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

Abstract

The present invention relates to an assembly (1) comprising an aircraft turbine engine (2), a mounting bracket (40) for mounting the turbine engine on an aircraft component, and a system for suspending the turbine engine on the mounting bracket, the turbine engine having a longitudinal axis (X) and comprising, from upstream to downstream, along the gas flow direction: > a fan housing (11) extending about the longitudinal axis, and > a gas generator (16) configured to receive an airflow generated by the fan, the mounting bracket (40) having a generally elongated shape along the longitudinal axis and adapted to be attached to an aircraft component, characterized in that all connecting elements for the suspension system are located upstream of the combustion chamber (19).

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, from upstream to downstream of the gas flow in the turbine engine, at least one compressor, a combustion chamber, and at least one turbine. In the case of a twin-body turbofan engine with low and high pressure components, the gas generator sequentially includes a low-pressure compressor, a compressor housing, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine. The gas generator has a main annular duct for the main gas flow through the compressor, combustion chamber, and turbine.

[0003] The rotors of the high-pressure compressor and the high-pressure turbine are mechanically connected via a high-pressure shaft to form the high-pressure body. The rotors of the low-pressure compressor and the low-pressure turbine are mechanically connected via a low-pressure shaft to form the low-pressure body. The low-pressure shaft passes through the high-pressure shaft and rotates the fan propeller / blades, which are typically located upstream of the gas generator.

[0004] When the fan propeller / blade is ducted and thus surrounded by an annular casing, it generates an airflow around the gas generator. This 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 secondary flow. That is, the fan propeller / blade can be non-ducted and fitted with moving blades of variable pitch. Turbine engines equipped with non-ducted propellers include turbine engines with two counter-rotating non-ducted propellers (referred to as an unducted fan (UDF)) or turbine engines with a single non-ducted propeller and a rectifier comprising multiple stator blades (referred to as an unducted single fan (USF)).

[0005] The fan housing includes a fan housing and an intake housing, the intake housing being 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 portion of the secondary ductwork.

[0006] The turbine engine includes a compressor housing that extends between the low-pressure compressor and the high-pressure compressor.

[0007] The turbine engine also includes a nacelle located around the fan casing and gas generator. The nacelle is annular and extends around the longitudinal axis of the turbine engine. The outer shells of the fan casing and intake casing are typically connected to the nacelle.

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

[0009] Suspension systems typically include multiple upstream and / or downstream connecting elements for attaching and suspending pylons to and from the turbine engine. These connecting elements function to withstand forces generated along different axes within the turbine engine or aircraft, as well as moments relative to these axes, and are typically connected to the turbine engine casing.

[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 mount, 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's intake (called control forces). These control forces are typically distributed between the hub of the intake casing upstream of the turbine and the turbine casing or exhaust casing downstream of the turbine. In turbine engines with ducted propellers / blades, these control forces are distributed between the propeller blades upstream of the turbine and the exhaust casing downstream of the turbine. Therefore, when forces are applied upstream of the turbine, they can be transmitted downstream and may cause gas generator bending and high-pressure body deformation.

[0012] One solution is to reinforce the turbine engine casing to withstand these control forces, thereby preventing the gas generator from bending. Another solution is to transfer the control forces to the turbine engine nacelle. However, this solution is not entirely satisfactory because it introduces problems regarding the accessibility and maintenance of the turbine engine.

[0013] In current technology, some of the connecting elements used to attach the mount to the turbine engine are located downstream of the combustion chamber, more specifically at the turbine engine's exhaust casing, to withstand control forces. Bearing control forces downstream of the combustion chamber, and particularly within the exhaust casing, puts stress on the high-pressure body and affects the turbine engine's performance and operability. This particularly affects the operation of the high-pressure compressor and its turbine.

[0014] In turbine engines with non-ducted propellers / blades, the torque generated by the asymmetry of axial forces on the blades is also borne by the exhaust casing, which affects the operation of the high-pressure compressor and its turbine.

