CN214560502U - A bush puller for aircraft engine maintenance - Google Patents
A bush puller for aircraft engine maintenance Download PDFInfo
- Publication number
- CN214560502U CN214560502U CN202120368137.8U CN202120368137U CN214560502U CN 214560502 U CN214560502 U CN 214560502U CN 202120368137 U CN202120368137 U CN 202120368137U CN 214560502 U CN214560502 U CN 214560502U
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- CN
- China
- Prior art keywords
- sleeve
- fixedly connected
- bush
- aircraft engine
- puller
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000012423 maintenance Methods 0.000 title claims abstract description 17
- 238000007789 sealing Methods 0.000 claims description 8
- 238000013016 damping Methods 0.000 claims description 7
- 210000001503 joint Anatomy 0.000 claims description 5
- 230000008439 repair process Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model relates to an aircraft engine repair tools technical field just discloses a bush puller for aircraft engine maintenance, which comprises a sleeve, the equal fixedly connected with quantity in the upper and lower both ends of sleeve inboard is a plurality of dead levers, and is two sets of from beginning to end fixedly connected with lantern ring between the relative one side of dead lever, the inboard swing joint of the lantern ring has the thread bush, the equal threaded connection in both ends has the screw rod about the thread bush is inboard, two the equal fixedly connected with gag lever post in one side that the screw rod carried on the back mutually, the one end fixedly connected with butt plate of screw rod is kept away from to the gag lever post, the driven awl tooth of the fixed surface of thread bush is connected with. This a bush puller for aircraft engine maintenance, overall structure is simple, places this puller in the bush to convert the revolving force of pivot into the butt force between butt plate and the bush inner wall, then through pulling this puller, can realize the dismantlement to the bush, easy and simple to handle, labour saving and time saving, it is convenient to use.
Description
Technical Field
The utility model relates to an aircraft engine repair tools technical field specifically is a bush puller for aircraft engine maintenance.
Background
The aircraft engine is a precise and highly complex thermal machine, is known as the heart of an aircraft as the 'industrial flower', and the performance, reliability and economy of the aircraft are directly affected by the quality of the aircraft engine, so that the aircraft engine is an important embodiment of national science and technology, industry and national defense strength.
The bush is an important component of an engine, has the effects of sealing, abrasion protection and the like, the existing bush puller for maintaining the aircraft engine on the market at present has the defect of inconvenience in use, when the engine is maintained, the bush on the engine needs to be disassembled, and the bush puller is difficult to disassemble without the help of tools due to the fact that the bush is tightly matched with the engine, and tools such as a screwdriver and the like are used for prying out the bush to easily damage the bush, are labor-consuming and inconvenient to use, so that the bush puller for maintaining the aircraft engine is provided to solve the problems.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
The utility model provides a not enough to prior art, the utility model provides a bush puller for aircraft engine maintenance possesses advantages such as convenient to use, has solved when the maintenance engine, needs dismantle the bush on the engine, because the bush is comparatively inseparable with the cooperation of engine, consequently hardly dismantles it under the condition without the help of instrument, uses instruments such as screwdrivers to prize out the bush and leads to the bush to damage easily, and comparatively hard, the problem of being not convenient for to use.
(II) technical scheme
In order to realize the purpose of convenient use, the utility model provides a following technical scheme: a bush puller for maintenance of an aircraft engine comprises a sleeve, wherein the upper end and the lower end of the inner side of the sleeve are fixedly connected with a plurality of fixed rods, a lantern ring is fixedly connected between one opposite sides of the front fixed rod and the rear fixed rod, the inner side of the lantern ring is movably connected with a threaded sleeve, the left end and the right end of the inner side of the threaded sleeve are respectively in threaded connection with a screw rod, one opposite side of the two screw rods is respectively and fixedly connected with a limiting rod, one end of the limiting rod, far away from the screw rods, is fixedly connected with a butt plate, the outer surface of the threaded sleeve is fixedly connected with a driven bevel gear, the front of the sleeve is movably connected with a sealing cover through a fixed bolt, the inner side of the sealing cover is movably connected with a rotating shaft, the back of the outer surface of the rotating shaft is fixedly connected with a driving bevel gear meshed with the driven bevel gear, the front of the rotating shaft is fixedly connected with a rotating disk, and the outer surface of the sleeve is movably connected with a fixed ring through a mounting bolt, the front of the fixed ring is fixedly connected with a pull rod.
Preferably, the sleeve is a cylinder with a hollow inner part and a missing front surface, and the number of the fixing rods is four.
Preferably, the outer surfaces of the two screws are fixedly connected with threads in opposite directions, and thread grooves matched with the threads on the outer surfaces of the two screws are formed in the left end and the right end of the inner side of the thread sleeve respectively.
Preferably, square through holes are formed in the left end and the right end of the sleeve, one end, far away from the screw rod, of the limiting rod penetrates through and extends to the outside of the square through holes, and the limiting rod is square.
Preferably, the butt joint board is the arc, the one end fixedly connected with damping rubber pad that the gag lever post was kept away from to the butt joint board.
