CN215510646U

CN215510646U - Flexible clamping tool for aero-engine blade

Info

Publication number: CN215510646U
Application number: CN202120142842.6U
Authority: CN
Inventors: 胡昌旦; 钟广燎
Original assignee: Guangzhou United Faith Intelligent Equipment Co ltd
Current assignee: Guangzhou United Faith Intelligent Equipment Co ltd
Priority date: 2021-01-19
Filing date: 2021-01-19
Publication date: 2022-01-14
Anticipated expiration: 2031-01-19

Abstract

The utility model discloses a flexible clamping tool for an aircraft engine blade, which comprises a clamping device, wherein the clamping device comprises a movable main body, the movable main body is composed of a plurality of movable rods arranged in a matrix manner, the movable main body is movably arranged in a box body, and a pressing device for relatively fixing the movable main body is further arranged on the box body. A plurality of movable rods are mutually independent, and the bottom of each movable rod is clamped with a spring. The top end of the movable rod extends out of the upper surface of the box body and is exposed outside the box body. The upper surface of the box body and the movable rods are provided with guide holes in a one-to-one correspondence mode, and the movable rods extend out of the guide holes. The utility model can realize repeated clamping of the same type of workpieces, is compatible with the advantages of clamping of multiple types and models of blades of an aircraft engine, and can also improve the overall operation efficiency; the utility model is flexible and practical, and has the characteristics of convenience, easy learning and easy operation.

Description

Flexible clamping tool for aero-engine blade

Technical Field

The utility model relates to the technical field of manufacturing of aero-engine blades, in particular to a flexible clamping tool for an aero-engine blade.

Background

As is known, an aircraft engine is the core of an entire aircraft, and its performance directly determines the overall performance of the aircraft, so the aircraft engine is also called "pearl on industrial crown". The most severe working environment and the most complicated stress in the aircraft gas turbine engine are turbine blades, and the turbine blades are also the key points for achieving high performance of the aircraft engine in the aspects of small size and light weight. So, if the aero-engine is said to be the core of the entire aircraft, then the turbine blades are the "core in core" of the entire aircraft!

Secondly, the number of the propelling stages of the engine is large, the shape and the model of each stage of blade are different, the whole automatic production and batch operation are greatly influenced, the aero-engine has the production characteristics of small-batch multi-model products, and a flexible blade clamp is urgently needed to be designed and produced for improving the detection efficiency of aero-engine blades.

The prior art has the following defects: the design of anchor clamps in the past all is single model number blade to single blade, one-to-one anchor clamps design mode promptly, will design a large amount of double-layered tools like this, the on-the-spot production of being not convenient for, and in actual production process the workman need spend a large amount of time to find corresponding double-layered tool, and a lot of double-layered tools need very big place to deposit and maintain. And is not conducive to automated production.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects of the prior art, the utility model provides a flexible clamping tool for an aero-engine blade.

In order to solve the technical problems, the technical scheme adopted by the utility model is that the flexible clamping tool for the blades of the aircraft engine comprises a clamping device, wherein the clamping device comprises a movable main body, the movable main body consists of a plurality of movable rods arranged in a matrix manner, the movable main body is movably arranged in a box body, and a pressing device for relatively fixing the movable main body is further arranged on the box body.

Further, a plurality of movable rods are independent each other, and the bottom of every movable rod all blocks and is provided with the spring.

Further, the top end of the movable rod protrudes from the upper surface of the case and is exposed outside the case.

Furthermore, the upper surface of the box body and the movable rods are provided with guide holes in a one-to-one correspondence mode, and the movable rods extend out of the guide holes.

Further, the spring is fixed in the case by providing a holder at the bottom of the spring.

Further, the box body comprises a main box body and a lower box body which can be separated, and the retainer is arranged in the lower box body.

Further, closing device includes the compact heap, and the compact heap is located the side of box body, and extends to the box body is inside from the side, can extrude the movable rod in the inside of box body.

Further, the pressing degree of the movable rod by the pressing block is adjusted through the bolt.

Further, the clamping tool comprises two clamping devices, the movable bodies of the two clamping devices are opposite, and the two clamping devices move relatively under the action of the air cylinder.

