Horizontal hoisting device and method for single-section hoisting point eccentric assembly of aero-engine

Abstract

The invention discloses a horizontal hoisting device and method for a single-section hoisting point eccentric assembly of an aero-engine. The hoisting device mainly comprises a hoisting ring, a mounting shaft, an inner hexagonal bolt, a small hexagonal nut, a force bearing wheel assembly, an I-shaped beam, a force bearing shaft with a bearing, a connecting pin, a side plate, a hexagonal flower nut, a hexagonal bolt with a hole, a force bearing plate, a fixed seat, a trapezoidal screw rod, a bottom plate, a flat hexagonal nut, a mounting seat, a pull rod, a cotter pin, a handle, a long cotter pin and a large hexagonal nut. During hoisting, the tail ends of the two pull rods are connected with two lifting lugs on the single-section hoisting point eccentric assembly respectively, and the square block, the fixed seat, the force bearing plate and the force bearing wheel assembly are sequentially driven to move relative to the I-shaped beam by rotating the trapezoidal screw rod, so that the gravity center position of the horizontal hoisting device is adjusted. According to the method, the time for adjusting the lifting posture is greatly shortened, the assembly efficiency is improved, and the lifting quality risk is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft engine complete machine assembly and test running, and specifically relates to a horizontal lifting device and method for eccentric components of a single-section lifting point of an aircraft engine. Background Art

[0002] like Figure 1 As shown in the figure, due to structural limitations, an aircraft engine booster has only two points with lifting functions, which are located in the same cross section, and the lifting point is not at the center of gravity, so the problem of "top-heavy" will occur during lifting. The traditional lifting method uses a balance belt tied to the pull rod for lifting. Since the lifting position is not at the center of gravity, it will be skewed during the lifting process, and additional counterweights are needed to ensure the level of the booster, which increases the difficulty of operation and is very likely to cause the counterweight to damage the booster.

[0003] Based on the above reasons, it is necessary to design a special lifting device to achieve free adjustment during the lifting process, make adjustments faster, eliminate the method of adding counterweights, and make the lifting process safer. Summary of the invention

[0004] The present invention aims to provide a horizontal lifting device and method for eccentric components of a single-section lifting point of an aircraft engine, which greatly shortens the time for adjusting the posture before lifting, improves the assembly efficiency of the engine components, and reduces quality risks.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A horizontal lifting device for an aircraft engine single-section lifting point eccentric component, comprising:

[0007] A lifting ring and a mounting shaft, wherein the lifting ring is fixed on the mounting shaft;

[0008] Load-bearing plates, wherein two load-bearing plates are arranged in parallel and at intervals, the lifting ring and the mounting shaft are placed between the two load-bearing plates, and both ends of the mounting shaft are fixed to the two load-bearing plates respectively;

[0009] An I-beam, the I-beam is placed between the two bearing plates and below the mounting axis, the web of the I-beam is parallel to the two bearing plates, and both ends of the I-beam in the length direction are respectively connected to a side plate on the bearing plates;

[0010] A bearing wheel assembly, wherein the rotating shaft of the bearing wheel assembly is fixed on the bearing plate, and the roller of the bearing wheel assembly is rollingly connected to the flange of the I-beam;

[0011] A load-bearing shaft, which is placed between two load-bearing plates and is located below the mounting shaft and above the I-beam. Both ends of the load-bearing shaft are respectively fixed to a load-bearing plate. A load-bearing bearing is rotatably mounted on the load-bearing shaft, and the load-bearing bearing is attached to the flange surface of the I-beam.

[0012] A fixing seat and a trapezoidal screw, wherein the fixing seat is installed between the two bearing plates and fixedly connected to the two bearing plates, a square block is slidably connected in the fixing seat, and the sliding direction of the square block is perpendicular to the I-beam, a trapezoidal threaded through hole is opened on the square block, and the trapezoidal screw passes through the trapezoidal threaded through hole and the two ends are respectively installed on the two side plates;

[0013] The bottom plate and the tie rods, the bottom plate is located below the fixed seat and the two ends of the bottom plate are respectively connected to the two side plates, the upper ends of the two tie rods are rotatably connected to the bottom plate, and the rotation planes of the two tie rods are coplanar and perpendicular to the web and flange of the I-beam at the same time.