[0015] Documents FR3114129A1, WO2012 / 085388A1, WO2022 / 248791 A1 and WO2007 / 033994A1 disclose an assembly including an aircraft turbine engine, a pylon for mounting the turbine engine to an aircraft component, and a system for suspending the turbine engine on the pylon.

[0016] This invention proposes a solution to at least some of the problems mentioned above. Summary of the Invention

[0017] This invention proposes an assembly comprising an aircraft turbine engine, a pylon for mounting the turbine engine on an aircraft component, and a system for suspending the turbine engine on the pylon. The turbine engine has a longitudinal axis and comprises, during operation, along the gas flow direction from upstream to downstream: >Fan housing, which extends around the longitudinal axis and around the fan of the turbine engine, and A gas generator configured to receive an airflow generated by a fan includes a main duct for directing the main flow through a low-pressure compressor, a compressor housing, a high-pressure compressor, an annular combustion chamber, and at least one turbine. The fan housing is located radially outside the gas generator relative to its longitudinal axis. Together with the gas generator, the fan housing defines a secondary duct for directing the secondary flow. The pylon has a generally elongated shape along the longitudinal axis and is adapted for attachment to components of the aircraft. The suspension system includes connecting elements for connecting a mount to a turbine engine, characterized in that all connecting elements are located upstream of the combustion chamber and include: - A first force-bearing rod, extending from the bracket to the compressor housing, is configured to bear thrust along two axes perpendicular to each other and perpendicular to the longitudinal axis. - A connection structure for attaching the mount to the fan housing, configured to withstand thrust along two axes and torques generated along these axes, which are perpendicular to each other and perpendicular to the longitudinal axis. The connecting element is configured to withstand control forces.

[0018] The components according to the invention solve at least some of the problems of the prior art. In fact, all connecting elements are located upstream of the combustion chamber. In other words, there are no connecting elements located at or downstream of the combustion chamber. This means there are no connecting elements located at the turbine or even the exhaust casing. Simultaneously, the first force-bearing rod and connecting structure are configured to bear thrust along two perpendicular axes and the torque generated along these axes, while also cooperating to bear control forces. This means no control forces can be transmitted through the turbine engine, as all these forces are borne by the first thrust-bearing rod and connecting structure upstream of the combustion chamber. Therefore, the risks of gas generator bending and high-pressure body deformation are avoided, and the resulting degradation of the high-pressure body's performance and operability is also prevented.

[0019] Different features according to the present invention, which can be used together or individually: - The connecting structure is also configured to withstand thrust along the longitudinal axis; -The first thrust bearing rod and connecting structure are the only connecting elements used to connect the mount to the turbine engine; - The connecting element also includes a second thrust bearing rod that extends from the bracket to the intake housing located upstream of the low-pressure compressor and the high-pressure compressor, and the second thrust bearing rod is configured to bear thrust along the longitudinal axis; - The first thrust bearing rod, the second thrust bearing rod, and the connecting structure are the only connecting elements used to connect the mount to the turbine engine; - The second thrust bearing rod is connected to the hub of the intake housing, which includes radial blades that extend radially outward from the hub and through a secondary duct to rigidly connect the gas generator to the fan housing. - The mounting bracket includes an upstream end, which is located in a plane perpendicular to the longitudinal axis and upstream of the combustion chamber, preferably upstream of the compressor housing; - The upstream end of the mounting bracket is located downstream of the fan housing; - The upstream end of the bracket is located in a plane that is perpendicular to the longitudinal axis and passes through the downstream axial end of the fan housing. The connecting structure is connected to the downstream axial end of the fan housing and the upstream end of the bracket. - The connection structure includes two lateral links, which are located in a second plane having a Y-axis and a Z-axis; - Using a clock face as an analogy, the bracket is located at the 12 o'clock position; - Using a clock face as an analogy, the bracket is located at the 3 o'clock or 9 o'clock position; - The bracket can be tilted by ±10 degrees. Attached Figure Description

