Aeroengine Rotor Disk Disassembly Tool

Abstract

The present invention discloses a disassembly tool for an aero-engine rotor disk, which comprises a front disassembly plate, a rear disassembly plate, a centering mechanism and a boosting mechanism; the front disassembly plate is used to abut against the front-stage rotor disk; the rear disassembly plate is used to abut against the rear-stage rotor disk; the centering mechanism is arranged on the front disassembly plate and is used to quickly determine the center of the front-stage rotor disk and make it visible on the axis of the boosting mechanism; the boosting mechanism connects the front disassembly plate and the rear disassembly plate, and a force perpendicular to the rear disassembly plate is applied to the boosting mechanism to realize the disassembly of the rear-stage rotor disk. For the disassembly tool for an aero-engine rotor disk of the present invention, the centering mechanism is applicable to rotor disks with different hole diameters and different thicknesses, and has universality; moreover, its structure is simple, facilitating quick installation and disassembly, and the operation of disassembling the rotor disk is simple; during the disassembly process, the load applied by the boosting mechanism is in the axial direction of the rotor disk, and the rotor disk is uniformly stressed, so that the rotor disk to be disassembled will not be pulled off to cause failure of disassembly.

Description

Technical Field

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

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

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

[0005] A disassembly tool for an aero-engine rotor disc, which comprises:

[0006] A front disassembly plate, the front disassembly plate has a first surface, and the first surface is used to abut against the previous-stage rotor disc;

[0007] Centering mechanism, the centering mechanism is arranged on the first surface of the front decomposition plate. The centering mechanism includes a four-bar linkage mechanism, two centering parts and a driving device. The four-bar linkage mechanism is symmetrically arranged in a diamond shape. The four-bar linkage mechanism has a first hinge point, a second hinge point, a third hinge point and a fourth hinge point arranged in sequence. The two centering parts are respectively arranged on the first hinge point and the third hinge point. The driving device is connected to the second hinge point and the fourth hinge point. The driving device is used to drive the second hinge point and the fourth hinge point to approach or separate from each other;

[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 application mechanism, the force application mechanism is connected to the front decomposition plate and the rear decomposition plate, and the force application mechanism can apply a load perpendicular to the front decomposition plate and the rear decomposition plate to the front decomposition plate and the rear decomposition plate.

[0010] In this solution, the centering mechanism is used to determine the center of the rotor disc. By setting the centering mechanism as a diamond-shaped four-bar linkage mechanism, the two centering parts used to contact the rotor disc are arranged at the first hinge point and the third hinge point of the four-bar linkage mechanism. During the decomposition process, the center of the rotor disc coincides with the center of the four-bar linkage mechanism; the two centering parts are used to contact the rotor disc. The driving device is connected to the second hinge point and the fourth hinge point of the four-bar linkage mechanism. When the driving device drives the second hinge point and the fourth hinge point to approach or separate from each other, the two centering parts also approach or separate from each other, realizing the adjustment of the distance between the two centering parts, which can be used for the positioning and decomposition of rotor discs with different apertures and different thicknesses, thus realizing the versatility of the aero-engine rotor disc decomposition tool; during the decomposition process, the force application mechanism transmits the load perpendicular to the front decomposition plate and the rear decomposition plate to the front-stage rotor disc and the rear-stage rotor disc, realizing the decomposition of the rotor disc. The operation of decomposing the rotor disc is convenient, and the decomposition is stable and reliable.

[0011] Preferably, the front decomposition plate and the rear decomposition plate have dimensions in two directions smaller than the diameter of the center of the rotor disc.

[0012] In this solution, the aero-engine rotor disc decomposition tool is divided into three parts: the front decomposition plate, the rear decomposition plate and the force application mechanism. The front decomposition plate and the rear decomposition plate can pass through the rotor disc, and the centering mechanism is installed on the front decomposition plate and can also pass through the rotor disc with the front decomposition plate, which is convenient for the quick installation and disassembly of the aero-engine rotor disc decomposition tool.

[0013] Preferably, the force application mechanism includes a fixed rod and a movable rod. The movable rod can move relative to the fixed rod. The movable rod is connected to the front decomposition plate, and the connection point of the movable rod and the front decomposition plate is located at the center of the four-bar linkage mechanism. The fixed rod is connected to the rear decomposition plate.

