Structure for connecting and fastening a turbomachine to an aircraft pylon

Description

Domaine technique de l'invention

[0001] The present invention relates to a structure for connecting and supporting a turbomachine to an aircraft pylon. Arrière-plan technique

[0002] The state of the art includes in particular documents FR-A1-2 892 706, FR-A1-2 969 700, FR-A1-2 987 347, FR-A1-2 987 401, FR-A1-3 015 434, FR-A1-3 058 127, US-B1-6,474,597, US-B2-7,232,091, US-A-5,452,575 and US-A1-2008 / 156930. Document US-B1-6,474,597 discloses a connecting and supporting structure of a turbomachine, with a first axial portion for attachment to the pylon, which is sandwiched between the pylon and a main support. Suspension rods are used to secure the turbomachine in the event of failure of the main connecting structure. The suspension rods are attached to the first axial portion by transverse lugs that form part of an upper end of the first axial portion.

[0003] An aircraft turbomachine comprises a gas generator which conventionally comprises, from upstream to downstream, with reference to the flow of gases in the turbomachine, at least one compressor, an annular combustion chamber and at least one turbine. In the case of a twin-spool turbojet engine, respectively low pressure and high pressure, the gas generator successively comprises a low pressure compressor, a high pressure compressor, the combustion chamber, the high pressure turbine and the low pressure turbine. The gas generator defines an annular flow vein for a gas flow, called the primary flow, which passes through the compressors, the combustion chamber and the turbines.

[0004] The rotor of the high-pressure compressor is connected to the rotor of the high-pressure turbine by a high-pressure shaft. The rotor of the low-pressure compressor is connected to the rotor of the low-pressure turbine by a low-pressure shaft which passes through the high-pressure shaft and which rotates a propulsion propeller generally located upstream of the gas generator.

[0005] When this propeller is shrouded and therefore surrounded by an annular casing, this propeller is called a fan and generates an airflow that flows around the gas generator and is called a secondary flow. When the propeller is not shrouded, it also generates an airflow that flows around the gas generator.

[0006] The turbomachine is attached to an element of the aircraft, such as a wing or the fuselage, by means of a mounting pylon also called a mast. This pylon generally has an elongated general shape and includes a beam which extends parallel to the longitudinal axis of the turbomachine. In the case where the turbomachine is attached under a wing of the aircraft, the pylon is located at 12 o'clock (12 o'clock) by analogy with the face of a clock.

[0007] In the current technique, the pylon comprises upstream members for fixing and suspending the turbomachine which are dedicated to one type of turbomachine and which cannot be used for another type of turbomachine. These fixing members are for example intended to be fixed on a fan casing of a turbomachine, which surrounds the fan propeller, and which therefore cannot be used for a turbomachine with an unducted propeller because this turbomachine does not have a fan casing.

[0008] Furthermore, the attachment pylon may comprise downstream members for attaching and suspending the downstream end of a turbomachine. However, this configuration has drawbacks. Indeed, in operation, the gas generator ensures a transmission of forces between the upstream and downstream attachment points to the pylon, which result in deformations of the generator and gas and in modifications of the clearances between the rotors and the stators of the gas generator. The gas generator is thus subjected to a moment generated by the axial forces (off-axis thrust and thrust recovery). The turbomachine is also subjected to a moment generated by the asymmetry of axial forces on the blades of the fan propeller, and to forces originating from the air capture (stem forces) by the turbomachine. It is therefore understood that the performance and operability of the turbomachine can be affected by these forces.

[0009] One solution to this problem would be to cantilever the turbomachine to the pylon. This would mean suspending a front or upstream part of the turbomachine from the pylon and leaving the rear or downstream part of the turbomachine, such as its turbine casing, free.

[0010] Another issue is hoisting the turbomachine from a ground-based storage station to the pylon to which the turbomachine is to be attached. Hoisting a turbomachine may require movement in several directions until the turbomachine reaches the pylon and can be attached to the pylon.

