An assembly including an aircraft turbine engine and a mounting pylon for the aircraft turbine engine

Abstract

The invention relates to an assembly (1) comprising a turbine engine (2) of an aircraft, a hanger (40) for mounting the turbine engine on an element of the aircraft, and a system for suspending the turbine engine on the hanger, the turbine engine having a longitudinal axis (X) and comprising, in the gas flow direction from upstream to downstream: > a fan casing (11) centered on the longitudinal axis (X) and having a first axial end (12) upstream of a fan (10), and > a gas generator (16) configured to receive the air flow generated by the fan, the hanger (40) having a substantially elongated shape along the longitudinal axis (X) and being adapted to be attached to an element of the aircraft, characterized in that the suspension system comprises at least one intake force-bearing link (30, 30a, 30b), a first end (31, 31a, 31b) of the at least one intake force-bearing link being connected to an attachment point (11a, 11b) of the fan casing (11), the attachment point being located on the first axial end or on an upstream section of the fan casing, a second opposite end (32, 32a, 32b) of the at least one intake force-bearing link being connected to said hanger.

Description

Technical Field

[0001] This invention relates to an assembly comprising an aircraft turbine engine and its mounting bracket. Background Technology

[0002] An aircraft turbine engine includes a gas generator, which typically comprises at least one compressor, a combustion chamber, and at least one turbine from upstream to downstream of the gas flow in the turbine engine. In the case of a low-pressure and high-pressure dual-body turbojet engine, the gas generator includes a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine. The gas generator includes a main annular duct for directing the main gas flow through the compressor, combustion chamber, and turbine.

[0003] The rotor of the high-pressure compressor is connected to the rotor of the high-pressure turbine via a high-pressure shaft. The rotor of the low-pressure compressor is connected to the rotor of the low-pressure turbine via a low-pressure shaft that passes through the high-pressure shaft and drives the propeller blades / propeller, which is typically located upstream of the gas generator, to rotate.

[0004] When the blade / propeller is a ducted propeller and is surrounded by an annular casing, the blade / propeller is referred to as a fan and generates an airflow that flows around the gas generator. The annular casing, referred to as the fan casing, is located radially outside the gas generator relative to the longitudinal axis of the turbine engine, and together with the gas generator, defines a secondary duct for the flow of the secondary airflow.

[0005] The fan housing includes a fan housing and an intake housing, the latter located downstream of the fan housing and connecting the fan housing to the gas generator. The intake housing typically includes a hub centered on the longitudinal axis of the turbine engine and an annular housing arranged coaxially around the hub. The annular housing is attached downstream of the intake housing and, together with the hub, defines a section of secondary ductwork.

[0006] The turbine engine also includes a compressor housing that extends between two consecutive compressors of the gas generator, or around all or part of one or more compressors of the gas generator, such as between a low-pressure compressor and a high-pressure compressor.

[0007] The turbine engine also includes a nacelle located around the fan and gas generator. The nacelle is annular and extends around the longitudinal axis of the turbine engine.

[0008] The turbine engine is attached to components of an aircraft, such as the wing or fuselage, via a mounting pylon (also called a mast) and suspension system. The pylon is generally elongated in shape and consists of beams extending parallel to the longitudinal axis of the turbine engine. If the turbine engine is attached under the wing of the aircraft, analogous to a clock face, the pylon is located at the 12 o'clock (12 hours) position.

[0009] A suspension system typically includes multiple upstream and / or downstream connecting elements for attaching and suspending hangers to a turbine engine. These connecting elements function to withstand forces generated in the turbine engine along different axes and moments relative to those axes; these connecting elements are typically connected to the turbine engine housing.

[0010] Specifically, the turbine engine experiences thrust corresponding to the torque generated by the axial force. In fact, during operation, the gas generator transmits forces between the upstream and downstream attachment points on the hanger, which causes the gas generator to deform and change the clearance between the rotor and stator of the gas generator.

[0011] Turbine engines are also subjected to torques generated by the asymmetry of axial forces on the fan blades, as well as forces generated by the turbine intake (called intake forces). These intake forces are typically distributed between the hub of the intake casing located upstream of the turbine engine and the turbine casing or exhaust casing located downstream of the turbine engine. Therefore, when a force is applied upstream of the turbine engine, it can be transmitted downstream of the turbine engine and may cause the gas generator to bend and the high-pressure body to deform.

