CN215942769U - Tool for disassembling rotor disc of aircraft engine - Google Patents

Abstract

The utility model discloses a tool for disassembling a rotor disc of an aircraft engine, which comprises a front disassembling plate, a rear disassembling plate, a centering mechanism and a force application mechanism, wherein the front disassembling plate is arranged on the front end of the rotor disc; the front decomposition plate is used for abutting against a front-stage rotor disc; the rear decomposition plate is used for abutting against a rear stage rotor disc; the centering mechanism is arranged on the front decomposition plate and used for quickly determining the center of a front-stage rotor disc and dominating the center to the axis of the stress application mechanism; the force applying mechanism is connected with the front decomposition plate and the rear decomposition plate, and a force perpendicular to the rear decomposition plate is applied to the force applying mechanism to realize the decomposition of the rear-stage rotor disk. According to the tool for disassembling the rotor disc of the aircraft engine, the centering mechanism is suitable for the rotor discs with different apertures, and has universality; the structure is simple, the rapid installation and the disassembly are convenient, and the operation of disassembling the rotor disc is simple; in the decomposition process, the load applied by the force applying mechanism is in the axial direction of the rotor disc, the stress of the rotor disc is uniform, and the rotor disc to be decomposed cannot be pulled to be deviated so as not to be decomposed.

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 composed of multiple stages of rotor disks 1 ', the diameters of the core holes of the rotor disks 1 ' of each stage are different, and the thicknesses of the rotor disks 1 ' of each stage are also greatly different. 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 hole diameters, 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 defects that tools for disassembling an aircraft engine rotor disc in the prior art are not universal and are complex to operate, and provides a tool for disassembling an aircraft engine rotor disc.

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

an aircraft engine rotor disk disassembly tool, comprising:

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

the centering mechanism is arranged on the front decomposition plate and comprises a rotary disc, two connecting rods, two centering parts and a driving device, the rotary disc is arranged on the first surface and can rotate around the axis of the rotary disc, the two centering parts are arranged on the first surface and are symmetrical relative to the central axis of the rotary disc, the rotary disc is provided with a first hinge point and a second hinge point which are symmetrical relative to the central axis of the rotary disc, one end of one connecting rod is hinged to the first hinge point, the other end of the connecting rod is hinged to one centering part, one end of the other connecting rod is hinged to the second hinge point, the other end of the other connecting rod is hinged to the other centering part, the driving device is connected with the rotary disc, and the driving device is used for driving the rotary disc to rotate so as to drive the two centering parts to be relatively close to or far away from each other;

a rear breaker plate disposed parallel to the front breaker plate, the rear breaker plate for abutting against a rear stage rotor disk;

a force applying mechanism connected to the front decomposition plate and the rear decomposition plate, the force applying mechanism being capable of applying a load perpendicular to the rear decomposition plate to the front decomposition plate and the rear decomposition plate.

In the scheme, the centering mechanism is used for determining the center of the rotor disc, the two centering parts are used for contacting with the rotor disc, and the connecting rods are rotationally symmetrical about the central axis of the rotor disc through the arrangement of hinge points by arranging the two centering parts at symmetrical positions about the central axis of the rotor disc so as to realize that the central axis of the rotor disc is coincident with the central axis of the rotor disc when in positioning; the driving device drives the turntable to rotate and drives the two centering parts to be away from or close to each other through the connecting rod, so that the distance adjustment between the two centering parts is realized, and the tool can be used for positioning and decomposing rotor discs with different apertures, thereby realizing the universality of the tool for decomposing the rotor discs of the aircraft engine; the front decomposition plate abuts against a front-stage rotor disc, the rear decomposition plate abuts against a rear-stage rotor disc, the front decomposition plate and the rear decomposition plate are connected through a force application mechanism, the centering mechanism is installed on the front decomposition plate, and the decomposition tool structure of the rotor disc of the aircraft engine is simple, so that the rapid disassembly and assembly are facilitated; in the process of decomposition, the stress 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, so that the rotor discs are decomposed, the operation of the rotor discs is convenient, and the decomposition is stable and reliable.