Preferably, the pull rod is U-shaped, and the front of the outer surface of the pull rod is sleeved with the anti-skidding sleeve, and the outer surface of the anti-skidding sleeve is provided with the anti-skidding groove.
(III) advantageous effects
Compared with the prior art, the utility model provides a bush puller for aircraft engine maintenance possesses following beneficial effect:
1. the bushing puller for maintaining the aircraft engine is characterized in that a sleeve is placed on the inner side of the bushing, a rotating disc is rotated to drive a rotating shaft to rotate with a driving bevel gear, the back of the driving bevel gear is meshed with a driven bevel gear, the driven bevel gear drives a threaded sleeve to rotate, the outer surfaces of two screws are fixedly connected with threads in opposite directions, the left end and the right end of the inner side of the threaded sleeve are respectively provided with a thread groove matched with the threads on the outer surfaces of the two screws, the left end and the right end of the sleeve are respectively provided with a square through hole, one end of a limiting rod, far away from the screws, penetrates through and extends to the outer part of the square through hole, the limiting rod is square, the square through hole is matched with the limiting rod to limit the screws to do circular motion along with the threaded sleeve and enable the two screws to move towards one side opposite to the other side, so that the two screws are abutted against the inner wall of the bushing through an abutting plate and then pulling the pulling rod, and the device is simple in overall structure, the pulling tool is placed in the bushing, the rotating force of the rotating shaft is converted into the abutting force between the abutting plate and the inner wall of the bushing, and then the bushing can be detached by pulling the pulling tool, so that the pulling tool is simple and convenient to operate, time-saving and labor-saving, and convenient to use.
2. This a bush pulling tool for aircraft engine maintenance, through set up the rubber damping pad on butt plate, the effectual frictional force that has improved between butt plate and the bush inner wall makes it more stable, rubber damping pad also can protect the bush inner wall simultaneously, avoid dismantling the in-process of bush, cause the damage to the bush, through setting up fixing bolt and closing cap, the convenient to detach closing cap, and maintain sleeve inside, further improve the convenience when using.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a bottom view of the present invention;
fig. 3 is a perspective view of the screw rod and the limiting rod of the present invention.
In the figure: the device comprises a sleeve 1, a fixing rod 2, a lantern ring 3, a thread bush 4, a screw rod 5, a limiting rod 6, a butting plate 7, driven bevel teeth 8, a fixing bolt 9, a sealing cover 10, a rotating shaft 11, driving bevel teeth 12, a rotating disk 13, a mounting bolt 14, a fixing ring 15 and a pull rod 16.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-3, a bushing puller for maintaining an aircraft engine comprises a sleeve 1, wherein the upper end and the lower end of the inner side of the sleeve 1 are fixedly connected with a plurality of fixing rods 2, a lantern ring 3 is fixedly connected between the opposite sides of the front and the rear two groups of fixing rods 2, the inner side of the lantern ring 3 is movably connected with a threaded sleeve 4, the sleeve 1 is cylindrical, the inner side of the sleeve is hollow and the front side of the sleeve is absent, the number of the fixing rods 2 is four, the left end and the right end of the inner side of the threaded sleeve 4 are respectively in threaded connection with screw rods 5, the outer surfaces of the two screw rods 5 are respectively in threaded connection with threads in opposite directions, the left end and the right end of the inner side of the threaded sleeve 4 are respectively provided with threaded grooves matched with the outer surface threads of the two screw rods 5, one side of the two screw rods 5 opposite to each other is respectively in threaded connection with a limiting rod 6, the left end and the right end of the sleeve 1 are respectively provided with a square through hole, one end of the limiting rod 6, which is far away from the screw rods 5, penetrates through and extends to the outside of the square through holes, and gag lever post 6 is squarely, gag lever post 6 keeps away from one end fixedly connected with butt plate 7 of screw rod 5, butt plate 7 is the arc, the one end fixedly connected with damping rubber pad of gag lever post 6 is kept away from to butt plate 7, the external fixed surface of thread bush 4 is connected with driven awl tooth 8, there is closing cap 10 in the front of sleeve 1 through fixing bolt 9 swing joint, the inboard swing joint of closing cap 10 has pivot 11, the back fixedly connected with of pivot 11 surface and the initiative awl tooth 12 of driven awl tooth 8 engaged with, the positive fixedly connected with rotary disk 13 of pivot 11, the surface of sleeve 1 has solid fixed ring 15 through mounting bolt 14 swing joint, gu fixed ring 15's positive fixedly connected with pull rod 16, pull rod 16 is the U-shaped, and the front of pull rod 16 surface has cup jointed the antiskid cover, the antiskid groove has been seted up to the surface of antiskid cover.
