DRIVE ARRANGEMENT WITH A SUSPENSION SYSTEM OF THE REAR PART OF THE MOTORIZATION PROCESS, AERIAL VEHICLE WITH AT LEAST SUCH A DRIVE ARRANGEMENT

Description

[0001] This application relates to a propulsion system comprising a suspension system for the rear part of the engine and to an aircraft comprising at least one such propulsion system.

[0002] According to a configuration visible on the figures 1 et 2 , an aircraft 10 comprises several propulsion units 12 which are positioned under the wing 14 of the aircraft 10.

[0003] A propulsion unit 12 includes a motor 16, a nacelle (not shown on the figure 2 ) positioned around the engine 16 and a mast 18 connecting the engine 16 to the rest of the aircraft 10, in particular to the wing 14.

[0004] For the remainder of this description, a longitudinal direction X is parallel to the axis of rotation of the A16 motor. A transverse plane is a plane perpendicular to the axis of rotation of the A16 motor. A horizontal transverse direction Y is a direction perpendicular to the axis of rotation of the A16 motor and horizontal. A vertical transverse direction Z is a direction perpendicular to the axis of rotation of the A16 motor and vertical. A vertical median plane is a vertical plane containing the axis of rotation of the A16 motor. The terms front and rear refer to the direction of airflow within the A16 motor, which flows from front to rear.

[0005] The engine 16 comprises a fan 20 and a reactor core 22, which includes a forward section 22.1, incorporating compression stages and combustion chambers, and a rear section 22.2 incorporating turbines and a nozzle. The mast 18 includes a primary structure 24, in the form of a box girder, which is connected to the wing 14 by a wing attachment 26 and to the engine 16 by a forward engine attachment 28.1, as well as a rear engine attachment 28.2 and a pair of thrust rods 28.3 that transfer thrust forces. More specifically, the forward and rear engine attachments 28.1 and 28.2 connect the forward section 22.1 of the reactor core 22 to the primary structure 24 of the mast 18.

[0006] In the event of a turbine disc burst, the rear part 22.2 of the reactor core 22 can separate from the front part 22.1 at a rupture zone ZR and detach from the propulsion assembly 12.

[0007] CN 116 280 221 A discloses a propulsion assembly according to the preamble of claim 1.

[0008] The present invention aims to remedy all or part of the drawbacks of the prior art. To this end, the invention relates to a propulsion assembly according to claim 1.

[0009] In the event of a failure, if the rear part of the reactor core detaches from the front part, this rear part remains connected to the mast and does not fall.

[0010] According to another feature, the rear part of the reactor core includes an exhaust casing which has several structural frames offset from each other in a direction parallel to the axis of rotation of the engine, the suspension system being connected to one of the structural frames of the exhaust casing.

[0011] According to another characteristic, the suspension system includes at least one linking element extending between first and second ends and at least one joint connecting the first or second end and an element between the mast and the rear part of the reactor core, said joint including at least one pivot axis parallel to the axis of rotation of the engine.

[0012] According to another feature, the suspension system comprises first and second connecting rods in series, each having first and second ends; the first ends of the first and second connecting rods being connected to each other by a first joint, the second end of the first connecting rod being connected to the mast by a second joint, the second end of the second connecting rod being connected to the rear part of the reactor core by a third joint, the first, second and third joints each having at least one pivot axis parallel to the axis of rotation of the engine.

[0013] According to another characteristic, the first joint includes: a pivot cylinder, a flat end, having a through orifice configured to house the pivot cylinder, integral with a first part among the first and second connecting rods, a clevis configured to house the flat end, having through orifices configured to house the pivot cylinder, integral with a second part different from the first part among the first and second connecting rods.

[0014] According to another characteristic, the second joint includes: a pivot cylinder, a flat end or a fitting, having a through orifice configured to house the pivot cylinder, integral with a first part among the first connecting rod and the mast, a clevis configured to house the flat end, having through orifices configured to house the pivot cylinder, integral with a second part different from the first part among the first connecting rod and the mast.

[0015] According to another characteristic, the third joint includes: a pivot cylinder, a flat end or a fitting, having a through orifice configured to house the pivot cylinder, integral with a first part among the second connecting rod and the rear part of the reactor core, a clevis configured to house the flat end, having through orifices configured to house the pivot cylinder, integral with a second part different from the first part among the second connecting rod and the rear part of the reactor core.

[0016] According to another feature, the suspension system includes: a flexible and deformable element which has a length, an elongation of less than 20% of its length and extends between first and second ends, a first articulation, connecting the first end and the mast, which has a pivot axis parallel to the longitudinal direction, a second articulation, connecting the second end and the rear part of the reactor core, which has a pivot axis parallel to the longitudinal direction.

[0017] According to another characteristic, the flexible element is a cable.