[0011] The present invention provides an improvement to current technologies, which makes it possible to resolve at least some of the problems and drawbacks mentioned above. Résumé de l'invention

[0012] The invention relates to a structure for connecting and supporting a turbomachine to an aircraft pylon, the structure having a generally elongated shape and having a first axis of elongation intended to extend parallel to a second axis of elongation of the pylon, the structure comprising: a first axial portion for attachment to the pylon, this first portion comprising an upper end which defines a substantially horizontal plane of interface with the pylon, and a lower end carrying suspension rods which are intended to be connected to the turbomachine and which extend in a first substantially vertical plane, called the rear plane, and a second axial portion intended to extend in front of the pylon and comprising at least one suspension member which is intended to be connected to the turbomachine and which extends in a second substantially vertical plane, called the front plane, this front plane being at an axial distance from the rear plane.

[0013] The connecting structure according to the invention has a double advantage. The first advantage is that it allows the turbomachine to be suspended in two planes, respectively front and rear. In other words, the front and rear suspensions of the turbomachine are brought together and integrated within the structure, which allows for a single suspension structure for the turbomachine. The structure is preferably connected to an upstream part of the turbomachine, such as an intermediate casing. The turbomachine is then intended to be mounted cantilevered on the pylon since it does not include a downstream part, such as a turbine casing, intended to be connected to the pylon.

[0014] A second advantage of the invention is related to the hoisting of the turbomachine, which is facilitated by the connecting structure. This connecting structure comprises a horizontal interface plane which defines a docking zone of the pylon. When hoisting the turbomachine, it can simply be moved in a single vertical direction from bottom to top, until the structure is resting on the pylon in this plane. The structure is then fixed to the pylon. Furthermore, the second portion is advantageously connected directly to the root of the blade to facilitate the integration of the connecting structure into the turbomachine.

[0015] The structure according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another: said at least one suspension member is located at a free front end of the second portion; said at least one suspension member is a snout which comprises: a connecting rod for attachment to the turbomachine, which extends in said front plane, and a cylindrical body which is engaged in a housing of the free end of the second portion and which is capable of pivoting in this housing around an axis parallel to said first axis of elongation; the first portion carries three suspension connecting rods in said rear plane, these three connecting rods comprising: two lateral connecting rods extending respectively on one side and the other of the first portion, symmetrically with respect to a vertical median plane passing through said first axis of elongation, and a central connecting rod located under the first portion; the first portion has a length L1 measured along the first axis of elongation, which is less than or equal to a length L2 of the second portion measured along this axis;alternatively, L1 is greater than or equal to L2; the second portion comprises an upper platform for fixing at least one root of a rectifier blade; -- the second portion carries a root blank of a rectifier blade; -- the or each rectifier blade is a fixed blade or a variable-pitch blade; the second portion carries a root blank configured to be at the root of a rectifier blade; the rectifier blade being variable-pitch, the structure comprises a mechanism for guiding the root of the blade and / or an actuation system; said front plane is located upstream or in line with the leading edges of the blades, and the rear plane is located downstream of the trailing edges of the blades. ;

[0016] The present invention also relates to an assembly comprising an aircraft turbomachine and a connecting structure as described above, the turbomachine being configured to be mounted cantilevered on a pylon using this connecting structure.