[0014] In this solution, a fixed rod and a movable rod capable of relative movement are provided. During the disassembly process, the fixed rod is connected to the rear disassembly plate, and the movable rod is connected to the front disassembly plate. The structure is simple, facilitating quick disassembly and assembly and the disassembly of the rotor disc. The connection point between the movable rod and the front disassembly plate is located at the center of the four-bar linkage mechanism, and the center of the rotor disc is made explicit on the axis of the movable rod of the force adding mechanism. During the disassembly process of the rotor disc, the axis of the rotor disc coincides with the axis of the movable rod, ensuring that the load applied by the force adding mechanism is in the direction of the axis of the rotor disc, making the force on the rotor disc uniform during the disassembly process, and preventing the rotor disc to be disassembled from being pulled off and unable to be disassembled.

[0015] Preferably, the front disassembly plate and the movable rod are connected through a concave-convex structure.

[0016] In this solution, by setting a concave-convex structure on the front disassembly plate, it is convenient for the quick installation of the disassembly tool for the aero-engine rotor disc, ensuring the reliable connection between the front disassembly plate and the force adding mechanism. And through the setting of the cooperation part of the concave-convex structure and some cooperation dimensions, it can ensure that the center of the four-bar linkage mechanism coincides with the axis of the movable rod of the force adding mechanism.

[0017] Preferably, a through hole is provided at the middle position of the rear disassembly plate, an internal thread is provided on the through hole, an external thread is provided on the fixed rod, and the fixed rod passes through the through hole and is connected to the through hole by a thread.

[0018] In this solution, a through hole is provided at the middle of the rear disassembly plate, facilitating the force adding mechanism to pass through the through hole and connect with the front disassembly plate. When disassembling the rotor disc, the force adding mechanism is connected to the rear disassembly plate by a thread and fixed on the rear disassembly plate.

[0019] Preferably, the force adding mechanism includes a hydraulic rod.

[0020] In this solution, by selecting a hydraulic rod as the force adding mechanism, the hydraulic rod has the advantages of large load output and stable output. There is no need for an operator to manually apply a load, improving the operational convenience of the disassembly tool for the aero-engine rotor disc and reducing the labor intensity of the operator.

[0021] Preferably, the two centering parts are respectively fixed on the first hinge point and the third hinge point of the four-bar linkage mechanism through fasteners, and the shape of the centering part is cylindrical.

[0022] In this solution, the centering parts are fixed on the first hinge point and the third hinge point of the four-bar linkage mechanism, and the shape of the centering part is set to be cylindrical. No matter how the centering part rotates or moves relative to the hinge point, the distance between the outside of the centering part and the hinge point remains unchanged, so as to ensure that the center of the rotor disc in contact with the centering part coincides with the center of the four-bar linkage mechanism.

[0023] Preferably, the four-bar linkage further includes two connecting seats, which are respectively arranged corresponding to the second hinge point and the fourth hinge point of the four-bar linkage. One ends of the four link rods are respectively movably connected to the two connecting seats, and the driving device is connected to the two connecting seats.

[0024] In this solution, connecting seats are arranged at the second hinge point and the fourth hinge point of the four-bar linkage. The driving mechanism is connected to the four-bar linkage through the connecting seats. The driving mechanism drives the connecting seats to move, driving the second hinge point and the fourth hinge point of the four-bar linkage to move, thereby driving the movement of the two centering parts.

[0025] Preferably, the driving device includes a screw rod, and external threads with opposite helix directions are provided on both sides of the screw rod. Internal threads are provided on the two connecting seats, and the screw rod is movably connected to the connecting seats through threads and drives the two connecting seats to move.

[0026] In this solution, screw drive is adopted. Screw drive has a self-locking function, which is stable and reliable. By providing threads with opposite helix directions on both sides of the screw rod, when the screw rod moves, the second hinge point and the fourth hinge point of the four-bar linkage move inwards or outwards simultaneously.

[0027] Preferably, the centering mechanism further includes a fixing device, which is located at the center of the four-bar linkage, and the driving device is fixed on the front decomposition plate through the fixing device.

[0028] In this solution, the driving device is fixed on the front decomposition plate through the fixing device; the fixing device is arranged at the center of the four-bar linkage, fixing the center of the four-bar linkage to the fixing device.

[0029] Preferably, the driving device includes a screw rod, and an annular groove is provided in the middle of the screw rod. The screw rod is installed on the fixing device through the annular groove.

