CN215942772U - Tool for disassembling rotor disc of aircraft engine - Google Patents

Abstract

The utility model provides a tool for disassembling a rotor disc of an aircraft engine. The front decomposition plate has a first surface; the inclined wedge centering mechanism comprises an inclined wedge driving part and centering rods, the inclined wedge driving part is arranged between the two centering rods and comprises two first inclined planes which are oppositely arranged, the centering rods abut against the first inclined planes, and the inclined wedge driving part drives the centering rods to move along the axial direction of the centering rods through the first inclined planes; the rear decomposition plate is arranged in parallel to the front decomposition plate; the force applying mechanism is connected to the front decomposition plate and the rear decomposition plate, and is capable of applying a load perpendicular to the rear decomposition plate between the front decomposition plate and the rear decomposition plate. The tool for disassembling the rotor disc of the aircraft engine determines the center of the rotor disc through the wedge centering mechanism, and the load of the stress application mechanism is transmitted to the front-stage rotor disc and the rear-stage rotor disc through the front decomposition plate and the rear decomposition plate, so that the front-stage rotor disc and the rear-stage rotor disc are disassembled.

Description

Tool for disassembling rotor disc of aircraft engine

Technical Field

The utility model relates to a tool for disassembling a rotor disc of an aircraft engine.

Background

As shown in fig. 1, the aircraft engine compressor rotor is formed by a plurality of rotor disks 1'. The diameters of the central holes of the rotor discs 1 'of all stages are different, and the thicknesses of the rotor discs 1' of all stages are also different greatly. In the process of assembling the aircraft engine rotor, in order to ensure the concentric installation of the rotor disks 1 'of each stage, the adjacent rotor disks 1' of two stages are matched through interference rabbets. And adjacent two stages of rotor disks 1' are connected by short bolts. The aero-engine rotor disc 1 'is generally decomposed by overcoming the friction force at the interference seam allowance by using a special decomposition tool under the influence of thermal stress after the aero-engine works, and the seam allowance connection tightness between the adjacent rotor discs 1' is increased. As shown in fig. 2, the conventional disassembling device is shown in patent application No. CN201811014980.5 "a disassembling device for primary disk of fan rotor of engine". The primary disk disassembling device 2 ' of the existing engine fan rotor takes a disk center web plate of a rotor disk 1 ' to be disassembled as a force application point, and a plurality of pulling claws are driven by a screw rod or a pressure cylinder to pull out the rotor disk 1 ' to be disassembled from a connecting seam of an adjacent disk. Because the number of stages of the aeroengine rotor discs 1 ' is more, the diameters and the thicknesses of inner holes of the rotor discs 1 ' of all stages are different, and the existing claw pulling type decomposing device is difficult to simultaneously satisfy the decomposition of the rotor discs 1 ' of different stages. For the disassembly requirements of the rotor disks 1' with different apertures and thicknesses, disassembly devices with various specifications are often manufactured. The decomposers with various specifications are similar in shape but different in specification, so that the decomposers with different specifications are easily misused, and the rotor disc 1' cannot be decomposed. The conventional disassembling device with the claw structure has higher manufacturing cost and management cost and inconvenient operation because of no universality.

SUMMERY OF THE UTILITY MODEL

The utility model aims to overcome the defect that the operation for decomposing an aircraft engine rotor disc in the prior art is complex, and provides an aircraft engine rotor disc decomposition tool.

The utility model solves the technical problems through the following technical scheme:

an aircraft engine rotor disc disassembly tool, comprising:

a front decomposition plate having a first face for abutting against a preceding stage rotor disk;

the wedge centering mechanism comprises a wedge driving part and two centering rods, the two centering rods are coaxially and symmetrically arranged, the wedge driving part is arranged between the two centering rods, the wedge driving part comprises two first inclined planes which are oppositely arranged, the two centering rods are respectively abutted against the two first inclined planes, and the wedge driving part drives the centering rods to move along the axial direction of the centering rods through the first inclined planes;

a rear decomposition plate disposed parallel to the front decomposition plate;

the force applying mechanism is connected to the front decomposition plate and the rear decomposition plate, can apply a load perpendicular to the rear decomposition plate between the front decomposition plate and the rear decomposition plate, and is arranged at the symmetrical centers of the two centering rods.

