Aircraft propulsion assembly having jet engine, pylon and means for attaching jet engine to pylon
By designing jet engine attachments with articulated and ball joints, the problem of large space occupation and weight weight caused by the rigidity of the jet engine attachment mount structure in the prior art is solved, and the space saving and aerodynamic performance of the propulsion assembly are achieved promote.
Patent Information
- Application Number
- CN202410760525.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2024-05-29
- Filing Date
- 2024-06-13
- Publication Date
- 2024-12-17
AI Technical Summary
The existing jet engine attachment mount structure is relatively rigid, resulting in large space occupancy, heavy weight and is not conducive to the aerodynamic performance of the aircraft.
A propulsion assembly is designed including a jet engine, a rigid structural hanger with a front wall and an upper spar, and an attachment with a hinged and ball joint joint, to achieve a reaction to the thrust by reducing the size and optimizing the structure of the attachment. balanced delivery.
Space saving, weight reduction and aerodynamic performance are achieved, and through optimized structural design, the size of the attachment is reduced and load transfer is balanced.
Smart Images
Figure CN119142541A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the general field of attaching a jet engine under the wing of an aircraft. It relates in particular to a propulsion assembly comprising a jet engine, in particular a turbofan engine, a pylon and an attachment device intended to attach the jet engine under the pylon. The invention also relates to an aircraft equipped with such a propulsion assembly. Background Art
[0002] Prior art propulsion assemblies are fastened under the wing of an aircraft, the wing having a jet engine and an attachment pylon, the jet engine being fastened under the wing via the attachment pylon. Typically, the attachment pylon has a rigid structure, also referred to as a primary structure, carrying a first fastening element intended to attach the jet engine.
[0003] These first fastening elements are formed by a front engine attachment, a rear engine attachment and a device for reacting the thrust generated by the jet engine.
[0004] The attachment pylon also has a second fastening element which allows the attachment pylon to be fastened to the wing.
[0005] The jet engine has a fan casing at the front surrounding an annular fan duct and a smaller center casing towards the rear which encloses the core of the jet engine.
[0006] The front engine attachment is interposed between the front end of the rigid structure and the front upper part of the central housing, and the rear engine attachment is interposed between the rigid structure and the rear upper part of the central housing. The device for reacting the thrust generated by the jet engine comprises two rods arranged on either side of a median vertical plane of the jet engine, articulated on the one hand to the central housing and on the other hand to a single diffuser fastened to the rigid structure. The device for reacting thrust formed by the two rods and the diffuser is designed to react all or most of the forces directed along the longitudinal axis X of the jet engine.
[0007] The front engine attachment has a rod on each side of the pylon, each rod being fastened in an articulated manner with one end to the pylon and in an articulated manner with the other end to the center housing. One of the rods is fastened to the pylon via two connection points and to the center housing via one connection point, and the second rod is fastened to the pylon via one connection point and to the center housing via one connection point.
[0008] Although such a structure is satisfactory, it is desirable to find an arrangement which allows saving space, in order to reduce weight and improve the aerodynamics of the aircraft. Summary of the invention
[0009] An object of the present invention is to propose a propulsion assembly comprising a jet engine, a pylon and an attachment device for attaching the jet engine below the pylon.
[0010] To this end, a propulsion assembly for an aircraft is proposed, the propulsion assembly having:
[0011] - a jet engine having a fan casing and a center casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis;
[0012] - an attachment pylon having a rigid structure in the form of a box having a front wall and an upper spar extending forwardly relative to the front wall;
[0013] - a front engine attachment, which is fixed between the upper area of the fan case and the front end of the upper spar; and
[0014] A complementary front engine attachment part fixed between the upper area of the central housing and the lower end of the front wall.
[0015] With this arrangement, the size of the attachment is reduced.
[0016] Advantageously, the propulsion assembly comprises a rod secured between the upper spar and the front wall.
[0017] Advantageously, the front engine attachment comprises a lever hingedly mounted at a vertical mid-plane on the front end of the upper spar and comprising ends on each side of the vertical mid-plane hingedly mounted on the upper region of the fan casing, each articulation being at least a rotation about an axis parallel to the longitudinal axis.
[0018] Advantageously, each articulation of the rod is a ball joint.
[0019] Advantageously, the articulation of one of the two ends is a fail-safe articulation.
[0020] Advantageously, the complementary front engine attachment comprises a pair of first rods on each side of the vertical median plane, wherein a first end of each first rod is hingedly mounted on the lower end of the front wall, and wherein a second end of each first rod is hingedly mounted to the upper region of the central housing.
