Aeroengine Rotor Disc Disassembly Tool

Abstract

The present invention discloses an aircraft engine rotor disc disassembly tool, comprising a front disassembly plate, a belt centering mechanism, the belt centering mechanism comprising two symmetrically arranged centering rods, the centering rods being fixedly connected to a belt, the two centering rods being used to respectively abut against a front rotor disc so that the symmetry centers of the two centering rods correspond to the disc center of the front rotor disc; a rear disassembly plate, the rear disassembly plate being arranged parallel to the front disassembly plate; and a force adding mechanism, the force adding mechanism being connected to the front disassembly plate and the disassembly plate, the force adding mechanism being capable of applying a load perpendicular to the rear disassembly plate between the front disassembly plate and the rear disassembly plate, the force adding mechanism being arranged at the symmetry centers of the two centering rods. The aircraft engine rotor disc disassembly tool of the present invention determines the center of the rotor disc by the belt centering mechanism, and the load of the force adding mechanism is transmitted to the front rotor disc and the rear rotor disc through the front disassembly plate and the rear disassembly plate, thereby achieving disassembly of the front rotor disc and the rear rotor disc.

Description

Technical Field

[0001] The invention relates to a tool for disassembling a rotor disc of an aero-engine. Background Art

[0002] like Figure 1 As shown, the aircraft engine compressor rotor is composed of a multi-stage rotor disk 1'. The diameters of the center holes of each stage rotor disk 1' are different, and the thicknesses of each stage rotor disk 1' are also quite different. During the assembly of the aircraft engine rotor, in order to ensure the concentric installation of each stage rotor disk 1', the two adjacent stages rotor disks 1' are matched through interference fit stops. And the two adjacent stages rotor disks 1' are connected by short bolts. After the aircraft engine is in operation, it is affected by thermal stress, and the connection tightness of the stops between adjacent rotor disks 1' increases. It is usually necessary to use special disassembly tooling to overcome the friction at the interference fit stops in order to achieve the disassembly of the aircraft engine rotor disk 1'. As shown Figure 2 As shown, the existing disassembly device is shown in patent application number CN201811014980.5, "A Disassembly Device for the First Stage of an Engine Fan Rotor." The existing disassembly device 2' for the first stage of an engine fan rotor uses the center web of the rotor disc 1' to be disassembled as the force application point, and uses a screw or a pressure cylinder to drive multiple claws to pull the rotor disc 1' to be disassembled out of the connecting stop of the adjacent disc. Since there are many stages of rotor discs 1' in an aircraft engine, the inner hole diameter and thickness of each stage of the rotor disc 1' are different. It is difficult for the existing claw-type disassembly device to meet the disassembly requirements of rotor discs 1' at different stages at the same time. In order to meet the disassembly requirements of rotor discs 1' with different hole diameters and thicknesses, disassembly devices of various specifications are often manufactured. Disassembly devices of various specifications are similar in shape but different in specifications, which can easily lead to the misuse of disassembly devices of different specifications, resulting in the inability to disassemble the rotor disc 1'. Due to its lack of versatility, conventional disassembly devices with claw structures have high manufacturing and management costs and are inconvenient to operate. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to overcome the defect of complicated operation for disassembling an aircraft engine rotor disk in the prior art and to provide an aircraft engine rotor disk disassembly tool.

[0004] The present invention solves the above technical problems through the following technical solutions:

[0005] A tool for disassembling an aircraft engine rotor disk, comprising:

[0006] A front decomposition plate, the front decomposition plate having a first surface, the first surface being used to abut against the front-stage rotor disk;

[0007] a belt centering mechanism, the belt centering mechanism being fixedly mounted on the first surface of the front decomposition plate, the belt centering mechanism comprising two symmetrically arranged centering rods, the centering rods being fixedly connected to the belt, the two centering rods being configured to respectively abut against the preceding rotor disk so that the centers of symmetry of the two centering rods correspond to the center of the preceding rotor disk;

[0008] a rear decomposition plate, the rear decomposition plate being arranged parallel to the front decomposition plate;

[0009] A force-adding mechanism is connected to the front decomposition plate and the rear decomposition plate, and can apply a load perpendicular to the rear decomposition plate between the front decomposition plate and the rear decomposition plate. The force-adding mechanism is arranged at the symmetrical center of the two centering rods.