[0014] Furthermore, the horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine also includes a handle, which is located on the outside of the side plate and connected to one end of the trapezoidal screw.

[0015] Furthermore, the horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine also includes a mounting seat, two of which are detachably connected to the base plate, and the mounting seat has a U-shaped mounting groove, one end of the pull rod is rotatably connected to the U-shaped mounting groove, and the notches of the two U-shaped mounting grooves are located in the same plane that is perpendicular to the web and flange of the I-beam.

[0016] Furthermore, the load-bearing wheel assembly is symmetrically arranged on both sides of the web of the I-beam, and the rotating shaft of the load-bearing wheel assembly is assembled with the roller through a first bearing.

[0017] Furthermore, the fixed seat is mainly composed of two fixed seat side plates and two fixed seat sealing plates, wherein the two fixed seat side plates are respectively fixed on two load-bearing plates, the two fixed seat sealing plates are arranged in parallel and spaced apart, and the two ends of each fixed seat sealing plate are respectively connected to a fixed seat side plate, and through holes are opened on the two fixed seat sealing plates, and the blocks are slidably connected in the through holes of the two fixed seat sealing plates.

[0018] Furthermore, a waist-shaped hole is provided on the hanging ring.

[0019] A horizontal hoisting method for an aircraft engine single-section hoisting point eccentric component, comprising:

[0020] Step 1: Select a lifting device with a horizontally adjustable center of gravity, and install the lifting device on the hook of the overhead crane;

[0021] Step 2: Connect the lifting device to two lifting points of the single-section lifting point eccentric type component through a rigid connector;

[0022] Step three, lift the lifting device and the rigid connector by lifting the overhead crane to above the single-section lifting point eccentric component, adjust the center of gravity of the lifting device in the horizontal direction until its center of gravity is in the same vertical plane as the center of gravity of the single-section lifting point eccentric component, and start lifting the single-section lifting point eccentric component.

[0023] further,

[0024] In the step 1, the aforementioned horizontal lifting device is selected;

[0025] In the step 2, the ends of the two tie rods are respectively connected to two lifting ears on the single-section lifting point eccentric type component;

[0026] In the step three, the trapezoidal screw is rotated to sequentially drive the block, the fixing seat, the load-bearing plate and the load-bearing wheel assembly to move relative to the I-beam, thereby adjusting the center of gravity position of the horizontal lifting device.

[0027] Furthermore, in the step 2, the ends of the two pull rods are connected to two lifting ears on the single-section lifting point eccentric component through connecting pins and small hexagonal nuts.

[0028] Compared with the prior art, the present invention utilizes a specific lifting device structural design to achieve free adjustment of the center of gravity position of horizontal lifting of eccentric components with a single-section lifting point, and can accurately and quickly adjust the center of gravity position without adding counterweights, which can not only improve efficiency but also avoid the occurrence of problems such as bumps and scratches caused by adding counterweights. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 A schematic diagram showing the force-adding device and its lifting lugs, tie rods and center of gravity position;

[0030] Figure 2 It is the general diagram of the horizontal lifting device of the eccentric type components with a single cross-section lifting point;

[0031] Figure 3 for Figure 2 Left view of

[0032] Figure 4 for Figure 2 sectional view of

[0033] Figure 5 It is a schematic diagram of the fixed seat structure;

[0034] Figure 6 It is a three-dimensional diagram of the fixed seat;

[0035] Figure 7 It is a schematic diagram of the load-bearing shaft structure;

[0036] Figure 8 It is a three-dimensional diagram of the load-bearing axis;

[0037] Fig. 9 It is a schematic diagram of the structure of the bearing wheel assembly;

[0038] Fig.10 It is a three-dimensional diagram of the bearing wheel assembly;

[0039] In the figure: 1. lifting ring, 2. mounting shaft, 3. hexagon socket bolt, 4. small hexagon nut, 5. load-bearing wheel assembly, 6. I-beam, 7. load-bearing shaft with bearing, 8. connecting pin, 9. side plate, 10. hexagonal nut, 11. hexagonal bolt with hole, 12. load-bearing plate, 13. fixed seat, 14. trapezoidal screw, 15. bottom plate, 16. flat hexagonal nut, 17. mounting seat, 18. pull rod, 19. cotter pin, 20. handle, 21. long cotter pin, 22. large hexagonal nut, 23. fixed seat side plate, 24. fixed seat sealing plate, 25. block, 26. load-bearing shaft, 27. distance sleeve, 28. second bearing, 29. retaining ring, 30. step shaft, 31. first bearing, 32. roller. DETAILED DESCRIPTION

[0040] The present invention is further described below in conjunction with specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to common technical knowledge and customary means in the field are included in the scope of the present invention.

