Propulsion device and aircraft comprising at least one such propulsion device
By designing a suspension system in the aircraft propulsion assembly, the problem of the rear components of the engine core when the turbine disc bursts is solved, and stable connection and thrust bearing are achieved in the event of a fault are achieved, ensuring the safety and stability of the aircraft.
Patent Information
- Application Number
- CN202410878117.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2023-07-04
- Filing Date
- 2024-07-02
- Publication Date
- 2025-01-07
AI Technical Summary
When existing aircraft propulsion components burst when the turbine discs are burst, the rear components of the engine core may disengage in the broken area, resulting in loss of connection and falling problems.
A suspension system is designed, which includes rear components connecting the hanger and the engine core. The rear components and hanger are connected through the suspension system to ensure that they do not fall off in the event of a failure. The suspension system design is Carry the weight of the engine core in the event of a failure. The system includes a length between the first and second ends of the suspension system greater than the distance between the anchor points, a hinge and a connecting rod ensure a stable connection, and a discharge housing is provided on the rear part of the engine core to increase the structure Frame, using deformable flexible elements for added flexibility.
When the rear components of the engine core fail, the suspension system can maintain its connection with the hanger, prevent it from falling, and effectively carry thrust in the event of a failure, ensuring the stability and safety of the aircraft.
Smart Images
Figure CN119262307A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to a propulsion assembly comprising a suspension system of a rear part of a maneuvering device, and also to an aircraft comprising at least one such propulsion assembly. Background Art
[0002] according to Figure 1 and Figure 2 As can be seen in the configuration shown, the aircraft 10 includes a plurality of propulsion assemblies 12 positioned beneath wings 14 of the aircraft 10 .
[0003] The propulsion assembly 12 includes a maneuvering device 16, a pod positioned around the maneuvering device 16 ( Figure 2 ) and a pylon 18 that connects the maneuvering device 16 to other components of the aircraft 10 , particularly the wing 14 .
[0004] In the following description, the longitudinal direction X is parallel to the axis of rotation (rotational stacking axis) A16 of the motor device. The transverse plane is a plane perpendicular to the axis of rotation A16 of the motor device. The transverse and horizontal direction Y is a direction perpendicular to the axis of rotation A16 of the motor device and horizontal. The transverse and vertical direction Z is a direction perpendicular to the axis of rotation A16 of the motor device and vertical. The vertical median plane is a vertical plane containing the axis of rotation A16 of the motor device. The terms "front" and "rear" refer to the direction of flow of the air flow in the motor device 16, which flows from the front to the rear.
[0005] The motorized device 16 comprises a fan 20 and an engine core 22 comprising a front part 22 . 1 integrating in particular the compression stage and the combustion chamber, and a rear part 22 . 2 integrating in particular the turbine and the nozzle.
[0006] The pylon 18 comprises a main box-shaped structure 24 connected to the wing 14 via a wing attachment 26 and to the maneuvering device 16 via a front engine attachment 28.1 and a rear engine attachment 28.2 and a pair of thrust rods 28.3 ensuring the bearing of thrust stresses. More specifically, the front engine attachment 28.1 and the rear engine attachment 28.2 connect the front part 22.1 of the engine core 22 and the main structure 24 of the pylon 18.
[0007] In the event of a blowout of the turbine disk (dish), the rear part 22 . 2 of the engine core 22 may separate from the front part 22 . 1 at the fracture (crush) zone ZR and detach from the propulsion assembly 12 . Summary of the Invention
[0008] The present invention aims to remedy some or all of the disadvantages of the prior art.
[0009] To this end, the present invention relates to a propulsion assembly comprising: a motorized device having a motorized device rotation axis; a pod positioned around the motorized device; a pylon; and an engine attachment system connecting the motorized device and the pylon, the motorized device extending between a front end and a rear end and comprising a fan and an engine core (jet engine core). The engine core comprises a front part and a rear part; the engine attachment system comprises a front engine attachment, a rear engine attachment, and a pair of thrust rods ensuring thrust bearing, the rear part of the engine core being offset relative to the rear engine attachment towards the rear end of the motorized device and extending to the rear end.
[0010] According to the invention, the propulsion assembly comprises a suspension system connecting the pylon and the rear part of the engine core, between the rear engine attachment and the rear end of the motor unit.
[0011] In the event of a failure, if the rear part of the engine core separates from the front part, it remains connected to the pylon and does not fall off.
[0012] According to another feature, the suspension system includes a first end connected to a first anchor point integral with the pylon and a second end connected to a second anchor point integral with a second component of the engine core, the length of the suspension system separating the first and second ends being greater than the distance separating the first and second anchor points.