[0010] In this solution, the center of the rotor disk is determined by a belt centering mechanism, and the load of the force-adding mechanism is transmitted to the front-stage rotor disk and the rear-stage rotor disk through the front decomposition plate and the rear decomposition plate, thereby realizing the decomposition of the front-stage rotor disk and the rear-stage rotor disk. The aircraft engine rotor disk decomposition tool has a simple structure, is easy to operate, and can decompose stably and reliably. The centering mechanism adopts a belt drive, which has the advantages of smooth operation, low noise, and low vibration. It also has a simple structure and is easy to adjust. The belt drive does not have high requirements on the manufacturing and installation accuracy of the pulley as the gear meshing drive, thereby reducing the manufacturing cost of the centering mechanism.

[0011] Preferably, the belt centering mechanism further comprises two pulleys, and the midpoint of the line connecting the centers of the two pulleys is located at the geometric center of the first surface of the front decomposition plate.

[0012] In this solution, the position of the belt is determined by setting two pulleys, and there is no need for multiple pulleys to determine the position of the belt, which simplifies the structure of the belt centering mechanism and reduces the overall volume of the aircraft engine rotor disk disassembly tool; the midpoint of the line connecting the centers of the two pulleys is located at the geometric center of the first surface. With this arrangement, the two centering rods only need to be relatively installed on the belt to achieve centering of the rotor disk, which simplifies the installation steps of the centering rod and improves the installation efficiency of the centering rod.

[0013] Preferably, the connecting line of the two pulley centers is arranged parallel to the length direction of the front decomposition plate.

[0014] In this solution, the line connecting the pulley centers is set parallel to the length direction of the front decomposition plate, so that the belt is set to move along the length direction of the front decomposition plate. During the movement of the belt, it is parallel to the axial direction of the front decomposition plate, preventing the load generated during the movement of the belt from causing the front decomposition plate to have a flipping torque around the rotation axis of the front decomposition plate, thereby improving the stability of the connection between the belt centering mechanism and the front decomposition plate.

[0015] Preferably, the belt centering mechanism further includes two positioning seats, and the centering rod is connected to the belt via the positioning seats.

[0016] In this solution, the centering rod is detachably connected to the belt through a positioning seat. The length of the centering rod can be selected according to the center of the rotor disk to be disassembled. When the center hole diameter of the rotor disk to be disassembled is large, a centering rod with a longer length is selected; when the center hole diameter of the rotor disk to be disassembled is small, a centering rod with a shorter length is selected. The detachable connection between the centering rod and the belt is realized, the interchangeability is high, and the versatility of the belt centering mechanism is improved.

[0017] Preferably, the belt centering mechanism further includes a driving rod, one end of which is movably connected to the front decomposition plate, and the other end of which is fixedly connected to one of the positioning seats, and the driving rod is used to drive the positioning seat to move.

[0018] In this solution, a driving rod is set up to connect the front decomposition plate and the positioning seat. The driving rod drives the belt to rotate through the positioning seat to move the centering rod, avoiding the situation where the axis of the two centering rods deviates due to direct manual manipulation of the centering rod, thereby ensuring accurate centering of the centering rod.

[0019] Preferably, a through hole is provided on the positioning seat, and the driving rod is passed through the through hole on the positioning seat. The belt centering mechanism further includes a shift ring, and the shift ring fixedly connects the driving rod and the positioning seat.

[0020] In this solution, the drive rod and the positioning seat are fixedly connected by a gear ring. When the drive rod moves relative to the mounting seat, it can drive the fixing seat to move. The fixing group drives the centering rods on both sides to move outward or inward at the same time through the belt.