[0012] One solution is to reinforce the turbine engine casing to withstand these intake forces, thus preventing the gas generator from bending. Another solution is to transfer the intake forces to the turbine engine nacelle. However, this solution is not entirely satisfactory because it introduces problems with the turbine engine's accessibility and maintenance. Incidentally, the turbine engine's performance and operability may be affected.

[0013] Documents FR3020798A1, FR3133377A1, CN101263053A, FR2 887521A1, FR3071820 and FR2981046 A1 disclose components including an aircraft turbine engine, a pylon for mounting the turbine engine to components of an aircraft, and a system for suspending the turbine engine on the pylon.

[0014] This invention proposes a solution to at least some of the problems mentioned above. Summary of the Invention

[0015] This invention provides a component including a turbine engine for an aircraft, a pylon for mounting the turbine engine to components of the aircraft, and a system for suspending the turbine engine on the pylon. The turbine engine has a longitudinal axis and includes, during operation, components from upstream to downstream along the gas flow direction: > Fan housing, the fan housing surrounding the fan of the turbine engine with the longitudinal axis as its center, the fan housing including a first axial end located upstream of the fan and a second axial end located downstream of the fan, and > A gas generator configured to receive an airflow generated by a fan, the gas generator including a main duct for directing the main flow through at least one compressor, a combustion chamber, and at least one turbine, the fan housing being radially located outside the gas generator relative to a longitudinal axis, the fan housing together defining a secondary duct for directing the secondary flow. The suspender has a generally elongated shape along the longitudinal axis and is adapted for attachment to components of the aircraft. The suspension system includes a connecting element and at least one intake force-bearing link. The connecting element is used to connect the hanger to the turbine engine, and a second opposite end of the at least one intake force-bearing link is connected to the hanger. The characteristic feature is that the first end of the connecting rod is connected to an attachment point on the fan housing, the attachment point being located on the first axial end or upstream section of the fan housing, the upstream section of the fan housing extending from the first axial end by a distance that is at most 40% of the total length of the fan housing along the longitudinal axis.

[0016] The components according to the invention solve at least some of the problems of the prior art. The intake force-bearing linkage connects the attachment point and hanger of the fan housing, the attachment point being located on a first axial end or upstream section of the fan housing. This hanger enables the bearing of intake forces without requiring reinforcement of the turbine housing or penetration through the turbine nacelle. When forces are applied upstream of the turbine, the forces do not pass through the gas generator (in particular, do not travel from upstream to downstream of the turbine), but are transmitted directly to the hanger. This reduces the risk of gas generator bending and, for example, deformation of the high-pressure body of the gas generator.

[0017] Different features according to the present invention, which can be used together or individually: - The hanger is connected to the first end of the fan housing by a single link, which lies in a plane passing through the longitudinal axis and through the hanger; - The hanger is connected to the first axial end of the fan housing by two adjacent links, which are arranged symmetrically with respect to a plane that passes through the longitudinal axis, between the links and through the hanger; - The angle formed between the links is between 2° and 50°, preferably between 20° and 40°; -The link or the second end of each link is directly connected to the hanger; - The link, or the second end of each link, is connected to an intermediate structure that is attached to the hanger and the fan housing; - The fan housing includes a fan housing and an intake housing located downstream of the fan housing, with attachment points located at the downstream axial end of the fan housing or the upstream axial end of the intake housing; -The link, or the first and second ends of each link, includes a ball-and-socket joint; - The hanger includes an upstream end, which is located in a plane perpendicular to the longitudinal axis and upstream of the combustion chamber; - The upstream end of the hanger is located upstream of the second axial end of the fan housing; - The connecting element includes a thrust bearing link, a first end of which is connected to a gas generator and located upstream of the combustion chamber of the gas generator, and a second opposite end of which is connected to a hanger; - The first end of the thrust bearing link is connected to the intake housing, and in particular to the hub of the intake housing; - The intake housing also includes an arm that extends radially outward from the hub and passes through a secondary duct to rigidly connect the gas generator to the fan housing; - The connecting elements also include a suspension structure attached to the gas generator and hanger, located downstream of the combustion chamber of the gas generator; - The suspension structure is attached to the exhaust casing of the turbine engine, which is located downstream of one or more turbines of the gas generator; -The second end of the thrust bearing link is connected to the hanger via a suspension structure; - Using a clock face as an analogy, the hanging bracket is located at the 12 o'clock position; - Using a clock face as an analogy, the hanger is located at the 3 o'clock or 9 o'clock position; - The hanger is tilted by ±10 degrees. Attached Figure Description