Preferably, the front decomposition plate and the rear decomposition plate have two dimensions smaller than the diameter of the disk center of the rotor disk.

In the scheme, the tool for disassembling the rotor disc of the aero-engine is divided into a front disassembling plate, a rear disassembling plate and a force applying mechanism, the front disassembling plate and the rear disassembling plate can penetrate through the rotor disc, the centering mechanism is mounted on the front disassembling plate and can also penetrate through the rotor disc along with the front disassembling plate, and the tool for disassembling the rotor disc of the aero-engine is convenient to mount and dismount quickly.

Preferably, the force applying mechanism comprises a fixed rod and a movable rod, the movable rod can move relative to the fixed rod, the movable rod is connected with the front decomposition plate, the joint of the movable rod and the front decomposition plate coincides with the center of the turntable, and the fixed rod is connected with the rear decomposition plate.

In the scheme, the fixed rod and the movable rod which can move relatively are arranged, in the decomposition process, the fixed rod is connected with the rear decomposition plate, and the movable rod is connected with the front decomposition plate, so that the structure is simple, and the rapid disassembly and assembly and the rotor disc decomposition are convenient; in the decomposition process, the central axis of the rotor disc is superposed with the central axis of the turntable, and the joint of the movable rod and the front decomposition plate is superposed with the center of the turntable, so that the center of the rotor disc is dominantly arranged on the axis of the movable rod of the stress application mechanism; in the process of decomposing the rotor disc, the central shaft of the rotor disc is overlapped with the central shaft of the movable rod, so that the load applied by the stress application mechanism is ensured in the direction of the central shaft of the rotor disc, the stress of the rotor disc is uniform in the process of decomposing, and the rotor disc to be decomposed cannot be deviated by pulling to cause incapability of decomposing.

Preferably, the front decomposition plate is connected with the movable rod through a concave-convex structure.

In the scheme, the concave-convex structure is arranged on the front decomposition plate, so that the rapid installation of the decomposition tool of the rotor disc of the aircraft engine is facilitated, and the reliability of the connection between the front decomposition plate and the stress application mechanism is ensured; and through the concave-convex structure matching part matching size, the central shaft of the turntable can be ensured to coincide with the axis of the force application mechanism movable rod.

Preferably, a through hole is formed in the middle of the rear decomposition plate, an internal thread is formed in the through hole, an external thread is formed in the fixing rod, and the fixing rod penetrates through the through hole and is connected with the through hole through a thread.

In the scheme, the through hole is formed in the middle of the rear decomposition plate, so that the stress application mechanism can penetrate through the rear decomposition plate through the through hole to be connected with the front decomposition plate conveniently; when the rotor disc is disassembled, the force applying mechanism is connected with the rear decomposing plate through threads and is fixed on the rear decomposing plate.

Preferably, the force applying mechanism comprises a hydraulic lever.

In this scheme, through selecting for use the hydraulic stem as the energizing mechanism, the hydraulic stem 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 for use, has reduced operating personnel's intensity of labour.

Preferably, the centering mechanism further comprises a guide member, the guide member is mounted on the first surface, the guide member is used for limiting the centering portion and forms a first moving pair with the centering portion, and the direction of freedom of the first moving pair is consistent with the direction of a connecting line of the two centering portions.

In the scheme, the guide piece is arranged for restraining the motion direction of the centering part, a moving pair is formed between the guide piece and the centering part, the centering part is connected with the turntable through the connecting rod, the rotation of the turntable is converted into the linear movement of the centering part, and the device has the characteristics of flexible and stable transmission; the centering parts can move, the relative distance between the two centering parts is adjustable, and the effect that the centering mechanism can be suitable for rotor discs with different sizes is achieved, so that the universality of the tool for disassembling the rotor discs of the aircraft engine is realized; by setting the freedom direction of the sliding pair to be consistent with the connecting line direction of the two centering parts, when the centering mechanism is used for decomposing different rotor disks, the relative distance between the two centering parts changes, and the disk center of the front-stage rotor disk always coincides with the connecting line center of the two centering parts, namely the center of the rotary disk, so that the centering reliability of the centering mechanism is ensured.

