CN117424405B - Disassembly tools for turbojet engine motor rotors - Google Patents

Abstract

This application discloses a disassembly tool for a turbojet engine motor rotor, which includes: a barrel for inner sleeve on the inner hole; a plurality of arc-shaped force-applying parts having an arc-shaped body and located at the lower end of the arc-shaped body The top block and the first connecting block located at the upper end of the arc body; the bushing is used to insert the holding cylinder, the force applying member is located between the bushing and the holding cylinder, the upper end of the bushing has a second connecting block, and the hollow of the bushing The part has an internal thread section; the connecting piece is used to connect the first connecting block and the second connecting block; the screw is used to extend into the hollow part of the liner, and the screw is threaded with the internal thread section to limit the liner when working. By rotating the screw, the screw is brought into contact with the bottom wall of the inner hole. By further rotating the screw, the force-applying member and the bushing can be moved upward, and then the top block can be used to synchronously drive the rotor assembly to move upward. The disassembly of this application is smooth and the operation is simple. After use is completed, after loosening the connecting parts, the parts can be taken out in sequence without any damage to the impeller and rotor components.

Description

Disassembly tools for turbojet engine motor rotors

Technical field

The invention relates to a disassembly tool, in particular to a disassembly tool for a turbojet engine motor rotor.

Background technique

The turbojet engine impeller is equipped with a motor rotor component. The motor rotor is a thin-walled cylindrical part, which matches the inner hole of the impeller with a small gap and is connected with high-strength locking glue. When a component is damaged and needs repair, the motor rotor (magnet) needs to be removed from the inner hole of the impeller. The impeller and motor rotor are relatively precise. The motor rotor is compact in the impeller, has no force application point, and cannot be removed by force. Because the motor rotor is connected with locking glue, it is usually disassembled by heating to make the locking glue invalid. However, in order to ensure performance, the motor rotor is processed with special magnetic materials and has limited temperature resistance, so it cannot be disassembled by heating the entire part. Disable the locking glue.

That is, when disassembling the turbojet engine motor rotor, the following problems exist:

(1) The motor rotor is compact, the process is cumbersome and difficult to disassemble using common methods;

(2) Material breakage and damage may easily occur during the disassembly process.

Contents of the invention

In view of the above problems, the present invention overcomes at least one shortcoming and proposes a disassembly tool for a turbojet engine motor rotor.

The technical solutions adopted by the present invention are as follows:

A disassembly tool for a turbojet engine motor rotor, used to cooperate with an impeller. The impeller has an inner hole, and a rotor assembly is bonded to the inner hole. The disassembly tool for a turbojet engine motor rotor includes:

The holding tube is used to be placed on the inner hole. When the holding tube is placed on the inner hole, the outer wall of the holding tube is fit with the inner wall of the rotor assembly;

A plurality of arc-shaped force applying members. The force applying members have an arc-shaped body, a top block located at the lower end of the arc-shaped body, and a first connecting block located at the upper end of the arc-shaped body. The top block protrudes toward the outside of the arc-shaped body. It is configured that the force-applying member is used to extend into the inside of the holding cylinder, and the top block is used to contact and cooperate with the lower end of the rotor assembly after extending from the lower end of the holding cylinder;

The bushing is used to insert the holding cylinder. The force-applying member is located between the bushing and the holding cylinder, and the force-applying member is in contact with both the bushing and the holding cylinder. The upper end of the lining sleeve has a second connecting block. , the hollow part of the liner has an internal thread section;

A connecting piece used to connect the first connecting block and the second connecting block so that each force-applying member is fixed to the bushing;

The screw rod is used to extend into the hollow part of the liner. The screw rod is threaded with the internal thread section. When working, the liner is limited. By rotating the screw rod, the screw rod contacts the bottom wall of the inner hole. Further rotation of the screw can move the force-applying member and the bushing upward, and then the rotor assembly can be synchronously moved upward through the top block.

