Aircraft assembly comprising a turbomachine, a pylon and a mounting system

Abstract

Assembly for an aircraft comprising a turbomachine (100), a pylon (2), and a mounting system (605) for the turbomachine (100) to the pylon (2), the turbomachine comprising, along the longitudinal axis (XX) in the direction of the generated flow, a low-pressure compressor (12), a high-pressure compressor (14), and a rear section (1), the mounting system comprising first (506) and second downstream mounting means (604, 614) for the turbomachine to the pylon fixed to the turbomachine in a downstream plane BB perpendicular to the longitudinal axis and passing through the high-pressure compressor, and thrust force transfer means (208) connecting the turbomachine to the pylon. Figure for the abbreviation: [Fig. 2]

Description

Title of the invention: Aircraft assembly comprising a turbomachine, a pylon and a mounting system. Technical field of the invention

[0001] The invention relates to the field of turbomachine attachments to an aircraft. In particular, the invention relates to an aircraft assembly comprising a turbomachine, a pylon, and a system for attaching the turbomachine to the pylon, prior art

[0002] Existing systems for fixing a turbomachine to an aircraft pylon are described, for example, in documents WO2022 / 245363, WO2022 / 248791 or WO2023 / 198962.

[0003] A turbomachine generally comprises, in one flow direction, an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air enters through the inlet section and flows to the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section, where combustion gases are generated. The combustion gases then flow from the combustion section along a defined hot gas path in the turbine section and exit the combustion section through the exhaust section. Such a turbomachine produces thrust capable of propelling a motor vehicle, such as an aircraft.On an aircraft, the thrust generated by the turbomachine produces thrust forces transmitted to a support, such as a pylon or cradle, and similarly, the aircraft applies equal and opposite reaction forces to the support. This load induces a pitching moment or a yaw moment in the turbomachine. It is therefore necessary to reduce these pitching and yaw moments applied to the turbomachine so that it does not deform to the point of degrading its operating performance.

[0004] Indeed, when the turbomachine produces thrust and is subjected to maneuvering loads (aerodynamic forces on a nacelle or propeller associated with the turbomachine), the turbomachine itself is subjected to stresses. The backbone bending of a turbomachine casing, induced by these stresses, creates gap closures and even wear, degrading the turbomachine's performance, thus increasing fuel consumption and accelerating the turbomachine's aging.

[0005] In the context of unfaired turbomachinery generally used on short- or medium-range aircraft, the attachment of the turbomachinery is important in the direction where the turbomachine's propeller has a large diameter, thus inducing significant axial moment loads. Furthermore, to achieve high performance, the turbomachine has a small, high-pressure body which is therefore sensitive to all stresses such as gravitational loads, aircraft maneuvers, and axial moment loads.

[0006] A conventional turbomachine suspension with an upstream attachment on an upstream casing and a downstream attachment on a turbine casing or an exhaust casing does not allow for optimization of the performance of the turbomachine assembly and aircraft cradle or pylon.

[0007] Another known solution, from document WO2022 / 245363, is to position a downstream suspension on the casing upstream of a high-pressure body (cantilevered high-pressure body solution). The bending moments induced by the aerodynamic forces upstream of the turbomachine and the thrust will no longer be transmitted through the high-pressure body. Furthermore, this solution can create significant displacements between the tower and the turbomachine at the level of the high-pressure body not held by suspensions, particularly when the turbomachine is subjected to acceleration factors, such as gravitational acceleration and aircraft maneuvers, causing significant clearance wear and displacements between the turbomachine and the tower.Furthermore, as the two suspension planes are close together, it is difficult to achieve a good compromise of rigidity between the pylon and the upstream casing, which also leads to significant clearance consumption between the turbomachine and the pylon under axial moment loads. Description of the invention

[0008] An object of the invention is to provide an aircraft assembly comprising a turbomachine, a pylon and a system for attaching the turbomachine to the pylon which does not have the disadvantages of the prior art.

