A horizontal hoisting device and method for eccentric components with single cross-section lifting points in aero-engines

Abstract

This invention discloses a horizontal lifting device and method for single-section eccentric lifting point components of aero-engines. The lifting device mainly consists of lifting rings, mounting shafts, hexagonal bolts, small hexagonal nuts, load-bearing wheel assemblies, I-beams, a load-bearing shaft with bearings, connecting pins, side plates, hexagonal nuts, perforated hexagonal bolts, load-bearing plates, fixing seats, trapezoidal screws, base plates, flat hexagonal nuts, mounting seats, tie rods, cotter pins, handles, long cotter pins, and large hexagonal nuts. During lifting, the ends of the two tie rods are connected to two lifting lugs on the single-section eccentric lifting point component. By rotating the trapezoidal screws, the block, fixing seat, load-bearing plate, and load-bearing wheel assembly are sequentially moved relative to the I-beam, thereby adjusting the center of gravity of the horizontal lifting device. This invention significantly shortens the time for adjusting the lifting posture, improves assembly efficiency, and reduces the risk of lifting quality issues.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine assembly and testing technology, specifically a horizontal hoisting device and method for eccentric components with a single cross-section hoisting point in aero-engines. Background Technology

[0002] like Figure 1 As shown, due to structural limitations, an aero-engine afterburner has only two lifting points, located within the same cross-section, and these points are not at the center of gravity. Therefore, a "top-heavy" problem occurs during lifting. Traditional lifting methods use balance belts attached to the tie rods. Because the lifting point is not at the center of gravity, tilting occurs during lifting, requiring additional counterweights to ensure the afterburner is level, increasing operational difficulty, and also greatly increasing the risk of the counterweights damaging the afterburner.

[0003] For the reasons mentioned above, it is necessary to design a dedicated hoisting device to enable free adjustment during the hoisting process, make adjustments faster, eliminate the need for adding counterweights, and make the hoisting process safer. Summary of the Invention

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

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A horizontal lifting device for eccentric components with a single cross-section lifting point in aero-engines, comprising:

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

[0008] The load-bearing plates are arranged in parallel and spaced apart. The lifting ring and the mounting shaft are placed between the two load-bearing plates, and the two ends of the mounting shaft are respectively fixed to the two load-bearing plates.

[0009] An I-beam is placed between two load-bearing plates and below the mounting shaft. The web of the I-beam is parallel to the two load-bearing plates, and both ends of the I-beam along its length are connected to a side plate on the load-bearing plate.

[0010] A load-bearing wheel assembly, wherein the shaft of the load-bearing wheel assembly is fixed to the load-bearing plate, and the rollers of the load-bearing wheel assembly are rotatably connected to the flange of the I-beam;

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

[0012] A fixed seat and a trapezoidal screw rod are provided. The fixed seat is installed between two load-bearing plates and is fixedly connected to the two load-bearing plates. A block is slidably connected inside the fixed seat, and the sliding direction of the block is perpendicular to the I-beam. A trapezoidal threaded through hole is opened on the block. The trapezoidal screw rod passes through the trapezoidal threaded through hole and its two ends are respectively installed on two side plates.

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

[0014] Furthermore, the horizontal hoisting device for single-section eccentric components of aero-engines 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 hoisting device for eccentric components with single cross-section lifting points of aero engines also includes mounting seats. Two mounting seats are detachably connected to the base plate. Each mounting seat has a U-shaped mounting groove. One end of the tie rod is rotatably connected to the U-shaped mounting groove. The openings of the two U-shaped mounting grooves are located in the same plane that is perpendicular to both the web and the 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 shaft of the load-bearing wheel assembly is connected to the roller via a first bearing.

[0017] Furthermore, the fixing seat is mainly composed of two fixing seat side plates and two fixing seat end plates connected together. The two fixing seat side plates are respectively fixed on two load-bearing plates, and the two fixing seat end plates are arranged in parallel and spaced apart. Each fixing seat end plate is connected to a fixing seat side plate at both ends. Both fixing seat end plates have through holes, and the block is slidably connected in the through holes of the two fixing seat end plates.

[0018] Furthermore, the lifting ring has a waist-shaped hole.

[0019] A method for horizontally hoisting eccentric components with a single cross-section lifting point for aero-engines includes:

[0020] Step 1: Select a lifting device whose center of gravity can be adjusted horizontally, and install the lifting device onto the hook of the gantry crane.

[0021] Step 2: Connect the hoisting device to the two lifting points of the single-section eccentric lifting point component via rigid connectors;

[0022] Step 3: The gantry crane lifts the lifting device and rigid connector above the single-section eccentric lifting point component. The center of gravity of the lifting device is adjusted horizontally until its center of gravity and the center of gravity of the single-section eccentric lifting point component are in the same vertical plane. Then, the single-section eccentric lifting point component is lifted.

[0023] further,

[0024] In step one, the aforementioned horizontal hoisting device is selected;

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

[0026] In step three, the block, fixed seat, load-bearing plate and load-bearing wheel assembly are driven to move relative to the I-beam by rotating the trapezoidal screw in sequence, thereby adjusting the center of gravity of the horizontal hoisting device.