[0013] According to another feature, the rear part of the engine core comprises an exhaust casing having a plurality of structural frames offset relative to one another in a direction parallel to the axis of rotation of the motor, the suspension system being connected to one of the structural frames of the exhaust casing.
[0014] According to another feature, the suspension system includes at least one connecting element extending between a first end and a second end and at least one articulation connecting the first or second end and one of the elements of the pylon and the rear part of the engine core, the articulation including at least one pivot axis parallel to the axis of rotation of the maneuvering device.
[0015] According to another feature, the suspension system includes a first connecting rod and a second connecting rod connected in series, each having a first end and a second end; the first ends of the first connecting rod and the second connecting rod are connected to each other by a first hinge, the second end of the first connecting rod is connected to the hanger by a second hinge, and the second end of the second connecting rod is connected to the rear component of the engine core by a third hinge, and the first, second and third hinges each include at least one pivot axis parallel to the rotation axis of the maneuvering device.
[0016] According to another feature, the first hinge comprises:
[0017] - pivoting cylinder;
[0018] a flat end having a through hole configured to receive the pivot cylinder, the flat end being integral with the first component of the first connecting rod and the second connecting rod;
[0019] A U-shaped joint configured to receive the flat end, having a through hole configured to receive the pivot cylinder, integral with a second part of the first and second connecting rods that is different from the first part.
[0020] According to another feature, the second end comprises:
[0021] - pivoting cylinder;
[0022] - a flat end or hinged portion having a through hole configured to receive a pivot cylinder, integral with the first connecting rod and the first component of the hanger;
[0023] A U-shaped joint configured to receive the flat end, having a through hole configured to receive the pivot cylinder, is integral with the first connecting rod and a second part of the hanger that is different from the first part.
[0024] According to another feature, the third end comprises:
[0025] - pivoting cylinder;
[0026] - a flat end or hinge portion having a through hole configured to receive a pivot cylinder, integral with the second connecting rod and the first of the rear parts of the engine core;
[0027] A U-shaped joint configured to receive the flat end, having a through hole configured to receive the pivot cylinder, integral with the second connecting rod and a second part of the rear part of the engine core that is different from the first part.
[0028] According to another feature, the suspension system comprises:
[0029] a deformable flexible element having a length and an elongation of less than 20% of its length, and extending between a first end and a second end;
[0030] - a first hinge connecting the first end to the hanger, the pivot axis of which is parallel to the longitudinal direction;
[0031] A second hinge connecting the second end to the rear part of the engine core, the pivot axis of which is parallel to the longitudinal direction.
[0032] According to another feature, the flexible element is a cable.
[0033] The invention also relates to an aircraft comprising at least one propulsion assembly according to one of the preceding characteristics. BRIEF DESCRIPTION OF THE DRAWINGS
[0034] Other features and advantages will become apparent from the following description of the invention, given by way of example and with reference to the accompanying drawings, in which:
[0035] - Figure 1 This is a perspective view of the aircraft.
[0036] - Figure 2 is a longitudinal cross-sectional schematic diagram showing a propulsion assembly according to an embodiment of the prior art.
[0037] - Figure 3 is a schematic longitudinal cross-sectional view showing a propulsion assembly according to an embodiment of the present invention,
[0038] - Figure 4 This is a perspective view showing a suspension system for a rear component of an engine core according to an embodiment of the present invention.
[0039] - Figure 5 yes Figure 4 A front view of the suspension system visible in FIG, wherein part (A) is not faulty and part (B) is faulty, and
[0040] - Figure 6 This is a perspective view showing a suspension system of a rear component of an engine core according to another embodiment of the present invention. DETAILED DESCRIPTION
[0041] according to Figure 3 In the illustrated embodiment, a propulsion assembly 30 includes a motorized device 32, a pod (not shown) positioned around the motorized device 32, and a pylon 34 for connecting the propulsion assembly 30, and in particular the motorized device 32, to a wing 36 of the aircraft. The aircraft includes at least one such propulsion assembly 30.
[0042] The motor 32 comprises a fan 38 and an engine core 40 comprising a front part 40.1 which integrates, in particular, the compression stage and the combustion chamber, and a rear part 40.2 which integrates, in particular, the turbine and the nozzle. According to one embodiment, the front part 40.1 and the rear part 40.2 are connected at a connection area 40.3 located between the combustion chamber and the turbine.