[0009] To this end, the invention provides an assembly for an aircraft comprising a turbomachine, a pylon, and a system for attaching the turbomachine to the pylon. The turbomachine extends along a longitudinal axis oriented along an X-axis, oriented in the direction of a flow generated by the turbomachine, from an orthonormal coordinate system comprising a Z-axis oriented towards the pylon, and a Y-axis. The turbomachine comprises, along the longitudinal axis, a low-pressure compressor, a high-pressure compressor, and a rear section. The attachment system comprises first downstream attachment means for the turbomachine to the pylon, fixed to the turbomachine in a downstream plane perpendicular to the longitudinal axis and passing through the high-pressure compressor, and thrust force transfer means connecting the turbomachine to the pylon. The first downstream attachment means are fixed to the pylon upstream of the means. to resume thrust forces, the fixing system includes second means of fixing downstream of the turbomachine to the pylon fixed to the turbomachine in the downstream plane.

[0010] Advantageously, but optionally, the assembly according to the invention has at least one of the following technical characteristics: • the means for recovering thrust forces include a recovery linkage forming in a plane ZX an angle a with a longitudinal axis of the turbomachine between 30° and 60°; • angle a is approximately 45°; • the second downstream fastening means include a "yoke" type suspension; • the second downstream fixing means include a ball-to-ball joint and a "boomerang" type link, mounted on the pylon and extending towards the turbomachine; • the ball joint and the linkage are inclined downstream; • The ball-joint connecting rod and the joint extend on either side of a plane ZX; • The ball-joint connecting rod and part of the joint are mirror-symmetrical with respect to the ZX plane; and, • the fixing system also includes a flexible connection between the rear part and the pylon. brief description of the figures

[0011] Other features and advantages of the invention will become apparent from the following description of an embodiment of the invention. See the accompanying drawings:

[0012] [Fig-1] is a schematic half-view of an aircraft assembly comprising a turbomachine, a pylon and a system for linking the turbomachine to the pylon;

[0013] [Fig.2] is a schematic half-view of an aircraft assembly according to the invention, comprising a turbomachine, a pylon and a system for connecting the turbomachine to the pylon;

[0014] [Fig.3] is a schematic view along the downstream plane of the aircraft assembly of the [Fig.2];

[0015] [Fig.4] is a schematic top view along the downstream plane of the assembly for aircraft of the [Fig.2]; and,

[0016] [Fig.5] is a schematic side view along the downstream plane of the aircraft assembly in the figure.

[0017] For clarity, identical or similar elements are identified by identical reference signs throughout the figures. detailed description of a method of implementation

[0018] With reference to [Fig. 1], we will describe an example of a mounting system 5 for a turbomachine 100 attached to an aircraft pylon 2. The pylon 2 is itself attached to an aircraft wing 3. The turbomachine 100 comprises, in the direction of flow, a propeller 7, a low-pressure compressor 12, a high-pressure compressor 14, and a rear section 1 including a combustion chamber, a high-pressure turbine, and a low-pressure turbine. The turbomachine 100 extends along a longitudinal axis XX oriented along an axis X, oriented in a direction of the flow generated by the turbomachine, from an orthonormal frame R comprising an axis Z oriented towards the pylon, and an axis Y. Depending on a type of attachment of the turbomachine 100 on the aircraft, the Z axis is vertical if the attachment is under the wing 3, or the Z axis is horizontal if the attachment is behind a fuselage of the aircraft.

[0019] The pylon 2 here includes one or more guide vanes 11 generally intended to direct an airflow through a bypass of the turbomachine 100. Alternatively, the guide vanes 11 are mounted on the turbomachine 100.