[0017] The assembly according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in combination with one another: said structure has a generally elongated shape, the turbomachine has a longitudinal axis and comprises a gas generator comprising from upstream to downstream, in the direction of gas flow, at least one compressor, an annular combustion chamber and at least one turbine, the gas generator defining a main annular flow vein for a first air flow, and the gas generator being intended to be surrounded by a secondary annular flow vein for a second air flow, the gas generator driving a propeller located upstream of the main and secondary veins, the connecting structure being fixed to the gas generator, downstream of the propeller, so that its axis of elongation is located at a radius measured relative to the longitudinal axis, which is between the minimum radius and the maximum radius of the propeller; said turbomachine is of the shrouded or unshrouded type, said secondary vein is shrouded or unshrouded;said propeller is located upstream of the main and secondary veins; alternatively, the propeller is located downstream of these veins; the connecting structure is fixed to the gas generator downstream of the propeller; alternatively, the connecting structure is fixed to the gas generator upstream of the propeller; the turbomachine comprises an annular row of stator blades which is located downstream of the propeller in the secondary vein, the second portion of the structure being located between two adjacent blades of this row of blades or carrying one of the blades of this row of blades; the stator blades are fixed blades or variable-pitch blades; the stator blades are located downstream of the propeller in the secondary vein; said front plane is located upstream or in line with the leading edges of the blades of the row of blades, and / or said rear plane is located downstream of the trailing edges of the blades of the row of blades;the assembly further comprises a pylon having a second axis of elongation and comprising a front end for attachment to the first portion of the structure; the assembly further comprises thrust recovery bars, these bars comprising front ends attached to the gas generator and rear ends connected to a spreader bar attached to the pylon, behind the structure.; Brève description des figures

[0018] Other characteristics and advantages of the invention will appear during the reading of the detailed description which follows for the understanding of which reference will be made to the appended drawings in which: [ Fig.1 ] there figure 1 is a very schematic view of an assembly comprising an aircraft turbomachine and its attachment pylon, according to the technique prior to the invention; [ Fig.2 ] there figure 2 is a very schematic view of an aircraft turbomachine and shows points of attachment and suspension to a suspension pylon, according to the technique prior to the invention; [ Fig.3 ] there figure 3 is a very schematic view of another aircraft turbomachine and shows points of attachment and suspension to a suspension pylon, according to the technique prior to the invention; [ Fig.4 ] there figure 4 is a schematic perspective view of an assembly comprising an aircraft turbomachine, a mounting pylon, and a structure for connecting the turbomachine to the pylon, according to a preferred embodiment of the invention; [ Fig.5 ] there figure 5 is a schematic side view of the pylon and the connecting structure of the figure 4 ; [ Fig.6 ] there figure 6 is a schematic perspective view of a front suspension member of the connecting structure of the figure 4 ; [ Fig.7 ] there figure 7 is another schematic perspective view of the front suspension member of the connecting structure of the figure 4 ; [ Fig.8 ] there figure 8 is a schematic perspective view of rear suspension connecting rods of the connecting structure of the figure 4 ; [ Fig.9 ] there figure 9 is a schematic front view of a part of the turbomachine and the connecting structure of the figure 4 ; [ Fig.10 ] there figure 10 is a schematic top view of a part of the turbomachine and the connecting structure of the figure 4 ; [ Fig.11 ] there figure 11 is a view similar to that of the figure 9 and representing an alternative embodiment of the invention; [ Fig.12 ] there figure 12 is a view similar to that of the figure 10 and representing the same variant embodiment of the invention; [ Fig.13 ] there figure 13 is a schematic side view of the connecting structure of the figure 4 during a hoisting stage towards the pylon; and [ Fig.14 ] there figure 14 is a schematic perspective and front view of the connecting structure and the pylon of the figure 4 , and illustrate the moments which apply in operation at the connection points of the structure to the turbomachine. Description détaillée de l'invention

[0019] There figure 1 shows a turbomachine 10 for an aircraft, this turbomachine 10 here being a double-flow, double-spool turbojet.

[0020] The A axis designates the longitudinal axis of the turbomachine. The orthonormal XYZ coordinate system is represented in certain figures including the figure 1 The X direction is parallel to the X axis and oriented upstream or forward of the turbomachine 10, the Y axis is oriented upward, and the Z axis is oriented to one side.

[0021] The turbomachine 10 comprises a gas generator 12 which comprises from upstream to downstream with reference to the flow of gases along the axis A, a LP 14 or low pressure compressor, an HP 16 or high pressure compressor, an annular combustion chamber 18, an HP 20 or high pressure turbine and a LP 22 or low pressure turbine.