Preferably, the guide member has a guide surface thereon, the guide surface being perpendicular to the first surface and parallel to a line connecting the two centering portions.

In the scheme, the guide surface is used for ensuring that the centering part can move along the connecting line direction of the two centering parts and limiting the transverse movement of the centering part.

Preferably, the guide member has a limiting surface, the limiting surface is parallel to the first surface, and the limiting surface is used for positioning the centering portion on the front decomposition plate.

In the scheme, the limiting surface is used for restraining the centering part between the front decomposition plate and the limiting surface, and the centering part is ensured not to fall off from the front decomposition plate.

Preferably, the guide member is provided with a gap in a direction perpendicular to a connecting line of the two centering portions, the centering portions are hinged to the connecting rod at the first hinge point by a hinge member, and a size of the hinge member is smaller than a size of the gap.

In the scheme, the guide piece is provided with the gap, so that the guide piece can not interfere with the movement of the connecting rod in the moving process of the centering part.

Preferably, the portion of the centering portion for contact with the forward stage rotor disk is semi-cylindrical in shape.

In the scheme, the outer side of the centering part is semi-cylindrical, and the arc-shaped centering part is convenient to contact with the wall of the disc center hole of the rotor disc; when the semi-cylindrical centering parts on the outer sides abut against different rotor disks, the positions on the circle center connecting line of the semi-cylindrical centering parts of the two centering parts are contacted with the rotor disks, so that the disk centers of the different rotor disks can be coincided with the center of the connecting line of the centering parts, namely the center of the rotating disk, and the centering reliability of the centering mechanism is ensured.

Preferably, the driving device comprises a positioning block, a screw rod, a driving block and a push rod, the positioning block is fixed on the front decomposition plate, the screw rod is connected with the positioning block through threads, the screw rod is installed on the driving block, one end of the push rod is hinged on the driving block, and the other end of the push rod is hinged on the turntable.

In the scheme, the screw rod is arranged on the front decomposition plate through the positioning block and rotates to drive the driving block and the push rod to move so as to drive the turntable to rotate, so that the centering parts are driven to move, and the distance between the two centering parts is adjusted; the screw drive is adopted, the screw drive has a self-locking function, and the driving block and the centering part can be locked at any position in the stroke, so that the device is stable and reliable; the conversion of rotary motion and linear motion, the transmission form is nimble, is convenient for the structural arrangement installation.

Preferably, the front decomposition plate is provided with a second surface, the second surface is adjacent to the first surface, and the positioning block is fixed on the second surface.

In the scheme, the driving device is fixed on the side surface of the front decomposition plate through the positioning block, so that the operation space is wide and visible, and the operation is convenient.

Preferably, the driving block is mounted on the front decomposition plate through a guide structure and forms a second moving pair with the front decomposition plate, and the direction of freedom of the second moving pair is consistent with the axial direction of the screw.

In the scheme, the driving block and the front decomposition plate form a moving pair, and when the screw rod is rotated, the driving block can move along with the screw rod.

Preferably, the driving block is provided with a clamping groove, and the driving block is mounted on the front decomposition plate through the clamping groove and can slide along the front decomposition plate.

In this scheme, the drive block is installed in the front and is decomposed the board and slide along preceding decomposition board, and preceding decomposition board has the spacing and the direction function of drive block concurrently to make compact structure.

Preferably, the front decomposition plate is provided with an anti-falling groove, the extension direction of the anti-falling groove is consistent with the axial direction of the screw, the driving block is provided with an anti-falling device, and the anti-falling device is fixed on the driving block and is arranged in the anti-falling groove.