[0018] Other objects, features, and advantages of the invention will become clearer in the following description with reference to the accompanying drawings, in which: - Figure 1a This is a schematic perspective view of an assembly including an aircraft turbine engine and its mounting bracket according to a first embodiment of the present invention; - Figure 1b This is a schematic perspective view of an assembly including an aircraft turbine engine and its mounting bracket according to a second embodiment of the present invention; - Figure 2aSuch as according to the third embodiment of the present invention Figure 1a A schematic perspective view of the components shown; - Figure 2b Such as according to the fourth embodiment of the present invention Figure 1b A schematic perspective view of the components shown; - Figure 3 It is based on Figure 1a A schematic side view of a variant of the component shown in the embodiment; - Figure 4 This is a schematic diagram of the intermediate structure of the component according to the present invention; - Figure 5 This is a schematic diagram of an aircraft turbine engine according to an embodiment of the present invention, and shows the attachment points and suspension points on the mounting bracket. Detailed Implementation

[0019] Figure 1a A component 1 according to a first embodiment of the present invention is shown. The component 1 includes a turbine engine 10 for an aircraft, a pylon 40 for mounting the turbine engine 2 onto components of the aircraft, and a system for suspending the turbine engine 10 onto the pylon 40. The turbine engine extends about and along a longitudinal axis X. The longitudinal axis X is oriented from upstream to downstream of the turbine engine 2.

[0020] In this application, the terms “axial,” “axially,” “radially,” and “radially” are defined relative to the longitudinal axis X.

[0021] The terms "upstream" and "downstream" are defined relative to the direction in which gas flows along the longitudinal axis X in the turbine engine 2. In this application, the components of the turbine engine located upstream of the combustion chamber are upstream of the turbine engine, while the components of the turbine engine located downstream of the combustion chamber are downstream of the turbine engine.

[0022] In this specification, when the term "link" is not followed by the phrase "intake force bearing" or "thrust bearing", the link is assumed to be an intake force bearing link.

[0023] In this configuration, turbine engine 2 is a dual-flow, dual-body turbojet engine. During operation, turbine engine 2 includes a fan 10 and a gas generator 16 along the gas flow direction from upstream to downstream. Although in Figure 1a While not visible in the foreground, the gas generator 16 includes, from upstream to downstream, at least one compressor (such as a low-pressure compressor 17 and a high-pressure compressor 18), a combustion chamber 19, and at least one turbine (such as a high-pressure turbine 20 and a low-pressure turbine 21). These various components of the turbine engine 2 are... Figure 5 It is shown schematically in the diagram.

[0024] Fan 10 draws in airflow F, which is divided into a first airflow called the main flow F1 and a second airflow called the secondary flow F2. Gas generator 16 defines a main annular duct V1 for the flow of the main flow F1. Gas generator 16 is used to surround a secondary annular duct V2 for the flow of the secondary flow F2.

[0025] The main air mass is compressed in low-pressure compressor 17 and then in high-pressure compressor 18. The compressed air from the main mass is mixed with fuel and burned in combustion chamber 19. The combustion gases pass through high-pressure turbine 20 and low-pressure turbine 21. Finally, the gases escape through nozzles whose cross-section allows the gases to be accelerated to generate thrust (a portion of the thrust, approximately 20%).

[0026] The rotor of the high-pressure compressor 18 is connected to the rotor of the high-pressure turbine 20 via the high-pressure shaft 3, and the rotor of the low-pressure compressor 17 is connected to the rotor of the low-pressure turbine 21 via the low-pressure shaft 4, which passes through the high-pressure shaft and drives the propulsion wheel / propeller located upstream of the gas generator 16 to rotate. The propulsion wheel / propeller is surrounded by an annular housing called the fan housing 11.

[0027] The fan housing 11 surrounds the fan 10 of the turbine engine, centered on the longitudinal axis X. Together with the gas generator 16, the fan housing 11 defines a secondary duct V2 for the flow of the secondary flow F2. The fan housing 11 may include a fan housing 29 and an intake housing 25, or alternatively, the fan housing 29 and the intake housing 25 may be formed as a single unit. In this application, the fan housing 11 includes a first axial end 12 (e.g., a flange for attaching an air inlet) located upstream of the fan 10 and a second axial end 13 (e.g., for securing a connection to a thrust reverser or nacelle fairing) located downstream of the fan 10. The first axial end 12 is located at the fan housing 29, while the second end 13 is located at the intake housing 25. Incidentally, the first axial end 12 is therefore further away from the gas generator 16 than the second axial end 13.

[0028] In other words, end 12 is located in a first plane P12 perpendicular to the axis X, and is upstream of the fan blade 14. End 13 is located in a second plane P13 perpendicular to the axis X, and is downstream of the fan blade 14.

