUSPENSION ARRANGEMENT FOR A TURBOMACH

Abstract

The invention relates to a suspension assembly for a turbomachine (10), the assembly comprising: • - a beam (12) for the attachment thereof to an aircraft pylon (13), the beam (12) comprising a first portion (12a) and a second portion (12b) each carrying a half-housing (16a, 16b) jointly defining a ball joint housing (17); • - a ball joint nut (16) rotatably hingedly enaged in the ball joint housing (17); and • - a cylindrical portion (14) intended to be attached to a fixed portion (15) of the turbomachine (10) hinged to the ball joint housing (17) and mounted so as to be pivotable about its axis (X) in the ball joint nut (16), wherein the suspension assembly (11) further comprises a retaining ring (23) surrounding the two half-housings (16a, 16b) around the entire circumference thereof, the retaining ring (23) being provided to perform a safety function in the event of the failure of at least one element of the suspension assembly (11).

Description

Description TITLE: SUSPENSION ASSEMBLY FOR A TURBOMACHINE

[0001] This disclosure relates to a suspension assembly for a turbomachine, specifically for a turbofan engine. Previous technique

[0002] A turbofan engine typically comprises a primary annular airflow path, or primary annular path, which includes, from upstream to downstream in the direction of gas flow within the turbomachine, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine. The turbofan engine also includes a secondary annular airflow path, or secondary path, which externally surrounds the primary annular path. The primary and secondary annular paths are coaxial, with the secondary annular path arranged radially outside the primary airflow path. The terms radial and axial are defined with respect to the axis of the turbomachine. The terms upstream and downstream are defined with respect to the direction of gas flow within the turbomachine.

[0003] The turbofan engine is typically mounted on an aircraft pylon or mast, which is itself attached to the aircraft's structure, such as the wing. The pylon transmits the forces generated by the turbofan engine to the aircraft's structure and also allows for the routing of fuel, air, and electrical and hydraulic systems between the turbofan engine and the aircraft.

[0004] Patent application FR 2 867 155 in the name of the Applicant discloses a turbomachine attached to a pylon by means of a suspension assembly comprising an upstream suspension assembly and a downstream suspension assembly. The upstream suspension assembly is attached to an intermediate housing integral with a fan housing, while the downstream suspension assembly is attached to an exhaust housing. Both housings are structural elements of the turbomachine.

[0005] The suspension systems are designed to transmit mechanical forces between the turbomachine and the pylon. These forces include the thrust generated by the turbomachine, directed along its axis, lateral aerodynamic loads, and the weight of the turbomachine.

[0006] In the following description, we will focus in particular on the upstream suspension assembly.

[0007] Such a known upstream suspension assembly typically comprises a beam intended to be attached to an aircraft pylon, a cylindrical section articulated on a ball joint housing, the ball joint housing having a body, a ball joint nut articulated on the body, the cylindrical section being pivotally mounted around its axis within the ball joint nut. The body of the ball joint housing is fixed to a stationary part of the turbojet engine, for example, an intermediate casing or an inter-compressor casing, located between the low-pressure compressor and the high-pressure compressor of the primary intake.

[0008] Due to the significant forces transmitted by the suspension assembly, the scenario of a component failure must be considered, while ruling out the possibility of the turbofan engine separating from the rest of the aircraft. To this end, the suspension assembly may include an additional, or standby, load path designed to withstand a residual load, or limit load, in the event of a suspension component failure.

[0009] Furthermore, there is currently a need to limit the size of turbomachinery while still accommodating a significant amount of equipment. To meet these various constraints, it is also necessary to reduce the footprint of the suspension systems.

[0010] There is also a need to improve the suspension devices, for a ducted or unducted turbomachine. Summary

[0011] A suspension system for a turbomachine is therefore proposed, comprising: - a beam for its attachment to an aircraft pylon, the beam comprising a first part and a second part, each carrying a half-housing which together define a ball joint housing, - a ball joint nut engaged and articulated for rotation in the ball joint housing, and - a cylindrical part intended to be fixed to a fixed part of the turbomachine, articulated in the ball joint housing, and mounted pivotally around its axis in the ball joint nut, in which the suspension assembly further includes a retaining ring surrounding the two half-housings over their entire circumference, said retaining ring being intended to implement a safety function in the event of failure of at least one element of the suspension assembly.

[0012] In addition, the beam can extend axially and the two parts and the two halves are symmetrical with respect to each other, with respect to a radial plane and joined to each other by fastening elements arranged on the beam.