[0020] Other objects, features, and advantages of the invention will become clearer in the following description with reference to the accompanying drawings, in which: - Figure 1 This is a schematic diagram of an aircraft turbine engine according to a first embodiment of the present invention, and shows the attachment points and suspension points on the mounting bracket; - Figure 2 This is a schematic diagram of an aircraft turbine engine according to a second embodiment of the present invention, and shows the attachment points and suspension points on the mounting bracket; - Figure 3 This is a schematic diagram of the connection structure of the components according to the present invention. Detailed Implementation

[0021] Figure 1 A component 1 according to a first embodiment of the present invention is shown. The component 1 includes a turbine engine 2 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 2 on the pylon 40. The turbine engine 2 extends about and along a longitudinal axis X. The longitudinal axis X is oriented from upstream to downstream of the turbine engine 2.

[0022] In this application, the terms “axial,” “axially,” “radially,” and “radially” are defined relative to the longitudinal axis X.

[0023] The terms "upstream" and "downstream" are defined relative to the direction of gas flow along the longitudinal axis X in the turbine engine 2. In this application, components of the turbine engine located upstream of the combustion chamber are upstream of the turbine engine, and vice versa, while components of the turbine engine located downstream of the combustion chamber are downstream of the turbine engine, and vice versa.

[0024] In this configuration, turbine engine 2 is a twin-body turbofan engine with dual flow. 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 1 Not visible in a, but the gas generator 16 includes, from upstream to downstream, at least one low-pressure compressor 17, compressor housing 24, high-pressure compressor 18, annular combustion chamber 19 and at least one turbine (such as high-pressure turbine 20 and low-pressure turbine 21). Figure 1 These various components of the turbine engine 2 are shown schematically.

[0025] Fan 10 draws in airflow F, which is divided into a first airflow, referred to as the main flow F1, and a second airflow, referred to as the secondary flow F2. In this respect, the fan includes fan blades 14 extending perpendicular to the longitudinal axis X. 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.

[0026] In mainstream F1 combustion, the fuel is compressed in low-pressure compressor 17 and then in high-pressure compressor 18. The compressed air is then 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 them to be accelerated to generate thrust.

[0027] The rotor of the high-pressure compressor 18 is mechanically connected to the rotor of the high-pressure turbine 20 via a high-pressure shaft 3 to form a high-pressure body, while the rotor of the low-pressure compressor 17 is mechanically connected to the rotor of the low-pressure turbine 21 via a low-pressure shaft 4 to form a low-pressure body. The low-pressure shaft 4 passes through the high-pressure shaft 3 and rotates a propeller located upstream of the gas generator 16. This propeller is surrounded by an annular casing referred to as the fan casing 11.

[0028] The fan housing 11 extends about a longitudinal axis X and about a fan 10 of a turbine engine. The fan housing 11 is radially outward of the gas generator 16 relative to the longitudinal axis X, and together with the gas generator 16 defines a secondary duct V2 for the secondary flow F2. The fan housing 11 may include a fan housing and an intake housing 25, or alternatively may be formed as a single piece. 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 blades 15 connecting the hub 26 to the fan housing 11. More specifically, the radial blades 15 extend radially outward from the hub 26 and through the secondary duct V2 to rigidly connect the gas generator 16 to the fan housing 11. These radial blades (referred to as outlet guide vanes (OGVs)) are used to straighten the airflow exiting the fan blades. In this application, the "intake housing" is the housing that connects the gas generator 16 to the fan housing 11.

[0029] The turbine engine 2 includes a compressor housing 24 extending between the low-pressure compressor 17 and the high-pressure compressor 18. Therefore, the compressor housing 24 is located between the two consecutive compressors 17 and 18 of the gas generator. The turbine engine 2 also includes a turbine housing 27 axially arranged between the low-pressure turbine 20 and the high-pressure turbine 21. The turbine engine 2 further includes a bearing support 28 supporting a shaft guide bearing.

