SUSPENSION ARRANGEMENT FOR A TURBOMACH

Description

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

[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 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 both enclosed and unenclosed turbomachinery. Prior art is known from document WO 2020 / 074811 A1. Résumé

[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 defining together a ball joint housing, a ball joint nut engaged and articulated in rotation in the ball joint housing, and a cylindrical part intended to be attached to a fixed part of the turbomachine, articulated in the ball joint housing, and mounted pivotally about its axis in the ball joint nut, in which the suspension assembly further comprises a retaining ring surrounding the two half-housings over their entire circumference, said retaining ring being provided 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] 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.

[0019] 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 fastening of each half-cylinder to the fixed part of the turbomachine.

[0020] 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.

[0021] 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.

[0022] According to 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. Brève description des dessins

[0023] Other features, details, and advantages will become apparent upon reading the detailed description below and analyzing the attached drawings, on which: Fig. 1 [ Fig. 1 ] there figure 1 is an overview of a turbomachine attached to an aircraft pylon via a suspension assembly. Fig. 2A [ Fig. 2A ] there figure 2A is a perspective view of a suspension system according to a first example of implementation. Fig. 2B [ Fig. 2B ] there figure 2B is a perspective and exploded view of the whole of the figure 2A . Fig. 3A [ Fig. 3A ] there figure 3A is a perspective view of a suspension assembly according to a second example of implementation. Fig. 3B [ Fig. 3B ] there figure 3B is a perspective and exploded view of the whole of the figure 3A . Fig. 4A [ Fig. 4A ] there figure 4A is a perspective view of a suspension assembly according to a third example of implementation. Fig. 4B [ Fig. 4B ] there figure 4B is a perspective and exploded view of the whole of the figure 4A . Fig. 5 [ Fig. 5 ] there figure 5 is a cross-sectional view along a radial plane of an alternative embodiment of the suspension assembly. Description des modes de réalisation

[0024] There 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.

[0025] In the following description, the terms radial and axial are defined with respect to the axis of the turbomachine, denoted L on the figure 1 .

[0026] THE figures 2A, 2B , 3A, 3B , 4A et 4B illustrate different examples of the realization 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.

[0027] 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 distributed in 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. Therefore, the beam is separated into two parts so as to keep at least one part of the beam intact in case of failure of the other part of the beam.

[0028] 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.

[0029] 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.

[0030] According to an alternative, as illustrated in the figure 5 The suspension assembly 11 may further include a vibration damping element 20. The vibration damping element 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 element may be interposed between the ball joint housing 17 and the ball joint ring 19. The vibration damping element 20 limits vibrations and their structural and acoustic consequences. It is characterized by its high elasticity and deformation capacity. The vibration damping element 20 is, for example, a flexible annular element of the elastomer type. The vibration damping element 20 reduces the vibrations transmitted from the turbomachine to the aircraft pylon.

[0031] 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 enables 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 specifically, according to the figures, the first half-cylinder 14a and the second half-cylinder 14b can be symmetrical with respect to each other, along a radial plane of symmetry, passing through the X axis and the axis marked Z.Alternatively, the first half-cylinder 14a and the second half-cylinder 14b can be symmetrical to each other along a plane of axial 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 a plane of axial 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.

[0032] The first half-cylinder 14a and the second half-cylinder 14b each comprise a first half-cylinder flange 21a and a second half-cylinder flange 21b, respectively. 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 a first fastening means 22a and a second fastening means 22b, respectively. 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.

[0033] Furthermore, the suspension assembly 11 includes a retaining ring 23. The retaining ring 23 is designed to provide a safety function in the event of a failure of at least one element of the suspension assembly 11. Alternatively, the suspension assembly 11 also includes a retention ring 24. The retaining ring 23 and the retention ring 24 are described with reference to the alternative embodiments shown in the figures 2A, 2B , 3A, 3B , 4A et 4B .

[0034] As illustrated in figures 2A et 2B The suspension assembly 11 includes the retaining ring 23 and the retention ring 24. The retention ring 24 is designed to keep the two half-housings 16a, 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 connection between that section and the pylon, the first section 12a and the second section 12b, and in particular the two half-housings 16a, 16b, can separate from each other, causing the ball joint housing 17 to open. Therefore, there is 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 in the ball joint housing 17, and the cylindrical part 19 loses its connection with the pylon. Consequently, the turbomachine 10 is 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 withstand, i.e., not break, up to a load limit, 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 part of the beam 12, this failed part no longer fulfilling its force-transmission function.More specifically, 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 load. The retaining ring 24 is capable of fulfilling its load-absorbing function at least until the next mechanical inspection of the suspension assembly 11. The retaining ring thus prevents a sudden failure of the connection between the turbomachine and the pylon by maintaining a sufficient load level until the aircraft's next inspection. Furthermore, the retaining ring 24 can be annular or ring-shaped. Advantageously, its inner surface is complementary to the outer surface of the ball joint housing, and the outer surface of the retaining ring can be complementary to the inner surface of the retaining ring 23.