[0022] Although this is not visible in the figure 1 , the rotor of the HP compressor 16 is connected to the rotor of the HP turbine 20 by a high pressure shaft, and the rotor of the LP compressor 14 is connected to the rotor of the LP turbine 22 by a low pressure shaft which passes through the high pressure shaft and which drives in rotation a propulsion propeller located upstream of the gas generator 12 and which is surrounded by an annular casing called fan casing 24.

[0023] The fan casing 24 is connected to the gas generator 12 by an intermediate casing 26 which comprises a central hub 28 and a series of radial arms connecting the hub 28 to the fan casing 24.

[0024] The gas generator 12 defines a main annular flow vein for a first air flow, called the primary flow. The gas generator 12 is surrounded by a secondary annular flow vein for a second air flow, called the secondary flow.

[0025] The air flow entering the blower is divided into a part forming the primary flow. The air of this primary flow is compressed in the LP 14 and HP 16 compressors, then mixed with fuel and burned in the combustion chamber 18. The combustion gases of the primary flow are then expanded in the HP 20 and LP 22 turbines and finally flow into an exhaust nozzle 30.

[0026] The other part of the air flow entering the blower forms the secondary flow which flows around the gas generator 12 and which is intended to be mixed with the primary flow downstream of the nozzle 30.

[0027] The turbomachine 10 is fixed to an element of the aircraft by means of a pylon 32 which has a general elongated shape along the axis A and therefore comprises an elongation axis B parallel to the axis A. The pylon 32 comprises members 34, 38 for fixing and suspending the turbomachine 10.

[0028] THE figures 1 à 3 illustrate the state of the art prior to the present invention.

[0029] In the first case illustrated in figures 1 et 2 , there are three points or areas of attachment of the pylon 32 to the turbomachine 10. Two of the points are located in an upstream or front plane P1 perpendicular to the axis A and the last point is located in a downstream or rear plane P2 perpendicular to the axis A.

[0030] At the plane P1, a first fixing member 34 ensures the connection of the pylon 32 to the fan casing 24. At the plane P2, the fixing member 38 ensures the connection of the pylon 32 to a turbine or exhaust casing 40. This fixing member 38 is further connected by thrust recovery bars 36 to the hub 28 of the intermediate casing 26. These bars 36 ensure the transmission of the thrust from the turbomachine 10 to the pylon 32 and therefore to the aircraft.

[0031] In the second case illustrated in the figure 3 , there are only the two fixing points in the aforementioned plane P1, and therefore the turbomachine is fixed in cantilever to the pylon 32. In this case, at the level of the plane P1, the fixing member 34 ensures the connection of the pylon 32 to the fan casing 24, and thrust recovery connecting rods 36 ensure the connection of the hub 28 of the intermediate casing 26 to the pylon 32, by means of a fixing member (not shown) which is fixed to the pylon without being fixed to the turbomachine.

[0032] There figure 4 illustrates a preferred embodiment of the invention which relates to a connecting structure 50 and cantilever fixing of an aircraft turbomachine 10 to a pylon 32.

[0033] The turbomachine 10 is partially illustrated in the figure 4 and the foregoing description in relation to the figure 1 can be applied to the turbomachine 10 of the figure 4 except with regard to the attachment of the turbomachine 10 to the pylon 32. In this figure, the fan casing 24 is not shown because the invention applies to a propeller 52 which is faired by such a casing 24 to form a fan, or which on the contrary is not faired.

[0034] The propeller 52 comprises blades which extend radially relative to the axis A of the turbomachine 10. The blades of the propeller 52 extend between a minimum radius Rmin measured at the blade roots from the axis A, and a maximum radius Rmax measured from the tips of the blades from the axis A. As mentioned above, the air flow F1 which passes through the propeller 52 is divided downstream of the propeller 52 into a primary flow F2 which flows into the gas generator 12, and into a secondary flow F3 which flows around the gas generator 12.

[0035] Downstream of the propeller 52, the turbomachine 10 comprises fixed rectifier vanes 54, commonly called OGV (acronym for Outer Guide Vanes ). These blades 54 extend radially relative to the axis A from a shell of the intermediate casing 26.