[0030] The turbine engine 2 is attached to components of the aircraft, such as the 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 components. The extension axis B is parallel to the longitudinal axis X of the turbine engine. When the turbine engine 2 is attached under the wing of the aircraft, analogous to a clock face, the pylon 40 is located at the 12 o'clock position (12 o'clock ± 10°, parallel to the ground or the dihedral of the wing). 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, axis X and axis B are in the same vertical plane. The pylon can also be tilted a few degrees relative to the vertical plane (vertical plane / dihedral plane of the wing) or the horizontal plane, preferably ± 10° (to improve airflow around the fuselage).

[0031] Figure 1 An orthogonal reference frame XYZ is also shown, where X is oriented from upstream to downstream of the turbine engine. X is the longitudinal axis of turbine engine 2. The Z-axis is oriented vertically upwards, and the Y-axis is oriented to one side.

[0032] 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 aircraft component is generated by tensile stress, while the vertical force applied to the aircraft component is generated by tensile / compressive stress. That is, in addition to axial force, lateral force, and vertical force, torque is also applied to the aircraft component. The aircraft component experiences axial torque, lateral torque, and vertical torque along the X-axis, Y-axis, and Z-axis, respectively.

[0033] When a component of the suspension system (e.g., an attachment member for attaching the mount 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 or thrust 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 mount 40 to the turbine engine 2 bears a moment Mx about the X-axis, this means that the attachment member 45 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.

[0034] The purpose of this invention is to withstand control forces. As previously stated, when the engine is at an angle of attack, the control forces arise from the torque generated by the asymmetry of the resultant pressure on the propeller blades or the intake control column (in a ducted engine) connected to the fan housing. In the case of a turbine engine with a ducted propeller, the control forces are typically distributed between the exhaust casing 22 and the hub 26 of the intake casing 25 of the turbine engine. In the case of a turbine engine with a non-ducted propeller (not shown), the control forces are typically distributed between the exhaust casing of the turbine engine and the propeller blades.

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

[0036] According to the invention and as shown in the figures, the suspension system includes connecting elements for connecting the mounts to the turbine engine, all of which are located upstream of the combustion chamber 19. In other words, there are no connecting elements located at or downstream of the combustion chamber 19. This means that there are no connecting elements between the high-pressure turbine 20 and the low-pressure turbine 21, or even between these turbines and the exhaust casing 22 of the turbine engine. Because the assembly does not include any connecting elements at or downstream of the combustion chamber 19, the high-pressure body is referred to as cantilevered. The consequences of this arrangement will be described below.

[0037] According to the invention, these connecting elements include first thrust bearing rods 43, 44 extending from the bracket 40 to the compressor housing 24 and configured to bear forces along the Y-axis and Z-axis. More specifically, the first thrust bearing rods 43, 44 may include a first end 47a and a second opposite end 47b, the first end 47a being connected to the compressor housing 24 and the second opposite end 47b being connected to the bracket 40. Therefore, the first thrust bearing rods 43, 44 bear thrust vertically and laterally. This means that the first thrust bearing rods 43, 44 prevent any movement of the components connected to them along the Y-axis and Z-axis. The first thrust bearing rods 43, 44 function by default because, when the first thrust bearing rods 43, 44 are undamaged or unbroken, they provide attachment and suspension functions by default.

[0038] For example, the first thrust bearing rods 43 and 44 may include two inclined links in a second plane of the Y and Z axes, in this case a vertical link and a lateral link.

[0039] exist Figure 1 In China, due to Figure 1The schematic diagram is a side view of component 1, in which only one of the first thrust bearing rods 43 and 44 is visible. However, these first thrust bearing rods 43 and 44 can be tilted relative to each other, that is, these first thrust bearing rods 43 and 44 can form a non-zero angle with each other.