[0041] like Figure 2 to Figure 10 As shown, the horizontal lifting of the eccentric components of the single-section lifting point of the aircraft engine is achieved by a lifting device, which is mainly composed of a lifting ring 1, a mounting shaft 2, a hexagon socket bolt 3, a small hexagon nut 4, a load-bearing wheel assembly 5, an I-beam 6, a load-bearing shaft with a load-bearing bearing 7, a connecting pin 8, a side plate 9, a hexagonal nut 10, a hexagonal bolt with a hole 11, a load-bearing plate 12, a fixing seat 13, a trapezoidal screw 14, a bottom plate 15, a flat hexagonal nut 16, a mounting seat 17, a pull rod 18, a cotter pin 19, a handle 20, a long cotter pin 21, and a large hexagonal nut 22.

[0042] The lower end of the pull rod 18 is installed at the lifting ear of the force adding device, and is connected to the force adding device through the small hexagonal nut 4 and the connecting pin 8 to achieve fixation with the force adding device; the upper end of the pull rod 18 is connected to the mounting seat 17 in a way that the position is limited along the axial direction, and the cross-sectional direction can be rotated (i.e. Figure 2 The middle tie rod 18 is restricted from rotating in the axial direction of the trapezoidal screw 14 and can only rotate in a plane perpendicular to the axial direction of the trapezoidal screw 14). On the one hand, the tie rod 18 is conveniently installed at the lifting ear of the force-adding device by moving along the cross-sectional direction. The axial limit is to ensure that the lifting device and the force-adding device are rigidly connected to form an assembly.

[0043] The lifting ring 1 is designed to be rotatable around the mounting shaft 2 and has a waist-shaped hole, which is convenient for the installation of the lifting hook;

[0044] Among them, Figure 5 and Figure 6 The fixing seat 13 is designed with an internal thread that matches the trapezoidal screw 14. The fixing seat 13 is installed on the load-bearing plate 12. Through the interaction of the trapezoidal threads, the handle 20 is turned to drive the screw 14 to rotate, so that the fixing seat 13 can drive the load-bearing plate 12 to move freely within the travel range, and drive the load-bearing plate 12, the mounting shaft 2 and the lifting ring 1 to move horizontally, thereby realizing the free adjustment of the lifting center of gravity. The trapezoidal screw 14 is selected because the trapezoidal thread itself has a self-locking function and will not rotate freely due to the influence of gravity; on the other hand, the block 25 is slidably connected in the through hole of the fixing seat 13, so that when the horizontal lifting device is not used and the horizontal lifting device is stored normally, the dead weight of the load-bearing plate 12, the lifting ring 1 and the fixing seat 13 will not bend the trapezoidal screw 14, thereby preventing the thread transmission of the block 25 and the trapezoidal screw 14 from being stuck due to the bending of the trapezoidal screw 14.

[0045] Among them, Figure 7 and Figure 8 Two bearings are installed on the bearing shaft 7. When the lifting device is not used and stored normally, the weight of the bearing plate 12, the lifting ring 1 and the fixing seat 13 are loaded onto the I-beam 6 through the bearing shaft 7 and the bearing bearings. In normal use, the two bearing bearings and the bearing wheel assembly 5 cooperate with the flange of the I-beam 6 one above and one below to achieve the sliding adjustment of the lifting ring 1 in the horizontal direction.

[0046] Among them, Fig. 9 and Fig.10 The load-bearing wheel assembly 5 is designed as a structure in which the roller 32 is assembled on the stepped shaft 30, so that it can freely roll along the I-beam 6 while bearing the load.