[0029] The fan housing 11 is connected to the gas generator 16 via the intake housing 25. The intake housing 25 includes a central hub 26 and a series of radial arms 15 connecting the hub 26 to the fan housing 11.

[0030] The turbine engine 2 includes a compressor housing 24 extending between a low-pressure compressor 17 and a high-pressure compressor 18. The turbine engine 2 also includes a turbine housing 27 axially arranged between a low-pressure turbine 21 and a high-pressure turbine 20. The turbine engine 2 further includes a bearing support 28 supporting a shaft guide bearing.

[0031] The turbine engine 2 is attached to an aircraft component, such as a wing or fuselage, via a mounting pylon 40. The pylon 40 has a generally elongated shape along its extension axis B and is adapted for attachment to the aircraft component. The extension axis B is parallel to the longitudinal axis X of the turbine engine. When the turbine engine is attached under the wing of the aircraft, analogous to a clock face, the pylon 40 is located at the 12 o'clock position. However, when the pylon 40 is attached to the fuselage, it can be located at the 9 o'clock position. Other design variations are possible depending on the type of turbine engine. According to one embodiment, when the pylon 40 is at the 12 o'clock position, axes X and B are in the same vertical plane. The pylon can also be tilted a few degrees relative to the vertical plane (vertical plane / wing dihedral plane) or the horizontal plane, preferably ±10° (to improve airflow around the fuselage).

[0032] Figure 1a An orthogonal reference frame XYZ is also shown, in which the X-axis is oriented from upstream to downstream of the turbine engine 2, the Z-axis is oriented vertically upward, and the Y-axis is oriented to one side.

[0033] In this application, "force" refers to a force transmitted in the same direction as the X-axis, Y-axis, or Z-axis, which are used as references. Axial force, lateral force, and vertical force are forces transmitted in the same direction as the X-axis, Y-axis, and Z-axis, respectively. The axial force applied to the components of the aircraft is generated by tensile stress, while the vertical force applied to the components of the aircraft is generated by compressive stress. That is, in addition to axial force, lateral force, and vertical force, torque is also applied to the components of the aircraft. The components of the aircraft are subjected to axial torque, lateral torque, and vertical torque along the X-axis, Y-axis, and Z-axis, respectively.

[0034] When a component of the suspension system (e.g., an attachment member for attaching the hanger 40 to the turbine engine 2) bears a force along the X-axis, this means that the attachment member impedes any movement of the component to which it is attached along the X-axis. This bearing is called axial bearing. Similarly, when an attachment member bears a force along the Y-axis or Z-axis, this means that the attachment member impedes any movement of the component to which it is attached along the Y-axis or Z-axis, respectively. These bearings are called lateral bearing and vertical bearing, respectively. Similarly, when an attachment member for attaching the hanger 40 to the turbine engine 2 bears a moment Mx about the X-axis, this means that the attachment member impedes any rotational movement of the component to which it is attached about the X-axis. The same applies to moments My and Mz about the Y-axis and Z-axis, respectively.

[0035] In the context of this invention, the suspension system includes all elements that connect the turbine engine 2 to the hanger 40. These individual elements of the suspension system are arranged and / or configured to withstand forces in three directions (i.e., an axial direction with an X-axis, a vertical direction with a Z-axis, and a lateral direction with a Y-axis) or forces in some of these directions, and moments Mx, My, and Mz respectively about these three directions or about some of these directions.

[0036] To withstand the intake force, this invention proposes axial bearing, i.e., axial bearing along the X-axis. At this stage, it should be remembered, especially when the propulsion assembly is at an angle of attack, that the intake force is generated by the torque produced by the asymmetry of the axial forces on the fan blades and the forces associated with the intake. The resultant force and torque system generated by the pressure balance at the angle-of-attack intake is mainly composed of torque components My and Mz, but also by the intake force. The resultant force and torque system is typically distributed between the hub 26 of the intake casing 25 and the exhaust casing 22 of the turbine engine.

[0037] In this respect, according to the present invention and as shown in the figures, the suspension system includes at least one intake force bearing link 30, 30a, 30b, the first ends 31, 31a, 31b of the at least one intake force bearing link 30, 30a, 30b being connected to attachment points 11a, 11b of the fan housing 11, the attachment points 11a, 11b being located on the first axial end 12 or upstream section of the fan housing, and the second ends 32, 32a, 32b of the at least one intake force bearing link 30, 30a, 30b opposite to the first ends 31, 31a, 31b being connected to the hanger 40. The link, or each link 30, 30a, 30b, functions by default because, when the link, or each link 30, 30a, 30b, is undamaged or unbroken, it provides attachment and suspension functions by default.