[0021] Preferably, the aircraft engine rotor disc disassembly tool further comprises a mounting seat, which is fixedly mounted on the first surface of the front disassembly plate. A threaded hole is provided on the mounting seat, and the drive rod is connected to the mounting seat via threads.

[0022] In this solution, a threaded hole is provided on the mounting seat, and the driving rod is connected to the mounting seat through a thread. The position of the positioning seat is accurately adjusted by rotating the driving rod, thereby accurately adjusting the position of the centering rod to avoid excessive centering error caused by the centering rod and the inner wall of the rotor disk being too tight.

[0023] Preferably, a force-applying through hole is opened at the center of the rear decomposition plate, and the force-applying mechanism passes through the force-applying through hole of the rear decomposition plate and abuts against the front decomposition plate.

[0024] In this solution, by setting a force-adding through hole and connecting the force-adding mechanism, the force-adding mechanism can pass through the rear decomposition plate and transfer the load to the front decomposition plate. The force-adding through hole structure is simple and does not require additional load transfer, which simplifies the structure of the force-adding mechanism.

[0025] Preferably, a force-applying blind hole is opened on the front decomposition plate, and the force-applying mechanism abuts against the force-applying blind hole of the front decomposition plate.

[0026] In this solution, the load of the force-adding mechanism is transferred to the front decomposition plate through the movable rod via the force-adding blind hole. By setting the force-adding blind hole and the movable rod to match each other, the force-adding rod and the front decomposition plate do not require an additional connecting structure, and the connection between the two is simple, thereby improving the reliability of the connection between the movable rod and the front decomposition plate, and avoiding the situation where the load cannot be accurately transferred to the front decomposition plate due to the slippage of the movable rod and the front decomposition plate during the load application process.

[0027] Preferably, the force-adding mechanism includes a fixed rod and a movable rod, the movable rod can move relative to the fixed rod, the fixed rod is passed through the force-adding through hole, the diameter of the movable rod matches the diameter of the force-adding blind hole, and the movable rod abuts against the force-adding blind hole.

[0028] In this solution, by setting a fixed rod and a movable rod that can move relative to each other, the load drives the front decomposition plate to move through the movable rod. During the decomposition process, the fixed rod is fixedly connected to the rear decomposition plate, and the movable rod rests on the front decomposition plate. The structure is simple and the load application is reliable.

[0029] Preferably, the energizing mechanism includes a hydraulic energizing rod.

[0030] In this solution, a hydraulic boosting rod is selected as the boosting mechanism. The hydraulic boosting rod has the advantages of large load output and smooth output. There is no need for the operator to manually apply the load, which improves the usability of the aircraft engine rotor disk disassembly tool and reduces the labor intensity of the operator.

[0031] The positive progress effect of the present invention is:

[0032] The aero-engine rotor disc disassembly tool of the present invention determines the center of the rotor disc by a belt centering mechanism, and the load of the force-adding mechanism is transmitted to the front-stage rotor disc and the rear-stage rotor disc through the front disassembly plate and the rear disassembly plate, thereby realizing the disassembly of the front-stage rotor disc and the rear-stage rotor disc. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a schematic diagram of the structure of a multi-stage rotor disk of an aircraft engine.

[0034] Figure 2 This is a schematic diagram of the structure of an existing engine fan rotor first-stage disc decomposition device.

[0035] Figure 3 The figure is a schematic diagram of the aero-engine rotor disk disassembly tool of the present invention disassembling a rotor disk.

[0036] Figure 4 The figure is a schematic diagram of the parts disassembly of the aircraft engine rotor disk disassembly tool of the present invention.

[0037] Figure 5 This is a structural schematic diagram from a first perspective of the front disassembly plate and belt centering mechanism of the aircraft engine rotor disk disassembly tool of the present invention.

[0038] Figure 6 This is a structural schematic diagram from a second perspective of the front disassembly plate and belt centering mechanism of the aircraft engine rotor disk disassembly tool of the present invention.

[0039] Figure 7 This is a structural schematic diagram from a third perspective of the front disassembly plate and belt centering mechanism of the aircraft engine rotor disk disassembly tool of the present invention.