[0043] According to an embodiment, the rear part 40 . 2 of the engine core 40 comprises an exhaust casing having a plurality of structural frames offset relative to each other in the longitudinal direction.
[0044] The pylon 34 comprises a main structure 42 in the form of a box, which is connected to the wing 36 by a wing attachment 44 .
[0045] The propulsion assembly 30 comprises an engine attachment system 46 connecting the main structure 42 of the pylon 34 and the motorized device 32. According to one arrangement, the engine attachment system 46 is connected on the one hand to the main structure 42 of the pylon 34 and on the other hand to the front part 40.1 of the motorized device 32 and possibly also to the fan 38.
[0046] According to one embodiment, the engine attachment system 46 comprises a front engine attachment 46.1, a rear engine attachment 46.2 and a pair of thrust rods 46.3 ensuring the bearing of thrust (stress). More specifically, the front engine attachment 46.1 and the rear engine attachment 46.2 connect the front part 40.1 of the engine core 40 and the main structure 42 of the pylon 34. The rear engine attachment 46.2 and the pair of thrust rods 46.3 are connected to the main structure 42 of the pylon in an intermediate area of the main structure 42, substantially equidistant from the front and rear ends of the main structure 42. Of course, the present invention is not limited to this embodiment of the engine attachment system 46. The front engine attachment 46.1 can be connected to the fan 38. The engine attachment system 46 can include a number of between one and four engine attachments.
[0047] Regardless of the embodiment, the motorized device 32 comprises a front end E1 and a rear end E2. The engine attachment system 46 is spaced apart from the rear end E2 of the motorized device 32 and is configured to ensure the transfer of stresses between the motorized device 32 and the pylon 34, particularly in the absence of a fault. The rear component 40.2 of the engine core 40 is offset relative to the engine attachment system 46, particularly relative to the rear engine attachment 46.2, toward and extends to the rear end E2 of the motorized device 32.
[0048] The mobility device 32 , pylon 34 and engine attachment system 46 will not be described in detail as they may be identical to the prior art.
[0049] The propulsion assembly 30 comprises a suspension system 48 connecting the pylon 34 (particularly its main structure 42) and the rear part 40.2 of the engine core 40. If the rear part 40.2 were to become detached from the front part 40.1 in the event of a failure, the rear part 40.2 would remain connected to the pylon 34 and would not fall off.
[0050] The suspension system 48 is spaced apart from the rear engine attachment 46.2 and is located between the rear engine attachment 46.2 and the rear end E2 of the motorized device 32. The suspension system 48 is configured to ensure that stresses are not transferred between the motorized device 32 and the pylon 34 in the absence of a fault, but to ensure that the weight of the rear component 40.2 of the engine core 40 is supported in the event of a fault. To this end, the suspension system 48 includes a first end 48.1 connected to a first anchor point P1 integral with the pylon 34 and a second end 48.2 connected to a second anchor point P2 integral with the second component 40.2 of the engine core 40. The suspension system 48 has a length separating the first end 48.1 and the second end 48.2 that is greater than the distance separating the first anchor point P1 and the second anchor point P2. The first anchor point P1 is located near the rear end of the main structure 42 of the pylon 34.
[0051] According to one embodiment, the suspension system 48 is connected to one of the structural frames (one structural frame) of the exhaust housing, in particular the one located at the front, in order to ensure better load-bearing (absorption) of the stresses generated when the rear part 40.2 separates. Preferably, the suspension system 48 is offset towards the rear relative to the turbine to avoid damage in the event of a rupture of one of the turbines.
[0052] According to one construction, the suspension system 48 comprises at least one connecting element 50 extending between a first end 50.1 and a second end 50.2 and at least one hinge 52 connecting directly or indirectly the first end 50.1 or the second end 50.2 and an element of the pylon 34 and the rear part 40.2 of the engine core 40, the hinge 52 comprising at least one pivot axis A52 parallel to the longitudinal direction (parallel to the axis of rotation A32 of the maneuvering device).
[0053] This configuration allows the rear part 40 . 2 of the engine core 40 to move (displace) relative to the main structure 42 .
[0054] according to Figure 4 and Figure 5In the embodiment shown in, the suspension system 48 includes a first connecting rod 50 and a second connecting rod 50' connected in series, each having a first end 50.1, 50.1' and a second end 50.2, 50.2'; the first ends 50.1, 50.1' of the first connecting rod 50 and the second connecting rod 50' are connected to each other by a first hinge 52; the second end 50.2' of the first connecting rod 50 is connected to the hanger 34, in particular the main structure 42, by a second hinge 52'; the second end 50.2' of the second connecting rod 50' is connected to the rear part 40.2 of the engine core 40 by a third hinge 52", and each of the first hinge 52, the second hinge 52' and the third hinge 52" each includes at least one pivot axis A52, A52', A52" parallel to the longitudinal direction (parallel to the axis A32 of the maneuvering device).
