Rear hanging beam structure of aircraft engine
By introducing rotating parts and connectors into the rear hanging beam structure of the aircraft engine, the problem of precise alignment during the lifting process is solved, and the effect of rapid lifting and extended service life is achieved.
Patent Information
- Application Number
- CN202422341446.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-25
- Publication Date
- 2025-06-13
- Estimated Expiration
- 2034-09-25
AI Technical Summary
The rear hanging beam structure of existing aircraft engines is difficult to achieve accurate alignment during the lifting process, resulting in extended lifting time and increased safety risks.
An aircraft engine rear hanging beam structure including rotating parts and connecting parts is designed. The rotation and swing of the lifting ears are facilitated by the arrangement of the rotating parts, the movement range of the lifting ears is improved, and the rapid calibration is achieved.
The movement range of the hoisting lugs is improved, the lifting process is simplified, the lifting time is reduced, and the safety risks are reduced, while the service life of the hanging point is extended through wear-resistant bushings.
Smart Images
Figure CN222973626U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of engines, and more specifically, to a structure of a rear suspension beam of an aircraft engine. Background Art
[0002] The internal structure of an aircraft engine includes a heat insulation cover, an outer ring edge and an inner ring edge from outside to inside in sequence. The inner ring edge rotates continuously with the blades during operation to provide a power source. There is a gap between the outer ring edge and the inner ring edge of the aircraft, and the gap between the outer ring edge and the inner ring edge needs to be sealed to prevent combustible gas from entering the heat insulation cover through this gap and causing combustion and explosion.
[0003] Existing rear suspension beams of aircraft engines are provided with suspension points, usually in the form of screw holes for suspension. When suspending an aircraft engine, it is necessary to lift the engine and slowly move it to accurately align the suspension parts at its top with the suspension points on the rear suspension beam before inserting the screw and fixing it. However, the weight of an aircraft engine is extremely large, and it is difficult to adjust the fine distance during the hoisting of such a heavy object. Moreover, it will prolong the suspension calibration time and increase potential safety risks. Therefore, it needs to be improved. Summary of the Utility Model
[0004] In order to overcome the deficiencies of the prior art, the utility model provides a structure of a rear suspension beam of an aircraft engine.
[0005] To achieve the above purpose, the utility model provides the following technical solution: A structure of a rear suspension beam of an aircraft engine, including a rear suspension beam body, a rotating part is connected to the bottom of the rear suspension beam body, a suspension point is connected to the bottom of the rotating part, a suspension ear is movably connected to the lower end of the suspension point, and a connecting part is sleeved at the connection between the suspension point and the suspension ear;
[0006] The suspension point and the suspension ear can rotate relative to each other under the restriction of the connecting part;
[0007] The rotating part includes a rotating seat fixedly connected to the top of the suspension point. A connecting shaft is integrally formed on the top of the rotating seat. A limiting rotating shaft is integrally formed at the bottom of the connecting shaft. An installation seat is movably sleeved outside the connecting shaft and the limiting rotating shaft, and the installation seat is fixedly installed on the rear suspension beam body.
[0008] As a preferred technical solution of the utility model, the suspension ear includes a first suspension ear clamped outside the suspension point, and a second suspension ear is integrally formed at the bottom of the first suspension ear.
[0009] As a preferred technical solution of the utility model, reinforcing ribs are integrally formed on the opposite sides of the first suspension ear and the second suspension ear.
[0010] As a preferred technical solution of the present utility model, a first wear-resistant bushing is movably sleeved inside both the first lifting lug and the second lifting lug, a second wear-resistant bushing is sleeved inside the lifting point, and the connecting piece is sleeved inside the first wear-resistant bushing in the first lifting lug and inside the second wear-resistant bushing in the lifting point.
[0011] As a preferred technical solution of the present utility model, the mounting seat is fixedly installed on the rear hanging beam body by bolts. The outer peripheral diameter dimension of the connecting shaft is smaller than the outer peripheral diameter dimension of the limit rotating shaft. The outer surfaces of the limit rotating shaft and the connecting shaft are both smooth, and the outer surfaces of the limit rotating shaft and the connecting shaft are smoothly connected.
[0012] As a preferred technical solution of the present utility model, the connecting piece includes a sleeve rod movably sleeved inside the first wear-resistant bushing and the second wear-resistant bushing. Both ends of the sleeve rod penetrate through the first wear-resistant bushing and the second wear-resistant bushing and extend to the front and rear ends of the first lifting lug respectively, and an anti-detachment cap and a screw rod are integrally formed respectively. A locking ring is threadedly sleeved on the outer part of the screw rod.
[0013] As a preferred technical solution of the present utility model, the facing surfaces of the anti-detachment cap and the locking ring are respectively attached to the front and rear sides of the first lifting lug. The outer peripheral diameter dimension of the screw rod is smaller than the outer peripheral diameter dimension of the sleeve rod; the outer peripheral diameter dimensions of the anti-detachment cap and the locking ring are both larger than the outer peripheral diameter dimension of the first wear-resistant bushing.