[0030] In this solution, an annular groove is provided in the middle of the screw rod. The screw rod is installed on the front decomposition plate through the fixing device and can rotate around its own axis, realizing the limit of the screw rod on the front decomposition plate, so that the driving device will not move relative to the front decomposition plate, ensuring that the support seat is located at the symmetric center of the two connecting seats, that is, ensuring that the support seat is located at the center of the four-bar linkage, and ensuring the accuracy of the centering of the centering mechanism.

[0031] The positive and progressive effects of the present invention are as follows:

[0032] The disassembly tool for the rotor disc of an aero-engine of the present invention has an adjustable distance between two centering parts in the centering mechanism that contact the rotor disc, which is applicable to rotor discs with different hole diameters and different thicknesses, realizing the versatility of the disassembly tool for the rotor disc of an aero-engine; the disassembly tool for the rotor disc of an aero-engine is divided into three parts: a front disassembly plate, a rear disassembly plate, and a boosting mechanism, and the front disassembly plate and the rear disassembly plate can pass through the rotor disc, with a simple structure, facilitating the quick installation and disassembly of the disassembly tool for the rotor disc of an aero-engine, and having a low manufacturing cost; through the centering mechanism, the center of the rotor disc coincides with the center of the four-bar linkage mechanism and is made explicit on the axis of the movable rod of the boosting mechanism, ensuring that the load applied by the boosting mechanism is in the axial direction of the rotor disc, making the force on the rotor disc uniform during the disassembly process, and preventing the rotor disc to be disassembled from being pulled off and unable to be disassembled. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 FIG. is a schematic structural diagram of a multi-stage rotor disc of an aero-engine.

[0034] Figure 2 FIG. is a schematic structural diagram of an existing disassembly device for the first-stage wheel disc of an engine fan rotor.

[0035] Figure 3 FIG. is a schematic diagram of disassembling a rotor disc with the disassembly tool for the rotor disc of an aero-engine of the present invention.

[0036] Figure 4 FIG. is a schematic diagram of the part disassembly of the disassembly tool for the rotor disc of an aero-engine of the present invention.

[0037] Figure 5 FIG. is a schematic structural diagram of the centering mechanism and the front disassembly plate of the disassembly tool for the rotor disc of an aero-engine of the present invention from the first perspective.

[0038] Figure 6 FIG. is a schematic structural diagram of the centering mechanism and the front disassembly plate of the disassembly tool for the rotor disc of an aero-engine of the present invention from the second perspective.

[0039] Figure 7 For Figure 6 the sectional view at B-B in

[0040] Description of the reference numerals:

[0041] In the prior art:

[0042] Rotor disc 1'

[0043] Disassembly device 2' for the first-stage wheel disc of an engine fan rotor

[0044] In the present invention:

[0045] Disassembly tool 1000 for the rotor disc of an aero-engine, front-stage rotor disc 1

[0046] Rear-stage rotor disc 2

[0047] Boosting mechanism 30

[0048] Fixed rod 31

[0049] Movable rod 32

[0050] Boss 33

[0051] Hydraulic rod 34

[0052] Rear decomposition plate 40

[0053] Through hole 41

[0054] Front decomposition plate 50

[0055] First surface 51

[0056] Groove 52

[0057] Centering mechanism 100

[0058] First hinge point 101

[0059] Second hinge point 102

[0060] Third hinge point 103

[0061] Fourth hinge point 104

[0062] Centering part 110

[0063] Nut 111

[0064] Drive device 120

[0065] Screw rod 121

[0066] Adapter section 122

[0067] First end 123

[0068] Second end 124

[0069] Annular groove 125

[0070] Fixing device 130

[0071] Bolt 131

[0072] Support seat 132

[0073] Pressing plate 133

[0074] Four-bar linkage mechanism 140

[0075] Link 141

[0076] Connection seat 142

[0077] Pin 143 Specific implementation mode

[0078] The present invention will be further described below by way of embodiments, but the present invention is not limited to the scope of the described embodiments for this reason.

[0079] As Figures 3 - 7 shown, the present invention provides an aeroengine rotor disc disassembly tool 1000, which includes a boosting mechanism 30, a rear disassembly plate 40, a front disassembly plate 50, and a centering mechanism 100.

