CN220516374U - Auxiliary device for surface grinding of aircraft engine blade - Google Patents
Auxiliary device for surface grinding of aircraft engine blade Download PDFInfo
- Publication number
- CN220516374U CN220516374U CN202322127395.9U CN202322127395U CN220516374U CN 220516374 U CN220516374 U CN 220516374U CN 202322127395 U CN202322127395 U CN 202322127395U CN 220516374 U CN220516374 U CN 220516374U
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- holder
- engine blade
- aircraft engine
- fixedly connected
- groove
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- 238000000227 grinding Methods 0.000 title claims abstract description 18
- 238000009434 installation Methods 0.000 claims abstract description 16
- 230000003014 reinforcing effect Effects 0.000 claims description 17
- 230000005540 biological transmission Effects 0.000 claims description 5
- 210000002421 cell wall Anatomy 0.000 claims description 2
- 238000005728 strengthening Methods 0.000 claims 1
- 230000008859 change Effects 0.000 abstract description 3
- 238000003754 machining Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 12
- 230000008569 process Effects 0.000 description 8
- 238000012546 transfer Methods 0.000 description 6
- 238000012545 processing Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000013016 damping Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000003801 milling Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008447 perception Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
Abstract
The utility model relates to the technical field of engine blade machining and discloses an auxiliary device for surface grinding of an aircraft engine blade, which comprises a base, wherein the upper surface of the base is rotationally connected with a turntable, the upper surface of the turntable is fixedly connected with a connecting arm, a second motor is fixedly arranged in the connecting arm, an output shaft of the second motor is fixedly connected with a mounting block, a clamp holder is arranged on one side surface of the mounting block, and sliding grooves are formed in two ends of one side surface of the mounting block. This aircraft engine blade surface grinding auxiliary device, through being provided with installation piece, first spring, joint piece and draw-in groove, can be convenient for personnel install the dismantlement to the holder, when need dismantle the change holder, press two sliders simultaneously, can drive the fixture block and remove, make the distance of fixture block and draw-in groove increase, disconnection joint relation can stimulate the holder, takes out the holder, easy operation need not professional instrument also can dismantle the holder.
Description
Technical Field
The utility model relates to the technical field of engine blade machining, in particular to an auxiliary device for grinding the surface of an aircraft engine blade.
Background
The blade is used as one of key parts of the aeroengine, has a critical influence on the performance of the aeroengine, and determines that the blade is complex in shape, large in size span, severe in stress and maximum in bearing of the parts due to the functional life of the blade in the engine and the working characteristics of the blade.
According to the application number 201520820158.3, a portable aircraft engine blade grinding machine is disclosed, so that the heights of batch grinding workpieces are consistent, the grinding angles are consistent, and the quality requirement is completely ensured.
The following problems still exist in the actual use process:
(1) In aircraft blade processing, cut the appearance back of blade with the milling machine, need with the holder with the blade root, later polish with the sand mill, to different size blades, need use corresponding holder to carry out the centre gripping, current equipment installs the holder through the bolt, need borrow professional instrument just can dismantle, be inconvenient for the holder to change the maintenance.
(2) When the blades are subjected to multiple working procedures such as polishing and milling, the problem of inconvenient rotation exists after the blades are fixed.
Disclosure of Invention
Aiming at the defects of the prior art, the utility model provides an auxiliary device for grinding the surface of an aircraft engine blade, which has the advantages of convenient replacement and maintenance of a clamp holder and convenient rotation, and solves the problems in the background art.