[0014] Compared with the prior art, the beneficial effects of the present utility model are as follows:
[0015] 1. Due to the setting of the rotating components in the present utility model, it is convenient for the staff to rotate the lifting lug, and with the cooperation of the connecting piece, it is convenient for the staff to swing the lifting lug, thereby greatly increasing the moving range of the second lifting lug at the lower end of the lifting lug, enabling it to quickly align with the lifting ring at the top of the surrounding engine, so as to achieve the effect of quickly hoisting the engine.
[0016] 2. Due to the setting of the first wear-resistant bushing and the second wear-resistant bushing in the present utility model, the wear resistance of the hanging point can be improved, thereby prolonging the service life of the hanging parts. Once damage is found at the hanging point and the lifting lug, the hanging point and the lifting lug can be replaced separately, reducing the loss of original materials. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 is a schematic diagram of the installation structure of the present utility model and the hanging beam;
[0018] Figure 2 is Figure 1 a front-sectional view of the structure in
[0019] Figure 3 is a schematic diagram of the structure of the present utility model;
[0020] Figure 4 This is a cross-sectional view of the side of the utility model.
[0021] In the figure: 1. Rear suspension beam body; 2. Rotating component; 21. Rotating seat; 22. Connecting shaft; 23. Limit rotating shaft; 24. Mounting seat; 3. Hanging point; 4. Suspension ear; 41. First suspension ear; 42. Second suspension ear; 43. Reinforcing rib; 5. Connecting piece; 51. Sleeve rod; 52. Anti-detachment cap; 53. Lead screw; 54. Locking ring; 6. First wear-resistant bushing; 7. Second wear-resistant bushing. Specific embodiments
[0022] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.
[0023] As Figures 1 to 4 shown, the present utility model provides an aircraft engine rear suspension beam structure, including a rear suspension beam body 1, a rotating component 2 is connected to the bottom of the rear suspension beam body 1, a hanging point 3 is connected to the bottom of the rotating component 2, a suspension ear 4 is movably connected to the lower end of the hanging point 3, and a connecting piece 5 is sleeved at the connection between the hanging point 3 and the suspension ear 4;
[0024] The hanging point 3 and the suspension ear 4 can rotate relative to each other under the restriction of the connecting piece 5;
[0025] The rotating component 2 includes a rotating seat 21 fixedly connected to the top of the hanging point 3, a connecting shaft 22 is integrally formed on the top of the rotating seat 21, a limit rotating shaft 23 is integrally formed at the bottom of the connecting shaft 22, and a mounting seat 24 is movably sleeved outside the connecting shaft 22 and the limit rotating shaft 23, and the mounting seat 24 is fixedly installed on the rear suspension beam body 1; due to the setting of the rotating component 2, it is convenient for the staff to rotate the suspension ear 4, and with the cooperation of the connecting piece 5, it is convenient for the staff to swing the suspension ear 4, thereby greatly increasing the moving range of the second suspension ear 42 at the lower end of the suspension ear 4, enabling it to quickly align with the suspension ring on the top of the surrounding engine, so as to achieve the effect of quickly hoisting the engine.
[0026] Among them, the suspension ear 4 includes a first suspension ear 41 clamped outside the hanging point 3, and a second suspension ear 42 is integrally formed at the bottom of the first suspension ear 41; through the first suspension ear 41, it is convenient to swing the second suspension ear 42 along the lower end of the hanging point 3 with the cooperation of the connecting piece 5, so that the first wear-resistant bushing 6 in the second suspension ear 42 can quickly align with the suspension ring on the engine.
[0027] The first lifting ear 41 and the second lifting ear 42 have reinforcing ribs 43 integrally formed on their opposite surfaces.
[0028] Among them, the first lifting ear 41 and the second lifting ear 42 are both movably sleeved with the first wear-resistant bushing 6, the interior of the lifting point 3 is sleeved with the second wear-resistant bushing 7, and the connecting piece 5 is sleeved on the interior of the first wear-resistant bushing 6 in the first lifting ear 41 and the interior of the second wear-resistant bushing 7 in the lifting point 3; due to the arrangement of the first wear-resistant bushing 6 and the second wear-resistant bushing 7, the wear resistance of the hanging point can be improved, thereby extending the service life of the dropped parts. Once the lifting point 3 and the lifting ear 4 are found to be damaged, the lifting point 3 and the lifting ear 4 can be replaced separately to reduce the loss of original materials.
[0029] Among them, the mounting seat 24 is fixed on the rear hanging beam body 1 by bolts, the outer diameter of the connecting shaft 22 is smaller than the outer diameter of the limiting rotating shaft 23, the outer surfaces of the limiting rotating shaft 23 and the connecting shaft 22 are smooth, and the outer surfaces of the limiting rotating shaft 23 and the connecting shaft 22 are smoothly connected; due to the setting of the connecting shaft 22 and the limiting rotating shaft 23, it can be ensured that the rotating seat 21 can rotate continuously and stably at the bottom of the mounting seat 24, thereby facilitating the staff to rotate the hanging point 3 and the lifting ear 4.