When this application is working, first insert the holding cylinder into the inner hole, and then pass each force-applying member through the holding cylinder respectively, so that the outer wall of the arc body is in close contact with the holding cylinder, and the top block protruding from the lower end of the holding cylinder forms a The reverse step is placed on the lower edge of the rotor assembly; then the assembly formed by the screw and the bushing is inserted between the force-applying parts, the circumferential position of the bushing and the force-applying parts is adjusted, and the bushing and the force-applying parts are connected through the connector. , then restrict the liner, and rotate the screw to make the screw contact the bottom wall of the inner hole. By further rotating the screw, the force-applying member and the liner can move upward, and then the top block can synchronously drive the rotor assembly upward and away from the impeller. .

This application applies the force point to the bottom wall of the inner hole of the impeller, and evenly places it on the edge of the thin-walled part (rotor assembly) through the arc-shaped top block. By twisting the screw, the torque is slowly and evenly applied to convert the rotational torque into an axial force component to disassemble the rotor assembly and the impeller. This application solves the problem of disassembling the rotor components of turbojet engine motors, especially for high-precision, thin-walled parts with no force-bearing surfaces that cannot be heated or cooled. This application has a smooth disassembly and is simple to operate. After use, after loosening the connector, the parts can be taken out one by one without any damage to the impeller and rotor assembly.

The outer wall of the holding cylinder of this application is smooth and in contact with the rotor assembly. The holding cylinder can protect the rotor assembly. When the rotor assembly moves upward, it is limited to the space formed by the inner hole and the holding cylinder; the function of the lining is to limit the movement of the rotor assembly. The radial position of the force member ensures that the force-applying member is in contact with both the bushing and the holding cylinder.

In this application, the rotor assembly can be made of magnetic steel, and the magnetic steel is fixed to the inner hole of the impeller through high-strength locking glue. In actual use, a small gap between the outer wall of the barrel and the inner wall of the rotor assembly also belongs to the fit mentioned in this application.

In one embodiment of the present invention, there are two force applying members, which are symmetrically arranged on both sides of the bushing.

In one embodiment of the present invention, a pressure block is installed on the lower end of the screw rod, and the screw rod contacts and cooperates with the bottom wall of the inner hole through the pressure block.

In one embodiment of the present invention, the pressure block has an anti-separation cavity, the upper end of the anti-separation cavity has a first threaded hole, and the lower end of the screw has a small diameter part and a large diameter part arranged in sequence from top to bottom, so The large-diameter part has an external thread, and the external thread of the large-diameter part is threadedly matched with the first threaded hole. The large-diameter part passes through the first threaded hole and enters the anti-separation cavity through relative rotation. The small diameter portion is used to rotate with the first threaded hole.

In this way, when the screw rotates, it will not drive the pressing block to rotate synchronously, which can prevent the screw from damaging the bottom wall of the inner hole.

In one embodiment of the present invention, a first handle is further provided on the second connecting block, and the first handle is provided for convenient holding during work so that the bushing does not rotate with the screw.

In one embodiment of the present invention, it also includes a second handle provided on the upper end of the screw rod. A second handle is provided to facilitate rotating the screw.

In one embodiment of the present invention, the connecting member is a bolt, the first connecting block has a second threaded hole, the second connecting block has a through hole corresponding to the second threaded hole, and the connecting member passes through the through hole and is threadedly connected to the corresponding second threaded hole.

In one embodiment of the present invention, the lower end surface of the barrel has a downwardly extending support rod, and the length of the support rod is greater than or equal to the thickness of the top block; the support rod is used to connect with the bottom of the inner hole. A space is formed between the walls for the top block to pass through.

The support rod is designed to quickly install the force-applying member in place.

In one embodiment of the present invention, two arc-shaped bodies are arranged correspondingly, and an arc-shaped elastic member is provided between the two arc-shaped bodies. The elastic member is convex upward or downward, and the elastic member is used to make the two arc-shaped bodies have a tendency to move away from each other.

