CN218837581U - Disassembling wrench for blade retaining disc of aircraft engine - Google Patents
Disassembling wrench for blade retaining disc of aircraft engine Download PDFInfo
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- CN218837581U CN218837581U CN202222881172.7U CN202222881172U CN218837581U CN 218837581 U CN218837581 U CN 218837581U CN 202222881172 U CN202222881172 U CN 202222881172U CN 218837581 U CN218837581 U CN 218837581U
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- fine adjustment
- symmetrically arranged
- locking
- clamping
- base plate
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Abstract
The disassembly wrench for the blade retaining disc of the aircraft engine comprises a base plate, wherein the base plate is provided with connecting seats symmetrically arranged, mounting grooves symmetrically arranged, positioning strips symmetrically arranged and clamping heads symmetrically arranged, the mounting grooves are provided with handles and locking structures, the clamping heads are provided with positioning grooves matched with the positioning strips, fine adjustment screw rods and clamping grooves, and the fine adjustment screw rods are in threaded fit with fine adjustment screw holes in the base plate; the locking structure comprises a locking handle, and a locking screw is arranged on the locking handle. By adopting the structure, the clamping width is flexible and convenient to adjust, the bidirectional fine adjustment is realized, and the flexibility is strong; the device is stably fixed with the retaining ring in an opposite way, is not easy to fall off in the rotating use, and is stably and efficiently disassembled; make things convenient for the dismouting to use, the butt joint is nimble, and is fixed firm, greatly promotes work efficiency.
Description
Technical Field
The utility model relates to an aviation impeller machinery blade repair tools technical field, especially aircraft engine blade keeps a set dismantlement spanner.
Background
In a turbo machine such as an aircraft engine, when a rotor rotates at a high speed, a large centrifugal force is generated by a rotor blade in operation. It is necessary to support the root end in a suitable manner and to fix the blade at a point in the airfoil section using a retaining device, so that the blade is held substantially horizontally. This known type of retaining device comprises a stationary screw mechanism to apply a clamping force to the blade. In the existing retaining device, a wrench used when a retaining ring is detached is troublesome to operate, inconvenient to finely adjust and clamp, unstable to fix and inconvenient to rotate and detach.
Disclosure of Invention
The utility model aims to solve the technical problem of providing a disassembling wrench for a blade retaining disc of an aircraft engine, which has flexible adjustment of clamping width, bidirectional fine adjustment and strong flexibility; the device is stably fixed with the retaining ring in an opposite way, is not easy to fall off in the rotating use, and is stably and efficiently disassembled; make things convenient for the dismouting to use, the butt joint is nimble, and is fixed firm, greatly promotes work efficiency.
In order to solve the technical problem, the utility model discloses the technical scheme who adopts is: the disassembly wrench for the blade retaining disc of the aircraft engine comprises a base plate, wherein the base plate is provided with symmetrically arranged connecting seats, symmetrically arranged mounting grooves, symmetrically arranged positioning strips and symmetrically arranged clamping heads;
the locking structure comprises a locking handle, and a locking screw is arranged on the locking handle.
In a preferred scheme, the locking handle is provided with anti-skid textures.
In the preferred scheme, two positioning rings matched with the clamping head are arranged on the fine adjustment screw rod.
In a preferable scheme, the surface of the clamping groove is coated with an anti-slip coating.
The utility model provides an aircraft engine blade keeps dish dismantlement spanner through adopting above-mentioned structure, has following beneficial effect:
(1) The clamping width is flexible and convenient to adjust, bidirectional fine adjustment is realized, and the flexibility is strong;
(2) The device is stably fixed with the retaining ring in an opposite way, is not easy to fall off in the rotating use, and is stably and efficiently disassembled;
(3) Make things convenient for the dismouting to use, the butt joint is nimble, and is fixed firm, greatly promotes work efficiency.
Drawings
The invention will be further explained with reference to the following figures and examples:
fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a schematic view of the overall structure of the present invention.
Fig. 3 is a schematic view of the overall structure of the present invention.
Fig. 4 is a schematic view of the base plate and the upper structure thereof.
Fig. 5 is a schematic view of the clamping head structure of the present invention.