[0080] As Figure 3 shown, the front disassembly plate 50 has a first surface 51, and the first surface 51 on the front disassembly plate 50 abuts against the front-stage rotor disc 1. The rear disassembly plate 40 is arranged parallel to the front disassembly plate 50, and the rear disassembly plate 40 abuts against the rear-stage rotor disc 2. The front disassembly plate 50 and the rear disassembly plate 40 have dimensions in two directions smaller than the diameters of the centers of the front-stage rotor disc 1 and the rear-stage rotor disc 2, and the front disassembly plate 50 and the rear disassembly plate 40 can be inclined to pass through the holes at the centers of the front-stage rotor disc 1 and the rear-stage rotor disc 2. The centering mechanism 100 is arranged on the first surface 51 of the front disassembly plate 50, and can be quickly placed at the hole at the center of the front-stage rotor disc 1 after tilting with the front disassembly plate 50, so as to quickly determine the center of the front-stage rotor disc 1 and make the center of the front-stage rotor disc 1 visible.

[0081] As Figures 3 - 4 shown, a through hole 41 is formed in the middle of the rear disassembly plate 40. The boosting mechanism 30 passes through the through hole 41 and is connected to the front-stage rotor disc 1, and is connected to the rear disassembly plate 40 at the through hole 41. The boosting mechanism 30 includes a fixed rod 31 and a movable rod 32. The movable rod 32 can move relative to the fixed rod 31. There is a boss 33 at the end of the movable rod 32, and there is a groove 52 on the front disassembly plate 50. The groove 52 is used for quickly positioning the boosting mechanism 30, and the movable rod 32 is connected to the front disassembly plate 50 through the boss 33 and the groove 52. Threads are provided on the through hole 41 and the fixed rod 31, and the boosting mechanism 30 and the rear disassembly plate 40 are connected by the threaded connection of the fixed rod 31 and the through hole 41.

[0082] As Figures 5 - 6 shown, the centering mechanism 100 includes two centering parts 110, a driving device 120, a fixing device 130, and a four-link mechanism 140.

[0083] The four-bar linkage 140 is symmetrically arranged in a rhombus shape and has a first hinge point 101, a second hinge point 102, a third hinge point 103, and a fourth hinge point 104. The four-bar linkage 140 further includes two connection seats 142, which respectively correspond to the second hinge point 102 and the fourth hinge point 104 of the four-bar linkage 140. One ends of the four link rods 141 are respectively movably connected to the two connection seats 142 through pins 143. The two centering parts 110 are respectively fixed to the first hinge point 101 and the third hinge point 103 of the four-bar linkage 140 by nuts 111. The driving device 120 is driven by a screw rod 121. Threads with opposite helix directions are provided at the ends, that is, the first end 123 and the second end 124 of the screw rod 121. Internal threads are provided on the connection seats 142. The driving device 120 is connected to the second hinge point 102 and the fourth hinge point 104 of the four-bar linkage 140 through the threads on the screw rod 121 and the connection seats 142.

[0084] When the distance between the second hinge point 102 and the fourth hinge point 104 on one diagonal of the rhombus-shaped four-bar linkage 140 becomes longer / shorter, the first hinge point 101 and the third hinge point 103 on the other diagonal will follow and become shorter / longer. A transfer section 122 is provided on the screw rod 121, which is connected to a rotating wrench and rotates the wrench. The screw rod 121 can rotate around its own axis, driving the two connection seats 142 to move inward or outward simultaneously, driving the second hinge point 102 and the fourth hinge point 104 to move, and driving the first hinge point 101 and the third hinge point 103 to move, so as to realize the adjustment of the distance between the two centering parts 110.

[0085] The centering part 110 is cylindrical in shape. No matter how the centering part 110 rotates or moves relative to the first hinge point 101 or the third hinge point 103, the distance between the outer side of the centering part 110 and the first hinge point 101 or the third hinge point 103 remains unchanged, ensuring that the center of the front-stage rotor disk 1 in contact with the centering part 110 coincides with the center of the four-bar linkage 140.

[0086] The fixing device 130 includes a bolt 131, a support seat 132, and a pressing plate 133. The support seat is fixed to the middle of the first surface 51 of the front decomposition plate 50. There is an annular groove 125 in the middle of the screw rod 121. The screw rod 121 passes through two connecting seats 142 and is installed on the support seat 132 through the annular groove 125, and is positioned on the support seat 132 on the front decomposition plate 50 with the pressing plate 133 and the bolt 131. The positions of the two connecting seats 142 are symmetrical about the support seat 132 to ensure that the center of the four-bar linkage mechanism coincides with the center of the support seat 132 of the fixing device 130; the screw rod 121 is installed on the support seat 132 through the annular groove 125 to realize the limit of the screw rod 121 on the front decomposition plate 50, so that the driving device 120 will not move relative to the front decomposition plate 50, ensuring that the support seat 132 is located at the symmetric center of the two connecting seats 142, that is, ensuring that the support seat 132 is located at the center of the four-bar linkage mechanism 140, ensuring the accuracy of the centering of the centering mechanism 100.