Because there are multiple force-applying parts, the position between them needs to be adjusted, which is more inconvenient. This application can achieve automatic adjustment by setting elastic parts. During actual installation, the elastic parts are pressed to bring the two arc-shaped bodies closer to each other, and the top block can penetrate deep into the holding cylinder. When the top block passes through the lower end surface of the holding cylinder, the elastic part Under the action of , the two arc-shaped parts can be automatically moved away from each other and come into contact with the inner wall of the barrel.

In one embodiment of the present invention, there are multiple sets of limit bars on the barrel, each set of limit bars includes two spaced apart limit bars, and the force applying member is located on the corresponding set of two limit bars. between. Reliable positioning can be achieved through the limit strip.

The beneficial effects of the present invention are as follows: the present application applies the force point to the bottom wall surface of the inner hole of the impeller, and evenly places it on the edge of the thin-walled part (rotor assembly) through the arc-shaped top block. By twisting the screw, the torque is slowly and evenly applied to convert the rotational torque into an axial force component, and the rotor assembly and the impeller are decomposed. The present application solves the problem of disassembling the rotor components of turbojet engine motors, especially for the disassembly of high-precision, thin-walled parts with no force-bearing surfaces that cannot be heated or cooled. The present application has a smooth disassembly and is simple to operate. After use, the parts can be taken out one by one after loosening the connector without any damage to the impeller and the rotor assembly.

Description of drawings

Figure 1 is a schematic diagram of a disassembly tool for a turbojet engine motor rotor according to Embodiment 1;

Figure 2 is a cross-sectional view of the disassembly tool used for the turbojet engine motor rotor in Embodiment 1;

Figure 3 is an exploded view of the disassembly tool used for the turbojet engine motor rotor in Embodiment 1;

Figure 4 is a schematic diagram of the use of the disassembly tool for the turbojet engine motor rotor in Embodiment 1;

Figure 5 is a schematic diagram of two force applying members in Embodiment 2;

Figure 6 is a schematic diagram of the barrel holding tube in Embodiment 3;

Figure 7 is a schematic diagram of the force applying member installed on the holding cylinder in Embodiment 3;

Fig. 8 is a schematic diagram of a disassembly tool used for a turbojet engine motor rotor in Embodiment 4.

Each reference number in the figure is:

1. Impeller; 11. Inner hole; 12. Rotor assembly; 2. Holding tube; 21. Support rod; 22. Limiting strip; 3. Force-applying member; 31. Arc-shaped body; 32. Top block; 33. First connecting block; 331. Second threaded hole; 34. Elastic member; 4. Bushing; 41. Hollow part; 411. Internal thread section; 42. Second connecting block; 421. Through hole; 43. First handle; 5. Connecting member; 6. Screw; 61. Small diameter part; 62. Large diameter part; 621. External thread; 63. Second handle; 7. Pressing block; 71. Anti-slip cavity; 72. First threaded hole.

Detailed ways

In order to make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

In the description of this application, it should be noted that the orientation or positional relationship indicated by the terms "inside", "outer", etc. is based on the orientation or positional relationship shown in the drawings, or is the customary placement of the product of this application when in use. The orientation or positional relationship is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present application. In addition, the terms "first", "second", etc. are only used to differentiate descriptions and are not to be understood as indicating or implying relative importance.

In the description of this application, it should also be noted that, unless otherwise clearly stated and limited, the terms "setting" and "connection" should be understood in a broad sense. For example, it can be a fixed connection or a detachable connection, or Integrated connection; it can be directly connected, or indirectly connected through an intermediary, or it can be internal connection between two components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood on a case-by-case basis.

The present invention is described in detail below in conjunction with the accompanying drawings.

