Assembly for an aircraft comprising a turbomachine, a pylon and a fastening system

Abstract

An assembly for an aircraft comprising a turbomachine (100), a pylon (2) and a fastening system for fastening the turbomachine (100) to the pylon (2), the turbomachine comprising, along the longitudinal axis (XX) in the direction of the flow generated, a low-pressure compressor (12), a high-pressure compressor (14) and a rear part (1), the fastening system comprising upstream fastening means for fastening the turbomachine to the pylon that are fastened to the turbomachine in an upstream plane AA perpendicular to the longitudinal axis and passing through the low-pressure compressor, downstream fastening means for fastening the turbomachine to the pylon that are fastened to the turbomachine in a downstream plane BB perpendicular to the longitudinal axis and passing through the high-pressure compressor, and means for reacting thrust forces that connect the turbomachine to the pylon.

Description

DESCRIPTION TITLE: 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 connecting the turbomachine to the pylon. PRIOR TECHNOLOGY

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

[0003] A turbomachine typically comprises, in one flow direction, an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section. During 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. These 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 wing support, such as a pylon, and similarly, the aircraft applies equal and opposite reaction forces to the wing. 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 a turbomachine generates 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 the turbomachine casing, induced by these stresses, creates gaps and even wear, degrading the turbomachine's performance, thus increasing fuel consumption and accelerating its aging.

[0005] A 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. However, this solution can create significant displacements between the tower and the turbomachine at the level of the high-pressure body not supported by suspensions, particularly when the turbomachine is subjected to acceleration factors. DESCRIPTION OF THE INVENTION

[0006] One 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.

[0007] 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, which is oriented in the direction of a flow generated by the turbomachine, and is based on 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 includes upstream attachment means for the turbomachine to the pylon, fixed to the turbomachine in an upstream plane perpendicular to the longitudinal axis and passing through the low-pressure compressor, and 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 means for taking up thrust forces connecting the turbomachine to the pylon, the downstream fixing means being fixed on the pylon between the upstream fixing means and the means for taking up thrust forces, in which the downstream fixing means comprise a link including one degree of freedom along a direction of the Z axis.

[0008] Advantageously, but optionally, the assembly according to the invention has at least one of the following technical characteristics: - the thrust force recovery means comprise a recovery linkage forming, in a ZX plane, an angle α with a longitudinal axis of the turbomachine of between 30° and 60°; - the angle α is approximately 45°; - the downstream fastening means comprise an annular linear link oriented along the Z axis and fixed to the turbomachine along the direction of the Z axis; - the downstream fastening means comprise a ball-and-socket connecting rod oriented substantially in the XY plane and fixed to the turbomachine along the direction of the Z axis; - the ball-and-socket connecting rod is substantially along the Y axis; - the ball-and-socket connecting rod is substantially along the X axis; - the upstream fastening means comprise a ball-and-socket connecting rod extending in a YZ plane; - the ball-and-socket connecting rod is substantially parallel to the Z axis;- the ball-and-socket joint is fixed to the turbomachine along the Z-axis direction; - the upstream fixing means comprise another ball-and-socket joint, the two ball-and-socket joints being positioned symmetrically as mirror images along a ZX plane of each other, and an annular linear link oriented along the Z-axis and fixed to the turbomachine along the Z-axis direction; - the upstream fixing means comprise another ball-and-socket joint, the two ball-and-socket joints being positioned symmetrically as mirror images along a; plane ZX, one from the other, and another ball-joint connecting rod (324) oriented substantially along the Y-axis and fixed to the turbomachine along the Z-axis; - the upstream fixing means comprise an annular linear link oriented along the X-axis and fixed to the turbomachine along the Z-axis; and, - the fixing system further comprises a flexible link between the rear part and the pylon. BRIEF DESCRIPTION OF THE FIGURES