[0038] The link, or each link 30, 30a, 30b, bears a force along the X-axis, and therefore a traction / compression force along the link direction. In this way, the suspension system of component 1 according to the invention allows the intake force to pass through the hanger 40, rather than through the gas generator 16. Therefore, the risk of bending of the gas generator 16 and deformation of the high-pressure body is eliminated or greatly reduced.

[0039] Furthermore, the effectiveness of the invention in withstanding intake forces is also attributed to the distance between the first ends 31, 31a, 31b and the second ends 32, 32a, 32b of the link or each link 30, 30a, 30b. The first ends 31, 31a, 31b and the second ends 32, 32a, 32b are separated by a distance at least equal to the distance between the first axial end 12 and the second axial end 13 of the fan housing 11 (the axial distance between planes P12 and P13) or the distance between the upstream section of the fan housing and the second axial end. This means that intake forces can be effectively absorbed through a lever effect. In this regard, preferably, the upstream section of the fan housing extends from the first axial end 12 by a distance that is at most 60% of the total length of the fan housing, and preferably at most 40% of the total length of the fan housing along the longitudinal axis X. The length of the fan housing is the dimension of the fan housing along the longitudinal axis X.

[0040] exist Figure 1a In the first embodiment of component 1 shown, the hanger 40 is connected to the first axial end 12 of the fan housing via a single link 30, which lies in a plane P1 passing through the longitudinal axis X and through the hanger 40. In this first embodiment, the attachment point 11a of the fan housing 11 is therefore located on the first axial end 12 of the fan housing. The link 30 is referred to as axial because it extends primarily in a plane (in this case, P1) passing through the longitudinal axis X of the turbine engine 2. Therefore, the first end 31 and the second end 32 of the link 30 lie in plane P1. Preferably, the first end 31 and the second end 32 of the link 30 comprise ball joints. These ball joints are conventional ball-and-socket joints that allow each of the first end 31 and the second end 32 to rotate freely.

[0041] exist Figure 1aIn the specific case shown, plane P1 extends along directions X and Z. Link 30 forms a support directly on the first axial end 12, and thus a support at the point of force application. Therefore, link 30 can withstand forces along the X-axis and at least a portion of the forces along the Z-axis. Without link 30, the torque generated on the gas generator 16 would have to be borne by two vertical reaction forces, a first acting on the intake housing 25 and a second acting on the exhaust housing 22. However, this would cause not only bending and clearance degradation of the turbine engine, but also a torque My in the downstream portion of the turbine engine 2. Link 30 provides a direct connection between the first axial end 12 and the hanger 40. In this way, assembly 1 allows the maximum amount of force to be transmitted through the hanger 40, rather than through the gas generator 16 as in the prior art. As a result, the vertical force in the plane of the exhaust housing 22 and the torque My in the gas generator 16 are reduced. Therefore, the intake force is borne upstream of the combustion chamber 19 and upstream of the turbine engine 2.

[0042] Now for reference Figure 1b In component 1 according to the second embodiment, the hanger 40 is connected to the first axial end 12 of the fan housing via two adjacent links 30a and 30b. These two adjacent links 30a and 30b are arranged symmetrically with respect to a plane P1' that passes through the longitudinal axis X, between the links 30a and 30b, and through the hanger 40. In this second embodiment, attachment points 11a and 11b of the fan housing 11 are located on the first axial end 12 of the fan housing. The first link 30a and the second link 30b are arranged in a plane symmetrical with respect to the plane P1'. Compared with the first embodiment (… Figure 1a Similar to the individual links 30 of component 1 in the turbine engine 2, links 30a and 30b are axial because they are arranged symmetrically with respect to the plane P1' passing through the longitudinal axis X of the turbine engine 2. In this arrangement, the sum of the contributions of the first link 30a and the second link 30b to the bearing of the force along the X-axis produces the bearing of the axial force along the X-axis direction.

[0043] More specifically, connecting rods 30a and 30b allow forces with lateral components (i.e., along the Y-axis) and vertical components (i.e., along the Z-axis) to be borne. Additionally, the first connecting rod 30a and the second connecting rod 30b are used to bear the torque Mz about the Z-axis. As described above, the torque Mz about the Z-axis borne by connecting rods 30a and 30b originates from their symmetrical arrangement relative to plane P1' (particularly in two different planes). Therefore, connecting rods 30a and 30b prevent any axial movement of the fan housing 11 along the X-axis and any rotational movement about the vertical Z-axis. In this embodiment, the intake force is also borne upstream of the combustion chamber 19 and upstream of the turbine engine 2.