[0020] The fastening system 5 comprises, in an upstream plane AA perpendicular to the longitudinal axis XX of the turbomachine, upstream fastening means 4, and in a downstream plane BB perpendicular to the longitudinal axis XX of the turbomachine, downstream fastening means 6. In addition, the fastening system 5 comprises thrust force resistors 8. Thus, the forces and moments generated by a weight P and the operation (vertical forces and axial moments MF) of the turbomachine 100 are resisted between the upstream fastening means 4, downstream means 6 and the thrust force resistors 8. Furthermore, the upstream plane AA and downstream plane BB are positioned so that a center of gravity 10 (where the weight P is exerted) is located between said upstream plane AA and downstream plane BB, and consequently between the upstream fastening means 4 and downstream means 6.In particular, the upstream AA plane passes through the low-pressure compressor 12 and the downstream BB plane passes substantially through the high-pressure compressor. The thrust force recovery means 8 are fixed to the turbomachine 100 in the vicinity of the downstream BB plane.

[0021] Moreover, the upstream planes AA and downstream planes BB (and therefore the upstream fixing means 4 and downstream 6) are separated by a distance D. On the other hand, the thrust force retrieval means 8 are fixed on the pylon 2 at a distance D' from the upstream plane AA, and therefore from the upstream fixing means 4. The distance D' is, here, greater than the distance D. Consequently, as illustrated here, the rear part 1 of the turbomachine 100 is positioned in cantilever.

[0022] With reference to Figures 2 to 5, we will describe an embodiment of an aircraft assembly comprising a turbomachine 100, a pylon 2 and a Fixing system 605 of the turbomachine 100 according to the invention. Figures 3 to 5 correspond to the downstream plane BB.

[0023] The fastening system 605 includes thrust force resistors 208, which in this case comprise a thrust linkage 208 including two ball-and-socket connecting rods. The two ball-and-socket connecting rods 208 are positioned symmetrically, mirrored with respect to a vertical plane ZX passing through a longitudinal axis XX of the turbomachine. The thrust force resistors allow for the resisting of axial forces FX at the main and vertical forces FT. For this purpose, the ball-and-socket connecting rods 208 are oriented in the vertical plane ZX at an angle α with respect to the longitudinal axis XX of the turbomachine 100. The angle α has a value between 30° and 60°, ideally 45°.

[0024] Furthermore, the mounting system 605 includes first downstream mounting means 506. The first downstream mounting means comprise, in this case, an axial ball-and-socket joint 506 extending in the ZX plane. The axial ball-and-socket joint 506 is fixed at one end to the turbomachine 100 in the downstream BB plane, for example, along the direction of the Z axis, here at 12 o'clock in this plane. At the other end, the axial ball-and-socket joint 506 is fixed to the pylon 2 near a mounting point for a thrust force transfer linkage 208. The first downstream mounting means 506 limit the tilting of the turbomachine 100, at the level of the downstream BB plane, under the thrust forces and moments generated by the propeller 7.

[0025] The mounting system 605 further comprises second downstream mounting means 604, 614 of the turbomachine 100 to the pylon 2 at the level of the downstream plane BB. The second downstream mounting means here comprise a ball-and-socket joint 604 extending between the pylon 2 and the turbomachine 100. The ball-and-socket joint 604 is positioned here on one side of the plane ZX. On the other side of the plane ZX, still in the downstream plane BB, the second downstream mounting means further comprise a link 614, called a "boomerang," extending between the pylon 2 and the turbomachine 100 and positioned opposite the ball-and-socket joint 604, for a portion of the link fixed to the turbomachine 100, symmetrically mirrored with respect to the plane ZX. Link 614 includes a boomerang-shaped part fixed by three kinematic links: a ball joint with the turbomachine 100 and two ball joints with the pylon 2.The entire ball-joint 604 connecting rod and the 614 linkage form a "yoke" type suspension.

[0026] In addition, the ball joint 604 and the link 614 are inclined downstream so as to allow some of the axial forces FX to be taken up.

[0027] The ball-joint connecting rod 604 and the joint 614 allow lateral forces FL, vertical forces FT, and forces coming from the ZX plane to be absorbed on either side. engine torque generated by the turbomachine 100. For example, the recovery of forces by the first downstream fastening means 604,614 takes place at 10 o'clock and 2 o'clock respectively in the downstream plane BB on the turbomachine 100.