[0009] Other features and advantages of the invention will become apparent from the following description of an embodiment of the invention. In the accompanying drawings: [Fig. 1] is a schematic half-view of an aircraft assembly comprising a turbomachine, a pylon, and a system for connecting the turbomachine to the pylon; [Fig. 2] is a schematic view in the upstream, downstream, and top planes of a first embodiment of an aircraft assembly comprising a turbomachine, a pylon, and a system for connecting the turbomachine to the pylon according to the invention; [Fig. 3] is a schematic half-view of the assembly shown in Figure 2; [Fig. 4] is a schematic view in the upstream, downstream, and top planes of a variant embodiment of the first embodiment of an aircraft assembly comprising a turbomachine, a pylon, and a system for connecting the turbomachine to the pylon according to the invention; [Fig.5] is a schematic half view of the whole of figure 4; [Fig.[Fig. 6] is a schematic view according to the upstream, downstream and top planes of a second embodiment of an aircraft assembly comprising a turbomachine, a pylon and a turbomachine-to-pylon connection system according to the invention; [Fig. 7] is a schematic half view of the assembly of Figure 6; [Fig. 8] is a schematic view according to the upstream, downstream and top planes of an alternative embodiment of the second embodiment of an aircraft assembly comprising a turbomachine, a pylon and a system for connecting the turbomachine to the pylon according to the invention; [Fig. 9] is a schematic half view of the assembly of Figure 8; [Fig. 10] is a schematic view according to the upstream, downstream and top planes of a third embodiment of an aircraft assembly comprising a turbomachine, a pylon and a system for connecting the turbomachine to the pylon according to the invention; [Fig. 11] is a schematic view according to the upstream, downstream and top planes of a fourth embodiment of an aircraft assembly comprising a turbomachine, a pylon and a system for connecting the turbomachine to the pylon according to the invention; [Fig.[Fig. 12] is a schematic view according to the upstream and top planes of a fifth embodiment of an aircraft assembly comprising a turbomachine, a pylon and a turbomachine-to-pylon connection system according to the invention; and, [Fig. 13] is a half view of the assembly of Figure 12.

[0010] For clarity, identical or similar elements are identified by the same reference symbols throughout the figures. DETAILED DESCRIPTION OF AN IMPLEMENTATION METHOD

[0011] With reference to Figure 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 the 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 X-axis, which is oriented in the direction of the flow generated by the turbomachine, from an orthonormal coordinate system R comprising a Z-axis oriented towards the pylon and a Y-axis. Depending on one type of mounting of the turbomachine 100 on the aircraft, the Z-axis is vertical if the attachment is under wing 3, or the Z axis is horizontal if the attachment is behind an aircraft fuselage.

[0012] 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.

[0013] 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.

[0014] Furthermore, the upstream planes AA and downstream 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.

[0015] With reference to Figures 2 and 3, we will describe a first embodiment of an aircraft assembly comprising a turbomachine 100, a pylon 2, and a mounting system 205 for the turbomachine 100 according to the invention. In Figure 2, view A corresponds to the upstream plane AA, and view B to the downstream plane BB. and view C is a top view of the means of resuming thrust forces 208.

[0016] The upstream fastening means 204 here include a ball joint 204 connecting the turbomachine 100 to the pylon 2 in the upstream AA plane. This ball joint 204 allows for the transfer of axial forces FX, lateral forces FL, and vertical forces FT. In a first embodiment, the upstream fastening means 204 include an annular linear joint oriented to transfer axial forces FX and lateral forces FL, accompanied by a vertical ball-and-socket joint to transfer vertical forces FT. In a second embodiment, the upstream fastening means 204 include an annular linear joint oriented to transfer axial forces FX and vertical forces FT, accompanied by a ball-and-socket joint in the lateral direction to transfer lateral forces FL.

[0017] The fastening means 206 of the fastening system 205 includes a lateral ball-and-socket joint positioned so that the ball joint connection with the turbomachine 100 is along the direction of the Z-axis, here at 12 o'clock in the downstream plane BB. Thus, the fastening means 206 resist lateral forces FL. The fastening means 206 have one degree of freedom along the direction of the Z-axis.