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

[0028] Compared with existing technologies, this invention utilizes a specific hoisting device structure design to enable free adjustment of the center of gravity position of horizontally hoisted components with eccentric lifting points on a single cross-section. It can accurately and quickly adjust the center of gravity position without adding counterweights, which can improve efficiency and avoid problems such as bumps and scratches caused by adding counterweights. Attached Figure Description

[0029] Figure 1 A simplified schematic diagram of the force-applying device, its lifting lugs, tie rods, and center of gravity.

[0030] Figure 2 General drawing of a horizontal hoisting device for eccentric components with a single cross-section lifting point;

[0031] Figure 3 for Figure 2 The left view;

[0032] Figure 4 for Figure 2 Cross-sectional view;

[0033] Figure 5 This is a schematic diagram of the fixed base structure;

[0034] Figure 6 This is a three-dimensional view of the fixed base;

[0035] Figure 7 This is a schematic diagram of a load-bearing shaft structure with bearings.

[0036] Figure 8A 3D view of a load-bearing shaft with bearings;

[0037] Figure 9 This is a schematic diagram of the load-bearing wheel assembly structure;

[0038] Figure 10 This is a 3D view of the load-bearing wheel assembly;

[0039] In the diagram: 1. Lifting ring, 2. Mounting shaft, 3. Hex bolt, 4. Small hex nut, 5. Load-bearing wheel assembly, 6. I-beam, 7. Load-bearing shaft with bearing, 8. Connecting pin, 9. Side plate, 10. Hex nut, 11. Hex bolt with hole, 12. Load-bearing plate, 13. Fixing seat, 14. Trapezoidal screw, 15. Base plate, 16. Flat hex nut, 17. Mounting seat, 18. Tie rod, 19. Cotter pin, 20. Handle, 21. Long cotter pin, 22. Large hex nut, 23. Fixing seat side plate, 24. Fixing seat sealing plate, 25. Block, 26. Load-bearing shaft, 27. Spacer sleeve, 28. Second bearing, 29. Snap ring, 30. Stepped shaft, 31. First bearing, 32. Roller. Detailed Implementation

[0040] The present invention will be further described below with reference to specific embodiments, but it should not be construed as limiting the scope of the subject matter of the present invention to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

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

[0042] The lower end of the tie rod 18 is installed at the lifting lug of the force-applying device and is connected to the force-applying device by a small hexagonal nut 4 and a connecting pin 8; the upper end of the tie rod 18 is connected to the mounting base 17 by limiting its position along the axial direction, while allowing rotation in the cross-sectional direction (i.e., Figure 2 The 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, it is convenient to install the tie rod 18 at the lifting lug of the force-adding device by moving along the cross section direction. The axial limit is to ensure that the lifting device and the force-adding device are rigidly connected to form a component.

[0043] Among them, the lifting ring 1 is designed to rotate around the mounting shaft 2 and has a waist-shaped hole, which facilitates the installation of the gantry hook;

[0044] Among them, such as Figure 5 and Figure 6 The fixed seat 13 is designed with an internal thread that mates with the trapezoidal screw 14. The fixed seat 13 is installed on the support plate 12. Through the interaction of the trapezoidal threads, rotating the handle 20 drives the screw 14 to rotate, which allows the fixed seat 13 to drive the support plate 12 to move freely within its stroke range, thereby driving the support plate 12, the mounting shaft 2, and the lifting ring 1 to move horizontally, thus achieving 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 gravity. On the other hand, the block 25 is slidably connected in the through hole of the fixed seat 13, which can prevent the weight of the support plate 12, the lifting ring 1, and the fixed seat 13 from bending the trapezoidal screw 14 when the horizontal lifting device is not used and is stored normally. This prevents the block 25 from jamming with the thread transmission of the trapezoidal screw 14 due to bending of the trapezoidal screw 14.

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

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

[0047] Structural characteristics of horizontal lifting devices for eccentric components with single cross-section lifting points of aero engines:

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

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

[0050] ③ The handle 20, trapezoidal screw 14, and fixed seat 13 constitute the 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 center of gravity of the hoisting device is adjusted by the mutual rotation of the trapezoidal screw 14 and the trapezoidal thread of the block 25 in the fixed seat 13. The fixed seat 13 is installed on the load-bearing plate 12 by internal hex bolts 3.

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

[0052] ⑤ A load-bearing wheel assembly 5 and a load-bearing shaft 7 are respectively installed on the load-bearing plate 12. The load-bearing wheel assembly 5 includes a snap ring 29, a stepped shaft 30, a first bearing 31, and a roller 32. The load-bearing shaft 7 includes a load-bearing shaft 26, a spacer sleeve 27 (the length of the spacer sleeve 27 is used to ensure the installation position of the second bearing 28 on the load-bearing shaft 26), and a second bearing 28. When adjusting the center of gravity, the load-bearing wheel assembly 5 can move along the I-beam 6. During the lifting process, the load-bearing wheel assembly 5 contacts the I-beam 6 to achieve load bearing. When the horizontal hoisting device is stored, the load-bearing shaft 7 contacts the upper part of the I-beam 6 through the second bearing 28, and moves along the I-beam 6 through the second bearing 28, which can ensure the free adjustment of the center of gravity at this time. The load-bearing wheel assembly 5 and the load-bearing shaft 7 are respectively installed on the load-bearing plate 12 by hexagonal bolts 3 and small hexagonal nuts 4.