In this scheme, through anticreep device, prevent that the drive block from breaking away from in the past decomposing the board, guarantee that the drive block can only follow the side translation of decomposing the board.

Preferably, the driving device further comprises a stopper, the driving block is provided with a positioning hole, and the screw rod is mounted on the driving block through the positioning hole and the stopper

In this scheme, the through-hole on the driving block is used for cooperating with the screw rod, and the dog is used for retraining the screw rod on the driving block, when rotating the screw rod, can promote or pull the driving block and follow the screw rod and move together.

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

according to the tool for disassembling the rotor disc of the aero-engine, the distance between two centering parts in the centering mechanism, which are in contact with the rotor disc, is adjustable, the tool is suitable for rotor discs with different apertures, and the universality of the tool for disassembling the rotor disc of the aero-engine is realized; the tool for disassembling the rotor disc of the aero-engine is divided into a front disassembling plate, a rear disassembling plate and a force applying mechanism, the front disassembling plate and the rear disassembling plate can penetrate through the rotor disc, the structure is simple, the tool for disassembling the rotor disc of the aero-engine is convenient to mount and dismount quickly, and the manufacturing cost is low; the center of the rotor disc and the center of the rotary disc are overlapped and dominantly arranged on the axis of the movable rod of the force application mechanism through the centering mechanism, the load applied by the force application mechanism is ensured to be in the axis direction of the rotor disc, the stress of the rotor disc is uniform in the decomposition process, and the rotor disc to be decomposed cannot be deviated by pulling to cause incapability of decomposition.

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 prior art primary disk disassembling device for a fan rotor of an engine.

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 from a first perspective of a front breaker plate and a centering mechanism of the aircraft engine rotor disk breaker tool of the present invention.

Fig. 6 is a structural schematic diagram of a second perspective of a front breaker plate and a centering mechanism of the aircraft engine rotor disk breaker tool of the present invention.

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

Fig. 8 is a schematic cross-sectional view of a front disassembly plate and a centering mechanism of the aircraft engine rotor disk disassembly tool of the utility model.

Fig. 9 is an exploded view of the centering mechanism of the aircraft engine rotor disk disassembly tool of the present invention.

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:

an aircraft engine rotor disk disassembly tool 1000,

the forward stage rotor disk 1, the aft stage rotor disk 2,

a force applying mechanism 30, a fixed rod 31, a movable rod 32, a movable rod boss 33, a hydraulic rod 34,

a rear decomposition plate 40, a rear decomposition plate through hole 41,

a front decomposition plate 50, a first face 51, a second face 52, a center hole 53, a groove 54, a slip-off preventing groove 55,

the centering mechanism (100) is provided with a centering mechanism,

a centering part 110, a centering boss 111, a Z-shaped plate 120, a guide surface 121, a limiting surface 122, a gap 123, a first bolt 131,

a first hinge point 201, a second hinge point 202, a rotary disc 210, a first boss 211, a second boss 212, a connecting rod 220, a fixed shaft 231, a baffle ring 232,

the driving device 300, the screw 310, the end 311, the positioning block 320, the push rod 330, the driving block 340, the clamping groove 341, the positioning hole 342, the driving block boss 343, the retaining ring 351, the anti-slip bolt 352 and the second bolt 353

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. 3-9, the present invention provides an aircraft engine rotor disk disassembly tool 1000 comprising a force application mechanism 30, an aft disassembly plate 40, a forward disassembly plate 50, and a centering mechanism 100.