[0044] Preferably, the first ends 31a, 31b and the second ends 32a, 32b of the connecting rods 30a, 30b include a spherical joint that allows each of the first ends 31a, 31b and the second ends 32a, 32b to rotate freely.

[0045] In a particularly advantageous arrangement, connecting rods 30a and 30b form an angle between 2° and 50° with each other. Therefore, the first connecting rod 30a and the second connecting rod 30b are not parallel to each other. Furthermore, this also means that the first connecting rod 30a and the second connecting rod 30b are not parallel to the plane P1' passing through the longitudinal axis X of the turbine engine 2, because connecting rods 30a and 30b are symmetrical with respect to this plane P1'. Advantageously, the angle formed between connecting rods 30a and 30b is oriented from downstream to upstream, meaning that the second ends 32a and 32b of the connecting rods are closer together than the first ends 31a and 31b of the connecting rods.

[0046] For example, when links 30a and 30b form a 2° angle with each other, this means that each of links 30a and 30b forms a 1° angle with plane P1'. If links 30a and 30b form a 50° angle with each other, this means that each of links 30a and 30b forms a 25° angle with plane P1'. Regarding this last example, it should be noted that, preferably, the angle formed by links 30a and 30b between links 30a and 30b does not exceed 50°, so as to avoid contact between links 30a and 30b and fan housing 11, and to avoid generating lateral and vertical forces with torque Mx in plane YZ.

[0047] Advantageously, the connecting rods 30a and 30b form an angle between 20° and 40° with each other, which allows the moment My about the transverse Y-axis and the moment Mz about the vertical Z-axis to be effectively borne, thus enabling the intake force to be effectively borne in a configuration with two connecting rods 30a and 30b.

[0048] The second ends 32, 32a, 32b of the link or each link 30, 30a, 30b are directly connected to the hanger 40. Preferably, the second ends 32, 32a, 32b of the link or each link 30, 30a, 30b are directly connected to the center of the hanger 40. However, as will be better understood below, the second ends 32, 32a, 32b of the link or each link 30, 30a, 30b may not be directly connected to the hanger 40. The second ends 32, 32a, 32b of the link or each link 30, 30a, 30b may be connected to an intermediate structure 50. When the second ends 32, 32a, 32b are directly connected to the hanger 40, this eliminates the need for the intermediate structure 50. That is, in practice, because the intermediate structure 50 allows the fan housing 11 to be mounted to the hanger 40, component 1 must include such an intermediate structure 50. Therefore, the advantage of directly connecting the second ends 32, 32a, 32b to the hanger 40 lies more in the use of a simple intermediate structure 50.

[0049] Figure 4 An intermediate structure 50, which can be used in the context of this invention, is shown. The intermediate structure 50 includes at least a first attachment element 51 for attachment to the hanger 40 and a second attachment element 52 for attachment to the fan housing 11. The second attachment element 52 may have a generally curved shape. The second attachment element 52 may include a curved support 52 that follows the contour of the fan housing 11. The support 52 is configured to allow the mounting of lateral links 56a, 56b and a central link 57.

[0050] exist Figure 2a In the third embodiment of component 1 shown, the hanger 40 is connected to an attachment point 11a of the fan housing 11 via a link 30, the attachment point 11a being located in the upstream section of the fan housing. The link 30 forms a support at the attachment point 11a, and thus a support between the first axial end 12 and the second axial end 13. Under these conditions, the link 30 forms a support near the point of force application, which allows it to withstand at least a portion of the force along the X-axis and the force along the Z-axis. In this way, component 1 allows a portion of the force to be transmitted in the hanger 40 rather than in the gas generator 16. As a result, the vertical force in the plane of the exhaust housing 22 and the torque My in the gas generator 16 are reduced. As in the first and second embodiments, the link 30 may include a ball joint.

[0051] In other words, preferably, the attachment point 11a is located at a distance from the first axial end 12 of the fan housing, which is at most 40% of the length of the fan housing. The closer the attachment point 11a is to the first axial end 12, the more effective it is in bearing axial forces along the X-axis.