[0047] Structural features of the horizontal lifting device for aircraft engine single-section lifting point eccentric components:

[0048] ① The lifting ring 1 is installed on the installation shaft 2. The lifting ring 1 can rotate around the installation shaft 2. The installation shaft 2 is installed on the bearing plate 12 through a long cotter pin 21 and a large hexagonal nut 22 to achieve a rigid connection;

[0049] ② The I-beam 6, the side plate 9 and the bottom plate 15 constitute the main load-bearing member, which are respectively connected by the hexagonal bolts 11 with holes, the hexagonal nuts 10, the cotter pins 19 and the hexagonal bolts 3;

[0050] ③ The handle 20, the trapezoidal screw 14 and the fixed seat 13 constitute an adjustment mechanism. The fixed seat 13 includes a fixed seat side plate 23, a fixed seat sealing plate 24 and a block 25. The block 25 can slide up and down in the through hole of the fixed seat sealing plate 24. The trapezoidal screw 14 and the trapezoidal thread of the block 25 in the fixed seat 13 rotate with each other to adjust the center of gravity of the lifting device. The fixed seat 13 is installed on the bearing plate 12 by the hexagonal bolt 3;

[0051] ④ The tie rod 18, the mounting seat 17 and the connecting pin 8 constitute a connecting mechanism. The lower end of the tie rod 18 is connected to the lifting ear on the force-applying device and is stopped by a small hexagonal nut 4; the tie rod 18 is connected to the mounting seat 17 by a hexagonal nut 10, a hexagonal bolt with a hole 11, and a split pin 19; the mounting seat 17 is installed on the bottom plate 15 by a flat hexagonal nut 16;

[0052] ⑤ The bearing plate 12 is respectively installed with a bearing wheel assembly 5 and a bearing shaft 7, wherein the bearing wheel assembly 5 includes a retaining spring 29, a stepped shaft 30, a first bearing 31, and a roller 32, and the bearing shaft 7 includes a bearing shaft 26, a distance sleeve 27 (the length of the distance sleeve 27 is used to ensure the installation position of the second bearing 28 on the bearing shaft 26), and a second bearing 28. When adjusting the center of gravity, the bearing wheel assembly 5 can be displaced along the I-beam 6, and during the lifting process, the bearing wheel assembly 5 is in contact with the I-beam 6 to achieve load-bearing; when the horizontal lifting device is stored, the bearing shaft 7 with the second bearing 28 is in contact with the upper part of the I-beam 6, and the displacement along the I-beam 6 is achieved through the second bearing 28, which can ensure the free adjustment of the center of gravity at this time; the bearing wheel assembly 5 and the bearing shaft 7 with bearings are respectively installed on the bearing plate 12 through the hexagon socket bolt 3 and the small hexagon nut 4.

[0053] The method for hoisting using the above-mentioned horizontal hoisting device for eccentric components of a single-section hoisting point of an aircraft engine is as follows:

[0054] ①First install the horizontal lifting device on the overhead crane, and install the hook of the overhead crane on the lifting ring 1 of the horizontal lifting device;

[0055] ②Then install the horizontal lifting device on the lifting lug on the force-adding device and connect it through the connecting pin 8 and the small hexagonal nut 4;

[0056] ③ By turning the handle 20 to drive the trapezoidal screw 14 to rotate, the fixed seat 13 can drive the load-bearing plate 12 to move freely within the travel range, and then drive the installation shaft 2 and the lifting ring 1 to move horizontally, thereby realizing the free adjustment of the lifting center of gravity.

[0057] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in the field. Although the illustrative specific embodiments of the present invention are described above to facilitate the understanding of the present invention by the technical personnel in the field, it should be clear that the present invention is not limited to the scope of the specific embodiments. For the ordinary technical personnel in the field, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