[0021] Advantageously, the complementary front engine attachment comprises two fitting assemblies, each comprising a first hinge point with the lower end of the front wall at a vertical mid-plane and a second hinge point with the upper zone of the central housing on each side of the vertical mid-plane.
[0022] The invention also proposes an aircraft having a wing and a propulsion assembly according to the above-mentioned variant, wherein a rigid structure is fastened under the wing. BRIEF DESCRIPTION OF THE DRAWINGS
[0023] The above and other features of the present invention will become more apparent upon reading the following description of an exemplary embodiment, which description is given with reference to the accompanying drawings, in which:
[0024] Figure 1 is a side view of an aircraft according to the present invention;
[0025] Figure 2 is a schematic diagram of a propulsion assembly according to the present invention;
[0026] Figure 3 is a perspective view of a front engine attachment according to the present invention;
[0027] Figure 4 yes Figure 3 An exploded view of the engine attachment;
[0028] Figure 5 is a perspective view of an example of a complementary front engine attachment for use in a propulsion assembly according to the present invention;
[0029] Figure 6 yes Figure 5 a rear view of the complementary front engine attachment of; and
[0030] Figure 7 is a perspective view of another example of a complementary front engine attachment for use in a propulsion assembly according to the present invention. DETAILED DESCRIPTION
[0031] Figure 1 An aircraft 50 is shown having a fuselage 51 and wings 52 on each side of the fuselage 51. At least one propulsion assembly 100 is fastened under each wing 52 and it comprises a jet engine 102 and an attachment pylon 104.
[0032] By convention, X represents the longitudinal axis of the propulsion assembly 100, which corresponds to the longitudinal axis X of the jet engine 102. In addition, Y represents the lateral axis of the propulsion assembly 100, which corresponds to the transverse axis of the jet engine 102, which axis is horizontal when the aircraft is on the ground, and Z represents the vertical axis or vertical height of the propulsion assembly, which corresponds to the vertical axis of the jet engine 102, which axis is vertical when the aircraft is on the ground, and these three axes X, Y and Z are orthogonal to each other.
[0033] Furthermore, the terms "front" and "rear" are considered relative to the forward direction of movement of the aircraft when the jet engine 102 is in operation, which direction is schematically indicated by arrow 107. The jet engine 102 also has a vertical median plane P(XZ) passing through the longitudinal axis X and the vertical axis Z.
[0034] The jet engine 102 has at the front a fan casing 102a surrounding an annular fan duct in which the fan rotates, and at the rear of the fan casing 102a a center casing 102b of smaller dimensions enclosing the core of the jet engine 102. The fan casing 102a and the center casing 102b surround a longitudinal axis X.
[0035] The propulsion assembly 100 also has a nacelle 102a in which the jet engine 102 is mounted.
[0036] Figure 2 A propulsion assembly 100 is shown having a jet engine 102 and an attachment pylon 104 via which the jet engine 102 is fastened to the wing 52. The attachment pylon 104 is shown here by its rigid structure 106, also called primary structure, which is fastened below the wing 52.
[0037] The rigid structure 106 extends between the front and rear ends along the longitudinal axis X and takes the form of a box having a lower spar 106a, an upper spar 106b, two lateral walls 106c and a front wall 106d, which are fixed together to realize the rigid structure 106. The front wall 106d is oriented towards the front of the aircraft 50. The lateral walls 106c are arranged on each side of the vertical median plane P. The upper spar 106b is above the lateral walls 106c, while the lower spar 106a is below the lateral walls 106.
[0038] The upper spar 106b extends forwardly relative to the front wall 106d, which means that the upper spar 106b has a front end in the forward direction F away from the front wall 106d.
[0039] In this embodiment, the propulsion assembly 100 comprises a reaction device 170 for reacting the thrust generated by the jet engine 102. Here, the reaction device 170 comprises two reaction rods 170a, which are arranged on either side of the median plane P and are hinged on the one hand at the front to the central housing 102b and on the other hand at the rear to the rigid structure 106, for example to the lower spar 106a, thanks to appropriate fittings, which are not described in detail since they are not part of the invention and which a person skilled in the art will be able to implement as known in the art.
[0040] In this embodiment, the propulsion assembly 100 also includes a rear attachment 180 between the rigid structure 106 and the rear upper portion of the center shell 102b, in this case, between the lower spar 106a and the rear upper portion of the center shell 102b. Since the rear attachment 180 is not part of the present invention, the rear attachment 180 is not described in detail, and a person skilled in the art will be able to implement a prior art rear attachment.
[0041] In the present invention, propulsion assembly 100 includes a forward engine attachment 152 secured between upper region 103 of fan case 102a and a forward end of upper spar 106b.