[0053] The method for lifting the aforementioned eccentric component of a single-section lifting point of an aero-engine using a horizontal lifting device is as follows:

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

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

[0056] ③ By rotating the handle 20, the trapezoidal screw 14 can be rotated, which can enable the fixed seat 13 to move the load-bearing plate 12 freely within the stroke range, thereby driving the installation shaft 2 and the lifting ring 1 to move horizontally, thus realizing the free adjustment of the lifting center of gravity.

[0057] Contents not described in detail in this specification are prior art known to those skilled in the art. Although illustrative specific embodiments of the invention have been described above to facilitate understanding by those skilled in the art, it should be understood that the invention is not limited to the scope of the specific embodiments. Various modifications are readily apparent to those skilled in the art as long as they fall within the spirit and scope of the invention as defined and determined by the appended claims, and all inventions utilizing the concept of this invention are protected.

Claims

1. A horizontal hoisting device for eccentric components with a single cross-section lifting point in aero-engines, 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); The load-bearing plates (12) are arranged in parallel and spaced apart. The lifting ring (1) and the mounting shaft (2) are placed between the two load-bearing plates (12), and the two ends of the mounting shaft (2) are respectively fixed on the two load-bearing plates (12). I-beam (6), the I-beam (6) is placed between two load-bearing plates (12) and located below the mounting shaft (2), the web of the I-beam (6) is parallel to the two load-bearing plates (12), and the two ends of the I-beam (6) in the length direction are respectively connected to a side plate (9) on the load-bearing plate (12); The bearing wheel assembly (5) has its shaft fixed on the bearing plate (12), and its rollers (32) are tumblingly connected to the flange of the I-beam (6). The bearing-bearing shaft (7) is placed between two bearing plates (12) and located below the mounting shaft (2) and above the I-beam (6). The two ends of the bearing-bearing shaft (7) are respectively fixed on a bearing plate (12). A bearing bearing is rotatably mounted on the bearing-bearing shaft (7) and the bearing bearing is attached to the flange surface of the I-beam (6). The fixed seat (13) and the trapezoidal screw (14) are installed between two load-bearing plates (12) and fixedly connected to the two load-bearing plates (12). A block (25) is slidably connected inside the fixed 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). The trapezoidal screw (14) passes through the trapezoidal threaded through hole and its two ends are respectively installed on two side plates (9). The base plate (15) and the tie rods (18) are 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 hoisting device for eccentric components with a single cross-section lifting point of an aero-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 (14).

3. The horizontal hoisting device for eccentric components with a single cross-section lifting point of an aero-engine according to claim 1, characterized in that: It also includes mounting bases (17), two of which are detachably connected to the base plate (15). Each mounting base (17) has a U-shaped mounting groove, and one end of the tie rod (18) is rotatably connected to the U-shaped mounting groove. The openings 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. A horizontal hoisting device for eccentric components with a single cross-section lifting point in aero-engines 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 shaft of the load-bearing wheel assembly (5) is connected to the roller (32) via the first bearing (31).

5. A horizontal hoisting device for eccentric components with a single cross-section lifting point of an aero-engine according to claim 1, characterized in that: The fixed seat (13) is mainly composed of two fixed seat side plates (23) and two fixed seat end plates (24). The two fixed seat side plates (23) are fixed on two load-bearing plates (12) respectively. The two fixed seat end plates (24) are arranged in parallel and spaced apart. Each fixed seat end plate (24) is connected to a fixed seat side plate (23) at both ends. Both fixed seat end plates (24) have through holes. The block (25) is slidably connected in the through holes of the two fixed seat end plates (24).

6. A horizontal hoisting device for eccentric components with a single cross-section lifting point in an aero-engine, as described in claim 1, characterized in that: The lifting ring (1) has a waist-shaped hole.

7. A method for horizontally hoisting eccentric components with a single cross-section lifting point in aero-engines, characterized in that, include: Step 1: Select the horizontal lifting device as described in claim 1 and install the horizontal lifting device onto the hook of the gantry crane; Step 2: Connect the ends of the two tie rods (18) to the two lugs on the single-section eccentric component respectively; Step 3: The hoisting crane lifts the horizontal hoisting device and two tie rods (18) above the single-section eccentric lifting point component. By rotating the trapezoidal screw (14), the block (25), the fixed seat (13), the load-bearing plate (12) and the load-bearing wheel assembly (5) are driven to move relative to the I-beam (6) in sequence. This adjusts the center of gravity of the horizontal hoisting 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 eccentric lifting point component. Then, the single-section eccentric lifting point component is lifted.

8. A method for horizontally hoisting a single-section eccentric component of an aero-engine according to claim 7, characterized in that: In step two, the ends of the two tie rods (18) are connected to the two lugs on the single-section lifting point eccentric assembly via connecting pins (8) and small hexagonal nuts (4).

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