[0030] Among them, the connecting member 5 includes a sleeve rod 51 which is movably sleeved inside the first wear-resistant bushing 6 and the second wear-resistant bushing 7. Both ends of the sleeve rod 51 penetrate the first wear-resistant bushing 6 and the second wear-resistant bushing 7 and extend to the front and rear ends of the first lifting ear 41 respectively and are respectively integrally formed with an anti-drop cap 52 and a screw rod 53, and the external thread of the screw rod 53 is sleeved with a locking ring 54; due to the setting of the connecting member 5, it is convenient to connect and disassemble the lifting point 3 and the lifting ear 4 as well as the lifting ear 4 and the lifting ring, and it can prolong the wear and slow down the damage rate with the cooperation of the first wear-resistant bushing 6 and the second wear-resistant bushing 7.
[0031] Among them, the facing surfaces of the anti-drop cap 52 and the locking ring 54 are respectively attached to the front and rear sides of the first lifting ear 41, and the outer diameter of the screw rod 53 is smaller than the outer diameter of the sleeve rod 51; the outer diameter of the anti-drop cap 52 and the locking ring 54 are both larger than the outer diameter of the first wear-resistant bushing 6.
[0032] The working principle and use process of this utility model:
[0033] When hanging the engine, hang the engine and make its top lifting ring close to the lifting ear 4, then rotate or swing the lifting ear 4 with the cooperation of the rotating component 2 and the connecting member 5, so that the second lifting ear 42 at its lower end is quickly calibrated with the lifting ring on the engine, and then insert another connecting member 5 into the first wear-resistant bushing 6 and lock it to connect and fix it, and then after the engine angle is adjusted with the cooperation of the rotating component 2, it can be fixed by other components.
[0034] It should be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device.
[0035] Although the embodiments of the present utility model have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the present utility model, and the scope of the present utility model is defined by the appended claims and their equivalents.
Claims
1. A rear pylon structure for an aircraft engine, comprising a rear pylon body (1), characterized in that: The bottom of the rear hanging beam body (1) is connected to a rotating component (2), the bottom of the rotating component (2) is connected to a hanging point (3), the lower end of the hanging point (3) is movably connected to a hanging ear (4), and a connecting piece (5) is sleeved at the connection between the hanging point (3) and the hanging ear (4); The lifting point (3) and the lifting lug (4) can rotate relative to each other under the restriction of the connecting member (5); The rotating component (2) comprises a rotating seat (21) fixedly connected to the top of the suspension point (3); a connecting shaft (22) is integrally formed at the top of the rotating seat (21); a limited rotation shaft (23) is integrally formed at the bottom of the connecting shaft (22); an external movable sleeve of the connecting shaft (22) and the limited rotation shaft (23) is provided with a mounting seat (24); and the mounting seat (24) is fixedly mounted on the rear suspension beam body (1).
2. The aircraft engine rear suspending beam structure according to claim 1, characterized in that: The lifting lug (4) comprises a first lifting lug (41) clamped on the outside of the lifting point (3), and a second lifting lug (42) is integrally formed at the bottom of the first lifting lug (41).
3. The aircraft engine rear suspending beam structure according to claim 2, characterized in that: Reinforcing ribs (43) are integrally formed on the opposite back surfaces of the first lifting ear (41) and the second lifting ear (42).
4. The aircraft engine rear suspending beam structure according to claim 2, characterized in that: The first lifting ear (41) and the second lifting ear (42) are both movably sleeved with a first wear-resistant bushing (6), the interior of the lifting point (3) is sleeved with a second wear-resistant bushing (7), and the connecting piece (5) is sleeved inside the first wear-resistant bushing (6) in the first lifting ear (41) and inside the second wear-resistant bushing (7) in the lifting point (3).
5. The aircraft engine rear suspending beam structure according to claim 1, characterized in that: The mounting seat (24) is fixedly mounted on the rear suspension beam body (1) by means of bolts, the outer diameter of the connecting shaft (22) is smaller than the outer diameter of the limiting rotation shaft (23), the outer surfaces of the limiting rotation shaft (23) and the connecting shaft (22) are both smooth, and the outer surfaces of the limiting rotation shaft (23) and the connecting shaft (22) are smoothly connected.
6. The aircraft engine rear suspending beam structure according to claim 4, characterized in that: The connecting member (5) comprises a sleeve rod (51) movably sleeved inside the first wear-resistant bushing (6) and the second wear-resistant bushing (7), both ends of the sleeve rod (51) pass through the first wear-resistant bushing (6) and the second wear-resistant bushing (7) and extend to the front and rear ends of the first lifting ear (41) respectively and are respectively integrally formed with an anti-drop cap (52) and a screw rod (53), and the external thread of the screw rod (53) is sleeved with a locking ring (54).
7. The aircraft engine rear suspending beam structure according to claim 6, characterized in that: The facing surfaces of the anti-drop cap (52) and the locking ring (54) are respectively fitted to the front and rear sides of the first lifting ear (41); the outer diameter of the screw rod (53) is smaller than the outer diameter of the sleeve rod (51); and the outer diameters of the anti-drop cap (52) and the locking ring (54) are both larger than the outer diameter of the first wear-resistant bushing (6).