[0040] Figure 8 The figure is a cross-sectional schematic diagram of the belt centering mechanism of the aircraft engine rotor disk disassembly tool of the present invention.

[0041] Figure 9 This is a partially enlarged schematic diagram of the belt centering mechanism of the aircraft engine rotor disk disassembly tool of the present invention.

[0042] Description of reference numerals:

[0043] In the prior art:

[0044] Rotor disk 1'

[0045] Engine fan rotor first stage disc disassembly device 2'

[0046] In the present invention:

[0047] Aircraft engine rotor disc disassembly tool 100

[0048] Front decomposition plate 1

[0049] First side 11

[0050] Afterburner blind hole 12

[0051] Belt centering mechanism 2

[0052] Belt 21

[0053] Centering rod 22

[0054] Pulley 23

[0055] Positioning seat 24

[0056] Drive rod 25

[0057] Shift ring 26

[0058] Rear decomposition plate 3

[0059] Force through hole 31

[0060] Afterburner 4

[0061] Fixed rod 41

[0062] Active rod 42

[0063] Mounting Block 5

[0064] Front stage rotor disc 200

[0065] Rear stage rotor disc 300 DETAILED DESCRIPTION

[0066] The present invention is further described below by way of examples, but the present invention is not limited to the scope of the examples.

[0067] like Figure 4-Figure 9 As shown, the present invention provides an aircraft engine rotor disk disassembly tool 100, comprising a front disassembly plate 1, a belt centering mechanism 2, a rear disassembly plate 3 and a force adding mechanism 4.

[0068] like Figure 3 As shown, the front disassembly plate 1 has a first surface 11, which is used to abut against the front-stage rotor disk 200. When using the aircraft engine rotor disk disassembly tool 100 of the present invention to disassemble an aircraft engine rotor, the rotor disk located in the upper portion of the figure is referred to as the rear-stage rotor disk 300, and the rotor disk located in the lower portion of the figure is referred to as the front-stage rotor disk 200. To remove the rear-stage rotor disk 300 from the front-stage rotor disk 200 along the axial direction of the turbine case, the first surface 11 of the front disassembly plate 1 abuts against the surface of the front-stage rotor disk 200 that is closest to the rear-stage rotor disk 300.

[0069] The rear decomposition plate 3 is arranged parallel to the front decomposition plate 1 , and the rear decomposition plate 3 abuts against a surface of the rear-stage rotor disk 300 close to the front-stage rotor disk 200 .

[0070] The belt centering mechanism 2 is fixedly mounted on the first surface 11 of the front decomposition plate 1. It is used to abut against the wall of the center hole of the front rotor disk 200 and locate the center of the front rotor disk 200. The belt centering mechanism 2 includes two symmetrically arranged centering rods 22. The centering rods 22 are fixedly connected to the belt 21. The two centering rods 22 are used to abut against the wall of the center hole of the front rotor disk 200, so that the centers of symmetry of the two centering rods 22 correspond to the center of the front rotor disk 200. During the movement of the belt 21, the two centering rods 22 are driven by the belt 21 to move simultaneously toward each other. During use, the two centering rods 22 are first driven toward the center of the front decomposition plate 1, so that the distance between the centering heads of the two centering rods 22 is less than the inner diameter of the center hole of the front rotor disk 200. Then, the first surface 11 is abutted against the side of the front rotor disk 200 that is closest to the rear rotor disk 300. The two centering rods 22 are driven outward until their centering heads rest against the center holes of the preceding rotor disk 200 at two diametrically opposed points. At this point, the centers of symmetry of the two centering rods 22 coincide with the center of the preceding rotor disk 200. A belt 21 is used to drive the two centering rods 22. The belt drive offers the advantages of smooth operation, low noise, and low vibration. Furthermore, the belt drive has a simple structure and is easy to adjust. Belt drives do not require the same high manufacturing and installation precision of the pulleys 23 as gear transmissions, thus reducing the manufacturing cost of the centering mechanism.