[0040] The connecting element also includes a connecting structure 50 for connecting the bracket 40 to the fan housing 11. The connecting structure 50 is configured to withstand forces along the Y and Z axes, a thrust along the X axis, and a torque Mx caused by the motor torque. Therefore, the connecting structure 50 withstands the thrust vertically and laterally, meaning that it respectively prevents any movement of the component connected to it along the Y or Z axis. The connecting structure 50 is also configured to withstand the torque Mx caused by the motor torque, and it works in conjunction with the first bearing rods 43 and 44 to withstand the torques My and Mz generated along the Y and Z axes.

[0041] Therefore, the mount 40 is connected to the compressor housing 24 via first force-bearing rods 43 and 44, and to the fan housing 11 via a connecting structure 50. Preferably, the first force-bearing rods can be directly connected to the center of the mount 40 via one of their ends. These connecting elements 43, 44, and 50 work together to withstand control forces from the turbine engine 2. Thus, component 1 according to this embodiment of the invention enables the withstanding of control forces without requiring the mount 40 to be connected to the gas generator 16 downstream of the turbine engine (i.e., downstream of the combustion chamber 19).

[0042] Therefore, the control force is borne by the suspension system and does not need to be transmitted along the length of the turbine engine 2, especially not through the high-pressure body as described above. Therefore, the risk of bending of the gas generator 16 and deformation of the high-pressure body does not exist. Therefore, not only does the suspension system of component 1 according to this first embodiment of the invention not include any connecting elements downstream of the combustion chamber 19, but as described above, no attachment elements are required downstream of the combustion chamber 19.

[0043] In this respect, advantageously, Figure 1 In the first embodiment shown, the first force-bearing rods 43 and 44 and the connecting structure 50 are the only connecting elements for connecting the mount 40 to the turbine engine 2. Therefore, the control force is simply borne and is borne in a manner that maintains the performance and operability of the high-pressure body.

[0044] Still referencing Figure 1 In the first embodiment of component 1 shown, the connecting structure 50 is also configured to withstand a thrust along the longitudinal axis X. Therefore, the connecting structure 50 withstands the thrust longitudinally. This means that the connecting structure prevents any movement of the components connected to it along the longitudinal axis X.

[0045] Figure 3 A connection structure 50, which can be used in the context of this invention, is shown. The connection structure 50 includes at least a first element 51 and a second element 52, the first element 51 for attachment to the bracket 40, and the second element 52 for attachment to the fan housing 11, particularly to a first axial end 12 of 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 includes lateral links 56a, 56b and a central link 57.

[0046] Lateral links 56a and 56b are located in a second plane along the Y and Z axes, and each lateral link includes three joints, enabling it to withstand lateral and vertical forces. The central link 57 is located in the XZ plane and has two ends with conventional ball-and-socket joints. The central link 57 withstands axial forces. The connection structure 50 is capable of withstanding a moment Mx about the X-axis and also a longitudinal thrust along the longitudinal axis X of the turbine engine 2. The moment Mx is borne by the Y-bearings of the first force-bearing links 43 and 44 and links 56a and 56b, while the moment Mz is borne by the Z-bearings of the first force-bearing links 43 and 44 and links 56a and 56b.

[0047] In addition to the connecting structure, a ball-and-socket system can be provided to withstand forces at the 12 o'clock position on the X and Y axes (for the torque Mx connected to the motor torque). This ball-and-socket system includes two connecting rods with vertical clearance and inclined in the planes of the Y and Z axes to withstand forces along the Y and Z axes. As an alternative to the ball-and-socket system, a crank-type system can also be used to withstand these forces. A longitudinally oriented (i.e., oriented along the X-axis) bearing rod can then be added to the crank-type system.

[0048] Now for reference Figure 2 The following diagram illustrates the components according to a second embodiment of the invention in a very schematic manner. The second embodiment differs from the previous embodiment only in the presence of additional connecting elements as described below, and the connecting structure 50 may not be configured to withstand thrust along the longitudinal axis X.