[0042] At the same time, the propulsion assembly 100 includes a complementary front engine attachment 153 secured between the upper region 105 of the center housing 102b and the lower end of the front wall 106d.
[0043] With this arrangement, the size of the attachment is reduced and it allows to optimize the aerodynamics by reducing the size of the fairing of the nacelle.
[0044] According to a particular arrangement of the invention, the front engine attachment 152 reacts only lateral loads (parallel to the lateral axis Y), whereas the complementary front engine attachment 153 reacts both lateral loads (parallel to the lateral axis Y) and vertical loads (parallel to the vertical axis Z).
[0045] Furthermore, due to the side loads acting on the fan case 102a and the side loads acting on the center case 102b, the axial moment Mx is maintained by the forward engine attachment 152 and the complementary forward engine attachment 153. The load transfer from the jet engine 102 to the attachment pylon 104 with this engine mounting concept is balanced.
[0046] In this embodiment, in order to strengthen the upper spar 106b, the propulsion assembly 100 includes a main rod 156 fixed between the upper spar 106 and the front wall 106d. Each end of the main rod 156 is respectively mounted to the upper spar 106b and the front wall 106d in a hinged manner.
[0047] In one example of the present invention, each end of the main rod 156 is fixed by a clamp. For example, the end of the main rod 156 is a male clamp, which is inserted into a female clamp fixed to the upper spar 106b or the front wall 106d, and is maintained by an axis perpendicular to the vertical middle plane P.
[0048] Figure 3 and 4 A front engine attachment 152 according to the present invention is shown.
[0049] The front engine attachment 152 comprises a rod 154 mounted in an articulated manner at the front end of the upper spar 106b in the vertical mid-plane P. To this end, the front end of the upper spar 106b comprises a front cylindrical piece 157a, the axis of which is in the vertical mid-plane P and parallel to the longitudinal axis X, and the rod 157 comprises a front hole 157b into which the front cylindrical piece 157a is inserted in an articulated manner.
[0050] The rod 154 is at least movable in rotation, that is to say about an axis parallel to the longitudinal axis X, about the front cylindrical piece 157 a.
[0051] In this embodiment, the articulation of the rod 157 on the front cylindrical member 157a is a ball joint connection. For this purpose, a spherical bearing 157c is introduced into the front hole 157b, between the front cylindrical member 157a and the rod 154. The main articulation is a rotation around the front cylindrical member 157a, while a small rotation is performed around another axis.
[0052] On each side of the vertical median plane P, the rod 154 comprises an end 154a-b which is hingedly mounted on the upper zone 103 of the fan casing 102a. The two ends 154a-b are symmetrical relative to the vertical median plane P.
[0053] To this end, for each end 154a-b of the rod 154, a female clamping piece 159a-b is fixed to the upper area 103 of the fan housing 102a, while the said end 154a-154b of the rod 154 is a male clamping piece, which is hingedly mounted in the said female clamping piece 159a-b and is maintained by a hinge axis 161a-b inserted into the hinge hole of the end 154a-b and the hinge hole of the female clamping piece 159a-b, which is parallel to the longitudinal axis X.
[0054] As previously mentioned, each end portion 154a-b is at least rotatably movable about the corresponding portion.
[0055] In the present embodiment, the articulation of each end 154a-b of the rod 157 on the upper region 103 of the fan housing 102a is a ball joint. For this purpose, a spherical bearing 163a-b is introduced into the articulation hole of each end 154a-b, between the rod 157 and the associated articulation axis 161a-b. The main articulation is a rotation about an axis parallel to the longitudinal axis X, with a small rotation about another axis.
[0056] For safety reasons, the upper spar 106b is made of two superimposed plates 107a-b fixed together, and the front cylindrical element 157a is made of two semi-cylindrical elements, one of which is integral with one plate 107a and the other with the other plate 107b.
[0057] In the same manner, the rod 154 is made of two plates fixed together, each plate comprising a front hole 157b for receiving the front cylindrical member 157a, and each end of each plate comprising an articulation hole for receiving the articulation shaft 161a-b.
[0058] For safety reasons, the articulation of one of the two ends 154a-b is a waiting fail-safe articulation. This means that, in normal use, the main force path is defined by one of the ends 154a-b of the rod 154, through which the load is transmitted. In the event of a failure of the main force path, the second end 154a-b of the rod 154 is enabled, which means that a waiting fail-safe articulation is requested. In order to achieve the waiting fail-safe articulation, the diameter of the relevant articulation axis 161a-b is smaller than the diameter of the hole of the end 154a-b of the rod 154. Therefore, in normal operation, there is no contact between the articulation axis 161a-b and the hole of the end 154a-b, while in the event of a failure, the fan housing 102a will move and the articulation axis 161a-b will then come into contact with the hole of the end 154a-b.
