Aero-engine Rotor Disc Disassembly Tool

Abstract

The present invention discloses a disassembly tool for an aeroengine rotor disk, which comprises a front disassembly plate, a centering mechanism, a rear disassembly plate and a boosting mechanism. The front disassembly plate is used to abut against the front-stage rotor disk; the centering mechanism includes two centering parts and a driving device, and the driving device is used to drive the two centering parts to approach or move away from each other along the direction of the connection line of the two centering parts; the rear disassembly plate is used to abut against the rear-stage rotor disk; the boosting mechanism is arranged at the center of the connection line of the two centering parts and can apply a load perpendicular to the rear disassembly plate to the front disassembly plate and the rear disassembly plate. The disassembly tool for the aeroengine rotor disk in the present invention has a simple structure, is convenient to operate, and the disassembly is stable and reliable. By realizing the adjustable distance between the two centering parts, the two centering parts can abut against the rotor disks with different diameters of the disk center holes, so as to center the rotor disks with different diameters of the disk center holes, determine the force application centers of the rotor disks with different diameters of the disk center holes, and ensure uniform stress during the disassembly process of the front-stage rotor disk and the rear-stage rotor disk.

Description

Technical Field

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

[0002] As Figure 1 shown, the compressor rotor of an aero-engine is composed of multiple rotor disks 1'. The diameters of the central holes of the rotor disks 1' at each level are different, and the thicknesses of the rotor disks 1' at each level also vary greatly. During the assembly of the aero-engine rotor, to ensure the concentric installation of the rotor disks 1' at each level, the adjacent two-stage rotor disks 1' are fitted by interference rabbets. And the adjacent two-stage rotor disks 1' are connected by short bolts. After the aero-engine operates, affected by thermal stress, the tightness of the rabbet connection between the adjacent rotor disks 1' increases. Usually, a special disassembling tooling is needed to overcome the frictional force at the interference rabbet to disassemble the aero-engine rotor disk 1'. As Figure 2 shown, the existing disassembling device is as shown in the patent application No. CN201811014980.5, "A Disassembling Device for the First-stage Disk of an Engine Fan Rotor". The existing disassembling device 2' for the first-stage disk of an engine fan rotor takes the web plate of the rotor disk 1' to be disassembled as the force application point, and drives multiple pull claws through a screw or a pressure cylinder to pull the rotor disk 1' to be disassembled out of the connection rabbet of the adjacent disk. Since there are many stages of the aero-engine rotor disk 1', and the inner hole diameters and thicknesses of the rotor disks 1' at each level are different, it is difficult for the existing pull claw type disassembling device to meet the disassembly of the rotor disks 1' at different levels at the same time. For the disassembly requirements of the rotor disks 1' with different hole diameters and thicknesses, it is often necessary to manufacture multiple specifications of disassembling devices. The multiple specifications of disassembling devices are similar in shape but different in specifications, which is easy to cause misapplication of different specifications of disassembling devices, resulting in the inability to disassemble the rotor disk 1'. Due to the lack of universality, the manufacturing cost and management cost of the conventional pull claw structure disassembling device are relatively high, and the operation is inconvenient. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to overcome the defect of complex operation in the prior art for disassembling the aero-engine rotor disk, and provide a disassembling tool for the aero-engine rotor disk.

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

[0005] A disassembling tool for an aero-engine rotor disk, the disassembling tool for the aero-engine rotor disk includes:

[0006] A front disassembling plate, the front disassembling plate has a first surface, and the first surface is used for abutting against the previous-stage rotor disk;

[0007] Centering mechanism, the centering mechanism is arranged on the first surface of the front decomposition plate, the centering mechanism includes two centering parts and a driving device, the driving device includes a moving seat and two connecting rods, one end of the two connecting rods is hinged to the moving seat, and the other ends of the two connecting rods are respectively hinged to the two centering parts, the moving seat can move on the perpendicular bisector of the line connecting the two centering parts, and the driving device is used to drive the two centering parts to approach or move away from each other along the direction of the line connecting the two centering parts;

[0008] Rear decomposition plate, the rear decomposition plate is arranged parallel to the front decomposition plate, and the rear decomposition plate is used to abut against the rear-stage rotor disc;

[0009] Force adding mechanism, the force adding mechanism is connected between the front decomposition plate and the rear decomposition plate, the force adding mechanism can apply a load perpendicular to the rear decomposition plate to the front decomposition plate and the rear decomposition plate, and the force adding mechanism is arranged at the center of the line connecting the two centering parts.