[0018] The invention also relates to an aircraft comprising at least one propulsion system according to one of the preceding characteristics.

[0019] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which: There figure 1 is a perspective view from an aircraft, The figure 2 is a schematic longitudinal section of a propulsion assembly illustrating a prior art embodiment, The figure 3 is a schematic longitudinal section of a propulsion assembly illustrating one embodiment of the invention, The figure 4 is a perspective view of a suspension system for the rear portion of a reactor core, illustrating one embodiment of the invention. figure 5 is a front view of the suspension system visible on the figure 4 , in the absence of a failure on part (A) and in the presence of a failure on part (B), and The figure 6 is a perspective view of a suspension system for a rear part of a reactor core illustrating another embodiment of the invention.

[0020] According to an embodiment visible on the figure 3 A propulsion system 30 comprises a motor 32, a nacelle (not shown) positioned around the motor 32, and a mast 34 configured to connect the propulsion system 30, and more specifically the motor 32, to a wing 36 of an aircraft. The aircraft comprises at least one such propulsion system 30.

[0021] The propulsion system 32 comprises a fan 38 and a reactor core 40, which includes a forward section 40.1, incorporating compression stages and combustion chambers, and a rear section 40.2 incorporating turbines and a nozzle. In one arrangement, the forward and rear sections 40.1 and 40.2 are connected at a junction zone 40.3 located between the combustion chambers and the turbines.

[0022] According to one embodiment, the rear part 40.2 of the reactor core 40 includes an exhaust casing which has several structural frames offset from each other in the longitudinal direction.

[0023] The mast 34 includes a primary structure 42, in the form of a box, which is connected to the sail 36 by a sail attachment 44.

[0024] The propulsion assembly 30 includes at least one engine attachment system 46 connecting the primary structure 42 of the mast 34 and the engine 32. According to one arrangement, the engine attachment system 46 connects on the one hand the primary structure 42 of the mast 34 and, on the other hand, the front part 40.1 of the engine 32 and possibly the blower 38.

[0025] The engine attachment system 46 includes a front engine attachment 46.1, a rear engine attachment 46.2 and a pair of push rods 46.3 which ensure the transfer of thrust forces. More specifically, the forward and aft engine attachments 46.1, 46.2 connect the forward portion 40.1 of the reactor core 40 and the primary structure 42 of the pylon 34. The aft engine attachment 46.2 and the pair of thrust rods 46.3 are connected to the primary structure 42 of the pylon at a mid-section of the primary structure 42 located substantially equidistant from the forward and aft ends of the primary structure 42. Of course, the invention is not limited to this embodiment for the engine attachment system 46. The forward engine attachment 46.1 could be connected to the fan 38. As far as claim 1 is concerned, the engine attachment system 46 may comprise up to four engine attachments.

[0026] Regardless of the embodiment, the engine 32 comprises a forward end E1 and a rear end E2. The engine mounting system 46 is offset from the rear end E2 of the engine 32 and configured to ensure the transmission of forces between the engine 32 and the mast 34, particularly in the absence of a failure. The rear portion 40.2 of the reactor core 40 is offset towards the rear end E2 of the engine 32 relative to the engine mounting system 46, more specifically relative to the rear engine mounting 46.2, and extends to this rear end E2.

[0027] The motor 32, the mast 34 and the motor attachment system 46 are not described in more detail as they could be identical to those of the prior art.

[0028] The propulsion assembly 30 includes a suspension system 48 connecting the mast 34, more particularly its primary structure 42, and the rear part 40.2 of the reactor core 40. If this rear part 40.2 detaches from the front part 40.1 in the event of a failure, it remains connected to the mast 34 and does not fall.

[0029] The suspension system 48 is separate from the rear engine mount 46.2 and located between the rear engine mount 46.2 and the rear end E2 of the engine 32. This suspension system 48 is configured so as not to transmit forces between the engine 32 and the mast 34 in the absence of a failure, and to bear the weight of the rear section 40.2 of the reactor core 40 in the event of a failure. To this end, the suspension system 48 comprises a first end 48.1 connected to a first anchor point P1 attached to the mast 34, and a second end 48.2 connected to a second anchor point P2 attached to the second section 40.2 of the reactor core 40. The length of the suspension system 48 between the first and second ends 48.1 and 48.2 is greater than the distance between the first and second anchor points P1 and P2.The first anchor point P1 is located near the rear end of the primary structure 42 of the mast 34.

[0030] Depending on one configuration, the suspension system 48 is connected to one of the structural frames of the exhaust housing, in particular the one positioned furthest forward, to ensure better absorption of the forces generated during a detachment of the rear part 40.2. Preferably, the suspension system 48 is offset rearward relative to the turbines so as not to be damaged in the event of a turbine bursting.