[0013] In addition, the retaining ring may comprise two symmetrical ring parts with respect to each other and supported against each other by ring flanges, said ring flanges being provided for fixing the two ring parts together.

[0014] The two ring parts can further be symmetrical with respect to each other along the radial plane, the ring flanges being arranged radially internally and radially externally, and wherein each half-housing has ball joint housing flanges arranged radially internally and externally, the ring flanges and the ball joint housing flanges being provided for their common attachment.

[0015] Alternatively, the suspension assembly may include a retaining ring and the ball joint housing may be cylindrical and devoid of fasteners, the retaining ring being arranged on the outer circumference of the ball joint housing, and the retaining ring being arranged on the outer circumference of the retaining ring, the two ring parts of the retaining ring being symmetrical to each other along an axial plane perpendicular to the radial plane, the ring flanges of the two ring parts extending axially in an axial direction.

[0016] In addition, a ball joint bushing can be fitted against the inner circumference of the ball joint housing, with the ball joint nut fitting within the ball joint bushing. A vibration-damping device can also be fitted radially between the ball joint bushing and the inner circumference of the ball joint housing.

[0017] Furthermore, the cylindrical part may comprise a first half-cylinder and a second half-cylinder arranged circumferentially end to end, and in which the first half-cylinder comprises a first half-cylinder flange extending radially to the first half-cylinder and the second half-cylinder comprises a second half-cylinder flange extending radially to the second half-cylinder, the first half-cylinder flange and the second half-cylinder flange comprising respectively a first fastening means and a second fastening means for the independent fastening of each half-cylinder to the fixed part of the turbomachine.

[0018] In another respect, a suspension system for a turbomachine is proposed, comprising: - a beam for its attachment to an aircraft pylon, the beam comprising a first part and a second part, each carrying a half-housing which together define a ball joint housing, - a ball joint nut engaged and articulated for rotation in the ball joint housing, and - a cylindrical part intended to be fixed to a fixed part of the turbomachine, articulated in the ball joint housing, and mounted pivotally around its axis in the ball joint nut, said cylindrical part comprising a first half-cylinder and a second half-cylinder arranged circumferentially end to end.

[0019] If a portion of the cylindrical section, and therefore half a cylinder, fails, the faulty section can no longer properly connect to the fixed part of the turbomachine. Separating the cylinder into two parts prevents the failure from affecting the entire cylinder, thus preserving the full functionality of at least one portion of the cylindrical section attached to the turbomachine. Furthermore, the connection to the turbomachine remains intact despite the failure.

[0020] In addition, the first half-cylinder may include a first half-cylinder flange extending radially to the first half-cylinder and the second half-cylinder may include a second half-cylinder flange extending radially to the second half-cylinder, the first half-cylinder flange and the second half-cylinder flange respectively comprising a first fastening means and a second fastening means for the independent attachment of each half-cylinder to the fixed part of the turbomachine.

[0021] The independent fixing allows the two half-cylinders to remain independent of each other so as not to propagate a crack appearing on one of the half-cylinders to the fixed part of the turbomachine.

[0022] The beam can also extend axially and the two parts and the two half-housings can be symmetrical with respect to each other, with respect to a radial plane and joined to each other by fixing elements arranged on the beam.

[0023] In addition, since each half-housing is cylindrical, the suspension assembly may also include a retaining ring surrounding the two half-housings around their entire circumference, said retaining ring being intended to implement a safety function in the event of failure of at least one element of the suspension assembly.

[0024] Furthermore, the retaining ring may comprise two symmetrical ring parts with respect to each other and supported against each other by ring flanges, said ring flanges being provided for fixing the two ring parts together.

[0025] Also, the two ring halves can be symmetrical to each other along the radial plane, with the ring flanges arranged radially internally and radially externally, and each half-housing can have housing flanges of ball joints arranged radially internally and externally, the ring flanges and ball joint housing flanges being provided for their common attachment.

[0026] Alternatively, the suspension assembly may further include a retaining ring and the ball joint housing may be cylindrical and devoid of fasteners, the retaining ring being arranged on the outer circumference of the ball joint housing, and the retaining ring being arranged on the outer circumference of the retaining ring, the two ring parts of the retaining ring being symmetrical to each other along an axial plane perpendicular to the radial plane, the ring flanges of the two ring parts extending axially in an axial direction.