Example 1

As shown in Figures 1, 2, 3 and 4, a disassembly tool for a turbojet engine motor rotor is used to cooperate with the impeller 1. The impeller 1 has an inner hole 11, and a rotor assembly 12 is bonded to the inner hole 11. Removal tools for turbojet engine motor rotors include:

The holding cylinder 2 is used to be placed on the inner hole 11. When the holding cylinder 2 is placed on the inner hole 11, the outer wall of the holding cylinder 2 fits the inner wall of the rotor assembly 12;

A plurality of arc-shaped force-applying members 3. The force-applying member 3 has an arc-shaped body 31, a top block 32 located at the lower end of the arc-shaped body 31, and a first connecting block 33 located at the upper end of the arc-shaped body 31. The outer side of the body 31 is protrudingly arranged, the force-applying member 3 is used to extend into the inside of the barrel 2, and the top block 32 is used to extend from the lower end of the barrel 2 and then contact and cooperate with the lower end of the rotor assembly 12;

The bushing 4 is used to insert the holding cylinder 2. The force applying member 3 is located between the bushing 4 and the holding cylinder 2, and the force applying member 3 is in contact with both the bushing 4 and the holding cylinder 2. The upper end of the bushing 4 has a third Two connecting blocks 42, the hollow part 41 of the bushing 4 has an internal thread section 411;

A connecting member 5 is used to connect the first connecting block 33 and the second connecting block 42 so that each force applying member 3 is fixed to the liner 4;

The screw 6 is used to extend into the hollow part 41 of the liner 4. The screw 6 is threaded with the internal thread section 411. When working, the liner 4 is limited. By rotating the screw 6, the screw 6 contacts the bottom wall of the inner hole 11. By further rotating the screw 6, the force-applying member 3 and the bushing 4 can be moved upward, and then the top block 32 can synchronously drive the rotor assembly 12 to move upward.

When this application is working, first insert the holding tube 2 into the inner hole 11, and then put each force-applying member 3 through the holding tube 2 respectively, so that the outer wall of the arc body 31 is in close contact with the holding tube 2, and from the holding tube 2 The protruding top block 32 at the lower end forms a reverse step and rests on the lower edge of the rotor assembly 12; then the assembly formed by the screw 6 and the bushing 4 is inserted between the force-applying members 3, and the circumferences of the bushing 4 and the force-applying member 3 are adjusted. To the position, connect the bushing 4 and the force-applying member 3 through the connecting piece 5, and then limit the bushing 4. By rotating the screw 6, the screw 6 is in contact with the bottom wall of the inner hole 11. By further rotating the screw 6, the force can be applied. The component 3 and the bushing 4 move upward, and then the rotor assembly 12 is synchronously driven to move upward through the top block 32 and separate from the impeller 1.

In this application, the force application point is applied to the bottom wall surface of the inner hole 11 of the impeller 1, and the arc-shaped top block 32 is evenly placed on the edge of the thin-walled part (rotor assembly 12). By twisting the screw 6, the torque is slowly and evenly applied, and the torque is slowly and evenly applied. The rotational torque is converted into an axial force component, which decomposes the rotor assembly 12 and the impeller 1 . This application solves the problem of disassembly of turbojet engine motor rotor components, especially for the disassembly of high-precision, thin-walled parts that have no stress-bearing surface and cannot be heated or cooled. The disassembly of this application is smooth and the operation is simple. After use is completed, after loosening the connecting piece 5, the parts can be taken out in sequence without any damage to the impeller 1 and the rotor assembly 12.

The outer wall of the barrel 2 of this application is smooth and in contact with the rotor assembly 12. The barrel 2 can protect the rotor assembly 12. When the rotor assembly 12 moves upward, it is limited to the space formed by the inner hole 11 and the barrel 2; The function of the bushing 4 is to limit the radial position of the force-applying member 3 so that the force-applying member 3 contacts and cooperates with both the bushing 4 and the holding cylinder 2 .