As shown in fig. 3, the front decomposition plate 50 has a first face 51 thereon, and the first face 51 on the front decomposition plate 50 abuts against the front stage rotor disk 1. The rear decomposition plate 40 is arranged parallel to the front decomposition plate 50, the rear decomposition plate 40 abutting on the rear stage rotor disk 2. The front and rear resolving plates 50 and 40 have two dimensions smaller than the diameters of the centers of the front and rear rotor disks 1 and 2, and the front and rear resolving plates 50 and 40 are inclined to pass through holes at the centers of the front and rear rotor disks 1 and 2. The centering mechanism 100 is disposed on the front decomposition plate 50, and can be quickly placed on the disk center hole of the front stage rotor disk 1 after the front decomposition plate 50 is inclined, so as to quickly determine the center of the front stage rotor disk 1 and to make the center of the front stage rotor disk 1 dominant.

As shown in fig. 3 to 4, a rear decomposition plate through hole 41 is formed in the middle of the rear decomposition plate 40. The urging mechanism 30 is connected to the front stage rotor disk 1 after passing through the rear decomposition plate through-hole 41, and is connected to the rear decomposition plate 40 at the rear decomposition plate through-hole 41. The force applying mechanism 30 includes a fixed bar 31 and a movable bar 32, and the movable bar 32 can move relative to the fixed bar 31. The end of the movable rod 32 is provided with a movable rod boss 33, the front decomposition plate 50 is provided with a groove 54, the groove 54 is used for rapidly positioning the stress application mechanism 30, and the movable rod 32 and the front decomposition plate 50 are connected through the movable rod boss 33 and the groove 54. The through hole 41 of the rear decomposition plate and the fixing rod 31 are provided with matching threads, and the force applying mechanism 30 and the rear decomposition plate 40 are connected with the threads of the through hole 41 of the rear decomposition plate through the fixing rod 31.

As shown in fig. 5 to 6, the centering mechanism 100 includes two centering portions 110, a turntable 210, two links 220, and a driving device 300.

The front decomposition plate 50 is provided with a central hole 53, the turntable 210 is matched with the central hole 53 through a fixed shaft 231, and the turntable 210 is mounted on the front decomposition plate 50, so that the turntable 210 can only rotate around the axis of the turntable 210.

A centering portion 110 is mounted on the first surface 51 of the front decomposition plate 50 by a first bolt 131 and two symmetrically arranged Z-shaped plates 120, the Z-shaped plates 120 being guide members of the centering portion 110, the Z-shaped plates 120 forming a moving pair with the centering portion 110. As shown in fig. 9, one surface of the Z-shaped plate 120 is a guide surface 121, the guide surface 121 is used for guiding the centering portions 110, and the guide surface 121 is perpendicular to the first surface 51 and parallel to a line connecting the two centering portions 110, so that the centering portions 110 can only move along the line connecting the two centering portions 110, and the centering portions 110 can be prevented from moving laterally. Meanwhile, one surface of the Z-shaped plate 120 is a limiting surface 122, the limiting surface 122 is parallel to the first surface 51, the centering portion 110 is located between the limiting surface 122 and the first surface 51, and the limiting surface 122 is used for preventing the centering portion 110 from falling off from the front decomposition plate 50. The connecting line direction of the two centering parts 110 is consistent with the length direction of the front decomposition plate 50, so that the centering mechanism can conveniently pass through the centers of the front-stage rotor disc 1 and the rear-stage rotor disc 2 together with the front decomposition plate 50. The connecting rod 220 is hinged with the centering part 110 through a centering boss 111; a gap 123 is formed between the two Z-shaped plates 120 for mounting one centering portion 110, and the size of the gap 123 is larger than that of the centering boss 111, thereby preventing the Z-shaped plates 120 from interfering with the hinge, i.e., the centering boss 111. The side surface of the centering portion 110 is semi-cylindrical, so as to ensure that the center of the front stage rotor disc 1 contacting with the centering portion 110 coincides with the center of the rotating disc 210, thereby ensuring the centering reliability of the centering mechanism.