[0049] In this second embodiment, the connecting element further includes second thrust-bearing rods 45 and 46, which extend from the bracket 40 to the intake housing 25 located upstream of the low-pressure compressor 17 and the high-pressure compressor 18, and are configured to bear thrust along the longitudinal axis X. More specifically, the attachment points of the second rods 45 and 46 to the bracket 40 are located downstream of the attachment points of the second rods 45 and 46 to the intake housing 25. Therefore, the second thrust-bearing rods 45 and 46 bear thrust longitudinally. This means that the second thrust-bearing rods 45 and 46 prevent any movement of the components connected to them along the longitudinal axis X.

[0050] Therefore, with Figure 1 Unlike the first embodiment shown, the connecting structure 50 may not be configured to withstand thrust along the longitudinal axis X, because these longitudinal thrusts are borne by the second thrust-bearing rods 45, 46. In fact, in this second embodiment of the invention, the connecting structure 50 is not configured to withstand thrust along the longitudinal axis X. Therefore, in Figure 2 In the embodiment shown, the connecting structure 50 does not include the central connecting rod 57.

[0051] exist Figure 2 In China, due to Figure 2 The schematic diagram is a side view of component 1, in which only one of the second thrust bearing rods 45 and 46 is visible. The second thrust bearing rods 45 and 46 can be tilted relative to each other, that is, the second thrust bearing rods 45 and 46 can form a non-zero angle with each other.

[0052] In this second embodiment, the mount 40 is connected to the compressor housing 24 via first thrust bearing rods 43 and 44, to the intake housing 25 via second thrust bearing rods 45 and 46, and to the fan housing 11 via a connecting structure 50. These connecting elements 43, 44, 45, 46, and 50 work together to withstand control forces from the turbine engine 2. Therefore, the assembly 1 according to this second embodiment of the invention enables the withstand of control forces without requiring the mount 40 to be connected to the gas generator 16 downstream of the turbine engine (i.e., downstream of the combustion chamber 19).

[0053] Therefore, the control force is borne by the suspension system and does not need to be transmitted along the length of the turbine engine 2, especially not through the high-pressure body. Therefore, the risk of bending of the gas generator 16 and deformation of the high-pressure body does not exist. Therefore, not only does the suspension system of component 1 according to the second embodiment of the invention not include any connecting elements downstream of the combustion chamber 19, but as mentioned above, one or more attachment elements are not required downstream of the combustion chamber 19.

[0054] Advantageously, in this second embodiment, the first force-bearing rods 43 and 44, the second thrust-bearing rods 45 and 46, and the connecting structure 50 are the only connecting elements for connecting the mount 40 to the turbine engine 2. Therefore, the control force is simply borne and is borne in a manner that maintains the performance and operability of the high-pressure body.

[0055] like Figure 2 As shown in the schematic diagram, the second thrust bearing rods 45 and 46 are connected to the hub 26 of the intake housing 25. As previously described, the intake housing 25 includes radial blades 15 that extend radially outward from the hub 26 and through the secondary conduit V2 to rigidly connect the gas generator 16 to the fan housing 11. The second thrust bearing rods 45 and 46 include a first end 48a and a second opposite end 48b, the first end 48a being connected to the hub 26 of the intake housing 25 and the second opposite end 48b being connected to the hanger 40. Similar to the first thrust bearing rods 43 and 44, the second thrust bearing rods 45 and 46 function by default because they provide attachment and suspension functions by default when they are not damaged or broken.