[0087] The groove 51 of the front decomposition plate 50 is arranged at the center of the four-bar linkage mechanism 140, that is, corresponding to the position of the support seat 132 of the fixing device 130. By contacting the centers of the two centering parts 110 with the center of the front-stage rotor disk 1, the center of the front-stage rotor disk 1 is determined to be the symmetric center of the two centering parts 110, that is, the center of the four-bar linkage mechanism 140. The center of the four-bar linkage mechanism 140 corresponds to the positions of the support seat 132 and the groove 51, and the groove 51 is connected to the movable rod 32 of the force-applying mechanism 30, so as to realize quickly positioning the center of the front-stage rotor disk 1 to the center of the four-bar linkage mechanism 140 and making it explicit on the axis of the movable rod 32 of the force-applying mechanism 30. The force-applying mechanism 30 can apply a load perpendicular to the rear decomposition plate 40 between the front decomposition plate 50 and the rear decomposition plate 40, and the axis of the center of the front-stage rotor disk 1 coincides with the axis of the movable rod 32 of the force-applying mechanism 30. During the decomposition process, the front-stage rotor disk 1 and the rear-stage rotor disk 2 are evenly stressed, and the rear-stage rotor disk 2 will not be pulled off to cause failure of decomposition.

[0088] In this embodiment, the force-applying mechanism 30 includes a hydraulic rod 34. By selecting a hydraulic rod as the force-applying mechanism, the advantages of large load output and stable output of the hydraulic rod can be utilized, eliminating the need for operators to manually apply the load, improving the usability of the aero-engine rotor disk decomposition tool, and reducing the labor intensity of the operators. Moreover, the fixing rod 31 and the through hole 41 on the rear decomposition plate 40 are connected by threads, and the relative positions of the fixing rod 31 and the rear decomposition plate 40 remain unchanged. The front decomposition plate 50 abuts against the front-stage rotor disk 1, and the rear decomposition plate 40 abuts against the rear-stage rotor disk 2. The load of the hydraulic rod 34 is transmitted to the front decomposition plate 50 through the movable rod 32, transmitted to the rear decomposition plate 40 through the fixing rod 31, and then transmitted to the front-stage rotor disk 1 and the rear-stage rotor disk 2 through the front decomposition plate 50 and the rear decomposition plate 40 respectively to realize the disassembly of the front-stage rotor disk 1 and the rear-stage rotor disk 2.

[0089] In this embodiment, the boosting mechanism 30 is driven by a hydraulic rod 34. In other embodiments, the boosting mechanism 30 can also be driven by other solutions existing in the prior art such as a pneumatic rod. The pneumatic rod does not require liquid as a load transmission medium and has the advantages of being clean and easy to operate. Of course, the boosting mechanism 30 can also be driven by a screw mechanism. The fixed rod 31 and the movable rod 32 are threadedly connected. By rotating the movable rod 32 relative to the fixed rod 31, the screw mechanism has the advantages of simple structure, high reliability, and no need for an additional power source.

[0090] As Figures 3 - 7 shown, the disassembly tool provided in this embodiment can disassemble the front-stage rotor disk 1 and the rear-stage rotor disk 2 according to the following steps:

[0091] S1. As Figures 5 - 7 shown, complete the assembly of the aero-engine rotor disk disassembly tool 1000;

[0092] S2. As Figure 3 shown, place the front disassembly plate 50 with the centering mechanism 100 obliquely, pass it through the central hole of the rear-stage rotor disk 2, and then horizontally place it on the central end face of the front-stage rotor disk 1, and ensure that the first surface 51 of the front disassembly plate 50 is in contact with the front-stage rotor disk 1;

[0093] S3. Connect the adapter section 122 of the screw rod 121 with a wrench and rotate the wrench, so that the two connecting seats 142 move inward simultaneously, driving the two centering parts connected to the first hinge point 101 and the third hinge point 103 of the four-bar linkage mechanism 140 to contact the inner wall of the central hole of the front-stage rotor disk 1 simultaneously;