[0036] The pylon 32 has its elongation axis B parallel to the axis A and its upstream or front end is located downstream of the trailing edges 54b of the blades 54. The pylon 32 has its front end 32a which is located at or above the intermediate casing 26.

[0037] A specific feature of the assembly is linked to the position of the pylon 32 in relation to the secondary flow F3. Unlike the prior art of the figure 1 where the pylon 32 extends radially from the gas generator 12, the pylon 32 of the figure 4 extends as close as possible to the gas generator 12. The elongation axis B is thus located at a radius from the axis A, which is between Rmin and Rmax.

[0038] As mentioned above in relation to the figure 3 , the turbomachine 10 which is fixed in a cantilever manner to the pylon 32 is connected to the latter by thrust recovery bars 36.

[0039] The two bars 36 are arranged symmetrically with respect to a vertical median plane passing through the axis A. They each comprise front ends 36a fixed to the gas generator 12, for example at the intermediate casing 26, and rear ends 36b connected to a lifting beam 56 fixed to the pylon 32, at a distance from its axial end 32a. The ends 36a, 36b of the connecting rods 36 are preferably articulated by ball joints, respectively to clevises secured to the intermediate casing 26, and to clevises secured to the lifting beam 56.

[0040] The turbomachine 10 is fixed and suspended from the pylon 32 by means of a single connecting structure 50 which defines two planes, respectively front P1 and rear P2, for suspending the turbomachine from the pylon.

[0041] As can be seen in the figure 4 , the connecting structure 50 is located at the level of the front end 32a of the pylon 32, so that the rear suspension plane of the turbomachine 10 is brought closer towards the front and to the front plane P1, which allows the cantilever mounting of the turbomachine 10.

[0042] We now refer to the figures 5 à 8 which allow us to better see the characteristics of the 50 link structure.

[0043] The connecting structure 50 has a generally elongated shape and has an elongation axis C parallel to the axes A, B.

[0044] Structure 50 essentially comprises two axial portions, namely: a first axial portion 50a for attachment to the pylon 32, which is a rear portion, and a second axial portion 50b intended to extend in front of the pylon 32 and which is therefore a front portion.

[0045] Although this is not limiting, the figure 5 shows that the first portion 50a has a length L1 measured along the axis C, which is less than or equal to the length L2 of the second portion 50b measured along this axis.

[0046] The first portion 50a comprises an upper end 60 which defines a substantially horizontal plane P3 of interface with the pylon 32.

[0047] This first portion 50a further comprises a lower end carrying suspension rods 62, 64 which are intended to be connected to the turbomachine 10 and which extend in the rear plane P2.

[0048] The second portion 50b comprises at least one suspension member 66 which is intended to be connected to the turbomachine 10 and which extends in the front plane, P1.

[0049] The connecting structure 50 may be formed from a single piece or from several assembled pieces. Advantageously, it comprises a main beam 68 which forms the first portion 50a and an upper part of the second portion 50b. The lower part of the second portion 50b is then formed by a structural part 70 added and fixed under the beam 68, as shown in figure 7 , but which can be integrated into this beam 68. The interface plane P4 between the beam 68 and the part 70 can be substantially horizontal.

[0050] The suspension member 66 is located at a free front end of the second portion 50b and is here formed by a snout which comprises: a flange 72 for attachment to the turbomachine 10, which extends in said front plane P1, and a cylindrical body 74 which is engaged in a housing 76 of the free end of the second portion 50b, and in particular in the part 70. The body 74 is able to pivot in this housing 76 around an axis D parallel to the elongation axis C. It is thus understood that, in the front plane P1, the connecting structure 50 is connected to the turbomachine 10 by a sliding pivot connection allowing rotational movements around the axis D.

[0051] The member 66 may be configured to allow a degree of freedom to the turbomachine 10 along the X axis. In other words, the member 66 may not be configured to take up the forces of the turbomachine 10 and transmit them to the pylon 32 in the X direction. The member 66 is therefore advantageously configured to take up the forces in the Y and Z directions.