As shown in fig. 6-9, the turntable has two first bosses 211 corresponding to the first hinge point 201 and the second hinge point 202, respectively, the two first bosses 211 are symmetrical about the central axis of the turntable 210, and the connecting rod 220 is hinged to the turntable through the first bosses 211 and the baffle ring 232. The centering portion 110 has a centering boss 111, and the connecting rod 220 is hinged to the centering portion 110 through the centering boss 111 and the retainer ring 232. The two centering parts 110 are symmetrically arranged about the central axis of the turntable 210, and the two first bosses 211 on the turntable 210 are symmetric about the central axis of the turntable 210, so that the two connecting rods 220 are rotationally symmetric about the central axis of the turntable 210. When the driving device 300 drives the turntable 210 to rotate, the two centering portions 110 move closer to or away from each other along the connecting line of the two centering portions 110 under the pushing or pulling action of the connecting rod 220.

As shown in fig. 6, 7 and 9, the driving device 300 includes a screw 310, a positioning block 320, a push rod 330 and a driving block 340, wherein the positioning block 320 is fixed on the second surface 52 of the front decomposition plate 50 by a second bolt 353. The driving block 340 is provided with a slot 341, the driving block 340 is mounted on the edge of the front decomposition plate 50 through the slot 341 and can slide along the edge of the front decomposition plate 50, and the front decomposition plate 50 also serves as a positioning member and a guiding structure for the driving block 340. The screw 310 is engaged with the positioning block 320 through a screw thread, and the end 311 of the screw 310 passes through the positioning hole 342 of the driving block 340 and is mounted on the driving block 340 through the stop ring 351. One end of the push rod 330 is hinged to the driving block 340 through the driving block boss 343 and the catch ring 232 on the driving block 340, and the other end of the push rod 330 is hinged to the turntable 210 through the second boss 212 and the catch ring 232. The anti-dropping device of the driving block 340 is a bolt 352 and an anti-dropping groove 55, the bolt 352 is connected with the driving block 340 through a thread and extends into the anti-dropping groove 55 of the front decomposition plate 50 after passing through a threaded hole of the driving block 340, so as to prevent the driving block 340 from dropping from the side surface of the front decomposition plate 50. The driving device 300 is installed on the second surface 52 of the front decomposition plate 50, the second surface 52 is adjacent to the first surface 51, and the operation space is widely visible for convenient operation.

When the screw 310 is rotated, the screw 310 moves along the axis direction thereof, and drives the driving block 340 to slide along the edge of the front decomposition plate, so that the push rod 330 drives the turntable 210 to rotate, and further drives the connecting rod 220 to move, and finally drives the two centering portions 110 to move close to or away from each other along the connecting line direction of the two centering portions 110, thereby realizing the adjustment of the distance between the two centering portions 110.

The center of the preceding rotor disc 1 is determined as the symmetrical center of the two centering parts 110, namely the center of the turntable 210, by the contact of the two centering parts 110 and the center of the preceding rotor disc 1, the central axis of the turntable 210 coincides with the central axis of the groove 54 and the central hole 53, and the groove 54 is connected with the movable rod 32 of the force applying mechanism 30, so that the center of the preceding rotor disc 1 is quickly positioned to the center of the turntable 210 and is obviously positioned on the axis of the movable rod 32. 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 disk center axis of the front stage rotor disk 1 coincides with the axis of the movable rod 32 of the force applying mechanism 30, so that the front stage rotor disk 1 and the rear stage rotor disk 2 are uniformly stressed in the decomposition process, and the rear stage rotor disk 2 is not pulled to be deviated, so that the decomposition cannot be performed.

As shown in fig. 3, in the present embodiment, the urging mechanism 30 includes a hydraulic rod 34. The hydraulic rod is selected as the stress application mechanism, so that the hydraulic rod has the advantages of large load output and stable output, the manual application of load by operators is not needed, the usability of the tool for disassembling the rotor disc of the aircraft engine is improved, and the labor intensity of the operators is reduced. And the fixing rod 31 and the rear decomposition plate through hole 41 of the rear decomposition plate 40 are connected by screw, the relative positions of the fixing rod 31 and the rear decomposition plate 40 are maintained. The forward decomposition plate 50 abuts the forward stage rotor disk 1 and the aft decomposition plate 40 abuts the aft 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 fixed rod 31, and 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, thereby realizing the decomposition and disassembly of the front stage rotor disk 1 and the rear stage rotor disk 2.