[0059] Figure 5 and Figure 6 A complementary front engine attachment 153 is shown for use in the present invention.
[0060] The complementary front engine attachment 153 comprises a pair of first rods 352a-b on each side of the vertical median plane P, which means a pair of first rods 352a on the port side and a pair of first rods 352b on the starboard side.
[0061] For each of the first rods 352a-b, a first end is hingedly mounted on the lower end of the front wall 106d, and a second end is hingedly mounted on the upper area 105 of the central housing 102b.
[0062] Each first rod 352a-b is entirely in a plane perpendicular to the longitudinal axis X, and each end of each first rod 352a-b is attached by a pivot link, the rotation axis of which is entirely parallel to the longitudinal axis X.
[0063] To this end, each end of each first rod 352a-b has a first hinge hole 355, and for each pair of first rods 352a-b, the lower end of the front wall 106d and the upper area 105 of the central housing 102b have a second hinge hole 357. For each pair of first rods 352a-b, the propulsion assembly 100 includes a hinge shaft 359, which is inserted into the corresponding second hinge hole 357 of the front wall 106d or the central housing 102b and into the first hinge hole 355 of the pair of first rods 352a-b.
[0064] In this embodiment, in order to reduce interface loads, the second ends of the first rods 352a-b are closer to the vertical mid-plane P than the first ends. This means that the first rods 352a-b are oriented toward the longitudinal axis X from top to bottom.
[0065] For safety reasons, the propulsion assembly 100 comprises, for each first rod 352a-b, a second rod 354a-b, the first end of which is hingedly mounted on the lower end of the front wall 106d and the second end of which is hingedly mounted on the upper area 105 of the central housing 102b. The second rods 354a-b are also mounted by means of a swivel link and are here mounted on the same hinge axis 359 via appropriate swivel holes 361 in the second rod 354. Each second rod 355a-b is also entirely in a plane perpendicular to the longitudinal axis X, and each end of each second rod 354a-b is attached by means of a pivot link, the axis of rotation of which is entirely parallel to the longitudinal axis X.
[0066] The second rod 354a-b is a waiting fail-safe element. This means that in normal use, the main force path is defined by the first rod 352a-b, and the load is transmitted through this main force path. In the event of a failure of the main force path, the second rod 354a-b is activated, which means that a waiting fail-safe articulation is requested.
[0067] In order to achieve a waiting fail-safe articulation, the diameter of at least one of the rotation holes 361 of each second rod 354a-b is greater than the diameter of the articulation shaft 359. Thus, in normal operation, there is no contact between the second rods 354a-b and the articulation shaft 359, while in the event of a failure, the fan housing 102a will move and the second rods 354a-b will then come into contact with the articulation shaft 359.
[0068] In this embodiment, the first end of the second rod 354a-b is closer to the vertical middle plane P than the second end of the second rod.
[0069] Figure 7 Another complementary front engine attachment 153 for use in the present invention is shown.
[0070] The complementary front engine attachment 153 comprises two accessory components 452a-b, each of which comprises a first hinge point 454a at a vertical mid-plane P to achieve hinge connection with the lower end of the front wall 106d, and comprises a second hinge point 454b-c on each side of the vertical mid-plane P to achieve hinge connection with the upper area 105 of the central shell 102b.
[0071] Each fitting assembly 452a-b is generally in a plane perpendicular to the longitudinal axis X, and each hinge point 454a-c takes the form of a pivot link whose axis of rotation is generally parallel to the longitudinal axis X. Each hinge point 454a-c of one fitting assembly 452a-b is coaxial with a hinge point 454a-c of another fitting assembly 452a-b.
[0072] To this end, each hinge point 454a-c is realized by a combination of a first hinge hole 455 through the corresponding fitting component 452a-b and a second hinge hole 457 through the lower end of the front wall 106d or the upper region 105 of the central housing 102b.
[0073] In position, the first hinge hole 455 of one fitting component 452a-b is aligned with the first hinge hole 455 of the other fitting component 452b-a and the second hinge hole 457 of the lower end of the front wall 106d or the upper region 105 of the center housing 102b.
[0074] The propulsion assembly 100 also comprises, for each second hinge hole 457, a hinge shaft 459 which is inserted into said second hinge hole 457 and into the corresponding first hinge hole 455 of the two accessory assemblies 452a-b. The axis of each hinge shaft 459 is generally parallel to the longitudinal axis X.