[0010] In this solution, the front decomposition plate and the rear decomposition plate are respectively in contact with the front-stage rotor disc and the rear-stage rotor disc, and are used to apply the load applied by the force adding mechanism to the front decomposition plate and the rear decomposition plate to the front-stage rotor disc and the rear-stage rotor disc, so that the front-stage rotor disc and the rear-stage rotor disc can be separated, and the decomposition method is stable and reliable. In this solution, the movement of the moving seat is used to drive the centering parts connected to the moving seat to move, so as to realize the adjustable distance between the two centering parts, so that the two centering parts can abut against the rotor discs with different diameters of the disc center holes, realize centering for the rotor discs with different diameters of the disc center holes, and determine the force application centers of the rotor discs with different diameters of the disc center holes. The force adding mechanism applies a load perpendicular to the rear decomposition plate to the front decomposition plate and the rear decomposition plate at the force application center, ensuring uniform force during the decomposition of the front-stage rotor disc and the rear-stage rotor disc, and preventing the inability to decompose due to pulling deviation. The aero-engine rotor disc decomposition tool in this solution has a simple structure, is easy to operate, and the decomposition is stable and reliable.

[0011] Preferably, the centering mechanism further includes a guiding part, the guiding part is arranged on the front decomposition plate, the guiding part and the centering part form a moving pair, and the degree-of-freedom direction of the moving pair is consistent with the direction of the line connecting the two centering parts.

[0012] In this solution, the guiding part is used to guide the moving direction of the centering part on the one hand, and limit the degrees of freedom of the centering part in other directions on the other hand, prevent the position deviation of the centering part during the movement, improve the moving accuracy of the centering part and the reliability of determining the center of the rotor disc through the centering part.

[0013] Preferably, the guiding part includes a strip-shaped hole, and the strip-shaped hole extends along the direction of the line connecting the two centering parts.

[0014] In this solution, a structure of a guiding part is provided, and the centering part can only move in the extending direction of the strip-shaped hole.

[0015] Preferably, the strip-shaped hole is a through hole, the front decomposition plate has a second surface opposite to the first surface, the decomposition tool further includes a connecting piece and a limiting piece, one end of the connecting piece is connected to the centering part, the other end of the connecting piece passes through the strip-shaped hole and extends to the second surface, the limiting piece is arranged on the second surface and engages with the connecting piece, and the width of the limiting piece in the width direction of the strip-shaped hole is greater than the aperture of the strip-shaped hole.

[0016] In this solution, the limiting piece cooperates with the strip-shaped hole. By restricting the movement of the connecting piece in the depth direction of the strip-shaped hole, the movement of the centering part connected to the connecting piece in the depth direction of the strip-shaped hole is restricted, further restricting the position deviation of the centering part during movement, improving the movement accuracy of the centering part and the reliability of determining the center of the rotor disc through the centering part.

[0017] Preferably, the driving device further includes a fixing pin, and coaxial connecting holes are provided on both the moving seat and the two connecting rods. The fixing pin passes through the connecting holes on the moving seat and the two connecting rods.

[0018] In this solution, a connection method between the moving seat and the connecting rod is provided. The above connection method has a simple structure, low production and assembly costs, and by connecting the moving seat and the two connecting rods with one fixing pin at the same time, on the one hand, the number of components in the driving device can be reduced and the assembly steps can be simplified, and on the other hand, the position of the center of the connection line of the two centering parts can be further ensured not to change, improving the reliability of determining the center of the rotor disc through the centering part.

[0019] Preferably, the driving device further includes a driving rod and a fixing seat. The fixing seat is fixed on the front decomposition plate. One end of the driving rod is connected to the moving seat, the other end of the driving rod is connected to the fixing seat, the axial direction of the driving rod is parallel to the moving direction of the moving seat, and the driving rod can move relative to the fixing seat along the axial direction of the driving rod.

[0020] In this solution, the fixing seat plays a role in supporting the driving rod and cooperating with the driving rod to rotate. The moving seat is driven by rotating the driving rod, and the operation is simple.

[0021] Preferably, the driving rod has an external thread, and a threaded hole for the driving rod to pass through is provided on the fixing seat, and the driving rod is screwed with the threaded hole.