[0052] Particularly advantageously, the attachment point 11a can be located on the downstream axial end 29b of the fan housing 29, opposite its upstream end 29a. Alternatively, the attachment point 11a can be located on the upstream axial end 25a of the intake housing 25, opposite its downstream end 25b. In either case, the attachment point 11a is located on the upstream section of the fan housing 11. Therefore, preferably, the downstream axial end 29b of the fan housing 29 and the upstream axial end 25a of the intake housing are separated from the first axial end 12 of the fan housing by a distance that is at most 60% of the length of the fan housing.

[0053] exist Figure 2b In the fourth embodiment of component 1 shown, the hanger 40 is connected to attachment points 11a, 11b of the fan housing via two adjacent links 30a, 30b. Attachment points 11a, 11b are located on the upstream section of the fan housing. These two adjacent links 30a, 30b are arranged symmetrically with respect to a plane P1' that passes through the longitudinal axis X, between the links 30a, 30b, and through the hanger 40. The links 30a, 30b can withstand forces with lateral and vertical components, as well as a moment Mz about the Z-axis. Therefore, the links 30a and 30b prevent any axial movement of the fan housing 11 along the X-axis and any rotational movement about the vertical Z-axis.

[0054] In the third embodiment, attachment points 11a and 11b may be located at a distance from the first axial end 12, which is at most 60% of the length of the fan housing along the longitudinal axis X. However, preferably, attachment points 11a and 11b are located at a distance from the first axial end 12 of the fan housing, which is at most 40% of the length of the fan housing. The closer attachment points 11a and 11b are to the first axial end 12, the more effective they are in withstanding axial forces along the X-axis. In practice, attachment points 11a and 11b may be located on the downstream axial end 29b of the fan housing 29, or alternatively on the upstream axial end 25a of the intake housing 25.

[0055] In the illustrated embodiment, the hanger 40 includes an upstream end 42 located in a plane P2 perpendicular to the longitudinal axis X and upstream of the combustion chamber 19, preferably upstream of the second axial end 13 of the fan housing 11. Therefore, whether one or more second ends 32, 32a, 32b are directly connected to the upstream end 42 of the hanger or directly connected to the intermediate structure 51 (which itself is connected to the upstream end 42 of the hanger), lateral and vertical forces are borne in plane P2, and thus upstream of the gas generator 16.

[0056] Plane P2 need not be located upstream of the second axial end 13 of the fan housing 11. Importantly, plane P2 is located upstream of the combustion chamber 19, so that no intake force can pass through the combustion chamber.

[0057] As can also be seen from the accompanying drawings, in addition to one or more intake force-bearing links 30, 30a, 30b, the suspension system may also include a thrust-bearing link 45. A first end 47 of the thrust-bearing link 45 is connected to the gas generator 16, located upstream of the combustion chamber 19 of the gas generator, and a second opposing end 48 of the thrust-bearing link 45 is connected to the hanger 40 or intermediate structure 49. Similar to the one or more intake force-bearing links 30, 30a, 30b, the thrust-bearing link 45 functions by default, as it provides attachment and suspension functions by default when it is undamaged or unbroken.

[0058] exist Figures 1a to 1b In the suspension system, there are two thrust-bearing links 45. These two thrust-bearing links 45 are mainly used to bear axial forces, that is, forces generated along the X-axis.

[0059] Thrust-bearing links 45 are arranged in pairs on both sides of plane P1 or P1', where appropriate. Each side has one thrust-bearing link 45. Similar to the inlet force-bearing links 30, 30a, and 30b, these thrust-bearing links 45 are equipped with ball-and-socket joints. Figure 4 In the middle, the suspension system includes two thrust-bearing links 45, each of which is located on either side of plane P1.

[0060] According to a preferred embodiment, the first end 47 of the thrust-bearing link 45 is connected to the intake housing 25 of the gas generator, specifically to the hub 26 of the intake housing. The intake housing 25 includes an arm 15 extending radially outward from the hub 26 and passing through a secondary conduit V2 to rigidly connect the gas generator 16 to the fan housing 11. Therefore, the thrust-bearing link 45 is connected to a mounting component of the gas generator, in this case, to the hub 26 of the intake housing 25.

[0061] In the illustrated embodiment, using a clock face as an analogy, the hanger 40 is located at the 12 o'clock position.

[0062] According to a preferred embodiment, the connecting element further includes a suspension structure 49 attached to the gas generator 11 and the hanger 40, located downstream of the combustion chamber 19 of the gas generator. This suspension structure 49, by being located downstream of the combustion chamber 19 and therefore downstream of the turbine engine 2, performs the same function as the aforementioned intermediate structure 50. Therefore, the suspension structure 49 can withstand lateral and vertical forces, i.e., forces generated along the Y-axis and Z-axis directions.