[0071] The force mechanism 4 is connected to the front decomposition plate 1 and the rear decomposition plate 3. It can apply a load perpendicular to the rear decomposition plate 3 between the front decomposition plate 1 and the rear decomposition plate 3. By driving the rear decomposition plate 3 away from the front decomposition plate 1, the force mechanism 4 pushes the rear-stage rotor disk 300 away from the front-stage rotor disk 200, thereby removing the rear-stage rotor disk 300 from the connection stop in a direction away from the front-stage rotor disk 200. The force mechanism 4 is arranged at the symmetrical center of the two centering rods 22, so that the load applied by the force mechanism 4 to the front decomposition plate 1 and the rear decomposition plate 3 is also located at the symmetrical center of the centering rods 22. After the centering rod 22 determines the center position of the front-stage rotor disk 200, the symmetry center of the centering rod 22 coincides with the center of the front-stage rotor disk 200, and the force-adding mechanism 4 is arranged at the symmetry center of the two centering rods 22, so that the load applied by the force-adding mechanism 4 to the front-stage rotor disk 200 and the rear-stage rotor disk 300 through the front decomposition plate 1 and the rear decomposition plate 3 is also along the axial direction of the front-stage rotor disk 200, avoiding the load from being biased to one side of the rotor disk, causing the rear-stage rotor disk 300 and the connection stop to be stuck.

[0072] like Figure 8As shown, the belt centering mechanism 2 also includes two pulleys 23, which are mounted on the front decomposition plate 1 via bolts and nuts. The bolts extend through the front decomposition plate 1, and the pulleys 23 are sleeved onto the bolts. The nuts are tightened onto the bolts, thereby locking the pulleys 23, the bolts, and the front decomposition plate 1. The bolts are provided with a first threaded section and a second threaded section, wherein the outer diameter of the first threaded section is larger than that of the second threaded section. The first threaded section is threadedly fixed to the front decomposition plate 1, and the pulleys 23 are sleeved onto the second threaded section. A step between the first and second threaded sections restricts the axial movement of the pulleys 23 along the bolts, and the nuts are tightened onto the second threaded section. The midpoint of the line connecting the centers of the two pulleys 23 is located at the geometric center of the first surface 11 of the front decomposition plate 1. The centering rods 22 are fixedly mounted to the belt 21 in a centrosymmetrical manner, with the centers of symmetry of the two centering rods 22 coinciding with the midpoint of the line connecting the centers of the pulleys 23. The midpoint of the line connecting the centers of pulleys 23 coincides with the geometric center of first surface 11 of front decomposition plate 1, thereby aligning the center of symmetry of centering rod 22 with the geometric center of first surface 11. This arrangement simplifies the placement of force mechanism 4 at the geometric center of front decomposition plate 1, eliminating the need to compensate for eccentricity between the rotor disk center and the load of force mechanism 4. This simplifies the location of force mechanism 4 and makes load application simple and reliable.

[0073] The line connecting the wheel centers of the two pulleys 23 is set parallel to the length direction of the front decomposition plate 1. The front decomposition plate 1 is a long strip plate. The two pulleys 23 are set along the long side of the front decomposition plate 1, so as to lengthen the distance between the two pulleys 23 as much as possible, improve the parallelism of the line connecting the wheel centers of the pulleys 23 and the front decomposition plate 1, and reduce the centering error of the centering rod 22 caused by the non-parallelism of the two pulleys 23 and the front decomposition plate 1.

[0074] like Figure 9 As shown, the belt centering mechanism 2 also includes two positioning seats 24, and the two positioning seats 24 are "L"-shaped. One side of the positioning seat 24 is fixedly installed on the belt 21 by a fastener, and the centering rod 22 is connected to the belt 21 through the positioning seat 24. Corresponding through holes are respectively provided on the centering rod 22, the positioning seat 24 and the belt 21, and the fasteners are respectively passed through the centering rod 22, the positioning seat 24 and the belt 21 to fix the three together. The positioning seat 24 is installed on one side of the belt 21 and is also provided with two clamping parts. The distance between the two clamping parts is the same as the width of the belt 21, and the positioning seat 24 is clamped to the belt 21 through the two clamping parts. In addition, the centering rod 22 is clamped between the two clamping parts, and the positioning seat 24 ensures that the centering rod 22 and the belt 21 are installed in parallel through the clamping parts on both sides, thereby reducing the centering error caused by the centering rod 22 and the belt 21 being out of alignment.