In the present embodiment, the force applying mechanism 30 is driven by the hydraulic rod 34, but in other embodiments, the force applying mechanism 30 may also be driven by other schemes existing in the prior art, such as a pneumatic rod, which does not need liquid as a load transmission medium and has the characteristics of cleanness and easy operation. Of course, the force applying mechanism 30 may also be driven by a screw mechanism, the fixed rod 31 and the movable rod 32 are connected by a screw thread, and the movable rod 32 is rotated relative to the fixed rod 31, so that the screw mechanism has the advantages of simple structure, high reliability, no need of an additional power source, and the like.

As shown in fig. 3 to 9, the disassembling tool provided in the present embodiment can complete the disassembling of the front stage rotor disk 1 and the rear stage rotor disk 2 according to the following steps:

s1, as shown in FIGS. 5-9, completing the assembly of the aircraft engine rotor disc disassembling tool 1000;

s2, as shown in fig. 3, placing the front decomposition plate 50 with the centering mechanism 100 obliquely, passing through the center hole of the rear stage rotor disk 2, and horizontally placing on the center end face of the front stage rotor disk 1, and ensuring that the first face 51 of the front decomposition plate 50 contacts with the front stage rotor disk 1;

s3, rotating the screw 310, pushing the driving block 340 to move radially outward along the front stage rotor disc 1, driving the turntable 210 to rotate through the push rod 330, further pushing the two centering portions 110 to move away from each other through the connecting rod 220, and simultaneously contacting and abutting the cylindrical head of the centering portion 110 against the inner wall of the hub hole of the front stage rotor disc 1;

s4, placing the rear decomposition plate 40 into cavities of the front-stage rotor disc 1 and the rear-stage rotor disc 2 after inclining;

s5, installing the force applying mechanism 30 in the threaded connecting hole of the through hole 41 of the rear decomposition plate on the rear decomposition plate 40;

s6, adjusting the position of the force applying mechanism 30 with the rear decomposition plate 40 to enable the movable rod boss 33 of the force applying mechanism 30 to be positioned in the groove 54 of the front decomposition plate 50;

s7, loading the hydraulic rod 34 of the force applying mechanism 30, and driving the rear decomposition plate 40 to abut against the rear end face of the rear-stage rotor disc 2;

s8, the hydraulic ram 34 continues to be loaded until the rear stage rotor disk 2 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 (17)

1. An aircraft engine rotor disk disassembly tool, comprising:

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

the centering mechanism is arranged on the front decomposition plate and comprises a rotary disc, two connecting rods, two centering parts and a driving device, the rotary disc is arranged on the first surface and can rotate around the axis of the rotary disc, the two centering parts are arranged on the first surface and are symmetrical relative to the central axis of the rotary disc, the rotary disc is provided with a first hinge point and a second hinge point which are symmetrical relative to the central axis of the rotary disc, one end of one connecting rod is hinged to the first hinge point, the other end of the connecting rod is hinged to one centering part, one end of the other connecting rod is hinged to the second hinge point, the other end of the other connecting rod is hinged to the other centering part, the driving device is connected with the rotary disc, and the driving device is used for driving the rotary disc to rotate so as to drive the two centering parts to be relatively close to or far away from each other;

a rear breaker plate disposed parallel to the front breaker plate, the rear breaker plate for abutting against a rear stage rotor disk;

a force applying mechanism connected to the front decomposition plate and the rear decomposition plate, the force applying mechanism being capable of applying a load perpendicular to the rear decomposition plate to the front decomposition plate and the rear decomposition plate.