The utility model provides the following technical scheme: the utility model provides an aircraft engine blade surface grinding auxiliary device, includes the base, the upper surface of base rotates and is connected with the carousel, the upper surface fixedly connected with linking arm of carousel, the inside fixed mounting of linking arm has the second motor, the output shaft fixedly connected with installation piece of second motor, one side surface mounting of installation piece has the holder, installation piece one side surface both ends seted up the spout, the inside of spout is provided with the slider, the lower surface fixedly connected with fixture block of slider, one side surface fixedly connected with first telescopic link of slider, one side surface fixedly connected with joint piece of holder, the draw-in groove has all been seted up at the inner wall both ends of joint piece, the fixture block is located the inside of draw-in groove, a plurality of spacing groove has been seted up to one side surface of joint piece, the tank bottom fixedly connected with second telescopic link of spacing groove, the one end fixedly connected with reinforcing block of second telescopic link.
Preferably, the upper surface of base has seted up flutedly, the recess's cell wall has seted up the rotation groove, the carousel is located the inside of recess, the fixed surface of carousel is connected with the turning block, the turning block is located the inside of rotation groove, the lower surface fixedly connected with driven gear of carousel.
Preferably, the surface of the first telescopic rod is sleeved with a first spring in a sliding manner, and two ends of the first spring are fixedly connected with one side surfaces of the two clamping blocks.
Preferably, the surface of the second telescopic rod is sleeved with a second spring in a sliding manner, one end of the second spring is fixedly connected with the bottom of the limiting groove, and one end of the second spring is fixedly connected with one side surface of the reinforcing block.
Preferably, the first motor is fixedly arranged in the base, the output shaft of the first motor is fixedly connected with the transmission rod, one end of the transmission rod is fixedly connected with the braking gear, and the braking gear and the driven gear are meshed with each other.
Preferably, the inner wall of the installation block is provided with a plurality of reinforcing grooves, and the reinforcing block is positioned in the reinforcing grooves.
Compared with the prior art, the utility model has the following beneficial effects:
1. this aircraft engine blade surface grinding auxiliary device, through being provided with the installation piece, a first spring, joint piece and draw-in groove, can be convenient for personnel install the dismantlement to the holder, when need dismantle the change holder, press two sliders simultaneously, can drive the fixture block and remove, make the distance of fixture block and draw-in groove increase, disconnection joint relation, can pull the holder, take out the holder, easy operation, need not professional instrument and also dismantle the holder, be convenient for personnel's operation and understanding, improve work efficiency, because consolidate the piece surface and be the arc when pulling the holder, make it consolidate the groove multiplicable stability when the pulling, make the staff have the damping sense simultaneously, be convenient for personnel clearly perception whether install and accomplish, when the holder work rotates, because of the effect of centrifugal force makes first spring remove towards both ends, can make the fixture block butt in the inside of draw-in groove, make the installation back more stable.
2. This aircraft engine blade surface abrasive machining auxiliary device through being provided with base, carousel, first motor and second motor, can rotate the engine blade after fixing, be convenient for personnel's processing, fix the blade root through the holder, can polish, mill etc. processing, when need processing different positions of blade, start first motor, drive the transfer line and rotate, the transfer line drives brake gear and rotates, brake gear drives driven gear motion, thereby make carousel rotation in the recess, linking arm and holder rotate thereupon, can drive the blade and turn left and right sides, the rotor block is in the rotation inslot, can spacing to the carousel, prevent the shake, work efficiency has been improved, time is saved, start the second motor, can drive installation piece and holder rotation, thereby drive the blade and rotate from top to bottom, thereby process, be convenient for personnel's processing different positions of blade, increase the practicality.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the device of the present utility model;
FIG. 2 is a schematic view of the internal structure of the connecting arm according to the present utility model;
FIG. 3 is a schematic view of the internal structure of the mounting block of the present utility model;
FIG. 4 is an enlarged schematic view of the structure of FIG. 3A according to the present utility model;
FIG. 5 is a schematic view of a mounting block according to the present utility model;
FIG. 6 is a schematic view of the internal structure of the base of the present utility model;
fig. 7 is a schematic diagram of a turntable structure according to the present utility model.