[0022] In this solution, a connection method between the driving rod and the fixed seat is provided. On the one hand, the above structure can realize the rotation of the driving rod relative to the fixed seat to achieve the movement of the driving rod in the axial direction of its axis. On the other hand, when the driving rod does not rotate, the above structure can also ensure that the driving rod remains stationary relative to the fixed seat, and the screw drive has a self-locking function, which is stable and reliable.

[0023] Preferably, a force application through-hole is provided on the rear decomposition plate, and the force application mechanism passes through the force application through-hole of the rear decomposition plate and abuts against the front decomposition plate.

[0024] In this solution, by providing a connection between the force application through-hole and the force application mechanism, the force application mechanism can pass through the rear decomposition plate and transfer the load to the front decomposition plate. The structure of providing the force application through-hole on the rear decomposition plate is simple and does not require additional load transfer, simplifying the structure of the force application mechanism.

[0025] Preferably, a force application blind hole is provided on the front decomposition plate, and the force application mechanism abuts in the force application blind hole of the front decomposition plate.

[0026] In this solution, the load of the force application mechanism is transferred to the front decomposition plate through the movable rod via the force application blind hole. By setting the force application blind hole to match the movable rod, the force application rod and the front decomposition plate do not require additional connection structures, and their connection is simple, 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 application of the load.

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

[0028] In this solution, by providing 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 abuts against the front decomposition plate. The structure is simple and the load application is reliable.

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

[0030] In this solution, by selecting a hydraulic force application rod as the force application mechanism, the hydraulic force application rod has the advantages of large load output and stable output. It does not require manual load application by the operator, improving the usability of the aeroengine rotor disk decomposition tool and reducing the labor intensity of the operator.

[0031] The positive and progressive effects of the present invention are as follows: In the present invention, the front decomposition plate and the rear decomposition plate are respectively abutted against the front-stage rotor disk and the rear-stage rotor disk, and are used to apply the load applied by the boosting mechanism to the front decomposition plate and the rear decomposition plate to the front-stage rotor disk and the rear-stage rotor disk, so that the front-stage rotor disk and the rear-stage rotor disk can be separated, and the decomposition method is stable and reliable. In this solution, the movement of the moving seat is used to drive the movement of the centering part connected to the moving seat, so as to realize the adjustable distance between the two centering parts, so that the two centering parts can abut against the rotor disks with different diameters of the disk center holes, realize centering for the rotor disks with different diameters of the disk center holes, and determine the force application center of the rotor disks with different diameters of the disk center holes. The boosting mechanism applies a load perpendicular to the rear decomposition plate to the front decomposition plate and the rear decomposition plate at the force application center, ensuring uniform force during the decomposition process of the front-stage rotor disk and the rear-stage rotor disk, and preventing the inability to decompose due to pulling deviation. The aero-engine rotor disk decomposition tool in this solution has a simple structure, is convenient to operate, and the decomposition is stable and reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 FIG. is a schematic structural diagram of a multi-stage rotor disk of an aero-engine.

[0033] Figure 2 FIG. is a schematic structural diagram of an existing decomposition device for the first-stage wheel disk of an engine fan rotor.

[0034] Figure 3 FIG. is a schematic installation structure diagram of the decomposition tool of an embodiment of the present invention on a multi-stage rotor disk.

[0035] Figure 4 FIG. is a three-dimensional structural diagram of the decomposition tool of an embodiment of the present invention.

[0036] Figure 5 FIG. is a three-dimensional structural diagram of the front decomposition plate of an embodiment of the present invention.

[0037] Figure 6 FIG. is a three-dimensional structural diagram of the centering mechanism of an embodiment of the present invention.

[0038] Figure 7 FIG. is a cross-sectional structural diagram of the centering mechanism of an embodiment of the present invention.

[0039] DESCRIPTION OF REFERENCE NUMERALS:

[0040] In the prior art:

[0041] Rotor disk 1'

[0042] Decomposition device 2' for the first-stage wheel disk of an engine fan rotor

[0043] In the present invention:

[0044] Front-stage rotor disk 31

[0045] Rear rotor disk 32

[0046] Front decomposition plate 4

[0047] First surface 41

[0048] Second surface 42

[0049] Centering mechanism 5

[0050] Centering portion 51

[0051] Driving device 52

[0052] Moving seat 521

[0053] Connecting rod 522

[0054] Fixed pin 523

[0055] Driving rod 524

[0056] Fixed seat 525

[0057] Retaining ring 526

[0058] Slotted hole 6

[0059] Rear decomposition plate 7

[0060] Force - adding mechanism 8

[0061] Movable rod 81

[0062] Fixed rod 82

[0063] Connecting member 9

[0064] Limiting member 10

[0065] Force - adding through - hole 111

[0066] Force - adding blind - hole 112 Specific embodiments

[0067] The present invention will be further described below by way of embodiments, but the present invention is not limited to the scope of the embodiments thereby.