[0052] In the example shown, the connecting structure 50 comprises three suspension rods 62, 64 in the rear plane P2, among which: two lateral connecting rods 62 extending respectively on one side and the other of the first portion 50a, symmetrically with respect to a vertical median plane passing through the axis C, and a central connecting rod 64 located under the first portion 50a.

[0053] The connecting rods 62, 64 have their ends which are articulated by ball joints respectively to yokes 78 secured to the gas generator (in particular at the level of the intermediate casing), and to the portion 50a.

[0054] The connecting rods 62, 64 are configured to take up and transmit the forces applied to the turbomachine in the Y and Z directions and the moments along the X direction. figure 14 shows that the forces in the Y and Z directions are taken up by the connecting rods 62 (arrows F6), and that the connecting rod 64 takes up the moments in the X direction (arrow F7).

[0055] The thrust recovery connecting rods 36 take up the forces in the X direction.

[0056] As can be seen in the figure 4 in particular, the connecting structure 50 extends forward in the extension of the pylon 32 and is fixed to the gas generator 12, downstream of the propeller 52, so that its elongation axis C is located at a radius measured relative to the axis A, which is between the radii Rmin and Rmax.

[0057] The front portion 50b of the structure 50 is located at the level of the fixed blades 54 and two configurations are then possible.

[0058] According to a first configuration illustrated in figures 5 , 9 et 10 , the front portion 50b of the structure 50 carries one of the blades 54.

[0059] In this case, the front portion 50b comprises an upper platform 79 configured to be connected or secured to a blade 54, in particular to the one located at 12 o'clock. In practice, this upper platform 79 can carry a root blank 80 configured to be fixed to the root of a blade 54.

[0060] According to another configuration illustrated in figures 11 et 12 , the front portion 50b of the structure 50 is located between two adjacent blades 54.

[0061] In a variant not shown, the blades 54 are of the variable pitch type and are therefore each capable of being angularly positioned around a radial axis with a precise angle. In this case, the structure 50 may comprise a mechanism for guiding the root of the blade 54, such as a bearing, and / or an actuation system comprising, for example, connecting rods, a gear, an actuator, etc.

[0062] In yet another variant not shown, the structure 50 could support two or more blades 54.

[0063] There figure 5 allows to see that, in the example shown, the front plane P1 is located upstream or in line with the leading edges 54a of the blades 54, and the rear plane P2 is located downstream of the trailing edges 54b of the blades 54 and is intended to pass at the level of the intermediate casing of the turbomachine.

[0064] There figure 13 illustrates a step and a method of hoisting a turbomachine 10 equipped with the connecting structure 50 to the pylon 32.

[0065] Although the turbomachine is not shown in this drawing, it should be understood that the structure 50 is previously fixed to the turbomachine, that is to say that the flange 72 of its member 66 is fixed to a complementary flange of the gas generator 12, upstream or in line with the leading edges 54a of the blades 54, as mentioned above, and the connecting rods 62, 64 are also fixed to the gas generator. The structure 50 therefore has the advantage of being able to be fixed to the turbomachine in the assembly line of the latter. The thrust recovery connecting rods 36 can also be fixed to the turbomachine 10.

[0066] The turbomachine can be moved on the ground using a trolley or suspended and moved using one or more hoists.

[0067] The turbomachine is positioned under the pylon 32 so that the axes B and C are parallel and the portion 50a of the structure 50 is located just below the pylon 32, as illustrated in figure 13 The turbomachine is then hoisted towards the pylon 32, by a single vertical translational movement from bottom to top (arrows F5), until the portion 50a and the pylon are supported in the interface plane P3.

[0068] The structure 50 can then be fixed to the pylon 32, for example by screw-nut type means or the like. The spreader 56 fixed to the connecting rods 36 can also be fixed to the pylon behind the structure 50, as illustrated in figure 5 .