[0055] Such an embodiment allows freedom of movement of the motorized device 32 relative to the hanger 34 .
[0056] According to one arrangement, for each of the first connecting rod 50 and the second connecting rod 50, a first element in the first end 50.1, 50.1' and the second end 50.2, 50.2' comprises a U-shaped joint comprising two branches (forks) traversed by a coaxial through hole. Furthermore, a second element in the first end 50.1, 50.1' and the second end 50.2, 50.2', different from the first element, comprises a flat end having a through hole configured to mate with the U-shaped joint and to be positioned between the branches of the U-shaped joint.
[0057] According to one embodiment, the first hinge member 52 includes: a pivot cylinder; a flat end having a through hole configured to accommodate the pivot cylinder, which is integrated with a first component in the first connecting rod 50 and the second connecting rod 50'; and a U-shaped joint, which is configured to accommodate the flat end, having a through hole configured to accommodate the pivot cylinder, and is integrated with a second component in the first connecting rod 50 and the second connecting rod 50' that is different from the first component.
[0058] The second end 52' includes: a pivot cylinder; a flat end or hinge portion having a through hole configured to accommodate the pivot cylinder, which is integral with the first connecting rod 50 and a first component in the hanger 34 (especially its main structure 42); and a U-shaped joint, which is configured to accommodate the flat end, has a through hole configured to accommodate the pivot cylinder, and is integral with a second component different from the first component in the first connecting rod 50 and the hanger 34 (especially its main structure 42).
[0059] The third end 52" includes: a pivot cylinder; a flat end or hinge portion having a through hole configured to accommodate the pivot cylinder, which is integral with the second connecting rod 50" and a first component in the rear component 40.2 of the engine core 40; and a U-shaped joint configured to accommodate the flat end, having a through hole configured to accommodate the pivot cylinder, and is integral with a second component different from the first component in the second connecting rod 50' and the rear component 40.2 of the engine core 40.
[0060] According to one arrangement, the first connecting rod 50 and the second connecting rod 50' are sized to be misaligned and to form an angle of less than 180° under normal conditions and without faults, such as Figure 5 As shown in part (A) of . According to this arrangement, the first connecting rod and the second connecting rod have a first length L50 and a second length L50' (the distance separating the pivot axis A52 of the first hinge 52 from the pivot axes A52', A52" of the second hinge 52' or the third hinge 52"). The sum of the first length L50 and the second length L50 is greater than the direct distance (straight-line distance) separating the pivot axes A52', A52" of the second hinge 52' and the third hinge 52".
[0061] The first connecting rod 50 and the second connecting rod 50 ′ may be made of metal, composite material, or hybrid material (metal and composite material).
[0062] According to a second embodiment, the suspension system 48 includes a deformable flexible element 54 extending between a first end 54.1 and a second end 54.2 and having a length and an elongation of less than 20% of the length. A first hinge 56 connects the first end 54.1 to the pylon 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 component 40.2 of the engine core 40 and has a pivot axis A56' parallel to the longitudinal direction. The flexible element 54 is a cable made of metal, composite, or a hybrid material. The length L54 of the flexible element 54, i.e., the length between the pivot axes A56, A56' of the first hinge 56 and the second hinge 56', is greater than the direct distance (straight-line distance) separating the pivot axes A56, A56' of the first hinge 56 and the second hinge 56'.
[0063] According to one configuration, each of the first and second ends of the flexible element 54 includes a U-shaped joint ("chape"). In addition, the aft component 40.2 of the engine core 40 and the main structure 42 of the pylon 34 each include a joint configured to mate with the U-shaped joint of the first end 54.1 or the second end 54.2 of the flexible element 54.
[0064] Of course, the present invention is not limited to these embodiments of the suspension system 48 .