[0031] According to one configuration, the suspension system 48 comprises at least one linking element 50 extending between first and second ends 50.1, 50.2 and at least one hinge 52 connecting, directly or indirectly, the first or second end 50.1, 50.2 and an element between the mast 34 and the rear part 40.2 of the reactor core 40, said hinge 52 comprising at least one pivot axis A52 parallel to the longitudinal direction (parallel to the axis of rotation of the engine A32).

[0032] This configuration allows the rear part 40.2 of the reactor core 40 to move relative to the primary structure 42.

[0033] According to an embodiment visible on the figures 4 et 5 , the suspension system 48 includes first and second connecting rods 50, 50' in series, each having first and second ends 50.1, 50.2, 50.1', 50.2'; the first ends 50.1, 50.1' of the first and second connecting rods 50, 50' being connected to each other by a first joint 52, the second end 50.2 of the first connecting rod 50 being connected to the mast 34, more particularly to the primary structure 42, by a second joint 52', the second end 50.2' of the second connecting rod 50' being connected to the rear part 40.2 of the reactor core 40 by a third joint 52", the first, second and third joints 52, 52', 52" each having at least one pivot axis A52, A52', A52" parallel to the longitudinal direction (parallel to the axis of the propulsion A32).

[0034] This embodiment allows freedom of movement of the motor 32 relative to the mast 34.

[0035] According to one arrangement, for each of the first and second connecting rods 50, 50, a first element among the first and second ends 50.1, 50.2, 50.1', 50.2' comprises a yoke having two arms through which coaxial through holes pass. In addition, a second element, different from the first element among the first and second ends 50.1, 50.2, 50.1', 50.2', comprises a flat end, having a through hole, configured to cooperate with a yoke and to be positioned between the arms of the yoke.

[0036] According to one embodiment, the first articulation 52 comprises a pivot cylinder, a flat end, having a through orifice configured to house the pivot cylinder, integral with a first part among the first and second connecting rods 50, 50' and a clevis configured to house the flat end, having through orifices configured to house the pivot cylinder, integral with a second part different from the first part among the first and second connecting rods 50, 50'.

[0037] The second articulation 52' includes a pivot cylinder, a flat end or fitting, having a through orifice configured to house the pivot cylinder, integral with a first part from the first connecting rod 50 and the mast 34 (more particularly its primary structure 42) and a clevis configured to house the flat end, having through orifices configured to house the pivot cylinder, integral with a second part different from the first part from the first connecting rod 50 and the mast 34 (more particularly its primary structure 42).

[0038] The third articulation 52" includes a pivot cylinder, a flat end or fitting, having a through orifice configured to house the pivot cylinder, integral with a first part among the second connecting rod 50' and the rear part 40.2 of the reactor core 40 and a clevis configured to house the flat end, having through orifices configured to house the pivot cylinder, integral with a second part different from the first part among the second connecting rod 50' and the rear part 40.2 of the reactor core 40.

[0039] According to an arrangement, the first and second connecting rods 50, 50' are dimensioned so that they are not aligned and form an angle of less than 180° under normal conditions and in the absence of failure, as illustrated in part (A) of the figure 5According to this arrangement, the first and second connecting rods have first and second lengths L50, L50' (distance separating the pivot axis A52 of the first joint 52 and the pivot axis A52', A52" of the second or third joint 52', 52"). The sum of the first and second lengths L50, L50' is greater than the direct (straight-line) distance separating the pivot axes A52', A52" of the second and third joints 52', 52". The first and second connecting rods 50, 50' can be metallic, composite, or hybrid (metallic and composite).

[0040] According to a second embodiment, the suspension system 48 comprises a flexible and deformable element 54 extending between first and second ends 54.1, 54.2 and having a length and elongation less than 20% of its length. A first hinge 56 connects the first end 54.1 to the mast 34 and has a pivot axis A56 parallel to the longitudinal direction. A second hinge 56' connects the second end 54.2 to the rear portion 40.2 of the reactor core 40 and has a pivot axis A56' parallel to the longitudinal direction. The flexible element 54 is a metal cable, made of a composite or hybrid material. It has a length L54, the distance separating the pivot axes A56, A56' from the first and second joints 56, 56' greater than the direct distance (in a straight line) separating the pivot axes A56, A56' from the first and second joints 56, 56'.

[0041] Depending on the configuration, each of the first and second ends of the flexible element 54 includes a clevis. In addition, the rear part 40.2 of the reactor core 40 and the primary structure 42 of the mast 34 each include a fitting configured to cooperate with the clevis of the first or second end 54.1, 54.2 of the flexible element 54.

[0042] Of course, the invention is not limited to these embodiments for the suspension system 48.

