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 system for attaching 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 attachment system comprising upstream attachment means for the turbomachine to the pylon fixed to the turbomachine in an upstream plane AA perpendicular to the longitudinal axis and passing through the low-pressure compressor, downstream attachment means 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 connecting the turbomachine to the pylon. Figure for the abbreviation: [Fig. 1]

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 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 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 clearances and even wear, degrading the turbomachine's performance, thus increasing fuel consumption and accelerating the turbomachine's aging.

[0005] A known solution, from document WO2022 / 245363, is to position a downstream suspension on the housing upstream of a high-pressure body (body solution high-pressure cantilever). 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 pylon 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] 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.

[0007] To this end, according to the invention, an assembly is provided for an aircraft comprising a turbomachine, a pylon and a system for attaching the turbomachine to the pylon, the turbomachine extending along a longitudinal axis oriented along an X axis, oriented in a direction of a flow generated by the turbomachine, of an orthonormal frame comprising a Z axis oriented towards the pylon, and a Y axis, the turbomachine comprising, along the longitudinal axis, a low-pressure compressor, a high-pressure compressor and a rear part, the attachment system comprising upstream attachment means of 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, downstream attachment means of 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 absorbing the 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 absorbing the thrust forces, wherein 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 means for recovering thrust forces include a recovery linkage forming in a plane ZX an angle α with a longitudinal axis of the turbomachine between 30° and 60°; • angle a is approximately 45°; • the downstream fastening means include an annular linear link oriented along the Z axis, and fixed to the turbomachine along the direction of the Z axis; • the downstream fixing means include 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 joint is approximately along the Y axis; • the ball joint is substantially along the X axis; • the upstream fixing means include a ball-joint connecting rod extending in a YZ plane; • the ball joint is substantially parallel to the Z axis; • The ball-joint connecting rod is fixed to the turbomachine along the axis direction Z; • the upstream fixing means include another ball-and-socket connecting rod, the two ball-and-socket connecting rods being positioned symmetrically in mirror image along a ZX plane of each other, and an annular linear link oriented along the Z axis and fixed to the turbomachine along the direction of the Z axis; • the upstream fixing means comprise another ball-and-ball joint, the two ball-and-ball joints being positioned symmetrically in mirror image along a plane ZX of each other, and yet another ball-and-ball joint (324) oriented substantially along the Y axis and fixed to the turbomachine along the direction of the Z axis; • the upstream fastening means comprise an annular linear link oriented along the X-axis and fixed to the turbomachine along the Z-axis; and, • the fixing system also includes a flexible connection 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. See the accompanying drawings:

[0010] [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;

[0011] [Fig.2] is a schematic view according to the upstream, downstream and top planes of a first method of embodiment of an aircraft assembly comprising a turbomachine, a pylon and a system for linking the turbomachine to the pylon according to the invention;

[0012] [Fig.3] is a schematic half view of the whole of [Fig.2];

[0013] [Fig.4] is a schematic view according to 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 linking the turbomachine to the pylon according to the invention;

[0014] [Fig.5] is a schematic half view of the whole of [Fig.4];

[0015] [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 system for connecting the turbomachine to the pylon according to the invention;

[0016] [Fig.7] is a schematic half view of the whole of [Fig.6];

[0017] [Fig.8] is a schematic view according to the upstream, downstream and top planes of a variant embodiment of the second embodiment of an aircraft assembly comprising a turbomachine, a pylon and a system for linking the turbomachine to the pylon according to the invention;

[0018] [Fig.9] is a schematic half view of the whole of [Fig.8];

[0019] [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 linking the turbomachine to the pylon according to the invention;

[0020] [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 turbomachine-to-pylon connection system according to the invention;

[0021] [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 linkage system according to the invention; and,

[0022] [Fig.13] is a half view of the assembly of [Fig.12].

[0023] For clarity, identical or similar elements are identified by identical reference numerals throughout the figures, detailed description of an embodiment

[0024] 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.

[0025] The pylon 2 here comprises 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.

[0026] 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.

[0027] Moreover, 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.

[0028] 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 [Fig. 2], view A corresponds to the upstream plane AA, view B to the downstream plane BB, and view C is a top view of the thrust force transfer means 208.

[0029] The upstream fastening means 204 here comprise a ball joint 204 connecting the turbomachine 100 to the pylon 2 in the upstream AA plane. Such a ball joint 204 allows the axial forces FX, lateral forces FL, and vertical forces FT to be resisted. In a first embodiment, the upstream fastening means 204 comprise an annular linear joint oriented to resist axial forces FX and lateral forces FL, accompanied by a vertical ball-and-socket joint to resist vertical forces FT. In a second embodiment, the upstream fastening means 204 comprise an annular linear joint oriented to resist axial forces FX and vertical forces FT, accompanied by a ball-and-socket joint in the lateral direction to resist lateral forces FL.