[0027] In addition, a ball joint bushing can be fitted against the inner circumference of the ball joint housing, with the ball joint nut fitting within the bushing. A vibration-damping device can also be fitted radially between the ball joint bushing and the inner circumference of the ball joint housing.

[0028] According to yet another aspect, it is proposed an aircraft assembly comprising a pylon and a turbomachine, the turbomachine comprising a fixed part, the aircraft assembly further comprising a suspension assembly as described above. Brief description of the drawings

[0029] Other features, details, and advantages will become apparent upon reading the detailed description below and analyzing the attached drawings, on which: Fig. 1

[0030] [Fig. 1] Figure 1 is an overview of a turbomachine attached to an aircraft pylon by means of a suspension assembly. Fig. 2A

[0031] [Fig. 2A] Figure 2A is a perspective view of a suspension assembly according to a first example of implementation. Fig. 2B

[0032] [Fig. 2B] Figure 2B is a perspective and exploded view of the whole of Figure 2A. Fig. 3A

[0033] [Fig. 3A] Figure 3A is a perspective view of a suspension assembly according to a second embodiment. Fig. 3B

[0034] [Fig. 3B] Figure 3B is a perspective and exploded view of the whole of Figure 3A. Fig. 4A

[0035] [Fig. 4A] Figure 4A is a perspective view of a suspension assembly according to a third embodiment. Fig. 4B

[0036] [Fig. 4B] Figure 4B is a perspective and exploded view of the whole of Figure 4A. Fig. 5

[0037] [Fig. 5] Figure 5 is a cross-sectional view along a radial plane of an alternative embodiment of the suspension assembly. Description of the implementation methods

[0038] Figure 1 illustrates an overview of a turbomachine 10, on which a suspension assembly 11 is arranged. The suspension assembly 11 comprises a beam 12, fixed to an aircraft pylon 13, and a cylindrical part 14, fixed to a fixed part 15 of the turbomachine 10.

[0039] In the following description, the terms radial and axial are defined with respect to the axis of the turbomachine, denoted L in Figure 1.

[0040] Figures 2A, 2B, 3A, 3B, 4A and 4B illustrate different examples of embodiments of the suspension assembly 11. In these examples, the suspension assembly 11 includes in particular a beam 12, a ball joint nut 16 and a cylindrical part 14. The suspension assembly extends mainly in an axial direction, extending along the axis marked X in the figures, from upstream, the cylindrical part 14 to downstream, the beam 12.

[0041] Beam 12 comprises a first part 12a and a second part 12b. The first part 12a and the second part 12b are symmetrical to each other along a radial plane of symmetry passing through the axes X and Z. Each first part 12a and second part 12b includes an upper surface, 13a and 13b respectively, which may be substantially flat. The upper surfaces 13a and 13b are designed for attaching beam 12 to an aircraft pylon 13. Beam 12 thus allows the suspension assembly 11 to be attached to the aircraft, this attachment being divided into two parts. Therefore, if a failure occurs in one part of beam 12, such as the propagation of cracks, the other part of the beam is not affected by this failure. The beam is thus divided into two parts so that to keep at least one part of the beam intact in case of failure of the other part of the beam.

[0042] In addition, the first part 12a and the second part 12b are joined together by fasteners 50. These fasteners 50 are, for example, screw and nut assemblies, the screws passing through the first part 12a and the second part 12b in a direction along the axis denoted Y, perpendicular to the radial plane of symmetry.

[0043] Each first part 12a and 12b also includes, respectively, a first half-housing 16a and a second half-housing 16b. Each half-housing 16a, 16b is semi-cylindrical, the two half-housings being in edge-to-edge contact with each other and together defining a cylinder, this cylinder being a ball joint housing 17, comprising an inner circumference 18. The ball joint housing 17 receives the ball joint nut 16. More precisely, the suspension assembly 11 may further include a ball joint ring 19. The ball joint ring 19 is arranged against the inner circumference 18 of the ball joint housing 17. The ball joint nut 16 is arranged within the ball joint ring 19. The ball joint nut can be defined as a spherical part comprising a bore passing through the sphere on either side of the X-axis.