[0075] In the present embodiment, each fitting assembly 452a-b takes the form of a triangle, and the fitting assemblies 452a-b are arranged on each side of the lower end of the front wall 106d.
[0076] For safety reasons, each fitting assembly 452a - b comprises two plates fixed together and each plate comprises a first hinge hole 455 for each hinge point 454a - c .
[0077] For safety reasons, each accessory assembly 452a-b comprises, at the vertical mid-plane P, a waiting fail-safe hinge 456a-b for achieving a safe hinge with the upper zone 105 of the central housing 102b, each safety hinge point being in the form of a pivot link whose axis of rotation is globally parallel to the longitudinal axis X. The safety hinge 456a of one accessory assembly 452a is coaxial with the safety hinge 456 of another accessory assembly 452b.
[0078] To this end, each safety hinge 456a-b is realized by a combination of a first safety hole 461 passing through the corresponding accessory component 452a-b and a second safety hole 463 passing through the upper area 105 of the central housing 102b. In terms of position, the safety holes 461 are aligned with each other and with the corresponding second safety holes 463 of the upper area 105 of the central housing 102b.
[0079] The propulsion assembly 100 further comprises safety shafts inserted into the corresponding second safety holes 463 and first safety holes 461 of the accessory assemblies 452a-b. The axis of each safety shaft is generally parallel to the longitudinal axis X.
[0080] In the case where each fitting assembly 452 a - b is made of two plates, each plate comprises a first safety hole 461 .
[0081] The waiting fail-safe hinge 456a-b is a waiting fail-safe element. This means that in normal use, the main force path is defined by the first hinge point 454a and the second hinge point 454b-c, and the load is transmitted through this main force path. In the event of a failure of the main force path, the safety hinge 456a-b is enabled, which means that the waiting fail-safe hinge is requested.
[0082] To achieve a fail-safe articulation, the diameter of each safety hole 461 is larger than the diameter of the safety shaft. Thus, in normal operation, there is no contact between the accessory assemblies 452a-b and the safety shaft, while in the event of a failure, the fan housing 102a will move and the accessory assemblies 452a-b will then come into contact with the safety shaft.
Claims
1. A propulsion assembly (100) for an aircraft (50), the propulsion assembly (100) comprising: - a jet engine (102) having a fan casing (102a) and a center casing (102b) around a longitudinal axis (X) and having a vertical median plane (P) passing through said longitudinal axis (X); - an attachment pylon (104) having a rigid structure (106) in the form of a box having a front wall (106d) and an upper spar (106b) extending forwardly relative to the front wall (106d); - a front engine attachment (152) fixed between the upper region (103) of the fan casing (102a) and the front end of the upper spar (106b); and - A complementary front engine attachment (153) fixed between the upper area (105) of the central housing (102b) and the lower end of the front wall (106d).
2. The propulsion assembly (100) according to claim 1, characterized in that The propulsion assembly includes a main rod (156) fixed between the upper spar (106b) and the front wall (106d).
3. The propulsion assembly (100) according to claim 1 or 2, characterized in that: The front engine attachment (152) comprises a rod (154) which is hingedly mounted on the front end of the upper spar (106b) at the vertical mid-plane (P), and the rod (154) comprises ends (154a-b) on each side of the vertical mid-plane (P), which are hingedly mounted on the upper area (103) of the fan casing (102a), each hinged portion being at least a rotation portion around an axis parallel to the longitudinal axis (X).
4. The propulsion assembly (100) according to claim 3, characterized in that Each hinge of the rod (154) is a ball joint connection.
5. The propulsion assembly (100) according to claim 3 or 4, characterized in that: The articulation of one of the two ends (154a-b) is a fail-safe articulation.
6. The propulsion assembly (100) according to any one of claims 3 to 5, characterized in that: The complementary front engine attachment (153) comprises a pair of first rods (352a-b) on each side of the vertical middle plane (P), wherein the first end of each first rod (352a-b) is hingedly mounted on the lower end of the front wall (106d), and wherein the second end of each first rod (352a-b) is hingedly mounted on the upper area (105) of the central shell (102b).
7. The propulsion assembly (100) according to any one of claims 3 to 5, characterized in that: The complementary front engine attachment (153) comprises two fitting assemblies (452a-b), each of which comprises a first hinge point (454a) with the lower end of the front wall (106d) at the vertical mid-plane (P) and a second hinge point (454b-c) with the upper area (105) of the center shell (102b) on each side of the vertical mid-plane (P).
8. An aircraft (50) having wings (52) and a propulsion assembly (100) according to any one of the preceding claims, wherein: The rigid structure (106) is secured underneath the wing (52).