[0028] It follows from the above that the turbomachine 100 to pylon 2 mounting system 605, as previously described, is an isostatic mounting system where the vertical, axial, and lateral forces, as well as the engine torque MX, are transferred to the downstream plane BB. The turbomachine 100 to pylon 2 mounting system 605, as previously described, relieves a constraint on the integration of pylon 2 at the OGV (Outer Guide Vane), which provides an advantage in terms of aerodynamics, while also allowing a reduction in the length of pylon 2 and therefore the associated stiffness requirements.

[0029] It should be noted that the embodiments of the fastening system 605 of a turbomachine 100 according to the invention have been described in relation to a cantilevered rear part 1. However, the fastening system 605 of the turbomachine 100 to the pylon 2 according to the invention as previously described is applicable, mutatis mutandis, to a turbomachine 100 whose rear part 1 is suspended by one or more flexible links 9 from the pylon 2 and extending in the YZ plane, between the turbomachine 100, at the level of an exhaust casing, and the pylon 2, as illustrated in dashed lines on [Fig. 1]. The role of this (these) flexible link(s) 9 is to limit the impact of inertial forces while limiting the bending moments linked to the forces coming from the engine torque generated by the turbomachine 100 to take up load factors of vertical and possibly lateral maneuvers.The flexibility of these links 9 is adapted to find the best compromise between the inertial effects and the aerodynamic moments of the propeller 7 of the turbomachine 100.

[0030] Naturally, the invention is described above by way of example. It is understood that a person skilled in the art is able to carry out different embodiments of the invention without departing from the scope of the invention.

[0031] It is emphasized that all features, as they are apparent to a person skilled in the art from the present description, drawings and attached claims, even if in practice they have only been described in relation to other specific features, both individually and in any combinations, may be combined with other features or groups of features disclosed herein, provided that this has not been expressly excluded or that technical circumstances make such combinations impossible or meaningless.

Claims

Demands

1. Assembly for an aircraft comprising a turbomachine (100), a pylon (2), and a mounting system (605) for the turbomachine (100) to the pylon (2), the turbomachine extending along a longitudinal axis (XX) oriented along an X axis, oriented in the direction of a flow generated by the turbomachine, from an orthonormal frame (R) comprising a Z axis oriented towards the pylon, and a Y axis, the turbomachine comprising, along the longitudinal axis (XX), a low-pressure compressor (12), a high-pressure compressor (14), and a rear section (1), the mounting system comprising first downstream mounting means for the turbomachine to the pylon fixed to the turbomachine in a downstream plane (BB) perpendicular to the longitudinal axis (XX) and passing through the high-pressure compressor, and thrust-response means connecting the turbomachine to the pylon, the first downstream mounting means being fixed to the upstream pylon means of resuming thrusting effortsin which the fastening system (605) comprises second downstream fastening means (604, 614) of the turbomachine to the pylon fixed to the turbomachine in the downstream plane (BB).

2. Assembly according to claim 1, wherein the means for recovering thrust forces comprise a recovery linkage (208) forming in a plane ZX an angle α with a longitudinal axis of the turbomachine between 30° and 60°.

3. Assembly according to claim 2, wherein the angle a is equal to approximately 45°.

4. Assembly according to any one of claims 1 to 3, wherein the second downstream fastening means comprise a "yoke" type suspension.

5. Assembly according to claim 4, wherein the second downstream fastening means comprise a ball-to-ball joint (604) and a boomerang-type link (614), mounted on the pylon and extending towards the turbomachine.

6. Assembly according to claim 5, wherein the ball-joint connecting rod (604) and the linkage (614) are inclined downstream.

7. Assembly according to any one of claims 5 and 6, wherein the ball-joint connecting rod (604) and the linkage (614) extend on either side of a plane ZX.

8. Assembly according to claim 7, wherein the ball-to-ball joint (604) and a portion of the linkage (614) are mirror-symmetric with respect to the ZX plane.

9. Assembly according to any one of claims 1 to 8, wherein the fastening system further comprises a flexible connection (9) between the rear part and the pylon.