[0063] In a preferred embodiment, the suspension structure 49 is attached to the exhaust housing 22 of the turbine engine, which is located downstream of one or more turbines 20, 21 of the gas generator. The exhaust housing 22 (also referred to as the turbine housing) is connected to the intake housing 25 and aligned with the intake housing 25 along the longitudinal axis X of the turbine engine. Advantageously, the second end 48 of the thrust bearing link 45 is directly connected to the hanger 40 or connected to the hanger 40 via the suspension structure 49.

[0064] The configurations shown in the accompanying drawings are merely possible examples of the invention and are not intended to limit the invention. Rather, the invention includes design variations that would be conceived by those skilled in the art. For example, the turbine engine 2 is not necessarily a dual-flow, dual-body turbine engine.

Claims

1. An assembly (1) comprising a turbine engine (2) of an aircraft, a gantry (40) for mounting the turbine engine to a component of the aircraft, and a system for suspending the turbine engine on the gantry. The turbine engine (2) has a longitudinal axis (X) and includes, during operation, components from upstream to downstream along the gas flow direction: > Fan housing (11), the fan housing surrounding the fan (10) of the turbine engine with the longitudinal axis (X) as its center, the fan housing (11) including a first axial end (12) located upstream of the fan (10) and a second axial end (13) located downstream of the fan, and > Gas generator (16), the gas generator being configured to receive an airflow generated by the fan, the gas generator (16) including a main duct (V1) for causing a main flow (F1) through at least one compressor (17, 18), a combustion chamber (19) and at least one turbine (20, 21), the fan housing (11) being radially located outside the gas generator (16) relative to the longitudinal axis (X), the fan housing together with the gas generator (16) defining a secondary duct (V2) for causing a secondary flow (F2). The suspender (40) has a generally elongated shape along the longitudinal axis (X) and is adapted to be attached to the components of the aircraft. The suspension system includes connecting elements (45, 49) and at least one intake force bearing link (30, 30a, 30b), the connecting elements being used to connect the hanger to the turbine engine, and the second opposite ends (32, 32a, 32b) of the at least one intake force bearing link being connected to the hanger (40). The characteristic feature is that the first end (31, 31a, 31b) of the connecting rod (30, 30a, 30b) is connected to the attachment point (11a, 11b) of the fan housing (11), the attachment point being located on the first axial end (12) or upstream section of the fan housing (11), the upstream section of the fan housing extending from the first axial end (12) by a distance that is at most 40% of the total length of the fan housing along the longitudinal axis (X).

2. The component according to claim 1, wherein, The hanger (40) is connected to the first axial end (12) of the fan housing by a single link (30) located in a plane (P1) passing through the longitudinal axis (X) and through the hanger (40).

3. The component according to claim 1, wherein, The hanger (40) is connected to the first axial end (12) of the fan housing by two adjacent links (30a, 30b), which are arranged symmetrically with respect to a plane (P1') that passes through the longitudinal axis (X), between the links and through the hanger (40).

4. The component according to claim 3, wherein, The angle formed between the connecting rods (30a, 30b) is between 2° and 50°, preferably between 20° and 40°.

5. The component according to any one of claims 1 to 4, wherein, The second end (32, 32a, 32b) of the link or each link (30, 30a, 30b) is directly connected to the hanger (40).

6. The component according to any one of claims 1 to 4, wherein, The second end (32, 32a, 32b) of the link or each link (30, 30a, 30b) is connected to the intermediate structure (50), which is attached to the hanger (40) and the fan housing (11).

7. The component according to any one of the preceding claims, wherein, The fan housing (11) includes a fan housing (29) and an intake housing (25) located downstream of the fan housing (29), with attachment points (11a, 11b) located at the downstream axial end (29b) of the fan housing (29) or the upstream axial end (25a) of the intake housing (25).

8. The component according to any one of the preceding claims, wherein, The hanger (40) includes an upstream end (42) located in a plane (P2) perpendicular to the longitudinal axis (X) and upstream of the combustion chamber (19), preferably upstream of the second axial end (13) of the fan housing (11).

9. The component according to any one of the preceding claims, wherein, The connecting element further includes a thrust bearing link (45), the first end (47) of which is connected to the gas generator (16) and located upstream of the combustion chamber (19) of the gas generator, and the second opposite end (48) of which is connected to the hanger (40).

10. The component according to any one of the preceding claims, wherein, The connecting element further includes a suspension structure (49) attached to the gas generator (11) and the hanger (40), located downstream of the combustion chamber (19) of the gas generator.

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