[0035] The suspension assembly 11 of the figures 2A et 2B It also includes the retaining ring 23. The retaining ring 23 comprises two ring parts 23a, 23b. The two ring parts 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, on the figure 2B The plane of symmetry of the two ring parts 23a, 23b is perpendicular to the plane of symmetry of the two beam parts 12a, 12b. The two ring parts 23a, 23b are supported against each other by ring flanges 23c, 23d. The ring flanges 23c, 23d are provided for fixing the two ring parts 23a, 23b to each other. The ring flanges 23c, 23b extend axially along the direction of 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, particularly at the ball joint housing 17. The retaining ring 23 effectively reinforces the retaining ring 24 to ensure load transfer in the event of a failure of the retaining ring 24.The retaining ring 23 can thus be described as a secondary load-bearing ring, while the retaining ring 24 can be described as a primary load-bearing ring.

[0036] THE figures 3A et 3B , illustrate another example of the implementation of the suspension assembly 11. This example is identical to the example previously described with reference to the figures 2A et 2B The difference is that the retaining ring 23 is a single piece, meaning it is one unit. This configuration has the advantage of being more compact than the previous example, as there are no flanges or fasteners.

[0037] THE figures 4A et 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, on the 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 radially internally and radially externally, respectively, with respect to the L-axis of the turbomachine. Furthermore, each half-housing 16a, 16b has 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 are designed for common attachment. Compared to the example of the figures 2A et 2B , the two ring parts 23a, 23b are not supported against each other by the ring flanges 23c, 23d. On the contrary, in the example illustrated in figures 4A et 4BThe ring flanges 23c, 23d bear against the ball joint housing flanges 16c, 16d, and the two half-housings 16a, 16b are held together 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 held between the two ring flanges 23c, and the ball joint housing flanges 16d are held between the two ring flanges 23d. Fastening means on the flanges, such as a screw and nut assembly, join the two ball joint housing halves 16a, 16b and the two ring halves 23a, 23b. This configuration, and in particular the common fixings of the flanges 23c, 23d, 16c, 16d together, 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.

[0038] 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 a half-cylinder of the cylindrical part 14 breaks, i.e., 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 failed half-cylinder, maintains the connection with the turbomachine; if a beam part 12 breaks, i.e., if there is a loss of connection between the beam part and the pylon, then the other beam part maintains the connection with the pylon, and the retaining ring and the retaining ring, if applicable, maintain the connection with the ball joint nut by preserving the integrity of the ball joint housing.

Claims

1. Suspension assembly (11) for a turbine engine (10), 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) which together define a ball joint housing (17), - a ball joint nut (16) hingedly engaged to rotate in the ball joint housing (17), and - a cylindrical part (14) intended to be attached to a fixed portion (15) of the turbine engine (10), hinged in the ball joint housing (17) and mounted so as to be pivotable about its axis (X) in the ball joint nut (16), characterized in that the suspension assembly (11) further comprises a support ring (23) surrounding the two half-housings (16a, 16b) around their entire circumference, said support ring (23) being provided to perform 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 portions (12a, 12b) of the beam and the two half-housings (16a, 16b) are symmetrical to each other with respect to a radial plane and are secured to each other by fastening elements (50) arranged on the beam (12).

3. Suspension assembly (11) according to claim 2, wherein the support ring (23) comprises two ring portions (23a, 23b) which are symmetrical to each other and which bear against each other via ring flanges (23c, 23d), said ring flanges (23c, 23d) being provided for fastening the two ring portions (23a, 23b) together.

4. Suspension assembly (11) according to claim 3, wherein the two ring portions (23a, 23b) are symmetrical to each other according to the radial plane, the ring flanges (23c, 23d) being arranged radially internally and radially externally, and wherein each half-housing (16a, 16b) comprises 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 joint 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 without fastening elements, the retaining ring (24) being arranged on the outer circumference of the ball joint housing (17), and the support ring (23) being arranged on the outer circumference of the retaining ring (24), the two ring portions (23a, 23b) of the support ring (23) being symmetrical to each other according to an axial plane perpendicular to the radial plane, the ring flanges (23c, 23d) of the two ring portions (23a, 23b) extending axially in 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 (18) of the ball joint housing, the ball joint nut (16) being arranged in the ball joint ring (19).

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

8. Suspension assembly (11) according to any one of the preceding claims, wherein the cylindrical part (14) comprises a first half-cylinder (14a) and a second half-cylinder (14b) which are arranged end-to-end circumferentially, 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) respectively comprising a first attachment means (22a) and a second attachment means (22b) for the independent attachment of each half-cylinder (14a, 14b) to the fixed portion (15) of the turbine engine.

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