In this scheme, through setting up preceding division board and being used for leaning on in the preceding stage rotor dish, set up slide wedge centering mechanism and be used for confirming the disk center position of rotor dish, set up the back division board and lean on in the back stage rotor dish, the mechanism of applying force is used for applying load respectively so that the two separates to preceding stage rotor dish and back stage rotor dish, avoids leading to the unable dismantlement of back stage rotor dish because of the load of the mechanism of applying force because of the decentraction, easy operation improves the dismantlement efficiency of rotor dish.

Preferably, one end of the centering rod is provided with a second inclined surface corresponding to the wedge driving part, and the second inclined surface is attached to the first inclined surface.

In this scheme, through setting up the second inclined plane at the terminal surface of centering rod, the second inclined plane laminating is in first inclined plane to increase the area of contact of centering rod and slide wedge drive division, reduce the contact pressure between centering rod and the slide wedge drive division, resistance when reducing slide wedge drive division drive centering rod reduces slide wedge actuating mechanism's operating resistance, improves the ease for use of aeroengine rotor dish decomposition tool.

Preferably, the slide wedge centering mechanism further comprises a limiting column, the limiting column is fixedly connected to the first surface, the limiting column is arranged on two sides of the centering rod, and the limiting column limits the movement direction of the centering rod.

In this scheme, through set up spacing post in centering rod both sides, spacing post restriction centering rod direction of motion makes the centering rod can only move along the axial direction of centering rod, reduces the centering error because of the removal error of centering rod produces, improves the accuracy degree of slide wedge centering mechanism centering.

Preferably, the wedge centering mechanism further comprises an anti-falling rod, and the anti-falling rod is arranged at the top of the limiting column.

In this scheme, the first face of preventing falling pole, spacing post and preceding decomposition board carries on spacingly to the centering rod jointly, avoids leading to the centering rod to drop from slide wedge centering mechanism because of the change of slide wedge centering mechanism angle in the use, improves the stability of centering rod installation.

Preferably, the cam centering mechanism further comprises a rebound spring, two ends of the rebound spring are respectively connected to the two centering rods, and the rebound spring is in a stretching state.

In this scheme, through setting up the centering rod of the taut both sides of resilience spring, when the slide wedge drive division withdraws from along the axial direction of perpendicular to centering rod backward, the tensioning force effect of the resilience spring of the centering rod of both sides moves to the slide wedge drive division down, and need not manually to push back the centering rod, improves the convenience that aeroengine rotor disc decomposition tool used.

Preferably, the cam centering mechanism further comprises a centering wheel and an adapter rod, the adapter rod is fixedly connected to the end portion of the centering rod, and the centering wheel is pivoted to the adapter rod.

In the scheme, the end parts of the two centering rods are respectively provided with the centering wheels, and the centering wheels are used for contacting the inner wall of the disk centering hole of the rotor disk in the centering process; compared with a centering rod, the contact surface between the centering wheel and the inner wall of the central hole of the rotor disc is larger, and the centering deviation caused by too small contact area is reduced.

Preferably, the tool for disassembling a rotor disc of an aircraft engine further comprises a driving mechanism, the driving mechanism comprises a fixing plate and a driving rod, the driving rod is movably connected to the fixing plate, the driving rod can move relative to the fixing plate, the fixing plate is fixedly connected to the front disassembling plate, and one end of the driving rod is connected to the wedge driving portion.

In this scheme, through setting up fixed plate and actuating lever, the actuating lever passes through threaded connection in the fixed plate, and the tip swing joint of actuating lever in slide wedge drive division moves on the axis direction of perpendicular to centering rod through rotatory actuating lever drive slide wedge drive division to promote the centering rod and lean on or keep away from the inner wall in rotor dish heart hole, need not manual promotion slide wedge drive division, improve slide wedge centering mechanism's ease for use.