[0030] The fastening means 206 of the fastening system 205 comprise a lateral ball-joint connecting rod 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 means The fixing means 206 absorb lateral forces FL. The fixing means 206 include one degree of freedom along the direction of the Z axis.

[0031] The means for resisting the thrust forces 208 of the mounting system 205 comprise, here, a linkage 208 including, here, two ball-and-socket connecting rods. Here, 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 means for resisting the thrust forces allow for the resistance of axial forces FX to 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°.

[0032] 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 mounting system 205 for the turbomachine 100 according to the invention. The mounting system 215 differs from the first embodiment of the mounting system 205 in that the upstream mounting 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 mounting 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 mounting means 216 comprise one degree of freedom along the Z-axis. The thrust force resisting means 208 remain unchanged.

[0033] 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.

[0034] The fastening system 305 includes the means for taking up the thrust forces 208 previously described.

[0035] The upstream fastening means 304, 314 of the fastening system 305 comprise a vertically oriented annular linear link 314 about the Z-axis, thus resisting lateral FL and axial FX forces at 12 o'clock in the upstream AA plane. On either side of this annular linear link 314, in the upstream AA plane, the upstream fastening means comprise a ball-and-socket connecting rod 304. The two ball-and-socket connecting rods 304 allow the vertical FT forces and forces from the engine torque generated by the turbomachine 100 to be resisted on either side of the annular linear link 314. For example, the resistance of these ball-and-socket connecting rods 304 is at 10 o'clock and 2 o'clock respectively in the upstream AA plane.

[0036] With reference 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 for the turbomachine 100 according to the invention.

[0037] The fastening system 315 differs from the second embodiment of a fastening system 305 in that the annular linear link 314 is replaced by a ball-and-socket connecting rod 324 oriented along the Y-axis in the upstream fastening means 304,324. Thus, the fastening means 304,324 absorb lateral forces FL and vertical forces FT and forces from the engine torque generated by the turbomachine 100.

[0038] 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.

[0039] 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.

[0040] The fastening system 315 includes the means for taking up the thrust forces 208 previously described.

[0041] With reference to [Fig. 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.

[0042] The means for resisting the thrust forces 408, 418 of the fastening system 405 comprise a linkage 408, including, 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 in the ZX plane.

[0043] With reference to [Fig. 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 comprises the upstream mounting means 304, 324 previously described, as well as the downstream fastening means 316 previously described. The fastening system 415 incorporates the thrust force resistors 408, 418 previously described.

[0044] 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.

[0045] The mounting system 505 includes upstream mounting means 504, 514 for attaching the turbomachine 100 to the 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 the 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.

[0046] 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 is carried out at l0h and 2h respectively in the upstream plane AA on the turbomachine 100.

[0047] Furthermore, the fastening system 505 includes downstream fastening means 506. The downstream fastening 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 in the vicinity of the attachment point for the thrust force transfer linkage 208. The downstream fixing 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 fixing means 506 include one degree of freedom along the direction of the Z axis.

[0048] The means for resuming thrust forces 208 are unchanged and incorporated into the fastening system 505.

[0049] It follows from the above that the fastening system 205, 215, 305, 315, 405, 415, 505 of the turbomachine 100 to the pylon 2 as previously described is an isostatic fastening system without transfer of vertical forces FT in the downstream fastening means. The fastening system 205, 215, 305, 315, 405, 415, 505 of the turbomachine 100 The arrangement of the vertical forces FT on pylon 2, as previously described, allows the upstream fastening means to be used solely for resisting the thrust forces. For this to work, the downstream fastening means must have at least one degree of freedom along the Z-axis. Consequently, the vertical forces FT are no longer resisted by the downstream fastening means. This fastening system (205, 215, 305, 315, 405, 415, 505) of the turbomachine 100 on pylon 2, as previously described, increases the working length of the pylon in bending (distance D' in [Fig. 1] instead of distance D) and reduces the forces at the fastening 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.

[0050] 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 fastening systems 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 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 in [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.

[0051] 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.

[0052] It is emphasized that all features, as they are apparent to a person skilled in the art from this description, the drawings and the accompanying claims, even if specifically described only in relation to other specific features, both individually and in any combinations, may be combined with other features or groups of features disclosed herein, insofar as 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 (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 mounting system comprising upstream mounting 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 of 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 on the pylon between the upstream fixing means and the thrust force transfer means, wherein the downstream fixing means comprise a connection including one degree of freedom along a direction of the Z-axis.

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

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

4. Assembly according to any one of claims 1 to 2, wherein the downstream fastening means comprise a ball-and-socket 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-and-socket connecting rod (304), the two ball-and-socket 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 fixing means comprise another ball-joint connecting rod (304), the two ball-joint connecting rods being positioned symmetrically in mirror image along a plane ZX of each other, and yet another ball-joint 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 connection between the rear part and the pylon.

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