[0075] like Figure 6As shown, the belt centering mechanism 2 also includes a drive rod 25, one end of which is movably connected to the front decomposition plate 1. The drive rod 25 is connected to the front decomposition plate 1 via a threaded connection. The drive rod 25 is used to drive the positioning seat 24 to move. During use, by rotating the drive rod 25 around the axis of the drive rod 25, the drive rod 25 moves relative to the front decomposition plate 1 along its axis. The other end of the drive rod 25 is fixedly connected to one of the positioning seats 24. The drive rod 25 and the positioning seat 24 are fixedly connected perpendicular to one side of the belt 21. When the drive rod 25 moves relative to the front decomposition plate 1, the drive rod 25 drives the belt 21 to move around the pulley 23 through the positioning seat 24. The belt 21 simultaneously drives the two centering rods 22 to move toward or away from the symmetrical center of the centering rods 22.

[0076] like Figure 7 As shown, the positioning seat 24 has a through hole, and the drive rod 25 is inserted through the through hole of the positioning seat 24. The belt centering mechanism 2 also includes a retaining ring 26, which securely connects the drive rod 25 and the positioning seat 24. The retaining ring 26 is locked to the end of the drive rod 25 that is away from the mounting seat 5. The retaining ring 26 securely connects the mounting seat 5 and the drive rod 25. When the drive rod 25 is rotated to move relative to the mounting seat 5, the drive rod 25 drives the belt 21 through the positioning seat 24.

[0077] The aircraft engine rotor disk disassembly tool 100 also includes a mounting base 5, which is fixedly mounted on the first surface 11 of the front disassembly plate 1 and secured to the front disassembly plate 1 via fasteners. A threaded hole is defined in the mounting base 5, and a drive rod 25 is threadedly connected to the mounting base 5. By rotating the drive rod 25 about its axis, the drive rod 25 moves relative to the mounting base 5, thereby driving the belt 21.

[0078] like Figure 4 As shown, a force-adding through hole 31 is provided at the center of the rear decomposition plate 3. The force-adding mechanism 4 passes through the force-adding through hole 31 of the rear decomposition plate 3 and rests against the front decomposition plate 1. In this embodiment, an internal thread is processed on the hole wall of the force-adding through hole 31 on the rear decomposition plate 3, and an external thread is provided on the force-adding mechanism 4. The force-adding mechanism 4 and the rear decomposition plate 3 are connected by screwing. When in use, the connection between the force-adding mechanism 4 and the rear decomposition plate 3 is achieved by tightening the force-adding mechanism 4 and the rear decomposition plate 3. The force-adding mechanism 4 that outputs different loads can be replaced according to the size of the rotor disk to be disassembled. The threaded connection has a simple structure, is easy to disassemble and replace, and is reliable in connection. The load of the force-adding mechanism 4 is transmitted to the rear decomposition plate 3 through the thread, and a large load can be reliably transmitted through the thread. In other embodiments, the force-adding mechanism 4 can also be fixedly connected to the rear decomposition plate 3 by an interference fit.

[0079] like Figure 5 and Figure 8As shown, a force blind hole 12 is provided on the front decomposition plate 1. The force mechanism 4 rests against the force blind hole 12 of the front decomposition plate 1. The force blind hole 12 is provided on the surface of the front decomposition plate 1 opposite to the first surface 11, and the force blind hole 12 does not completely penetrate the front decomposition plate 1. The diameter of the force blind hole 12 is the same as the diameter of the force mechanism 4 and the end resting against the front decomposition plate 1, so that the force mechanism 4 extends into the force blind hole 12 on the front decomposition plate. The force mechanism 4 transfers the load to the front decomposition plate 1 through the force blind hole 12. By being stuck in the force blind hole 12, the force mechanism 4 is prevented from being biased to one side of the front decomposition plate 1 due to load deviation, thereby improving the reliability of load transfer. In addition, the provision of the force blind hole 12 facilitates the separation of the force mechanism 4 from the front decomposition plate 1, thereby improving the usability of the aircraft engine rotor disc disassembly tool 100.