Preferably, the rear decomposition plate is provided with a force application through hole, and the force application mechanism passes through the force application through hole of the rear decomposition plate and abuts against the front decomposition plate.

In this scheme, connect through setting up afterburning through-hole and afterburning mechanism, afterburning mechanism can pass back decomposition board and can transmit the load for preceding decomposition board, offers afterburning through-hole simple structure and need not extra load transmission on the decomposition board of back, has simplified the structure of afterburning mechanism.

Preferably, the front decomposition plate is provided with a force application blind hole, and the force application mechanism abuts against the force application blind hole of the front decomposition plate.

In this scheme, the load of mechanism of applying force passes through the movable rod and transmits preceding division board through afterburning blind hole, through setting up afterburning blind hole and movable rod phase-match, afterburning pole and preceding division board need not extra connection structure, and the two is connected simply, improves the reliability that movable rod and preceding division board are connected, avoids exerting the in-process at the load and leading to the unable accurate condition emergence of transmitting preceding division board of load because of movable rod and preceding division board slippage.

Preferably, the force applying mechanism comprises a fixed rod and a movable rod, the movable rod can move relative to the fixed rod, the fixed rod penetrates through the force applying through hole, the diameter of the movable rod is matched with that of the force applying blind hole, and the movable rod abuts against the force applying blind hole.

In this scheme, through setting up dead lever and the movable rod that can the relative activity, the decomposition plate removes before the load passes through the movable rod drive, and at the decomposition in-process, dead lever fixed connection is in back decomposition plate, and the movable rod supports and leans on in the preceding decomposition plate, simple structure, and the load is applyed reliably.

Preferably, the force applying mechanism comprises a hydraulic force applying rod.

In this scheme, through selecting for use hydraulic pressure application of force pole as straining device, hydraulic pressure application of force pole has that load output is big, output steady advantage, need not operating personnel manual application load, has improved aeroengine rotor dish decomposition tool's ease of use, has reduced operating personnel's intensity of labour.

The positive progress effects of the utility model are as follows:

according to the tool for disassembling the rotor disc of the aircraft engine, the center of the rotor disc is determined by the wedge centering mechanism, the load of the stress application mechanism is transmitted to the front-stage rotor disc and the rear-stage rotor disc through the front decomposition plate and the rear decomposition plate, the decomposition of the front-stage rotor disc and the rear-stage rotor disc is realized, the problem that the rear-stage rotor disc cannot be disassembled due to the fact that the load of the stress application mechanism is not concentric is avoided, the operation is simple, and the disassembling efficiency of the rotor disc is improved.

Drawings

FIG. 1 is a schematic structural view of an aircraft engine multi-stage rotor disk.

Fig. 2 is a schematic structural diagram of a conventional aircraft engine fan rotor disk decomposition device.

FIG. 3 is a schematic view of an aircraft engine rotor disk disassembly tool of the present invention disassembling a rotor disk.

FIG. 4 is an exploded view of the aircraft engine rotor disk disassembly tool of the present invention.

Fig. 5 is a schematic structural view of a first perspective of a forward decomposition plate and a wedge centering mechanism of an aircraft engine rotor disk decomposition tool of the present invention.

Fig. 6 is a second perspective structural schematic view of a forward decomposition plate and a cam centering mechanism of an aircraft engine rotor disk decomposition tool of the present invention.

Fig. 7 is a third perspective structural view of a forward decomposition plate and a wedge centering mechanism of an aircraft engine rotor disk decomposition tool of the present invention.

Fig. 8 is a schematic structural view of a front disassembly plate of the tool for disassembling a rotor disk of an aircraft engine according to the utility model.