[0068] As Figures 3 - 7 shown, this embodiment provides an aircraft engine rotor decomposition tool for decomposing multi - stage rotor disks. Among them, the centers of the multi - stage rotor disks are on the same axis. The multi - stage rotor disks include a front - stage rotor disk 31 and a rear - stage rotor disk 32. The front - stage rotor disk 31 and the rear - stage rotor disk 32 in this embodiment refer to two adjacent rotor disks to be decomposed.

[0069] As Figures 3 - 7 shown, the decomposition tool includes a front decomposition plate 4, a centering mechanism 5, a rear decomposition plate 7, and a force - adding mechanism 8.

[0070] As shown Figure 3 in the figure, the front decomposition plate 4 has a first surface 41, and the first surface 41 is used to abut against the front-stage rotor disk 31. The rear decomposition plate 7 is parallel to the front decomposition plate 4, and the rear decomposition plate 7 is used to abut against the rear-stage rotor disk 32. The front decomposition plate 4 and the rear decomposition plate 7 in this embodiment are both strip plate structures, and are both placed between the front-stage rotor disk 31 and the rear-stage rotor disk 32. Therefore, the first surface 41 of the front decomposition plate 4 in this embodiment abuts against the surface of the front-stage rotor disk 31 close to the rear-stage rotor disk 32, and the rear decomposition plate 7 abuts against the surface of the rear-stage rotor disk 32 close to the front-stage rotor disk 31.

[0071] The centering mechanism 5 is arranged on the first surface 41 of the front decomposition plate 4. The centering mechanism 5 includes two centering parts 51 and a driving device 52. The driving device 52 is used to drive the two centering parts 51 to approach or move away from each other along the direction of the connection line of the two centering parts 51, so that the two centering parts 51 can abut against the rotor disks with different diameters of the disk center holes. Furthermore, the centering mechanism 5 can center the rotor disks with different diameters of the disk center holes, reduce the cost of producing centering mechanisms 5 with different diameters, and can make the axis of the disk center hole of the rotor disk visible, which is convenient to determine the force application center of the rotor disks with different diameters of the disk center holes.

[0072] Specifically, the centering mechanism 5 is used to determine the center of the front-stage rotor disk 31. Since the front-stage rotor disk 31 and the rear-stage rotor disk 32 are coaxial, the center of the front-stage rotor disk 31 is also the center of the rear-stage rotor disk 32, and then the force application center of the force application mechanism 8 is determined. Since the first surface 41 of the front decomposition plate 4 abuts against the front-stage rotor disk 31, the two centering parts 51 arranged on the first surface 41 can also abut against the front-stage rotor disk 31. By adjusting the distance between the two centering parts 51, the two centering parts 51 can abut against the rotor disks with different diameters of the disk center holes. Further, by adjusting the positions of the centering parts 51, the two centering parts 51 cannot move in the disk center hole of the rotor disk, so that the length of the connection line of the two centering parts 51 corresponds to the diameter of the disk center hole of the rotor disk, realizing that the center of the connection line of the two centering parts 51 is coaxial with the disk center hole of the rotor disk, and the center of the connection line of the two centering parts 51 is also the force application center of the rotor disk.

[0073] As shown Figure 6As shown in the figure, the driving device 52 includes a moving seat 521 and two connecting rods 522. One end of each of the two connecting rods 522 is hinged to the moving seat, and the other ends of the two connecting rods 522 are respectively hinged to the two centering parts 51. The moving seat 521 can move on the perpendicular bisector of the line connecting the two centering parts 51. Since the length of the connecting rod 522 remains unchanged, when the moving seat 521 connected to one end of the connecting rod 522 moves, the centering part 51 connected to the other end of the connecting rod 522 also needs to move accordingly. Therefore, the movement of the moving seat 521 is used to drive the movement of the centering part 51 connected to the moving seat 521, so as to realize the adjustable distance between the two centering parts 51, so that the two centering parts 51 can abut against the rotor disks with different diameters of the disk center holes, realize centering for the rotor disks with different diameters of the disk center holes, and determine the force application centers of the rotor disks with different diameters of the disk center holes.