Claims
1. A propulsion assembly, comprising a motorized device (32) having a motorized device rotation axis (A32), a pod positioned around the motorized device (32), a pylon (34), and an engine attachment system (46, 46.1, 46.2) connecting the motorized device (32) and the pylon (34), the motorized device (32) extending between a front end (E1) and a rear end (E2), and comprising a fan (38) and an engine core (40), the engine core The engine core (40) comprises a front part (40.1) and a rear part (40.2), the engine attachment system (46) comprises a front engine attachment (46.1), a rear engine attachment (46.2) and a pair of thrust rods (46.3) for ensuring thrust bearing, the rear part (40.2) of the engine core (40) is offset relative to the rear engine attachment (46.2) towards the rear end (E2) of the motor device (32) and extends to the rear end (E2); It is characterized in that The propulsion assembly (30) includes a suspension system (48) connecting the pylon (34) and the rear part (40.2) of the engine core (40) and located between the rear engine attachment (46.2) and the rear end (E2) of the motor (32).
2. The propulsion assembly according to claim 1, characterized in that The suspension system (48) includes a first end (48.1) connected to a first anchor point (P1) integral with the pylon (34) and a second end (48.2) connected to a second anchor point (P2) integral with a second component (40.2) of the engine core (40), the suspension system (48) having a length separating the first end (48.1) and the second end (48.2) that is greater than a distance separating the first anchor point (P1) and the second anchor point (P2).
3. The propulsion assembly according to claim 1 or 2, characterized in that: The rear part (40.2) of the engine core (40) comprises an exhaust shell having a plurality of structural frames offset relative to each other in a direction parallel to the axis of rotation (A32) of the motor device, and wherein the suspension system (48) is connected to one of the exhaust shells.
4. A propulsion assembly according to any one of the preceding claims, characterised in that The suspension system (48) comprises at least one connecting element (50) and at least one hinge (52), wherein the connecting element (50) extends between a first end (50.1) and a second end (50.2), the hinge (52) connecting the first end (50.1) or the second end (50.2) and one of the pylon (34) and the rear part (40.2) of the engine core (40), the hinge (52) comprising at least one pivot axis (A52) parallel to the rotation axis (A32) of the maneuvering device.
5. The propulsion assembly according to claim 4, characterized in that The suspension system (48) includes a first connecting rod (50) and a second connecting rod (50') connected in series, each of which has a first end (50.1, 50.1') and a second end (50.2, 50.2'); The first ends (50.1, 50.1') of the first connecting rod (50) and the second connecting rod (50') are connected to each other via a first hinge (52), the second end (50.2') of the first connecting rod (50) is connected to the cradle (34) via a second hinge (52), the second end (50.2') of the second connecting rod (50') is connected to the rear part (40.1) of the engine core (40.2) via a third hinge (52"), each of the first, second and third hinges (52, 52', 52") comprising at least one pivot axis (A52, A52', A52") parallel to the rotation axis (A32) of the maneuvering device.
6. The propulsion assembly according to claim 5, characterized in that The first hinge (52) comprises: - pivoting cylinder; - a flat end having a through hole configured to receive the pivot cylinder, integral with the first part of the first connecting rod (50) and the second connecting rod (50'); - a U-shaped joint configured to receive the flat end, having a through hole configured to receive the pivot cylinder, and being integral with a second part of the first connecting rod (50) and the second connecting rod (50') different from the first part.
7. The propulsion assembly according to claim 5 or 6, characterized in that The second end (52') comprises: - pivoting cylinder; - a flat end or hinged portion having a through hole configured to receive the pivot cylinder and integral with the first connecting rod (50) and the first part of the hanger (34); - a U-shaped joint configured to receive the flat end, having a through hole configured to receive the pivot cylinder, and being integral with the first connecting rod (50) and a second part of the hanger (34) different from the first part.
8. A propulsion assembly according to any one of claims 5 to 7, characterized in that The third end (52") includes: - pivoting cylinder; - a flat end or hinged portion having a through hole configured to receive the pivot cylinder and integral with the second connecting rod (50') and the first of the rear parts (40.2) of the engine core (40); - a U-shaped joint configured to receive the flat end, having a through hole configured to receive the pivot cylinder, and being integral with a second connecting rod (50') and a second part of the rear part (40.2) of the engine core (40) different from the first part.
9. The propulsion assembly according to claim 4, characterized in that The suspension system (48) comprises: - a deformable flexible element (54) having a length and an elongation of less than 20% of said length and extending between a first end (54.1) and a second end (54.2); - a first hinge (56) connecting the first end (54.1) and the hanger (34) and having a pivot axis (A56) parallel to the longitudinal direction; - A second articulation (56') connecting the second end (54.2) and the rear part (40.2) of the engine core (40) and having a pivot axis (A56') parallel to the longitudinal direction.
10. The propulsion assembly according to claim 9, characterized in that The flexible element (54) is a cable.
11. An aircraft comprising at least one propulsion assembly according to any one of the preceding claims.