Description of reference numerals:

in the prior art:

rotor disk 1'

Primary wheel disc decomposing device 2 'of engine fan rotor'

In the utility model:

aircraft engine rotor disk disassembly tool 100

Front decomposition plate 1

First side 11

Stress application blind hole 12

Wedge centering mechanism 2

Cam driving part 21

First inclined plane 211

Centering rod 22

Spacing post 23

Anti-drop bar 24

Resilient spring 25

Centering wheel 26

Adapter rod 27

Rear decomposition plate 3

Forcing through hole 31

Stress application mechanism 4

Fixing rod 41

Movable rod 42

Drive mechanism 5

Fixed plate 51

Drive rod 52

Preceding stage rotor disk 200

Rear stage rotor disk 300

Detailed Description

The utility model is further illustrated by the following examples, which are not intended to limit the scope of the utility model.

As shown in fig. 4, the present invention provides a tool 100 for disassembling a rotor disk of an aircraft engine, which comprises a front disassembling plate 1, a wedge centering mechanism 2, a rear disassembling plate 3 and a force applying mechanism 4.

The front decomposition plate 1 has a first face 11, the first face 11 being intended to abut against a front stage rotor disk 200. The front decomposition plate 1 is plate-shaped, and two opposing faces are provided in the thickness direction of the front decomposition plate 1, and when the front stage rotor disk 200 and the rear stage rotor disk 300 are decomposed, the first face 11 is abutted against the front stage rotor disk 200, and the load of the urging means 4 is transmitted to the front stage rotor disk 200 through the first face 11.

The cam centering mechanism 2 comprises a cam driving part 21 and two centering rods 22, the two centering rods 22 are coaxially and symmetrically arranged, and the cam driving part 21 is arranged between the two centering rods 22. The whole isosceles triangle that has certain thickness of slide wedge drive division 21, slide wedge drive division 21 include two relative first inclined planes 211 that set up, and two equal limits department of slide wedge drive division 21 are first inclined plane 211, and the symmetry axis symmetry setting of the relative slide wedge drive division 21 of two first inclined planes 211. The two centering rods 22 respectively abut against the two first inclined surfaces 211. The centering rod 22 is a straight rod, and the center axis of the centering rod 22 is perpendicular to the symmetry axis of the cam driving unit 21. The wedge driving part 21 drives the centering rods 22 to move along the axial direction of the centering rods 22 through the first inclined planes 211, when the wedge driving part 21 is pushed along the width direction of the front decomposition plate 1, the first inclined planes 211 at two sides of the wedge driving part 21 push the centering rods 22 at two sides to move for the same distance towards the direction far away from the symmetry axis of the wedge driving part 21, so that the distance from the end parts of two ends of the two centering rods 22 to the symmetry axis of the wedge driving part 21 is the same in the moving process, and the two centering rods 22 are arranged at the center of the width direction of the front decomposition plate 1, so that the symmetry centers of the two centering rods 22 coincide with the geometric center of the front decomposition plate 1. When the two centering bars 22 abut against the inner walls of the disk center holes of the preceding rotor disk 200, respectively, the disk centers of the disk center holes of the preceding rotor disk 200 and the centers of symmetry of the centering bars 22 coincide.

The rear decomposition plate 3 is disposed parallel to the front decomposition plate 1, and the overall shape of the rear decomposition plate 3 is the same as that of the front decomposition plate 1. When used to disassemble forward stage rotor disk 200 and aft stage rotor disk 300, aft disassembly plate 3 is used to abut aft stage rotor disk 300. The force applying mechanism 4 transfers the load to the rear stage rotor disk 300 through the rear decomposition plate 3, the force applying mechanism 4 transfers the load to the front stage rotor disk 200 through the front decomposition plate 1, and the two decomposition plates move in opposite directions, respectively, thereby disassembling the front stage rotor disk 200 and the rear stage rotor disk 300.