[0074] The driving device 52 utilizes the principle of an isosceles triangle. When a force is applied to the vertex (the moving seat 521), the endpoints (the centering parts 51) of the two equal sides (the connecting rods 522) can be driven to move synchronously along the direction of the line connecting the two centering parts 51. When the endpoints (the centering parts 51) of the two equal sides (the connecting rods 522) contact the inner wall surface of the disk center hole of the front rotor disk, the perpendicular bisector of the midpoint of the line connecting the endpoints (the centering parts 51) of the two equal sides (the connecting rods 522) is the axis of the disk center of the rotor disk, thereby making the axis of the disk center of the rotor disk explicit.

[0075] Both ends of the connecting rod 522 are respectively hinged to the moving seat 521 and the centering part 51. Thus, the moving direction of the centering part 51 can be changed by the rotation of the connecting rod 522, so that the moving direction of the centering part 51 can be inconsistent with that of the moving seat 521, ensuring that the two centering parts 51 can approach or move away from each other.

[0076] As Figure 3 shown in the figure, the force applying mechanism 8 is connected to the front disassembly plate 4 and the rear disassembly plate 7. The force applying mechanism 8 is arranged at the center of the line connecting the two centering parts 51. The force applying mechanism 8 can apply a load perpendicular to the rear disassembly plate 7 to the front disassembly plate 4 and the rear disassembly plate 7. Among them, perpendicular to the rear disassembly plate 7 in this embodiment means parallel to the axis of the rotor disk. Also, since the force applying mechanism 8 is arranged at the force application center, the force applying mechanism 8 can apply a load along the axis direction of the rotor disk to the front disassembly plate 4 and the rear disassembly plate 7, ensuring uniform force during the disassembly process of the front-stage rotor disk 31 and the rear-stage rotor disk 32.

[0077] The front decomposition plate 4 and the rear decomposition plate 7 are respectively abutted against the front-stage rotor disk 31 and the rear-stage rotor disk 32, and are used to apply the load applied by the boosting mechanism 8 to the front decomposition plate 4 and the rear decomposition plate 7 to the front-stage rotor disk 31 and the rear-stage rotor disk 32, so that the front-stage rotor disk 31 and the rear-stage rotor disk 32 can be separated. The boosting mechanism 8 applies a load perpendicular to the rear decomposition plate 7 to the front decomposition plate 4 and the rear decomposition plate 7 at the force application center, ensuring that the forces on the front-stage rotor disk 31 and the rear-stage rotor disk 32 are evenly distributed during the decomposition process, and preventing the inability to decompose due to pulling deviation. The structure of the aero-engine rotor disk decomposition tool in this embodiment is simple, easy to operate, and stable and reliable during decomposition.

[0078] The driving device 52 further includes a fixing pin 523. Coaxial connection holes are provided on both the moving seat 521 and the two connecting rods 522, and the fixing pin 523 passes through the connection holes on the moving seat 521 and the two connecting rods 522. In this embodiment, the moving seat 521 and the two connecting rods 522 are simultaneously connected by one fixing pin 523. On the one hand, it can reduce the number of components in the driving device 52 and simplify the assembly steps. On the other hand, it can further ensure that the position of the center of the line connecting the two centering parts 51 does not change, improving the reliability of determining the center of the rotor disk through the centering parts 51. In addition, the connection method between the fixing pin 523 and the connection hole has a simple structure and low production and assembly costs.

[0079] The driving device 52 further includes a driving rod 524 and a fixing seat 525. The fixing seat 525 is fixed on the front decomposition plate 4 and remains stationary relative to the front decomposition plate 4. One end of the driving rod 524 is connected to the moving seat 521, and the other end of the driving rod 524 is connected to the fixing seat 525. The fixing seat 525 is used to support the driving rod 524 and cooperate with the driving rod 524 to rotate, preventing the driving rod 524 from shifting in position during rotation. The axial direction of the driving rod 524 is parallel to the moving direction of the moving seat 521. The driving rod 524 can move relative to the fixing seat 525 along the axial direction of the driving rod 524. By rotating the driving rod 524 to drive the moving seat 521 to move, the operation is simple and the moving accuracy is high.

[0080] Specifically, the driving rod 524 has an external thread, and a threaded hole for the driving rod 524 to pass through is provided on the fixing seat 525, and the driving rod 524 is screwed with the threaded hole. The threaded connection between the driving rod 524 and the fixing seat 525 can, on the one hand, realize the rotation of the driving rod 524 relative to the fixing seat 525 to achieve the movement of the driving rod 524 in its axial direction. On the other hand, when the driving rod 524 does not rotate, it can also ensure that the driving rod 524 remains stationary relative to the fixing seat 525. The threaded drive has a self-locking function and is stable and reliable.