In the figure: 1. a base; 2. a connecting arm; 3. a mounting block; 4. a holder; 5. a chute; 6. a slide block; 7. a clamping block; 8. a first telescopic rod; 9. a first spring; 10. a clamping block; 11. a clamping groove; 12. a limit groove; 13. a second telescopic rod; 14. a reinforcing block; 15. a second spring; 16. a reinforcing groove; 17. a groove; 18. a rotating groove; 19. a turntable; 20. a rotating block; 21. a driven gear; 22. a first motor; 23. a transmission rod; 24. a brake gear; 25. and a second motor.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-7, an auxiliary device for grinding the surface of an aircraft engine blade comprises a base 1, wherein a turntable 19 is rotationally connected to the upper surface of the base 1, a connecting arm 2 is fixedly connected to the upper surface of the turntable 19, a second motor 25 is fixedly installed inside the connecting arm 2, an output shaft of the second motor 25 is fixedly connected with a mounting block 3, a clamp holder 4 is installed on one side surface of the mounting block 3, sliding grooves 5 are formed in two ends of one side surface of the mounting block 3, a sliding block 6 is arranged inside the sliding grooves 5, a clamping block 7 is fixedly connected to the lower surface of the sliding block 6, a first telescopic rod 8 is fixedly connected to one side surface of the sliding block 6, a clamping block 10 is fixedly connected to one side surface of the clamp holder 4, clamping grooves 11 are formed in two ends of the inner wall of the clamping block 10, the clamping block 7 is located inside the clamping grooves 11, a plurality of limiting grooves 12 are formed in one side surface of the clamping block 10, second telescopic rods 13 are fixedly connected to bottoms of the limiting grooves 12, and one end of the second telescopic rods 13 is fixedly connected to a reinforcing block 14, and therefore people can conveniently install and detach the clamp holder 4.
Wherein; the upper surface of base 1 has seted up recess 17, and the recess wall of recess 17 has seted up and has rotated groove 18, and carousel 19 is located the inside of recess 17, and the fixed surface of carousel 19 is connected with rotor 20, and rotor 20 is located the inside of rotating groove 18, and the lower surface fixedly connected with driven gear 21 of carousel 19 can rotate the engine blade after fixing, and the personnel of being convenient for process.
Wherein; the surface sliding sleeve of first telescopic link 8 has cup jointed first spring 9, and the both ends of first spring 9 and one side fixed surface of two fixture blocks 7 are connected, can make fixture block 7 butt in the inside of draw-in groove 11, increase stability.
Wherein; the surface of the second telescopic rod 13 is sleeved with a second spring 15 in a sliding manner, one end of the second spring 15 is fixedly connected with the bottom of the limit groove 12, one end of the second spring 15 is fixedly connected with one side surface of the reinforcing block 14, the reinforcing block 14 can be forced to retract into the limit groove 12 through the second spring 15, and the reinforcing block 14 can be ejected out without being forced.
Wherein; the inside fixed mounting of base 1 has first motor 22, and the output shaft fixedly connected with transfer line 23 of first motor 22, and the one end fixedly connected with brake gear 24 of transfer line 23, intermesh between brake gear 24 and the driven gear 21 is convenient for personnel to rotate the blade.
Wherein; the inner wall of the installation block 3 is provided with a plurality of reinforcing grooves 16, and the reinforcing blocks 14 are positioned in the reinforcing grooves 16, so that the installation is more stable.