[0018] The thrust force transfer means 208 of the mounting system 205 comprise, here, a transfer linkage 208 including, here, two ball-and-socket transfer links. Here, the two ball-and-socket transfer links 208 are positioned symmetrically, mirrored with respect to a vertical plane ZX passing through a longitudinal axis XX of the turbomachine. The thrust force transfer means allow for the transfer of axial forces FX to the main and vertical forces FT. For this purpose, the ball-and-socket transfer links 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°.

[0019] With reference to Figures 4 and 5, we will describe a variant embodiment 215 of the first embodiment of the aircraft assembly comprising a turbomachine 100, a pylon 2, and a turbomachine mounting system 205. 100 according to the invention. The fastening system 215 differs from the first embodiment of the fastening system 205 in that the upstream fastening means 214 comprise an annular linear link oriented along the X-axis so as to resist lateral FL and vertical FT forces at 12 o'clock in the upstream AA plane, and in that the fastening means 216 comprise an annular linear link oriented along the Z-axis so as to resist lateral FL and axial FX forces at 12 o'clock in the downstream BB plane. Again, the fastening means 216 include one degree of freedom along the Z-axis. The thrust force resisting means 208 remain unchanged.

[0020] With reference to figures 6 and 7, we will describe a second embodiment of an aircraft assembly comprising a turbomachine 100, a pylon 2 and a fixing system 305 for a turbomachine 100 according to the invention.

[0021] The fastening system 305 includes the means for taking up the thrust forces 208 previously described.

[0022] The upstream fastening means 304, 314 of the fastening system 305 include a vertically oriented annular linear link 314, positioned at 12 o'clock in the upstream plane AA, which absorbs lateral FL and axial FX forces. On either side of this annular linear link 314, in the upstream plane AA, the upstream fastening means include a ball-and-socket connecting rod 304. The two ball-and-socket connecting rods 304 allow for the absorption, on either side of the annular linear link 314, of vertical FT forces and forces from the engine torque generated by the turbomachine 100. For example, the absorption of these ball-and-socket connecting rods 304 is located at 10 o'clock and 2 o'clock respectively in the upstream plane AA.

[0023] With regard to figures 8 and 9, we will describe a variant embodiment of the second embodiment of an aircraft assembly comprising a turbomachine 100, a pylon 2 and a fixing system 315 of the turbomachine 100 according to the invention.

[0024] The fastening system 315 differs from the second embodiment of a fastening system 305 in that the annular linear connection 314 is replaced by a ball-joint connecting rod 324 oriented along the Y axis in the upstream fixing means 304,324. Thus the fixing means 304,324 take up lateral forces FL and vertical forces FT and forces coming from the engine torque generated by the turbomachine 100.

[0025] The fastening system 315 differs further from the second embodiment, fastening system 305, in that the fastening system 315 includes downstream fastening means 316 comprising a ball-joint connecting rod oriented along the X-axis so as to absorb axial forces FX, here at 12 o'clock in the downstream plane BB. Again, the fastening means 316 include one degree of freedom along the direction of the Z-axis.

[0026] Thus the axial forces FX which were taken up by the upstream fixing means 304,314 of the second embodiment of the fixing system 305 are now taken up by the downstream fixing means 316 of this variant embodiment 315 of the second embodiment of the fixing system 305.

[0027] The fastening system 315 includes the means for taking up the thrust forces 208 previously described.

[0028] With reference to Figure 10, we will briefly describe a third embodiment of an aircraft assembly comprising a turbomachine 100, a pylon 2, and a mounting system 405 for the turbomachine 100 according to the invention. The mounting system 405 comprises the upstream mounting means 304, 314 described previously, as well as the downstream mounting means 206 described previously.