[0081] Such as Figure 7As shown, the driving device 52 further includes a retaining ring 526. The retaining ring 526 is used to connect the driving rod 524 to the moving seat 521, and keep the relative static state between the driving rod 524 and the moving seat 521. In other alternative embodiments, the driving rod 524 can also be connected to the moving seat 521 by other means, such as threaded connection, etc.

[0082] As Figure 5 and Figure 6 shown, in order to prevent the centering part 51 from moving in the same direction as the moving seat 521, the centering mechanism 5 further includes a guiding part. The guiding part is arranged on the front decomposition plate 4 and is used for limiting the centering part 51. The guiding part and the centering part 51 form a moving pair, and the degree-of-freedom direction of the moving pair is consistent with the connecting line direction of the two centering parts 51, so that the centering part 51 can only move along the connecting line direction of the two centering parts 51. On the one hand, the guiding part guides the centering part 51 to move along the connecting line direction of the two centering parts 51, and on the other hand, limits the degree of freedom of the centering part 51 in other directions, preventing the position deviation of the centering part 51 during the movement, and improving the movement accuracy of the centering part 51 and the reliability of determining the center of the rotor disc through the centering part 51.

[0083] As Figure 5 shown, the guiding part includes a strip-shaped hole 6. The strip-shaped hole 6 extends along the connecting line direction of the two centering parts 51, and the centering part 51 can only move in the extending direction of the strip-shaped hole 6.

[0084] Specifically, the strip-shaped hole 6 is a through hole. The front decomposition plate 4 has a second surface 42 opposite to the first surface 41. The decomposition tool further includes a connecting piece 9 and a limiting piece 10. One end of the connecting piece 9 is connected to the centering part 51, the other end of the connecting piece 9 passes through the strip-shaped hole 6 and extends to the second surface 42, and the limiting piece 10 is arranged on the second surface 42 and engages with the connecting piece 9. The width of the limiting piece 10 in the width direction of the strip-shaped hole 6 is greater than the aperture of the strip-shaped hole 6. Among them, the width direction of the strip-shaped hole 6 is perpendicular to the extending direction of the strip-shaped hole 6. The limiting piece 10 cooperates with the strip-shaped hole 6 to limit the movement of the connecting piece 9 in the depth direction of the strip-shaped hole 6, so as to limit the movement of the centering part 51 connected to the connecting piece 9 in the depth direction of the strip-shaped hole 6, further limiting the position deviation of the centering part 51 during the movement, and improving the movement accuracy of the centering part 51 and the reliability of determining the center of the rotor disc through the centering part 51.

[0085] As Figure 4As shown in the figure, a force - increasing through - hole 111 is formed at the center of the rear decomposition plate 7. The force - increasing mechanism 8 passes through the force - increasing through - hole 111 of the rear decomposition plate 7 and abuts against the front decomposition plate 4. In this embodiment, internal threads are machined on the inner wall of the force - increasing through - hole 111 on the rear decomposition plate 7, and external threads are provided on the force - increasing mechanism 8. The force - increasing mechanism 8 and the rear decomposition plate 7 are connected by screwing tightly. During use, the connection between the force - increasing mechanism 8 and the rear decomposition plate 7 is realized by screwing tightly the force - increasing mechanism 8 and the rear decomposition plate 7. The force - increasing mechanism 8 with different output loads can be replaced according to the size of the rotor disk to be disassembled. The threaded connection has a simple structure, is convenient for disassembly and replacement, and has reliable connection. The load of the force - increasing mechanism 8 is transmitted to the rear decomposition plate 7 through the thread, and a relatively large load can be reliably transmitted through the thread. In other embodiments, the force - increasing mechanism 8 can also be fixedly connected to the rear decomposition plate 7 by interference fit.