[0080] like Figure 3 As shown, the force mechanism 4 includes a fixed rod 41 and a movable rod 42, and the movable rod 42 can move relative to the fixed rod 41. The fixed rod 41 is inserted into the force through hole 31. An external thread is provided on the outer side of the fixed rod 41, and an internal thread is provided in the force through hole 31. The fixed rod 41 is tightened to the force through hole 31 through threads. The threaded connection prevents movement between the fixed rod 41 and the rear decomposition plate 3 along the axial direction of the fixed rod 41 during use. The diameter of the movable rod 42 matches the diameter of the force blind hole 12, and the movable rod 42 abuts against the force blind hole 12. The movable rod 42 abuts against the force blind hole 12, and the movable rod 42 transfers the load to the front decomposition plate 1 through the force blind hole 12, thereby realizing the disassembly and separation of the front-stage rotor disk 200 and the rear-stage rotor disk 300.

[0081] The boosting mechanism 4 includes a hydraulic boosting rod. The hydraulic boosting rod transfers the load to the front decomposition plate 1 through the movable rod 42, and the fixed rod 41 and the boosting through hole 31 on the rear decomposition plate 3 are connected by threads. The relative positions of the fixed rod 41 and the rear decomposition plate 3 remain unchanged, and the front decomposition plate 1 is moved away from the rear decomposition plate 3 by pushing the front decomposition plate 1. The front decomposition plate 1 abuts against the front-stage rotor disk 200, and the rear decomposition plate 3 abuts against the rear-stage rotor disk 300. The load of the hydraulic boosting rod is respectively transferred to the front-stage rotor disk 200 and the rear-stage rotor disk 300 through the front decomposition plate 1 and the rear decomposition plate 3, thereby realizing the disassembly and removal of the front-stage rotor disk 200 and the rear-stage rotor disk 300. In this embodiment, the boosting mechanism 4 includes a hydraulic boosting rod. In other embodiments, the boosting mechanism 4 may also include a pneumatic boosting rod. The pneumatic boosting rod does not require liquid as a load transfer medium and has the advantages of being clean and easy to operate. In other embodiments, the force-applying mechanism 4 may also be a spiral mechanism, in which the fixed rod 41 and the movable rod 42 are connected by threads. By rotating the movable rod 42 relative to the fixed rod 41, the spiral mechanism has the advantages of simple structure, high reliability, and no need for an additional power source.

[0082] like Figure 3 and Figure 4 As shown, the disassembly of the front-stage rotor disk 200 and the rear-stage rotor disk 300 is completed according to the following steps:

[0083] S1, such as Figure 4 As shown, the assembly of the aircraft engine rotor disc disassembly tool 100 is completed;

[0084] S2, such as Figure 3 As shown, the front decomposition plate 1 with the belt centering mechanism 2 is placed obliquely, passed through the center hole of the rear stage rotor disk 300, and then placed horizontally on the rear end surface of the center of the front stage rotor disk 200;

[0085] S3. Twist the drive rod 25 to drive the centering rod 22 to move radially outward. Under the action of the belt 21, the centering rod 22 installed on the other side synchronously follows the centering rod 22 driven by the drive rod 25 and moves radially outward, so that the positioning heads on the two centering rods 22 contact the inner wall of the center hole of the preceding rotor disk 200 at the same time.