Claims

1. Propulsion unit comprising an engine (32) which has an engine axis of rotation (A32), a nacelle positioned about the engine (32), a pylon (34), in addition to an engine mount system (46, 46.1, 46.2) which connects the engine (32) and the pylon (34), the engine (32) extending between the front and rear ends (E1, E2) and comprising a fan (38), in addition to a jet engine core (40) which comprises front and rear parts (40.1, 40.2), the engine mount system (46) comprising a front engine mount (46.1), a rear engine mount (46.2), in addition to a pair of thrust rods (46.3) which ensure the take-up of thrust forces, and the rear part (40.2) of the jet engine core (40) being offset toward the rear end (E2) of the engine (32) relative to the rear engine mount (46.2) and extending as far as this rear end (E2); the propulsion unit (30) comprising a suspension system (48) which connects the pylon (34) and the rear part (40.2) of the jet engine core (40) and which is located between the rear engine mount (46.2) and the rear end (E2) of the engine (32); the suspension system (48) comprising a first end (48.1) which is connected to a first anchoring point (P1) fixed to the pylon (34) and a second end (48.2) which is connected to a second anchoring point (P2) fixed to the rear part (40.2) of the jet engine core (40), characterized in that the suspension system (48) comprises a length, separating the first and second ends (48.1, 48.2), which is greater than a distance separating the first and second anchoring points (P1, P2) and is configured so as not to transmit forces between the engine (32) and the pylon (34) in the absence of a failure, and to support the weight of the rear part (40.2) of the jet engine core (40) in the event of a failure.

2. Propulsion unit as claimed in the preceding claim, wherein the rear part (40.2) of the jet engine core (40) comprises an exhaust casing which has a plurality of structural frames which are offset relative to one another in a direction parallel to the axis of rotation of the engine (A32) and wherein the suspension system (48) is connected to one of the structural frames of the exhaust casing.

3. Propulsion unit as claimed in one of the preceding claims, wherein the suspension system (48) comprises at least one connecting element (50) which extends between the first and second ends (50.1, 50.2), in addition to at least one joint (52) which connects the first or second end (50.1, 50.2) and an element from amongst the pylon (34) and the rear part (40.2) of the jet engine core (40), said joint (52) comprising at least one pivot axis (A52) parallel to the axis of rotation of the engine (A32).

4. Propulsion unit as claimed in the preceding claim, wherein the suspension system (48) comprises first and second links (50, 50') in series, each having first and second ends (50.1, 50.2, 50.1', 50.2'); the first ends (50.1, 50.1') of the first and second links (50, 50') being connected to one another by a first joint (52), the second end (50.2) of the first link (50) being connected to the pylon (34) by a second joint (52'), the second end (50.2') of the second link (50') being connected to the rear part (40.2) of the jet engine core (40) by a third joint (52"), and the first, second and third joints (52, 52', 52") each comprising at least one pivot axis (A52, A52', A52") parallel to the axis of rotation of the engine (A32).

5. Propulsion unit as claimed in the preceding claim, wherein the first joint (52) comprises: - a swivel cylinder, - a flat end, having a through-orifice which is configured to house the swivel cylinder, fixed to a first part from amongst the first and second links (50, 50') - a clevis which is configured to house the flat end, having through-orifices which are configured to house the swivel cylinder, fixed to a second part which is different from the first part from amongst the first and second links (50, 50').

6. Propulsion unit as claimed in one of claims 4 to 5, wherein the second joint (52') comprises : - a swivel cylinder, - a flat end or a bracket, having a through-orifice which is configured to house the swivel cylinder, fixed to a first part from amongst the first link (50) and the pylon (34), - a clevis which is configured to house the flat end, having through-orifices which are configured to house the swivel cylinder, fixed to a second part which is different from the first part from amongst the first link (50) and the pylon (34).

7. Propulsion unit as claimed in one of claims 4 to 6, wherein the third joint (52") comprises : - a swivel cylinder, - a flat end or a bracket, having a through-orifice which is configured to house the swivel cylinder, fixed to a first part from amongst the second link (50') and the rear part (40.2) of the jet engine core (40), - a clevis which is configured to house the flat end, having through-orifices which are configured to house the swivel cylinder, fixed to a second part which is different from the first part from amongst the second link (50') and the rear part (40.2) of the jet engine core (40).

8. Propulsion unit as claimed in claim 3, wherein the suspension system (48) comprises : - a flexible and deformable element (54) which has a length, an elongation which is less than 20% of the length and extends between the first and second ends (54.1, 54.2), - a first joint (56) which connects the first end (54.1) and the pylon (34) and which has a pivot axis (A56) parallel to the longitudinal direction, - a second joint (56') which connects the second end (54.2) and the rear part (40.2) of the jet engine core (40) and which has a pivot axis (A56') parallel to the longitudinal direction.

9. Propulsion unit as claimed in the preceding claim, wherein the flexible element (54) is a cable.

10. Aircraft comprising at least one propulsion unit as claimed in one of the preceding claims.