[0056] exist Figure 1 and Figure 2 In the illustrated embodiment, the mounting bracket 40 includes an upstream end 42 located in a plane P1 perpendicular to the longitudinal axis X and upstream of the combustion chamber 19, preferably upstream of the compressor housing 24. Advantageously, the second ends 47b and 48b of the first thrust bearing rods 43, 44 and the second thrust bearing rods 45, 46 are directly connected to the upstream end 42 of the mounting bracket. Therefore, lateral and vertical forces are borne in plane P1, and thus upstream of the gas generator 16. Also preferably, the upstream end 42 of the mounting bracket 40 and plane P1 are located downstream of the fan housing 11, which facilitates a connection between the mounting bracket 40 and the fan housing 11 via a connecting structure 50.

[0057] According to a variation of the embodiment, the upstream end 42 of the bracket lies in a plane (not shown) that is perpendicular to the longitudinal axis X and passes through the downstream axial end of the fan housing 11. In this configuration, advantageously, the connecting structure 50 is connected to the downstream axial end of the fan housing and the upstream end 42 of the bracket 40.

[0058] 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 an aircraft turbine engine (2), a pylon (40) for mounting the turbine engine on an aircraft component, and a system for suspending the turbine engine on the pylon. 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 extending about the longitudinal axis (X) and about the fan (10) of the turbine engine, and >A gas generator (16) 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 a low-pressure compressor (17), a compressor housing (24), a high-pressure compressor (18), an annular combustion chamber (19), and at least one turbine (20, 21), the fan housing (11) being located radially 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 pylon (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 (43, 44, 45, 46, 50) for connecting the mount to the turbine engine. The characteristic feature is that all of the connecting elements (43, 44, 45, 46, 50) are located upstream of the combustion chamber (19) and include: - A first force-bearing rod (43, 44), extending from the bracket (40) to the compressor housing (24), is configured to bear thrust along two axes (Y, Z), the two axes being perpendicular to each other and perpendicular to the longitudinal axis (X). - A connection structure (50) for connecting the bracket (40) to the fan housing (11) is configured to withstand thrust along two axes (Y, Z) and torque generated along these axes, which are perpendicular to each other and perpendicular to the longitudinal axis (X). The connecting elements (43, 44, 45, 46, 50) are configured to withstand control forces.

2. The component (1) according to claim 1, wherein, The connection structure (50) is also configured to withstand thrust along the longitudinal axis (X).

3. The component (1) according to claim 1 or 2, wherein, The first thrust bearing rod (43, 44) and the connecting structure (50) are the only connecting elements for connecting the mount (40) to the turbine engine (2).

4. The component (1) according to claim 1, wherein, The connecting element further includes a second thrust bearing rod (45, 46) extending from the bracket (40) to the intake housing (25) located upstream of the low-pressure compressor and the high-pressure compressor (17, 18), and the second thrust bearing rod is configured to bear thrust along the longitudinal axis (X).

5. The component (1) according to the preceding claim, wherein, The first thrust bearing rod (43, 44), the second thrust bearing rod (45, 46) and the connecting structure are the only connecting elements for connecting the mount (40) to the turbine engine (2).

6. The component (1) according to claim 4 or 5, wherein, The second thrust bearing rod (45, 46) is connected to the hub (26) of the intake housing (25), which includes radial blades (15) that extend radially outward from the hub (26) and through the secondary pipe (V2) to rigidly connect the gas generator (16) to the fan housing (11).

7. The component (1) according to the preceding claim, wherein, The mounting bracket (40) includes an upstream end (42) located in a plane (P1) perpendicular to the longitudinal axis (X) and upstream of the combustion chamber (19), preferably upstream of the compressor housing.

8. The component according to the preceding claim, wherein, The upstream end (42) of the bracket is located downstream of the fan housing (11).

9. The component (1) according to claim 7, wherein, The upstream end (42) of the bracket is located in a plane perpendicular to the longitudinal axis (X) and passing through the downstream axial end of the fan housing (11), and the connecting structure (50) is connected to the downstream axial end of the fan housing and the upstream end (42) of the bracket.

10. The component (1) according to any one of the preceding claims, wherein, The connection structure (50) includes two lateral links (56a, 56b) located in a second plane having a Y-axis and a Z-axis.

Images