The working principle, during the use, can polish, process such as milling through holder 4, when need process different positions of blade, start first motor 22, drive transfer lever 23 rotates, the transfer lever 23 drives brake gear 24 and rotates, brake gear 24 drives driven gear 21 motion, thereby make carousel 19 rotate in recess 17, the arm 2 rotates along with holder 4 simultaneously, can drive the blade and control the rotation, rotatory piece 20 is in rotary groove 18, can carry out spacing to carousel 19, prevent the shake, start second motor 25, can drive installation piece 3 and holder 4 rotation, thereby drive the blade and rotate from top to bottom, process different positions of blade, when need changing the maintenance to holder 4, simultaneously press two sliders 6, can drive fixture block 7 and remove, make fixture block 7 and draw-in groove 11's distance increase, break-in joint relation, can pull holder 4, take out holder 4, the specialized tool also can dismantle holder 4, because the reinforcement piece 14 surface is the arc, make it in the pulling in-process atress shrink in spacing groove 12, reinforcement piece 14 gets into the effect of the recess 16, can increase the effect of making the inside of the installation piece 16, make the inside of the inside diameter of a clamp 11 can be more stable, and the effect of the vibration damping device can be realized, the inside is realized by the installation personnel, and the vibration damping device can be more stable, and the vibration damper is realized when the vibration damper is installed to the inside the 9.
It is noted that relational terms such as first and second, and the like are 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. Moreover, 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.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides an aircraft engine blade surface grinding auxiliary device, includes base (1), a serial communication port, the upper surface of base (1) rotates and is connected with carousel (19), the last fixed surface of carousel (19) is connected with linking arm (2), the inside fixed mounting of linking arm (2) has second motor (25), the output shaft fixedly connected with installation piece (3) of second motor (25), one side surface mounting of installation piece (3) has holder (4), installation piece (3) one side surface both ends seted up spout (5), the inside of spout (5) is provided with slider (6), the lower fixed surface of slider (6) is connected with fixture block (7), one side surface fixedly connected with first telescopic link (8) of slider (6), one side fixed surface of holder (4) is connected with joint piece (10), draw-in groove (11) have all been seted up at the inner wall both ends of joint piece (10), fixture block (7) are located the inside of draw-in groove (11), one side surface of joint piece (10) has slider (12), a plurality of second telescopic link (13) are connected with telescopic link (13).
2. An aircraft engine blade surface grinding aid according to claim 1, wherein: the upper surface of base (1) has seted up recess (17), rotation groove (18) have been seted up to the cell wall of recess (17), carousel (19) are located the inside of recess (17), the fixed surface of carousel (19) is connected with rotor (20), rotor (20) are located the inside of rotation groove (18), the lower fixed surface of carousel (19) is connected with driven gear (21).
3. An aircraft engine blade surface grinding aid according to claim 1, wherein: the surface sliding sleeve of first telescopic link (8) has cup jointed first spring (9), the both ends of first spring (9) are connected with one side surface fixed of two fixture blocks (7).
4. An aircraft engine blade surface grinding aid according to claim 1, wherein: the surface sliding sleeve of second telescopic link (13) has cup jointed second spring (15), the tank bottom fixed connection of one end and spacing groove (12) of second spring (15), the one end and the one side surface fixed connection of strengthening piece (14) of second spring (15).
5. An aircraft engine blade surface grinding aid according to claim 1, wherein: the novel electric bicycle is characterized in that a first motor (22) is fixedly arranged in the base (1), an output shaft of the first motor (22) is fixedly connected with a transmission rod (23), one end of the transmission rod (23) is fixedly connected with a braking gear (24), and the braking gear (24) and the driven gear (21) are meshed with each other.
6. An aircraft engine blade surface grinding aid according to claim 1, wherein: a plurality of reinforcing grooves (16) are formed in the inner wall of the mounting block (3), and the reinforcing blocks (14) are located in the reinforcing grooves (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322127395.9U CN220516374U (en) | 2023-08-09 | 2023-08-09 | Auxiliary device for surface grinding of aircraft engine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322127395.9U CN220516374U (en) | 2023-08-09 | 2023-08-09 | Auxiliary device for surface grinding of aircraft engine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220516374U true CN220516374U (en) | 2024-02-23 |
Family
ID=89922921
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322127395.9U Active CN220516374U (en) | 2023-08-09 | 2023-08-09 | Auxiliary device for surface grinding of aircraft engine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220516374U (en) |
-
2023
- 2023-08-09 CN CN202322127395.9U patent/CN220516374U/en active Active
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