[0086] As Figure 4 and Figure 5 shown, a force - increasing blind - hole 112 is formed on the front decomposition plate 4. The force - increasing mechanism 8 abuts in the force - increasing blind - hole 112 of the front decomposition plate 4. The force - increasing blind - hole 112 is formed on the second surface 42 of the front decomposition plate 4 opposite to the first surface 41, and the force - increasing blind - hole 112 does not completely penetrate the front decomposition plate 4. The diameter of the force - increasing blind - hole 112 is the same as the diameter of one end of the force - increasing mechanism 8 that abuts against the front decomposition plate 4, so that the force - increasing mechanism 8 extends into the force - increasing blind - hole 112 on the front decomposition plate. The force - increasing mechanism 8 transmits the load to the front decomposition plate 4 through the force - increasing blind - hole 112. The force - increasing mechanism 8 is clamped into the force - increasing blind - hole 112 to prevent the force - increasing mechanism 8 from deflecting to one side of the front decomposition plate 4 due to the deviation of the load, improving the reliability of load transmission. And by providing the force - increasing blind - hole 112, it is convenient to separate the force - increasing mechanism 8 from the front decomposition plate 4, improving the usability of the disassembly tool for the rotor disk of the aero - engine.

[0087] As Figure 4 shown, the force - increasing mechanism 8 includes a fixed rod 82 and a movable rod 81, and the movable rod 81 can move relative to the fixed rod 82. The fixed rod 82 passes through the force - increasing through - hole 111. External threads are provided on the outer side of the fixed rod 82, and internal threads are provided in the force - increasing through - hole 111. The fixed rod 82 is screwed tightly in the force - increasing through - hole 111. The threaded connection prevents the fixed rod 82 from moving axially between the fixed rod 82 and the rear decomposition plate 7 during use. The diameter of the movable rod 81 matches the diameter of the force - increasing blind - hole 112, and the movable rod 81 abuts against the force - increasing blind - hole 112. The movable rod 81 abuts in the force - increasing blind - hole 112, and the movable rod 81 transmits the load to the front decomposition plate 4 through the force - increasing blind - hole 112, realizing the disassembly and separation of the front - stage rotor disk 31 and the rear - stage rotor disk 32.

[0088] The boosting mechanism 8 includes a hydraulic boosting rod. The hydraulic boosting rod transfers the load to the front decomposition plate 4 through the movable rod 81, and the fixed rod 82 is threadedly connected to the boosting through-hole 111 on the rear decomposition plate 7. The relative positions of the fixed rod 82 and the rear decomposition plate 7 remain unchanged, and by pushing the front decomposition plate 4 to move away from the rear decomposition plate 7. The front decomposition plate 4 abuts against the front-stage rotor disk 31, and the rear decomposition plate 7 abuts against the rear-stage rotor disk 32. The load of the hydraulic boosting rod is transferred to the front-stage rotor disk 31 and the rear-stage rotor disk 32 through the front decomposition plate 4 and the rear decomposition plate 7 respectively, realizing the disassembly of the front-stage rotor disk 31 and the rear-stage rotor disk 32. In other alternative embodiments, the boosting mechanism 8 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 boosting mechanism 8 may also be a screw mechanism. The fixed rod 82 and the movable rod 81 are threadedly connected. By rotating the movable rod 81 relative to the fixed rod 82, the screw mechanism has the advantages of simple structure, high reliability, and no need for an additional power source.

[0089] The following briefly describes the disassembly process of the multi-stage rotor disk according to the specific structure of the above-mentioned aero-engine rotor disassembly tool.

[0090] S1. Place the front decomposition plate 4 with the centering mechanism 5 obliquely, pass it through the central hole of the rear-stage rotor disk 32, and then place it horizontally on the front-stage rotor disk 31. The first surface 41 of the front decomposition plate 4 abuts against the front-stage rotor disk 31;

[0091] S2. Rotate the rotating rod of the centering mechanism 5 so that the two centering parts 51 are in contact with the inner wall of the central hole of the front-stage rotor disk 31 at the same time;

[0092] S3. Continue to rotate the rotating rod so that the two centering parts 51 are tightly pressed against the inner wall of the central hole of the front-stage rotor disk 31 and cannot be easily moved;

[0093] S4. Place the rear decomposition plate 7 obliquely, pass it through the central hole of the rear-stage rotor disk 32, and then place it between the front-stage rotor disk 31 and the rear-stage rotor disk 32;

[0094] S5. Threadedly connect the fixed part of the boosting mechanism 8 to the rear decomposition plate 7;

[0095] S6. Insert one end of the movable part of the boosting mechanism 8 close to the front decomposition disk into the positioning groove;

[0096] S7. Apply pressure to the boosting mechanism 8 to make the movable part move relative to the fixed part, driving the rear decomposition plate 7 to tightly press against the rear-stage rotor disk 32;

[0097] S8. Continue to apply pressure to the boosting mechanism 8 until the rear-stage rotor disk 32 is pushed out and the front-stage rotor disk 31 is separated from the rear-stage rotor disk 32.