[0044] According to an alternative, as illustrated in Figure 5, the suspension assembly 11 may further include a vibration damping means 20. The vibration damping means 20 may be arranged radially between the ball joint ring 19 and the inner circumference 18 of the ball joint housing 17. In other words, the vibration damping means may be interposed between the ball joint housing 17 and the ball joint ring 19. The vibration damping means 20 limits vibrations and their structural and acoustic consequences. It is characterized by its high elasticity and deformation capacity. The vibration damping means 20 is, for example, a flexible annular element of the elastomer type. The vibration damping means 20 reduces the vibrations transmitted from the turbomachine to the aircraft pylon.

[0045] The suspension assembly 11 further comprises a cylindrical portion 14. The cylindrical portion 14 is fixed to the fixed portion 15 of the turbomachine 10. The cylindrical portion 14 thus allows the suspension assembly 11 to be fixed to the turbomachine 10. The cylindrical portion 14 is arranged, at least partially, within the ball joint nut 16, and more specifically within its bore. In particular, the cylindrical portion 14 is pivotally mounted, about the X-axis, within the ball joint nut 16. Furthermore, the cylindrical portion 14 comprises a first half-cylinder 14a and a second half-cylinder 14b. The first half-cylinder 14a and the second half-cylinder 14b are arranged circumferentially end-to-end. More precisely, according to the figures, the first half-cylinder 14a and the second half- Cylinder 14b can be symmetrical to each other along a radial plane of symmetry passing through the X-axis and the Z-axis. Alternatively, the first half-cylinder 14a and the second half-cylinder 14b can be symmetrical to each other along an axial plane of symmetry passing through the X-axis and the Y-axis. Thus, "end-to-end" means that the two half-cylinders, when joined together, form a cylinder joined along the cylinder's median plane, which is also an axial plane of symmetry. Furthermore, each half-cylinder comprises a semi-cylindrical surface and an opposing flat surface. The circumferential end-to-end arrangement brings the flat surfaces of the two half-cylinders into contact.

[0046] The first half-cylinder 14a and the second half-cylinder 14b each comprise, respectively, a first half-cylinder flange 21a and a second half-cylinder flange 21b. The first half-cylinder flange 21a and the second half-cylinder flange 21b extend radially with respect to the first half-cylinder 14a and the second half-cylinder 14b, respectively. In other words, the first half-cylinder flange 21a and the second half-cylinder flange 21b extend radially with respect to the X-axis. The first half-cylinder flange 21a and the second half-cylinder flange 21b each comprise, respectively, a first fastening means 22a and a second fastening means 22b. The fastening means allow for the independent attachment of each half-cylinder to the fixed part 15 of the turbomachine 10.In particular and for example, the fastening means are a set of screws and nuts cooperating both with the half-cylinder flanges 21a, 21b and the fixed part of the turbomachine, the half-cylinder flanges not being fixed to each other.

[0047] In addition, the suspension assembly 11 includes a retaining ring 23. The retaining ring 23 is intended to implement a safety function in the event of failure of at least one element of the suspension assembly 11. Alternatively, the suspension assembly 11 further includes a retention ring 24. The retaining ring 23 and the retention ring 24 are described with reference to the alternative embodiments shown in Figures 2A, 2B, 3A, 3B, 4A and 4B.

[0048] As illustrated in Figures 2A and 2B, the suspension assembly 11 comprises the retaining ring 23 and the retention ring 24. The retention ring 24 is designed to keep the two half-housings 16a and 16b in contact with each other in the event of a break in the beam 12. In other words, it helps to reinforce the connection between the two beam sections in the area of ​​the two half-housings. For example, without the retention ring, if a section 12a or 12b of the beam 12 breaks, resulting in the loss of that section's connection to the pylon, the first section 12a and the second section 12b, and in particular the two half-housings 16a and 16b, could separate from each other. that the ball joint housing 17 opens. This results in a loss of integrity of the ball joint housing 17, and it no longer performs its function of receiving the ball joint nut 16. The ball joint nut 16 is thus no longer engaged and rotationally articulated within the ball joint housing 17, and the cylindrical part 19 loses its connection with the pylon. The turbomachine 10 is consequently no longer connected to the pylon. There is therefore a loss of force transmission between the turbomachine and the pylon. The retaining ring 24 is arranged on the outer circumference of the ball joint housing 17. In other words, the retaining ring 24 surrounds the ball joint housing 17. The retaining ring 24 is further configured to be able to withstand, i.e. not break, up to a limit load level, beyond which the retaining ring 24 would undergo permanent deformation.The retaining ring 24 therefore has a load-bearing function in the event of a failure of a portion of the beam 12, as this failed portion no longer performs its load-transmission function. More precisely, under normal operating conditions of the suspension assembly 11, i.e., without failure, the retaining ring 24 remains ready to absorb a certain load. It is when a failure occurs in the beam 12 that the retaining ring 24 absorbs, at least partially, the loads. The retaining ring 24 is capable of fulfilling its load-bearing function at least until the next mechanical inspection of the suspension assembly 11. The retaining ring thus prevents a sudden rupture of the connection between the turbomachine and the pylon by maintaining a sufficient load level until the next aircraft inspection. Furthermore, the retaining ring 24 can be annular or ring-shaped.Advantageously, its internal surface is complementary to the external surface of the ball joint housing, and the external surface of the retaining ring can be of complementary shape to the internal surface of the retaining ring 23.