Claims

1. A structure (50) for linking and supporting a turbine engine (10) to an aircraft pylon (32), the structure (50) having a first axis of elongation (C) intended to extend parallel to a second axis of elongation (B) of the pylon (32), the structure (50) comprising: - a first axial segment (50a) for fastening to the pylon (32), this first segment (50a) comprising an upper end which defines a substantially horizontal plane (P3) of interface with the pylon (32), and a lower end carrying suspension connecting rods (62, 64) which are intended to be connected to the turbine engine (10) and which extend in a first substantially vertical plane, referred to as the rear plane (P2), and - a second axial segment (50b) which is intended to extend in front of the pylon (32) and comprising at least one suspension member (66) which is intended to be connected to the turbine engine (10) and which extends in a second substantially vertical plane, referred to as the front plane (P1), this front plane being at an axial distance from the rear plane (P2).

2. The linking structure (50) according to claim 1, wherein said at least one suspension member (66) is located at a free front end of the second segment (50b).

3. The linking structure (50) according to claim 2, wherein said at least one suspension member (66) is a snout which comprises: - a connecting rod (72) for fastening to the turbine engine (10), which extends in said front plane (P1), and - a cylindrical body (74) which is engaged in a housing (76) of the free end of the second segment (50b) and which is able to pivot in this housing about an axis (D) parallel to said first axis of elongation (C).

4. The linking structure (50) according to one of the preceding claims, wherein the first segment (50a) carries three suspension connecting rods (62, 64) in said rear plane (P2), these three connecting rods comprising: - two lateral connecting rods (62) extending respectively on either side of the first segment (50a), symmetrically with respect to a vertical median plane passing through said first axis of elongation (C), and - a central connecting rod (64) located under the first segment (50a).

5. The linking structure (50) according to one of the preceding claims, wherein the second segment (50b) comprises an upper platform (79) for fastening at least one root of a rectifier vane (54).

6. The linking structure (50) according to one of the preceding claims, wherein, the rectifier vane (54) being of variable pitch, the structure (50) comprises a mechanism for guiding the root of the vane (54) and / or an actuation system.

7. The linking structure (50) according to one of the preceding claims, wherein said front plane (P1) is located upstream of or perpendicular to the leading edges (54a) of the vanes (54), and the rear plane (P2) is located downstream of the trailing edges (54b) of the vanes (54).

8. An assembly comprising an aircraft turbine engine (10) and a linking structure (50) according to one of the preceding claims, the turbine engine (10) being configured to be mounted in a cantilevered manner on a pylon (32) by means of this linking structure (50).

9. The assembly according to the preceding claim, wherein the turbine engine (10) has a longitudinal axis (A) and comprises a gas generator (12) comprising, from upstream to downstream, in the direction of flow of the gases, at least one compressor (14, 16), an annular combustion chamber (18) and at least one turbine (20, 22), the gas generator defining a main annular duct for the flow of a first air flow, and the gas generator (12) being intended to be surrounded by a secondary annular duct for a second air flow, the gas generator (12) driving a propeller (52) and the linking structure (50) being fastened to the gas generator (12) so that its axis of elongation (C) is located at a radius measured with respect to the longitudinal axis, which is between the minimum radius (Rmin) and the maximum radius (Rmax) of the propeller (52).

10. The assembly according to claim 8 or 9, wherein the turbine engine (10) comprises an annular row of rectifier vanes (54) which is located in the secondary duct, the second segment (50b) of the structure (50) being located between two adjacent vanes (54) of that row of vanes or carrying one of the vanes (54) of that row of vanes.

11. The assembly according to the preceding claim, wherein said front plane (P1) is located upstream of or perpendicular to leading edges (54a) of the vanes (54) of the row of vanes, and / or said rear plane (P2) is located downstream of trailing edges (54b) of the vanes (54) of the row of vanes.

12. The assembly according to one of claims 8 to 10, wherein it further comprises a pylon (32) having a second axis of elongation (B) and comprising a front end (32a) for fastening to the first segment (50a) of the structure (50).