The urging mechanism 4 is connected to the front decomposition plate 1 and the rear decomposition plate 3. The urging mechanism 4 is capable of applying a load perpendicular to the rear decomposition plate 3 between the front decomposition plate 1 and the rear decomposition plate 3. In this embodiment, the forcing mechanism 4 is disposed at the symmetric center of the two centering rods 22, after the centering rods 22 at two sides move towards two ends respectively and abut against the hole walls of the disk center hole of the preceding rotor disk 200, the symmetric center of the centering rod 22 after centering is the center of the disk center hole of the preceding rotor disk 200. The urging means 4 is cylindrical as a whole, and the axial line of the urging means 4 is provided at the disk center hole of the preceding rotor disk 200. The load direction of the force applying means 4 is also along the axial line direction of the force applying means 4, and is applied to the front stage rotor disk 200 and the rear stage rotor disk 300 by the front resolving plate 1 and the rear resolving plate 3, respectively, to move the front stage rotor disk 200 and the rear stage rotor disk 300 in opposite directions, thereby separating the rear stage rotor disk 300 and the front stage rotor disk 200. The load is applied along the axial lead direction of the stress application mechanism 4, so that the situation that the rear-stage rotor disc 300 cannot be pulled out from the interference seam allowance due to eccentricity in the moving process is avoided.

As shown in fig. 7, one end of the centering rod 22 is provided with a second inclined surface (not shown) corresponding to the wedge driving part 21, and the second inclined surface is fitted to the first inclined surface 211. An included angle between the first inclined surface 211 and a symmetrical central axis of the wedge driving part 21 is named as a first included angle; the angle between the second inclined surface and the axis of the centering rod 22 is named second angle. The first included angle and the second included angle are complementary angles with each other, so that the centering rod 22 and the wedge driving part 21 are abutted together through the first inclined surface 211 and the second inclined surface, and the axis of the centering rod 22 is perpendicular to the central symmetry axis of the wedge driving part 21. When the cam driving part 21 moves along the central symmetry axis thereof, the cam driving part 21 drives the centering rod 22 to always move in a direction perpendicular to the central symmetry axis of the cam driving part 21 through the first inclined surface 211 and the second inclined surface.

As shown in fig. 8, the cam centering mechanism 2 further includes a limiting column 23, the limiting column 23 is fixedly connected to the first surface 11, the limiting column 23 is disposed on two sides of the centering rod 22, four limiting columns 23 are mounted on the first surface 11, and the limiting columns 23 are mounted on two sides of one of the centering rods 22 respectively. The whole of spacing post 23 is the cuboid, and the side laminating of spacing post 23 is in the side of centering rod 22, and spacing post 23 limits the direction of motion of centering rod 22, sets up and prescribes a limit to the spacing post 23 of centering rod 22 both sides and prescribes a limit to centering rod 22 and can only follow the axis direction motion of centering rod 22. The limiting column 23 is fixedly connected to the first surface 11 through a bolt.

As shown in fig. 6, the cam centering mechanism 2 further includes a drop-preventing bar 24, and the drop-preventing bar 24 is a cross bar. The number of the drop prevention bars 24 is two. The anti-falling rod 24 is arranged at the top of the limiting column 23, and the anti-falling rod 24 is arranged at the top of the limiting column 23 at two sides of the centering rod 22. Through holes are respectively formed in two ends of the anti-falling rod 24, and the anti-falling rod 24 is respectively connected to the limiting columns 23 through the through holes in the two ends. Therefore, two limiting columns 23 are respectively arranged on two sides of the centering rod 22, the front decomposition plate 1 is arranged at the bottom of the centering rod 22, and the anti-falling rod 24 is arranged at the top of the centering rod 22. Under the above restriction, the moving direction of the centering rod 22 is defined as the direction along the axis of the centering rod 22.

As shown in fig. 6 and 7, the cam centering mechanism 2 further includes a resilient spring 25, two ends of the resilient spring 25 are respectively provided with two connecting buckles, and in contrast, a connecting column is provided at one end of the centering rod 22 close to the cam driving portion 21, the connecting buckles are sleeved on the connecting column, and two ends of the resilient spring 25 are respectively connected to the two centering rods 22. The length of the rebound spring 25 in a natural state is smaller than the distance between the connecting columns on the two centering bars 22, so that when the two ends of the rebound spring 25 are connected to the connecting columns on the centering bars 22, the rebound spring 25 is in a stretched state. When the wedge driving part 21 forwards decomposes the plate 1 and moves away from the edge of the fixed plate 51, the wedge driving part 21 drives the two centering rods 22 to move towards two sides under the action of overcoming the pulling force of the rebound spring 25; when the cam driving part 21 moves toward the side of the forward decomposition plate 1 where the fixed plate 51 is installed, the two centering rods 22 move toward the center of the forward decomposition plate 1 by the tensile force of the resilient spring 25.