[0094] S4. After tilting the rear disassembly plate 40, place it into the cavity between the front-stage rotor disk 1 and the rear-stage rotor disk 2;

[0095] S5. Install the boosting mechanism 30 into the threaded connection hole of the through hole 41 on the rear disassembly plate 40;

[0096] S6. Adjust the position of the boosting mechanism 30 with the rear disassembly plate 40, so that the boss 33 of the boosting mechanism 30 is located in the groove 52 of the front disassembly plate 50;

[0097] S7. Load the hydraulic rod 34 of the boosting mechanism 30 to drive the rear disassembly plate 40 to abut against the rear end face of the rear-stage rotor disk 2;

[0098] S8. Continue to load the hydraulic rod 34 until the rear-stage rotor disk 2 is pushed out.

[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 It includes: A front decomposition plate, the front decomposition plate having a first surface for abutting against the front-stage rotor disc; A centering mechanism, the centering mechanism being provided on the first surface of the front decomposition plate, the centering mechanism including a four-bar linkage mechanism, two centering parts and a driving device, the four-bar linkage mechanism being symmetrically arranged in a rhombus shape, the four-bar linkage mechanism having a first hinge point, a second hinge point, a third hinge point and a fourth hinge point arranged in sequence, the two centering parts being respectively arranged on the first hinge point and the third hinge point, the driving device being connected to the second hinge point and the fourth hinge point, the driving device being used to drive the second hinge point and the fourth hinge point to approach or move away from each other; A rear decomposition plate, the rear decomposition plate being arranged parallel to the front decomposition plate, the rear decomposition plate being used to abut against the rear-stage rotor disc; A force application mechanism, the force application mechanism being connected to the front decomposition plate and the rear decomposition plate, the force application mechanism being capable of applying a load perpendicular to the rear decomposition plate to the front decomposition plate and the rear decomposition plate, the force application mechanism being arranged at the center of the rhombus-shaped four-bar linkage mechanism.

2. The aero-engine rotor disc disassembly tool according to claim 1, wherein, The front decomposition plate and the rear decomposition plate have dimensions in two directions smaller than the diameter of the center of the rotor disc.

3. The aeroengine rotor disc disassembly tool according to claim 1, wherein The force application mechanism includes a fixed rod and a movable rod, the movable rod being capable of moving relative to the fixed rod, the movable rod being connected to the front decomposition plate, the connection position of the movable rod and the front decomposition plate being located at the center of the four-bar linkage mechanism, the fixed rod being connected to the rear decomposition plate.

4. The aero-engine rotor disc disassembly tool according to claim 3, wherein The front decomposition plate and the movable rod are connected through a concave-convex structure.

5. The aeroengine rotor disk disassembly tool according to claim 3, wherein A through hole is opened at the middle position of the rear decomposition plate, an internal thread is opened on the through hole, an external thread is opened on the fixed rod, and the fixed rod passes through the through hole and is connected to the through hole through a thread.

6. The aeroengine rotor disk disassembly tool according to claim 1, wherein The force application mechanism includes a hydraulic rod.

7. The aero-engine rotor disk disassembling tool according to claim 1, wherein, The two centering parts are respectively fixed on the first hinge point and the third hinge point of the four-bar linkage mechanism through fasteners, and the shape of the centering part is cylindrical.

8. The aeroengine rotor disk disassembling tool according to claim 1, wherein The four-bar linkage mechanism further includes two connection seats, the two connection seats being respectively arranged corresponding to the second hinge point and the fourth hinge point of the four-bar linkage mechanism, and one ends of the four connecting rods are respectively movably connected to the two connection seats.

9. The aero-engine rotor disc disassembling tool according to claim 8, wherein The driving device includes a screw rod, external threads with opposite helix directions are opened on both sides of the screw rod, internal threads are opened on the two connection seats, and the screw rod is movably connected to the connection seats through threads and drives the two connection seats to move.

10. The aeroengine rotor disc disassembly tool according to claim 1, wherein, The centering mechanism further includes a fixing device, the fixing device being located at the center of the four-bar linkage mechanism, and the driving device is fixed on the front decomposition plate through the fixing device.

11. The aeroengine rotor disk disassembly tool according to claim 10, characterized in that, The driving device includes a screw rod, an annular groove is opened in the middle of the screw rod, and the screw rod is installed on the fixing device through the annular groove.

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