In this application, the rotor assembly 12 can be made of magnetic steel, and the magnetic steel is fixed to the inner hole 11 of the impeller 1 through high-strength locking glue. In actual use, a small gap between the outer wall of the barrel 2 and the inner wall of the rotor assembly 12 also belongs to the fit mentioned in this application.

As shown in FIG. 3 , in this embodiment, there are two force applying members 3 , which are symmetrically arranged on both sides of the liner 4 .

As shown in Figures 2, 3 and 4, a pressure block 7 is installed on the lower end of the screw rod 6, and the screw rod 6 contacts and cooperates with the bottom wall of the inner hole 11 through the pressure block 7. In this embodiment, the pressure block 7 has an anti-separation cavity 71. The upper end of the anti-separation cavity 71 has a first threaded hole 72. The lower end of the screw 6 has a small diameter portion 61 and a large diameter portion 62 arranged in sequence from top to bottom. The diameter portion 62 has an external thread 621. The external thread 621 of the large diameter portion 62 is threadedly matched with the first threaded hole 72. The large diameter portion 62 passes through the first threaded hole 72 and enters the anti-separation chamber 71 through relative rotation. The small diameter portion 61 is To rotate with the first threaded hole 72 .

In this way, when the screw 6 rotates, it will not drive the pressure block 7 to rotate synchronously, which can prevent the screw 6 from damaging the bottom wall of the inner hole 11.

As shown in FIGS. 1 and 3 , this embodiment also includes a first handle 43 provided on the second connecting block 42 and a second handle 63 provided on the upper end of the screw rod 6 . The first handle 43 is provided to facilitate holding during work, so that the liner 4 does not rotate together with the screw 6; the second handle 63 is provided to facilitate the rotation of the screw 6.

As shown in Figures 2 and 3, in this embodiment, the connecting member 5 is a bolt, the first connecting block 33 has a second threaded hole 331, and the second connecting block 42 has a through hole opposite to the second threaded hole 331. hole 421, the connector 5 passes through the through hole 421 and is threadedly connected to the corresponding second threaded hole 331.

Example 2

As shown in Figure 5, the difference between this embodiment and Embodiment 1 is that two arc-shaped bodies 31 are arranged correspondingly, and there is an arc-shaped elastic member 34 between the two arc-shaped bodies 31. The elastic member 34 is convex upward or Protruding downward, the elastic member 34 is used to make the two arcs have a tendency to move away from each other.

Because there are multiple force-applying members 3, the positions between them need to be adjusted, which is inconvenient. This application can achieve automatic adjustment by arranging the elastic member 34. During actual installation, by pressing the elastic member 34 to bring the two arc-shaped bodies 31 closer to each other, the top block 32 can penetrate deep into the barrel 2. When the top block 32 passes out of the barrel 2 After the lower end surface, under the action of the elastic member 34, the two arc-shaped parts can be automatically moved away from each other and contacted with the inner wall of the barrel 2.

Example 3

As shown in Figures 6 and 7, the difference between this embodiment and Embodiment 1 is that the barrel 2 has multiple sets of limiting bars 22, and each set of limiting bars 22 includes two spaced apart limiting bars 22. Part 3 is located between the two limiting bars 22 of the corresponding group. Reliable positioning can be achieved through the limiting strip 22 .

Example 4

As shown in Figure 8, the difference between this embodiment and Embodiment 2 or 3 is:

The lower end surface of the barrel 2 has a support rod 21 extending downward. The length of the support rod 21 is greater than or equal to the thickness of the top block 32; the support rod 21 is used to form a gap with the bottom wall of the inner hole 11 to facilitate the passage of the top block 32. space.

The design of the support rod 21 enables the force applying member 3 to be quickly installed in place.

The above are only preferred embodiments of the present invention, and do not limit the scope of patent protection of the present invention. Any equivalent structural transformation made by using the description and drawings of the present invention can be directly or indirectly used in other related technical fields. All are similarly included in the protection scope of the present invention.