In the figure: base plate 1, connecting seat 2, mounting groove 3, handle 4, location strip 5, locking handle 6, locking screw 7, chucking head 8, fine setting screw 9, fine setting screw 10, holding ring 11, constant head tank 12, chucking groove 13.
Detailed Description
As shown in fig. 1-5, the wrench for disassembling the blade holding disc of the aircraft engine comprises a base plate 1, wherein the base plate 1 is provided with connecting seats 2 which are symmetrically arranged, mounting grooves 3 which are symmetrically arranged, positioning strips 5 which are symmetrically arranged, and clamping heads 8 which are symmetrically arranged, the mounting grooves 3 are provided with handles 4 and locking structures, the clamping heads 8 are provided with positioning grooves 12, fine adjustment screws 10 and clamping grooves 13 which are matched with the positioning strips 5, and the fine adjustment screws 10 are in threaded fit with fine adjustment screw holes 9 on the base plate 1;
the locking structure comprises a locking handle 6, and a locking screw 7 is arranged on the locking handle 6.
In a preferred scheme, the locking handle 6 is provided with anti-slip textures. The anti-skid property is good, and the retaining ring can be conveniently and quickly locked with the hole position on the retaining ring and can be matched and disassembled.
In a preferred scheme, two positioning rings 11 matched with the clamping head 8 are arranged on the fine adjustment screw 10. Accurate fine setting, it is stable convenient.
In a preferred scheme, the surface of the clamping groove 13 is coated with an anti-slip coating. Promote the frictional force between 13 surface courses in chucking groove and the retaining ring, the cooperation centre gripping is tight in top, and rotatory dismantlement stability is strong.
The utility model discloses a use method does: during the use, pull down in advance and place locking handle 6 on connecting seat 2, then place base plate 1 on the retaining ring to through the preliminary fixed of chucking head 8 and the retaining ring of both sides fine setting screw rod 10 control both sides, then pass mounting groove 3 and retaining ring with locking screw rod 7 on the locking handle 6 and be connected fixedly, hold the handle 4 rotation at last and can stably dismantle the retaining ring.
The utility model has the advantages that: the clamping width is flexible and convenient to adjust, bidirectional fine adjustment is realized, and the flexibility is strong; the device is stably fixed in opposite assembly with the retaining ring, is not easy to fall off in the rotating use, and is stable and efficient to disassemble; make things convenient for the dismouting to use, the butt joint is nimble, and is fixed firm, greatly promotes work efficiency.
Claims (4)
1. Aircraft engine blade keeps dish breakout wrench, including base plate (1), its characterized in that: the base plate (1) is provided with symmetrically arranged connecting seats (2), symmetrically arranged mounting grooves (3), symmetrically arranged positioning strips (5) and symmetrically arranged clamping heads (8), the mounting grooves (3) are provided with handles (4) and locking structures, the clamping heads (8) are provided with positioning grooves (12) matched with the positioning strips (5), fine adjustment screw rods (10) and clamping grooves (13), and the fine adjustment screw rods (10) are in threaded fit with fine adjustment screw holes (9) in the base plate (1);
the locking structure comprises a locking handle (6), and a locking screw (7) is arranged on the locking handle (6).
2. An aircraft engine blade retention disk breakout wrench as claimed in claim 1, wherein: the locking handle (6) is provided with anti-skid grains.
3. An aircraft engine blade retention disk breakout wrench as claimed in claim 1, wherein: and two positioning rings (11) matched with the clamping head (8) are arranged on the fine adjustment screw rod (10).
4. An aircraft engine blade retention disk breakout wrench as claimed in claim 1, wherein: the surface of the clamping groove (13) is coated with an anti-slip coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222881172.7U CN218837581U (en) | 2022-10-31 | 2022-10-31 | Disassembling wrench for blade retaining disc of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222881172.7U CN218837581U (en) | 2022-10-31 | 2022-10-31 | Disassembling wrench for blade retaining disc of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218837581U true CN218837581U (en) | 2023-04-11 |
Family
ID=87310796
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222881172.7U Active CN218837581U (en) | 2022-10-31 | 2022-10-31 | Disassembling wrench for blade retaining disc of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218837581U (en) |
-
2022
- 2022-10-31 CN CN202222881172.7U patent/CN218837581U/en active Active
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