The cam centring mechanism 2 further comprises a centring wheel 26 and an adapter rod 27. The number of the centering wheels 26 is two, and two centering wheels 26 are provided at the ends of the two centering bars 22, respectively. Two centering wheels 26 are arranged parallel to the front decomposition plate 1. One end of the centering rod 22 is provided with an adapter rod 27 perpendicular to the front decomposition plate 1, the adapter rod 27 passes through the center of the centering wheel 26, and the centering wheel 26 can rotate around the adapter rod 27. The adapter rod 27 is fixedly connected to the end of the centering rod 22, and the centering wheel 26 is pivoted to the adapter rod 27. In the use process, the wedge driving part 21 drives the centering rods 22 to move towards two ends, the moving directions of the two centering rods 22 are opposite, the moving speeds are the same, and the distances from the ends of the two centering rods 22 to the symmetrical centers of the two centering rods are always the same. Until after the centering wheel 26 abuts against the inner wall of the hub hole of the preceding rotor disk 200, the geometric centers of the two centering bars 22 are now at the hub of the preceding rotor disk 200.

The aircraft engine rotor disk disassembly tool 100 also includes a drive mechanism 5. The drive mechanism 5 includes a fixed plate 51 and a drive lever 52. The whole board that is the bending of fixed plate 51, fixed plate 51's one end fixed connection is in preceding decomposition plate 1, has seted up the screw hole on the fixed plate 51, is equipped with the external screw thread on the actuating lever 52, and the actuating lever 52 passes through threaded connection fixed plate 51 to actuating lever 52 is on a parallel with preceding decomposition plate 1 setting. The driving rod 52 is movably connected to the fixing plate 51, the driving rod 52 can move relative to the fixing plate 51, the fixing plate 51 is fixedly connected to the front decomposition plate 1, one end of the driving rod 52 is connected to the wedge driving portion 21, the driving rod 52 moves relative to the fixing plate 51 and drives the wedge driving portion 21 to move towards the side close to or far away from the front decomposition plate 1 and far away from the fixing plate 51 through rotating the driving rod 52, and then the driving rod 52 drives the centering rod 22 to move towards two sides through the wedge driving portion 21.

As shown in fig. 4, the rear decomposition plate 3 has a force application through hole 31 formed in the center thereof. The urging mechanism 4 is abutted against the front decomposition plate 1 through an urging through-hole 31 of the rear decomposition plate 3. In this embodiment, the hole wall of the urging through hole 31 of the rear decomposition plate 3 is formed with a female screw, and the urging means 4 is formed with a male screw. The stressing mechanism 4 and the rear decomposition plate 3 are connected by screw tightening. When the device is used, the stress application mechanism 4 is connected with the rear decomposition plate 3 by screwing the stress application mechanism 4 and the rear decomposition plate 3. The force application means 4 outputting different loads can be replaced according to the size of the rotor disc to be dismounted. Through threaded connection simple structure, it is convenient and connect reliably to dismantle the change. The load of the force applying mechanism 4 is transmitted to the rear decomposition plate 3 through the screw thread, and a large load can be reliably transmitted through the screw thread. In other embodiments, the force applying mechanism 4 may also be fixedly connected with the rear decomposition plate 3 by means of interference connection.