[0098] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship of the device or component in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation at any time, unless otherwise specified in the text.

[0099] Although the specific embodiments of the present invention have been described above, those skilled in the art should understand that this is only an example, and the protection scope of the present invention is defined by the appended claims. Without departing from the principles and essence of the present invention, those skilled in the art can make various changes or modifications to these embodiments, but these changes and modifications all fall within the protection scope of the present invention.

Claims

1. An aircraft engine rotor disk disassembly tool, characterized in that, The aero-engine rotor disk disassembly tool includes: A front disassembly plate, which has a first surface for abutting against the front-stage rotor disk; A centering mechanism disposed on the first surface of the front disassembly plate. The centering mechanism includes two centering parts and a driving device. The driving device includes a moving seat and two connecting rods. One end of each of the two connecting rods is hinged to the moving seat, and the other ends of the two connecting rods are respectively hinged to the two centering parts. The moving seat can move on the perpendicular bisector of the line connecting the two centering parts, and the driving device is used to drive the two centering parts to approach or move away from each other along the direction of the line connecting the two centering parts; A rear disassembly plate, which is arranged parallel to the front disassembly plate and is used to abut against the rear-stage rotor disk; A boosting mechanism connected to the front disassembly plate and the rear disassembly plate. The boosting mechanism can apply a load perpendicular to the rear disassembly plate to the front disassembly plate and the rear disassembly plate, and the boosting mechanism is arranged at the center of the line connecting the two centering parts.

2. The aero-engine rotor disc disassembly tool according to claim 1, characterized in that, The centering mechanism further includes a guiding part arranged on the front disassembly plate. The guiding part and the centering part form a moving pair, and the degree-of-freedom direction of the moving pair is the same as the direction of the line connecting the two centering parts.

3. The aero-engine rotor disc disassembly tool according to claim 2, characterized in that, The guiding part includes a strip-shaped hole extending along the direction of the line connecting the two centering parts.

4. The aeroengine rotor disk disassembly tool according to claim 3, wherein, The strip-shaped hole is a through hole. The front disassembly plate has a second surface opposite to the first surface. The disassembly tool further includes a connecting piece and a limiting piece. One end of the connecting piece is connected to the centering part, and the other end of the connecting piece extends through the strip-shaped hole to the second surface. The limiting piece is arranged on the second surface and engages with the connecting piece. The width of the limiting piece in the width direction of the strip-shaped hole is greater than the aperture of the strip-shaped hole.

5. The aeroengine rotor disk disassembling tool according to claim 1, wherein The driving device further includes a fixing pin. Coaxial connecting holes are provided on the moving seat and the two connecting rods, and the fixing pin passes through the connecting holes on the moving seat and the two connecting rods.

6. The aeroengine rotor disk disassembly tool according to claim 1, characterized in that The driving device further includes a driving rod and a fixing seat. The fixing seat is fixed on the front disassembly plate. One end of the driving rod is connected to the moving seat, and the other end of the driving rod is connected to the fixing seat. The axial direction of the driving rod is parallel to the moving direction of the moving seat, and the driving rod can move relative to the fixing seat along the axial direction of the driving rod.

7. The aeroengine rotor disc disassembling tool according to claim 6, wherein, The driving rod has an external thread, and a threaded hole for the driving rod to pass through is provided on the fixing seat. The driving rod is screwed with the threaded hole.

8. The aero-engine rotor disc disassembly tool according to claim 1, characterized in that, A boosting through hole is formed on the rear disassembly plate, and the boosting mechanism passes through the boosting through hole of the rear disassembly plate and abuts against the front disassembly plate.

9. The aero-engine rotor disc disassembly tool according to claim 8, characterized in that, A boosting blind hole is formed on the front disassembly plate, and the boosting mechanism abuts in the boosting blind hole of the front disassembly plate.

10. The aeroengine rotor disk disassembly tool according to claim 9, characterized in that, The boosting mechanism includes a fixed rod and a movable rod. The movable rod can move relative to the fixed rod. The fixed rod passes through the boosting through hole, and the diameter of the movable rod matches the diameter of the boosting blind hole. The movable rod abuts against the boosting blind hole.

11. The aeroengine rotor disk disassembly tool according to any one of claims 1-10, characterized in that, The boosting mechanism includes a hydraulic boosting rod.

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