[0086] S4. Tilt the rear decomposition plate 3 so that it rests against the surface of the rear-stage rotor disk 300 close to the front-stage rotor disk 200;

[0087] S5. Install the force adding mechanism 4 into the force adding through hole 31 of the rear decomposition plate 3;

[0088] S6. Adjust the position of the force-adding mechanism 4 with the rear decomposition plate 3 so that the head of the movable rod 42 is located in the force-adding blind hole 12 of the front decomposition plate 1;

[0089] S7, applying force to the force-applying mechanism 4, driving the rear decomposition plate 3 to press against the rear end surface of the center hole of the rear stage disk;

[0090] S8. Continue to apply force until the rear-stage rotor disk 300 is ejected.

[0091] Although specific embodiments of the present invention have been described above, those skilled in the art will appreciate that these are merely illustrative and that the scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, and such changes and modifications are intended to fall within the scope of the present invention.

Claims

1. A tool for disassembling an aircraft engine rotor disc, characterized in that: It includes: A front decomposition plate, the front decomposition plate having a first surface, the first surface being used to abut against the front-stage rotor disk; a belt centering mechanism, the belt centering mechanism being fixedly mounted on the first surface of the front decomposition plate, the belt centering mechanism comprising two symmetrically arranged centering rods, the centering rods being fixedly connected to the belt, the two centering rods being configured to respectively abut against the preceding rotor disk so that the centers of symmetry of the two centering rods correspond to the center of the preceding rotor disk; a rear decomposition plate, the rear decomposition plate being arranged parallel to the front decomposition plate; A force-adding mechanism is connected to the front decomposition plate and the rear decomposition plate, and can apply a load perpendicular to the rear decomposition plate between the front decomposition plate and the rear decomposition plate. The force-adding mechanism is arranged at the symmetrical center of the two centering rods.

2. The aircraft engine rotor disc disassembly tool according to claim 1, characterized in that: The belt centering mechanism further includes two pulleys, and the midpoint of the line connecting the centers of the two pulleys is located at the geometric center of the first surface of the front decomposition plate.

3. The aircraft engine rotor disc disassembly tool according to claim 2, characterized in that: The connecting line of the two pulley centers is arranged parallel to the length direction of the front decomposition plate.

4. The aircraft engine rotor disc disassembly tool according to claim 1, wherein: The belt centering mechanism further includes two positioning seats, and the centering rod is connected to the belt via the positioning seats.

5. The aircraft engine rotor disc disassembly tool according to claim 4, characterized in that: The belt centering mechanism also includes a driving rod, one end of which is movably connected to the front decomposition plate, and the other end of which is fixedly connected to one of the positioning seats, and the driving rod is used to drive the positioning seat to move.

6. The aircraft engine rotor disc disassembly tool according to claim 5, characterized in that: A through hole is provided on the positioning seat, and the driving rod is passed through the through hole on the positioning seat. The belt centering mechanism further includes a shift ring, and the shift ring is fixedly connected to the driving rod and the positioning seat.

7. The aircraft engine rotor disc disassembly tool according to claim 6, characterized in that: The aircraft engine rotor disc disassembly tool further comprises a mounting seat, which is fixedly mounted on the first surface of the front disassembly plate. A threaded hole is provided on the mounting seat, and the drive rod is connected to the mounting seat via threads.

8. The aircraft engine rotor disc disassembly tool according to claim 1, wherein: A force-applying through hole is provided at the center of the rear decomposition plate, and the force-applying mechanism passes through the force-applying through hole of the rear decomposition plate and abuts against the front decomposition plate.

9. The aircraft engine rotor disc disassembly tool according to claim 8, characterized in that: A force-adding blind hole is provided on the front decomposition plate, and the force-adding mechanism abuts against the force-adding blind hole of the front decomposition plate.

10. The aircraft engine rotor disc disassembly tool according to claim 9, characterized in that: The force-adding mechanism includes a fixed rod and a movable rod. The movable rod can move relative to the fixed rod. The fixed rod is inserted into the force-adding through hole. The diameter of the movable rod matches the diameter of the force-adding blind hole. The movable rod abuts against the force-adding blind hole.

11. The aircraft engine rotor disc disassembly tool according to any one of claims 1 to 10, characterized in that: The energizing mechanism includes a hydraulic energizing rod.

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