To sum up, the bushing puller for maintaining the aircraft engine has the advantages that the sleeve 1 is placed on the inner side of the bushing, the rotating disc 13 is rotated to drive the rotating shaft 11 and the driving bevel gear 12 to rotate, the back of the driving bevel gear 12 is meshed with the driven bevel gear 8, the driven bevel gear 8 drives the threaded sleeve 4 to rotate, the outer surfaces of the two screws 5 are fixedly connected with threads in opposite directions, the left end and the right end of the inner side of the threaded sleeve 4 are respectively provided with thread grooves matched with the threads on the outer surfaces of the two screws 5, the left end and the right end of the sleeve 1 are respectively provided with a square through hole, one end of the limiting rod 6, which is far away from the screws 5, penetrates through and extends to the outer part of the square through hole, the limiting rod 6 is square, the square through hole is matched with the limiting rod 6 to limit the screws 5 to do circular motion along with the threaded sleeve 4 and enable the two screws 5 to move towards the opposite sides, so that the abutting plate 7 abuts against the inner wall of the bushing, then the pull rod 16 is pulled, the whole structure of the device is simple, the pulling tool is placed in the bushing, the rotating force of the rotating shaft 11 is converted into the abutting force between the abutting plate 7 and the inner wall of the bushing, then the bushing can be disassembled by pulling the pulling tool, the operation is simple and convenient, time and labor are saved, the use is convenient, the rubber damping pad is arranged on the abutting plate 7, the friction force between the abutting plate 7 and the inner wall of the bushing is effectively improved, the rubber damping pad can protect the inner wall of the bushing, the bushing is prevented from being damaged in the process of disassembling the bushing, the sealing cover 10 is convenient to disassemble by arranging the fixing bolt 9 and the sealing cover 10, the maintenance is carried out on the inside of the sleeve 1, the problem that the bushing on the engine needs to be disassembled when the engine is maintained is solved, and the bushing is matched with the engine tightly, therefore, the lining is difficult to disassemble without the help of tools, and the lining is easy to damage by prying the lining out by using tools such as a screwdriver and the like, and is difficult and inconvenient to use.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. A bush puller for aircraft engine maintenance, includes sleeve (1), its characterized in that: the upper end and the lower end of the inner side of the sleeve (1) are fixedly connected with a plurality of fixing rods (2), a lantern ring (3) is fixedly connected between one opposite side of the front fixing rod and the rear fixing rod (2), a threaded sleeve (4) is movably connected to the inner side of the lantern ring (3), screw rods (5) are respectively and threadedly connected to the left end and the right end of the inner side of the threaded sleeve (4), two opposite sides of the screw rods (5) are respectively and fixedly connected with a limiting rod (6), one end, far away from the screw rods (5), of the limiting rod (6) is fixedly connected with a butt joint plate (7), driven conical teeth (8) are fixedly connected to the outer surface of the threaded sleeve (4), a sealing cover (10) is movably connected to the front side of the sleeve (1) through a fixing bolt (9), a rotating shaft (11) is movably connected to the inner side of the sealing cover (10), and driving conical teeth (12) meshed with the driven conical teeth (8) are fixedly connected to the back side of the outer surface of the rotating shaft (11), the front of the rotating shaft (11) is fixedly connected with a rotating disc (13), the outer surface of the sleeve (1) is movably connected with a fixing ring (15) through a mounting bolt (14), and the front of the fixing ring (15) is fixedly connected with a pull rod (16).
2. A bushing puller for aircraft engine maintenance as defined in claim 1, wherein: the sleeve (1) is hollow and cylindrical, the front face of the sleeve is absent, and the number of the fixing rods (2) is four.
3. A bushing puller for aircraft engine maintenance as defined in claim 1, wherein: the outer surface of the two screw rods (5) is fixedly connected with threads in opposite directions, and thread grooves matched with the threads on the outer surfaces of the two screw rods (5) are formed in the left end and the right end of the inner side of the thread sleeve (4) respectively.
4. A bushing puller for aircraft engine maintenance as defined in claim 1, wherein: square through holes are formed in the left end and the right end of the sleeve (1), one end, far away from the screw rod (5), of the limiting rod (6) penetrates through and extends to the outer portion of the square through holes, and the limiting rod (6) is square.
5. A bushing puller for aircraft engine maintenance as defined in claim 1, wherein: the butt joint board (7) are arc-shaped, and one end fixedly connected with damping rubber pad of gag lever post (6) is kept away from to butt joint board (7).
6. A bushing puller for aircraft engine maintenance as defined in claim 1, wherein: the pull rod (16) is U-shaped, the front surface of the outer surface of the pull rod (16) is sleeved with an anti-slip sleeve, and the outer surface of the anti-slip sleeve is provided with an anti-slip groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120368137.8U CN214560502U (en) | 2021-02-10 | 2021-02-10 | A bush puller for aircraft engine maintenance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120368137.8U CN214560502U (en) | 2021-02-10 | 2021-02-10 | A bush puller for aircraft engine maintenance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214560502U true CN214560502U (en) | 2021-11-02 |
Family
ID=78350886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120368137.8U Expired - Fee Related CN214560502U (en) | 2021-02-10 | 2021-02-10 | A bush puller for aircraft engine maintenance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214560502U (en) |
-
2021
- 2021-02-10 CN CN202120368137.8U patent/CN214560502U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20211102 |