[0049] The suspension assembly 11 of Figures 2A and 2B further includes the retaining ring 23. The retaining ring 23 comprises two ring sections 23a, 23b. The two ring sections 23a, 23b are symmetrical to each other with respect to an axial plane extending along the X and Y axes, the axial plane being perpendicular to the radial plane of the turbomachine. As can be seen, for example, in Figure 2B, the plane of symmetry of the two ring sections 23a, 23b is perpendicular to the plane of symmetry of the two beam sections 12a, 12b. The two ring sections 23a, 23b are supported against each other by ring flanges 23c, 23d. The ring flanges 23c, 23d are provided for securing the two ring parts 23a, 23b together. The ring flanges 23c, 23b extend axially along the X-axis. The retaining ring 23 is arranged on the outer circumference of the retaining ring 24.The retaining ring 23 provides additional security to the suspension assembly 11, in the event of a failure. appearing in particular at the level of the ball joint housing 17. The retaining ring 23 provides reinforcement around the retention ring 24, to ensure the load transfer in case of failure of the retention ring 24. The retaining ring 23 can thus be described as a secondary load transfer ring while the retaining ring 24 can be described as a primary load transfer ring.

[0050] Figures 3A and 3B illustrate another embodiment of the suspension assembly 11. This example is identical to the one previously described with reference to Figures 2A and 2B, except that the retaining ring 23 is a single piece. This configuration has the advantage of being more compact than the previous example, as it eliminates flanges and fasteners.

[0051] Figures 4A and 4B illustrate yet another embodiment of the suspension assembly 11. In this example, unlike the two examples described above, the suspension assembly does not include a retaining ring 24. The retaining ring 23 is thus arranged on the outer circumference of the ball joint housing 17. The retaining ring 23 also comprises two parts 23a, 23b and ring flanges 23c, 23d. In this example, the two ring parts 23a, 23b are symmetrical to each other with respect to a radial plane extending along the X and Z axes, the radial plane coinciding with the radial plane of the turbomachine. Furthermore, as can be seen for example in Figure 4B, the plane of symmetry of the two ring parts 23a, 23b coincides with the plane of symmetry of the two beam parts 12a, 12b. The ring flanges 23c, 23d are arranged respectively radially internally and radially externally with respect to the axis L of the turbomachine.Furthermore, each half-housing 16a, 16b includes flanges, hereinafter referred to as ball joint housing flanges 16c, 16d. The ball joint housing flanges 16c, 16d are arranged radially internally and radially externally with respect to the X-axis. The ball joint housing flanges 16c, 16d and the ring flanges 23c, 23d are arranged in the same planes and designed for common attachment. Compared to the example in Figures 2A and 2B, the two ring halves 23a, 23b are not supported against each other by the ring flanges 23c, 23d. In contrast, in the example illustrated in Figures 4A and 4B, the ring flanges 23c, 23d are supported by the ball joint housing flanges 16c, 16d, and the two half-housings 16a, 16b are supported against each other by the ball joint housing flanges 16c, 16d. More precisely, the ring flanges 23c, 23d clamp the ball joint housing flanges 16c, 16d.In other words, the ball joint housing flanges 16c are taken between the two ring flanges 23c, and the ball joint housing flanges 16d are taken between the two ring flanges 23d. Fastening means on the flanges, such as for example a set of screws and nuts, assemble the two ball joint housing parts 16a, 16b together. and the two ring parts 23a, 23b. This configuration, and in particular the common fixings of the flanges 23c, 23d, 16c, 16d between them, has the advantage of keeping the two half-housings 16a, 16b in contact with each other in the event of failure of the beam 12. In the event of failure of one part of the beam, the other part, which retains its connection with the pylon, can then maintain the transmission of forces between the turbomachine and the pylon.