Claims

1. A horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine, characterized in that: include: A lifting ring (1) and a mounting shaft (2), wherein the lifting ring (1) is fixed on the mounting shaft (2); Load-bearing plates (12), wherein two load-bearing plates (12) are arranged in parallel and at intervals, the lifting ring (1) and the mounting shaft (2) are placed between the two load-bearing plates (12), and both ends of the mounting shaft (2) are respectively fixed on the two load-bearing plates (12); An I-beam (6), the I-beam (6) being placed between two load-bearing plates (12) and located below the mounting shaft (2), the web of the I-beam (6) being parallel to the two load-bearing plates (12), and both ends of the I-beam (6) in the length direction being respectively connected to a side plate (9) on the load-bearing plates (12); A load-bearing wheel assembly (5), wherein the rotating shaft of the load-bearing wheel assembly (5) is fixed on the load-bearing plate (12), and the roller (32) of the load-bearing wheel assembly (5) is rollingly connected to the flange of the I-beam (6); A load-bearing shaft (7), the load-bearing shaft (7) being placed between two load-bearing plates (12) and being located below the mounting shaft (2) and above the I-beam (6), the two ends of the load-bearing shaft (7) being respectively fixed on a load-bearing plate (12), a load-bearing bearing being rotatably mounted on the load-bearing shaft (7), and the load-bearing bearing being attached to the flange surface of the I-beam (6); A fixing seat (13) and a trapezoidal screw rod (14), wherein the fixing seat (13) is installed between two load-bearing plates (12) and is fixedly connected to the two load-bearing plates (12); a block (25) is slidably connected inside the fixing seat (13), and the sliding direction of the block (25) is perpendicular to the I-beam (6); a trapezoidal threaded through hole is opened on the block (25); and the trapezoidal screw rod (14) passes through the trapezoidal threaded through hole and then its two ends are respectively installed on the two side plates (9); A base plate (15) and a tie rod (18), wherein the base plate (15) is located below the fixed seat (13) and the two ends of the base plate (15) are respectively connected to the two side plates (9), the upper ends of the two tie rods (18) are rotatably connected to the base plate (15), and the rotation planes of the two tie rods (18) are coplanar and perpendicular to the web and flange of the I-beam (6).

2. The horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine according to claim 1, characterized in that: It also includes a handle (20), which is located on the outside of the side plate (9) and connected to one end of the trapezoidal screw rod (14).

3. The horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine according to claim 1, characterized in that: It also includes a mounting seat (17), two of the mounting seats (17) are detachably connected to the base plate (15), the mounting seat (17) has a U-shaped mounting groove, one end of the pull rod (18) is rotatably connected in the U-shaped mounting groove, and the notches of the two U-shaped mounting grooves are located in the same plane that is perpendicular to the web and flange of the I-beam (6).

4. The horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine according to claim 1, characterized in that: The load-bearing wheel assembly (5) is symmetrically arranged on both sides of the web of the I-beam (6), and the rotating shaft of the load-bearing wheel assembly (5) and the roller (32) are assembled via a first bearing (31).

5. The horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine according to claim 1, characterized in that: The fixed seat (13) is mainly formed by connecting two fixed seat side plates (23) and two fixed seat sealing plates (24), wherein the two fixed seat side plates (23) are respectively fixed on the two bearing plates (12), the two fixed seat sealing plates (24) are arranged in parallel and spaced apart, and the two ends of each fixed seat sealing plate (24) are respectively connected to a fixed seat side plate (23), the two fixed seat sealing plates (24) are both provided with through holes, and the blocks (25) are slidably connected in the through holes of the two fixed seat sealing plates (24).

6. The horizontal lifting device for eccentric components of a single-section lifting point of an aircraft engine according to claim 1, characterized in that: The hanging ring (1) is provided with a waist-shaped hole.

7. A horizontal hoisting method for aircraft engine single-section lifting point eccentric components, characterized in that: include: Step 1: Select a lifting device with a horizontally adjustable center of gravity, and install the lifting device on the hook of the overhead crane; Step 2: Connect the lifting device to two lifting points of the single-section lifting point eccentric type component through a rigid connector; Step three, lift the lifting device and the rigid connector by lifting the overhead crane to above the single-section lifting point eccentric component, adjust the center of gravity of the lifting device in the horizontal direction until its center of gravity is in the same vertical plane as the center of gravity of the single-section lifting point eccentric component, and start lifting the single-section lifting point eccentric component.

8. The horizontal hoisting method for aero-engine single-section hoisting point eccentric components according to claim 7, characterized in that: In said step 1, the horizontal lifting device according to claim 1 is selected; In the step 2, the ends of the two tie rods (18) are respectively connected to two lifting ears on the single-section lifting point eccentric component; In the step three, the trapezoidal screw (12) is rotated to sequentially drive the block (25), the fixing seat (13), the load-bearing plate (12) and the load-bearing wheel assembly (5) to move relative to the I-beam (6), thereby adjusting the center of gravity position of the horizontal lifting device.

9. A horizontal hoisting method for aircraft engine single-section lifting point eccentric components according to claim 8, characterized in that: In the second step, the ends of the two pull rods (18) are connected to two lifting ears on the single-section lifting point eccentric component through a connecting pin (8) and a small hexagonal nut (4).

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