As shown in fig. 5, the front decomposition plate 1 is provided with a force application blind hole 12. The forcing mechanism 4 is abutted against the forcing blind hole 12 of the front decomposition plate 1. The force application blind hole 12 is opened on the surface of the front decomposition plate 1 opposite to the first surface 11, and the force application blind hole 12 does not completely penetrate through the front decomposition plate 1. The diameter of the force application blind hole 12 is the same as that of the force application mechanism 4 and one end abutting against the front decomposition plate 1, so that the force application mechanism 4 extends into the force application blind hole 12 on the front decomposition. The stressing mechanism 4 transmits the load to the front decomposition plate 1 through the stressing blind hole 12. The force applying mechanism 4 is clamped into the force applying blind hole 12, so that the force applying mechanism 4 is prevented from deviating to one side of the front decomposition plate 1 due to load deviation, and the reliability of load transmission is improved. And the force application blind hole 12 is arranged, so that the force application mechanism 4 is conveniently separated from the front decomposition plate 1, and the usability of the aircraft engine rotor disc decomposition tool 100 is improved.

As shown in fig. 3, the force applying mechanism 4 includes a fixed bar 41 and a movable bar 42, and the movable bar 42 is movable relative to the fixed bar 41. The fixing rod 41 is inserted through the force application through hole 31. The fixing rod 41 is externally threaded, the force application through hole 31 is internally threaded, and the fixing rod 41 is screwed to the force application through hole 31 through threads. The threaded connection prevents play between the fixing rod 41 and the rear decomposition plate 3 in the axial direction of the fixing rod 41 during use. The diameter of the movable rod 42 is matched with that of the stress application blind hole 12, and the movable rod 42 abuts against the stress application blind hole 12. The movable rod 42 abuts against the thrust blind hole 12, and the movable rod 42 transmits the load to the front decomposition plate 1 through the thrust blind hole 12, so that the front-stage rotor disc 200 and the rear-stage rotor disc 300 are detached and separated.

The force applying mechanism 4 comprises a hydraulic force applying rod. The hydraulic forcing rod transfers the load to the front decomposition plate 1 through the movable rod 42, and the fixed rod 41 and the forcing through hole 31 of the rear decomposition plate 3 are connected by screw. The relative positions of both the fixing lever 41 and the rear decomposition plate 3 are kept unchanged by pushing the front decomposition plate 1 to move in a direction away from the rear decomposition plate 3. 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 pressure force application rod is respectively transmitted to the front-stage rotor disc 200 and the rear-stage rotor disc 300 through the front decomposition plate 1 and the rear decomposition plate 3, so that the front-stage rotor disc 200 and the rear-stage rotor disc 300 are decomposed and disassembled. In the present embodiment, the force applying mechanism 4 comprises a hydraulic force applying rod, and in other embodiments, the force applying mechanism 4 may also comprise a pneumatic force applying rod, which does not need liquid as a load transfer medium and has the advantages of cleanness and easy operation. In other embodiments, the force applying mechanism 4 may also be a screw mechanism, the fixed rod 41 and the movable rod 42 are connected by a screw thread, and the screw mechanism has the advantages of simple structure, high reliability, no need of an additional power source, and the like by rotating the movable rod 42 relative to the fixed rod 41.

As shown in fig. 3, the disassembly of the rotor disk is completed:

s1, as shown in FIG. 4, completing the assembly of the aircraft engine rotor disc disassembling tool 100;

s2, as shown in fig. 3, placing the front decomposition plate 1 with the cam centering mechanism 2 obliquely, passing through the center hole of the rear stage rotor disk 300, and horizontally placing on the center rear end face of the front stage rotor disk 200;

s3, screwing the driving rod 52 on the wedge centering mechanism 2, the driving rod 52 driving the wedge driving part 21 to push the centering rods 22 on both sides, so that the centering rods 22 on both sides synchronously move outward along the axial direction at the same time, and the centering wheel 26 mounted at the end of the centering rod 22 simultaneously contacts with the inner wall of the disk center hole of the preceding stage rotor disk 200;

s4, continuing to screw the driving rod 52, so that the two centering wheels 26 abut against the inner wall surface of the disk center hole of the preceding rotor disk 200;

s5, placing the rear decomposition plate 3 into the cavity of the rear-stage rotor disc 300 after inclining;

s6, installing the force applying mechanism 4 in the force applying through hole 31 of the rear decomposition plate 3;

s7, adjusting the position of the force applying mechanism 4 to enable the movable rod 42 of the force applying mechanism 4 to be positioned in the force applying blind hole 12 of the front decomposition plate 1;

s8, pressurizing the force application mechanism 4, and driving the rear decomposition plate 3 to tightly abut against the rear end face of the disk center hole of the rear-stage rotor disk 300;

and S9, continuing pressurizing until the rear-stage rotor disc 300 is ejected.