[0052] From the various detailed examples above, it is clear that the suspension system is designed to maintain its function of connecting and transmitting force from the turbomachine to the pylon, even in the event of a component failure. For example: - if one half-cylinder of the cylindrical part 14 breaks, that is to say if there is a loss of connection between the half-cylinder and the turbomachine, then the other half-cylinder, which is not integral with the faulty half-cylinder, maintains the connection with the turbomachine, - if a part of beam 12 breaks, that is to say if there is a loss of connection between the part of beam and the pylon, then the other part of beam maintains the connection with the pylon, and the retaining ring and the retention ring where applicable maintain the connection with the ball joint nut by preserving the integrity of the ball joint housing.

Claims

Demands

1. Suspension assembly (11) for a turbomachine (10), comprising: - a beam (12) for its attachment to an aircraft pylon (13), the beam (12) comprising a first part (12a) and a second part (12b) each carrying a half-housing (16a, 16b) together defining a ball joint housing (17), - a ball joint nut (16) engaged and rotationally articulated in the ball joint housing (17), and - a cylindrical part (14) intended to be fixed to a fixed part (15) of the turbomachine (10), articulated in the ball joint housing (17), and pivotally mounted around its axis (X) in the ball joint nut (16), characterized in that the suspension assembly (11) further comprises a retaining ring (23) surrounding the two half-housings (16a, 16b) over their entire circumference, said retaining ring (23) being provided to implement a safety function in the event of failure of at least one element of the suspension assembly (11).

2. Suspension assembly (11) according to claim 1, wherein the beam (12) extends axially and wherein the two parts (12a, 12b) of the beam and the two half-housings (16a, 16b) are symmetrical with respect to each other, with respect to a radial plane and joined with respect to each other by fastening elements (50) arranged on the beam (12). [Claims] Suspension assembly (11) according to claim 2, in which the retaining ring (23) comprises two ring parts (23a, 23b) symmetrical with respect to each other and supported against each other by ring flanges (23c, 23d), said ring flanges (23c, 23d) being provided for fixing the two ring parts (23a, 23b) to each other.

4. Suspension assembly (11) according to claim 3 wherein the two ring parts (23a, 23b) are symmetrical to each other along the radial plane, the ring flanges (23c, 23d) being arranged radially internally and radially externally, and wherein each half-housing (16a, 16b) has ball joint housing flanges (16c, 16d) arranged radially internally and externally, the ring flanges (23c, 23d) and the ball joint housing flanges (16c, 16d) being provided for their common attachment.

5. Suspension assembly (11) according to claim 3 further comprising a retaining ring (24) and wherein the ball joint housing (17) is cylindrical and devoid of fixing elements, the retaining ring (24) being arranged on the outer circumference of the ball joint housing (17), and the retaining ring (23) being arranged on the outer circumference of the retaining ring (24), the two ring parts (23a, 23b) of the retaining ring (23) being symmetrical with respect to each other along an axial plane perpendicular to the radial plane, the ring flanges (23c, 23d) of the two ring parts (23a, 23b) extending axially along an axial direction (X).

6. Suspension assembly (11) according to any one of the preceding claims further comprising a ball joint ring (19) arranged against the inner circumference of the ball joint housing (18), the ball joint nut (16) being arranged in the ball joint ring (19).

7. Suspension assembly (11) according to claim 6, further comprising a vibration damping means (20) arranged radially between the ball joint ring (19) and the inner circumference of the ball joint housing (18).

8. Suspension assembly (11) according to any one of the preceding claims, wherein the cylindrical portion (14) comprises a first half-cylinder (14a) and a second half-cylinder (14b) arranged circumferentially end to end, and wherein the first half-cylinder (14a) comprises a first half-cylinder flange (21a) extending radially to the first half-cylinder (14a) and the second half-cylinder (14b) comprises a second half-cylinder flange (21b) extending radially to the second half-cylinder (14b), the first half-cylinder flange (21a) and the second half-cylinder flange (21b) comprising respectively a first fastening means (22a) and a second fastening means (22b) for the independent attachment of each half-cylinder (14a, 14b) to the fixed portion (15) of the turbomachine.

9. Aircraft assembly comprising a pylon (13) and a turbomachine (10), the turbomachine (10) comprising a fixed part (15), the aircraft assembly further comprising a suspension assembly (11) according to any one of claims 1 to 8.