[0029] The means for resisting the thrust forces 408, 418 of the fastening system 405 include a linkage 408, comprising, in this case, two ball-and-socket connecting rods, and a rocker arm 418 on which the two ball-and-socket connecting rods 408 are rotationally mounted symmetrically, mirrored with respect to the ZX plane. The pivot joint, in a plane perpendicular to a plane of the ball-and-socket connecting rods 408, of the rocker arm 418 with the pylon 2 allows the thrust forces to be resisted in a single direction that lies simultaneously in the XY plane and the ZX plane.

[0030] With reference to Figure 11, we will briefly describe a fourth embodiment of an aircraft assembly comprising a turbomachine 100, a pylon 2, and a mounting system 415 for the turbomachine 100 according to the invention. The mounting system 415 includes the upstream mounting means 304, 324 described previously, as well as the downstream mounting means 316 described previously. The mounting system 415 incorporates the thrust force resisting means 408, 418 described previously.

[0031] With reference to figures 12 and 13, we will describe a fifth embodiment of an aircraft assembly comprising a turbomachine 100, a pylon 2 and a fixing system 505 for the turbomachine 100 according to the invention.

[0032] The mounting system 505 includes upstream mounting means 504, 514 for attaching the turbomachine 100 to pylon 2 at the upstream plane AA. The upstream mounting means here include a ball-and-socket joint 504 extending in the YZ plane between pylon 2 and the turbomachine 100. The ball-and-socket joint 504 is positioned here on one side of the ZX plane. On the other side of the ZX plane, still in the upstream plane AA, the upstream mounting means further include a link 514, called a "boomerang," extending in the upstream plane AA and positioned opposite the ball-and-socket joint 504, for a portion of the link attached to the turbomachine 100, symmetrically mirrored with respect to the ZX plane. Link 514 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.

[0033] The ball joint 504 and the link 514 allow to take on both sides of the plane ZX lateral forces FL, vertical forces FT and forces coming from the engine torque generated by the turbomachine 100. For example, the taking of forces by the upstream fixing means 504,514 takes place at 10 o'clock and 2 o'clock respectively in the upstream plane AA on the turbomachine 100.

[0034] Furthermore, the fastening system 505 includes downstream fastening means 506. The downstream fastening means comprise, in this case, an axial ball-joint connecting rod 506 extending in the ZX plane. The axial ball-joint connecting rod 506 is fixed at one end to the turbomachine 100 in the downstream BB plane, for example according to the direction of the Z-axis, here at 12 o'clock in this plane. At another end, the axial ball-joint connecting rod 506 is fixed to pylon 2 near the attachment point of the thrust linkage 208. The downstream attachment means 506 limit the tilting of the turbomachine 100, at the downstream plane AA, under the thrust forces and moments generated by the propeller 7. Again, the attachment means 506 have one degree of freedom along the direction of the Z-axis.

[0035] The means for resuming thrust forces 208 are unchanged and incorporated into the fastening system 505.

[0036] It follows from the above that the fastening system 205, 215, 305, 315, 405, 415, 505 of the turbomachine 100 to pylon 2, as previously described, is an isostatic fastening system without transfer of vertical forces FT to the downstream fastening means. The fastening system 205, 215, 305, 315, 405, 415, 505 of the turbomachine 100 to pylon 2, as previously described, allows the transfer of vertical forces FT solely by the upstream fastening means and the transfer of thrust forces. For this reason, the downstream fastening means include at least one degree of freedom along the Z-axis. Consequently, the vertical forces FT are no longer transferred by the downstream fastening means. This fixing system 205,215,305,315,405,415,505 of the turbomachine 100 to the pylon 2 as previously described increases the working length of the pylon in bending (distance D' on figure 1 instead of distance D) and reduces the forces at the fixing means.Therefore, the 205,215,305,315,405,415,505 fixing system of the turbomachine 100 to the pylon 2 as previously described makes it possible to eliminate the bending forces due to aerodynamic forces / moments in the rear part 1 (rear part, here, cantilevered) and to limit the relative displacements between the pylon 2 and the rear part 1 (reduction of the bending of the pylon 2) while protecting the rear part 1 of the turbomachine 100 from bending moments.