While specific embodiments of the utility model have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the utility model, and these changes and modifications are within the scope of the utility model.

Claims (11)

1. An aircraft engine rotor disc disassembly tool, characterized in that it comprises:

a front decomposition plate having a first face for abutting against a preceding stage rotor disk;

the wedge centering mechanism comprises a wedge driving part and two centering rods, the two centering rods are coaxially and symmetrically arranged, the wedge driving part is arranged between the two centering rods, the wedge driving part comprises two first inclined planes which are oppositely arranged, the two centering rods are respectively abutted against the two first inclined planes, and the wedge driving part drives the centering rods to move along the axial direction of the centering rods through the first inclined planes;

a rear decomposition plate disposed parallel to the front decomposition plate;

the force applying mechanism is connected to the front decomposition plate and the rear decomposition plate, can apply a load perpendicular to the rear decomposition plate between the front decomposition plate and the rear decomposition plate, and is arranged at the symmetrical centers of the two centering rods.

2. The tool for disassembling a rotor disc of an aircraft engine according to claim 1, wherein one end of the centering rod is provided with a second inclined surface corresponding to the driving portion of the tapered wedge, the second inclined surface being attached to the first inclined surface.

3. The aircraft engine rotor disc disassembly tool of claim 1, wherein the cam pin centering mechanism further comprises a limiting post fixedly connected to the first face, the limiting post disposed on both sides of the centering rod, the limiting post limiting the direction of movement of the centering rod.

4. The aircraft engine rotor disc disassembly tool of claim 3, wherein the cam wedge centering mechanism further comprises a drop prevention rod disposed on top of the spacing post.

5. The aircraft engine rotor disc disassembly tool of claim 1, wherein the cam centering mechanism further comprises a rebound spring, both ends of the rebound spring are respectively connected to the two centering rods, and the rebound spring is in a stretched state.

6. The aircraft engine rotor disc disassembly tool of claim 1, wherein the cam centering mechanism further comprises a centering wheel and an adapter rod, the adapter rod being fixedly connected to an end of the centering rod, the centering wheel being pivotally connected to the adapter rod.

7. The tool for disassembling an aircraft engine rotor disc according to claim 1, further comprising a driving mechanism, wherein the driving mechanism includes a fixing plate and a driving rod, the driving rod is movably connected to the fixing plate, the driving rod is movable relative to the fixing plate, the fixing plate is fixedly connected to the front disassembling plate, and one end of the driving rod is connected to the wedge driving portion.

8. The tool for disassembling a rotor disc of an aircraft engine according to claim 1, wherein the rear disassembling plate is provided with a force applying through hole, and the force applying mechanism passes through the force applying through hole of the rear disassembling plate and abuts against the front disassembling plate.

9. The tool for disassembling a rotor disc of an aircraft engine according to claim 8, wherein the front disassembling plate is provided with a blind thrust-applying hole, and the thrust-applying mechanism abuts against the blind thrust-applying hole of the front disassembling plate.

10. The tool for disassembling a rotor disc of an aircraft engine of claim 9, wherein the force applying mechanism includes a fixed bar and a movable bar, the movable bar is capable of moving relative to the fixed bar, the fixed bar is disposed through the force applying through hole, a diameter of the movable bar matches a diameter of the force applying blind hole, and the movable bar abuts against the force applying blind hole.

11. An aircraft engine rotor disc disassembly tool according to any of claims 1 to 10, wherein the force applying mechanism comprises a hydraulic force applying rod.

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