Claims (8)

1. A removal tool for a turbojet engine motor rotor for mating with an impeller having an inner bore with a rotor assembly bonded thereto, the removal tool comprising:

the holding cylinder is used for being sleeved on the inner hole, and when the holding cylinder is sleeved on the inner hole, the outer side wall of the holding cylinder is attached to the inner wall of the rotor assembly;

the force application pieces are provided with arc-shaped bodies, ejector blocks positioned at the lower ends of the arc-shaped bodies and first connecting blocks positioned at the upper ends of the arc-shaped bodies, the ejector blocks are arranged in a protruding mode towards the outer sides of the arc-shaped bodies, the force application pieces are used for extending into the holding cylinders, and the ejector blocks are used for being in contact fit with the lower ends of the rotor assemblies after extending out of the lower ends of the holding cylinders;

the lining is used for being inserted into the holding cylinder, the force application piece is positioned between the lining and the holding cylinder, the force application piece is in contact fit with the lining and the holding cylinder, the upper end of the lining is provided with a second connecting block, and the hollow part of the lining is provided with an internal thread section;

the connecting piece is used for connecting the first connecting block and the second connecting block, so that each force application piece is fixed with the lining cylinder;

the screw rod is used for extending into the hollow part of the lining barrel, the screw rod is in threaded fit with the internal thread section, the lining barrel is limited in working, the screw rod is rotated to enable the screw rod to be in contact with the bottom wall of the inner hole, the force application piece and the lining barrel can be moved upwards by further rotating the screw rod, and then the rotor assembly is synchronously driven to move upwards by the jacking block;

the lower end face of the holding cylinder is provided with a supporting rod extending downwards, and the length of the supporting rod is greater than or equal to the thickness of the top block; the supporting rod is used for forming a space which is convenient for the top block to pass through with the bottom wall of the inner hole;

the two arc bodies are correspondingly arranged, an arc-shaped elastic piece is arranged between the two arc bodies, the elastic piece is upwards convex or downwards convex, and the elastic piece is used for enabling the two arc bodies to have a movement trend away from each other.

2. The disassembling tool for a rotor of a turbojet engine according to claim 1, wherein the force applying members are provided in two, symmetrically arranged on both sides of the liner.

3. The disassembling tool for a motor rotor of a turbojet engine according to claim 1, wherein a pressing block is mounted at the lower end of the screw rod, and the screw rod is in contact fit with the bottom wall of the inner hole through the pressing block.

4. The disassembling tool for a motor rotor of a turbojet engine according to claim 3, wherein the pressing block is provided with an anti-drop cavity, the upper end of the anti-drop cavity is provided with a first threaded hole, the lower end of the screw rod is provided with a small-diameter part and a large-diameter part which are sequentially arranged from top to bottom, the large-diameter part is provided with external threads, the external threads of the large-diameter part are in threaded fit with the first threaded hole, the large-diameter part penetrates through the first threaded hole to enter the anti-drop cavity through relative rotation, and the small-diameter part is used for being in rotary fit with the first threaded hole.

5. The removal tool for a turbojet engine motor rotor of claim 1 further comprising a first handle disposed on the second connection block.

6. The removing tool for a turbojet engine motor rotor of claim 1 further comprising a second handle disposed at an upper end of the screw.

7. The dismounting tool for a turbojet engine motor rotor as claimed in claim 1, wherein the connecting piece is a bolt, a second threaded hole is formed in the first connecting block, a through hole opposite to the second threaded hole is formed in the second connecting block, and the connecting piece is in threaded connection with the corresponding second threaded hole after passing through the through hole.

8. The dismounting tool for a turbojet engine motor rotor as claimed in claim 1, wherein the holding cylinder is provided with a plurality of groups of limiting strips, each group of limiting strips comprises two limiting strips arranged at intervals, and the force application piece is positioned between the two limiting strips of the corresponding group.