2. The aircraft engine rotor disc disassembly tool of claim 1, wherein the forward and aft disassembly plates have two directional dimensions that are smaller than a diameter of the rotor disc core.

3. The tool for disassembling a rotor disc of an aircraft engine as claimed in claim 1, wherein the force applying mechanism comprises a fixed bar and a movable bar, the movable bar is capable of moving relative to the fixed bar, the movable bar is connected to the front disassembling plate, the joint of the movable bar and the front disassembling plate coincides with the center of the rotor disc, and the fixed bar is connected to the rear disassembling plate.

4. The aircraft engine rotor disc disassembly tool of claim 3, wherein the forward disassembly plate is connected to the movable rod by a male-female structure.

5. The tool for disassembling a rotor disc of an aircraft engine of claim 3, wherein a through hole is formed at a middle position of the rear disassembling plate, an internal thread is formed on the through hole, an external thread is formed on the fixing rod, and the fixing rod passes through the through hole and is connected with the through hole through a thread.

6. The aircraft engine rotor disk disassembly tool of claim 1, wherein the force application mechanism comprises a hydraulic ram.

7. The tool for disassembling a rotor disc of an aircraft engine according to claim 1, characterized in that the centering mechanism further comprises a guide element mounted on the first face, the guide element being used for limiting the centering portion and forming a first kinematic pair with the centering portion, and the direction of freedom of the first kinematic pair being coincident with the direction of the line connecting the two centering portions.

8. The tool for disassembling a rotor disc of an aircraft engine according to claim 7, characterized in that said guide element has a guide surface thereon, said guide surface being perpendicular to said first surface and parallel to the line connecting two of said centering portions.

9. The aircraft engine rotor disc disassembly tool of claim 7, wherein the guide has a limiting surface thereon, the limiting surface being parallel to the first surface, the limiting surface being for positioning the centering portion on the front disassembly plate.

10. The tool for disassembling a rotor disc of an aircraft engine according to claim 7, characterized in that said guide is provided with a clearance in a direction perpendicular to a line connecting two said centering portions, said centering portions being hinged to said connecting rod at said first hinge point by means of a hinge having a dimension smaller than that of said clearance.

11. The tool for disassembling a rotor disc of an aircraft engine according to claim 7, characterized in that the portion of the centering portion intended to come into contact with the preceding rotor disc is semi-cylindrical in shape.

12. The tool for disassembling a rotor disc of an aircraft engine according to claim 1, wherein the driving device includes a positioning block, a screw, a driving block, and a push rod, the positioning block is fixed on the front disassembling plate, the screw is connected with the positioning block through a thread, the screw is mounted on the driving block, one end of the push rod is hinged on the driving block, and the other end of the push rod is hinged on the rotary disc.

13. The aircraft engine rotor disc disassembly tool of claim 12, wherein the forward disassembly plate has a second face thereon, the second face being adjacent to the first face, the locating block being secured to the second face.

14. The aircraft engine rotor disc disassembly tool of claim 12, wherein the drive block is mounted on the forward disassembly plate by a guide structure and forms a second sliding pair with the forward disassembly plate, the direction of freedom of the second sliding pair being aligned with the axial direction of the screw.

15. The aircraft engine rotor disc disassembly tool of claim 14, wherein the drive block defines a slot, and the drive block is mounted on the forward disassembly plate via the slot and is slidable along the forward disassembly plate.

16. The tool for disassembling a rotor disc of an aircraft engine according to claim 14, wherein the front disassembling plate is provided with a disengagement preventing groove, the extension direction of the disengagement preventing groove is the same as the axial direction of the screw, and the driving block is provided with a disengagement preventing device, and the disengagement preventing device is fixed on the driving block and is installed in the disengagement preventing groove.

17. The aircraft engine rotor disc disassembly tool of claim 12, wherein the drive assembly further comprises a stop, the drive block defines a positioning hole, and the screw is mounted to the drive block through the positioning hole and the stop.

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