[0037] It should be noted that the embodiments of the fastening system 205, 215, 305, 315, 405, 415, 505 of a turbomachine 100 according to the invention have been described in relation to a cantilevered rear part 1. However, these systems The fixing 205, 215, 305, 315, 405, 415, 505 of the turbomachine 100 to the pylon 2 according to the invention as previously described are applicable, mutatis mutandis, to a turbomachine 100 whose rear part 1 is suspended by one or more flexible links 9 to 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 dotted lines on Figure 1. The role of this (these) flexible link(s) 9 is to limit the impact of inertial forces while limiting the bending moments related 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.

[0038] Naturally, the invention described above is by way of example. It is understood that a person skilled in the art is capable of carrying out different embodiments of the invention without departing from its scope.

[0039] It is emphasized that all features, as they are apparent to a person skilled in the art from this description, the drawings and the 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 render such combinations impossible or meaningless.

Claims

CLAIMS 1. Assembly for an aircraft comprising a turbomachine (100), a pylon (2) and a fastening system (205; 215; 305; 315; 405; 415; 505) of the turbomachine (100) to the pylon (2), the turbomachine extending along a longitudinal axis (XX) oriented along an X axis, oriented in a direction of a flow generated by the turbomachine, of an orthonormal frame (R) comprising an axis Z oriented towards the pylon, and an axis Y, the turbomachine comprising, along the longitudinal axis (XX), a low-pressure compressor (12), a high-pressure compressor (14) and a rear part (1), the fastening system comprising upstream fastening means of the turbomachine to the pylon fixed to the turbomachine in an upstream plane (AA) perpendicular to the longitudinal axis (XX) and passing through the low-pressure compressor,downstream fixing 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 force transfer means connecting the turbomachine to the pylon, the downstream fixing means being fixed to the pylon between the upstream fixing means and the thrust force transfer means, characterized in that the downstream fixing means comprise a linkage including one degree of freedom along a direction of the Z-axis.

2. Assembly according to claim 1, wherein the thrust force transfer means comprise a transfer linkage (208; 408) forming in a plane ZX an angle α with a longitudinal axis of the turbomachine of between 30° and 60°.

3. Assembly according to any one of claims 1 to 2, wherein the downstream fixing means comprise an annular linear linkage (216) oriented along the Z-axis,and fixed to the turbomachine along the Z-axis.

4. Assembly according to any one of claims 1 to 2, wherein the downstream fastening means comprise a ball-joint connecting rod (206; 316) oriented substantially in the XY plane, and fixed to the turbomachine along the direction of the Z axis.

5. Assembly according to any one of claims 1 to 4, wherein the upstream fastening means comprise a ball-joint connecting rod (204; 304; 324; 504) extending in a YZ plane.

6. Assembly according to claim 5, wherein the ball-joint connecting rod (204; 304) is substantially parallel to the Z-axis.

7. Assembly according to claim 6, wherein the upstream fastening means comprise another ball-joint connecting rod (304), the two ball-joint connecting rods being positioned symmetrically in mirror image along a ZX plane of each other, and an annular linear link (314) oriented along the Z-axis and fixed to the turbomachine along the direction of the Z-axis. 8.Assembly according to claim 6, wherein the upstream fastening means comprise another ball-and-socket connecting rod (304), the two ball-and-socket connecting rods being positioned symmetrically in mirror image along a plane ZX of each other, and yet another ball-and-socket connecting rod (324) oriented substantially along the Y-axis and fixed to the turbomachine along the direction of the Z-axis.

9. Assembly according to any one of claims 1 to 4, wherein the upstream fastening means comprise an annular linear link (214) oriented along the X-axis and fixed to the turbomachine on the Z-axis.

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

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