The utility model can realize repeated clamping of the same type of workpieces, is compatible with the advantages of clamping of multiple types and models of blades of an aircraft engine, and can also improve the overall operation efficiency; the utility model is flexible and practical, and has the characteristics of convenience, easy learning and easy operation.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention.

Fig. 2 is a reference diagram of the use state of the present invention.

In the figure: 1. a clamping device; 2. a cylinder; 3. a movable rod; 4. a spring; 5. a holder; 6. a main box body; 7. a lower box body; 8. and (5) a compression block.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

The flexible clamping tool for the blades of the aircraft engine shown in the figure 1 comprises a clamping device 1, wherein the clamping device comprises a movable main body, the movable main body is composed of a plurality of movable rods arranged in a matrix form, the movable main body is movably arranged in a box body, a plurality of movable rods 3 are mutually independent, and the bottom of each movable rod is clamped with a spring 4. The bottom of movable rod is provided with the step and fixes spring and movable rod block, under the effect of spring, makes every movable rod all can move about independently.

The top end of the movable rod extends out of the upper surface of the box body and is exposed outside the box body. The top ends of the movable rods are used for clamping workpieces such as engine blades and the like, and because the movable rods independently move, a certain amount of retraction is carried out on the clamped workpieces according to the characteristics of the surfaces of the clamped workpieces, so that the profiling clamping effect is realized.

The spring is fixed in the box by arranging a holder 5 at the bottom of the spring. The retainer can keep the spring stably installed in the box body.

The box body comprises a main box body 6 and a lower box body 7 which can be separated, and the retainer is arranged in the lower box body. The box body design of upper and lower disconnect-type can help the installation and the dismantlement of this centre gripping frock: the retainer, the spring and the movable rod are installed in the lower box body at present, then the main box body is downwards sleeved on the movable rod, guide holes are formed in the upper surface of the box body and the movable rod in one-to-one correspondence, the movable rod extends out of the guide holes of the main box body, the movable rod conveniently extends out of the guide holes, and the installation of the clamping tool is completed.

The box body is also provided with a pressing device for relatively fixing the movable main body. The pressing device comprises a pressing block 8, the pressing block is located on the side face of the box body, extends from the side face to the inside of the box body, and can extrude the movable rod through the bolt in the box body. Adjusting bolt makes the compact heap withstand the movable rod from the side of movable rod and compresses tightly, has then increased the frictional force that the movable rod reciprocated and has made the movable rod be difficult to remove, just can fix the position of every movable rod to form a profile modeling tool surface.

As shown in fig. 2, when in use, the clamping tool comprises two clamping devices 1, the movable bodies of the two clamping devices are opposite, and the two clamping devices move relatively under the action of the cylinder 2.

The using principle and the method of the utility model are as follows:

during operation, as shown in fig. 2, the aero-engine blade is placed between the two clamping tools, clamping is carried out through cylinder output power, the clamping device can extrude due to the cylinder clamping force, the movable rod retracts a certain amount, the surface of the movable rod is formed into the shape identical to the surface of the blade, the pressing block is used for locking, the movable rod keeps the current position, good profiling is achieved on the surface of the aero-engine blade, and therefore the purpose of effective clamping is achieved.

The above embodiments are not intended to limit the present invention, and the present invention is not limited to the above examples, and those skilled in the art may make variations, modifications, additions or substitutions within the technical scope of the present invention.

Claims

1. The utility model provides an aeroengine blade flexible centre gripping frock which characterized in that: including clamping device (1), clamping device is including the activity main part, and the activity main part comprises the movable rod that a plurality of matrixes were arranged, and the activity of activity main part sets up in the box body, still is provided with the closing device with activity main part relatively fixed on the box body.

2. The flexible clamping tool for the aero-engine blade according to claim 1, wherein: a plurality of the movable rods (3) are mutually independent, and the bottom of each movable rod is clamped with a spring (4).

3. The flexible clamping tool for the aero-engine blade according to claim 2, wherein: the top end of the movable rod extends out of the upper surface of the box body and is exposed outside the box body.

4. The flexible clamping tool for the aero-engine blade according to claim 3, wherein: the upper surface of the box body and the movable rods are provided with guide holes in a one-to-one correspondence mode, and the movable rods extend out of the guide holes.

5. The flexible clamping tool for the aero-engine blade according to claim 3, wherein: the spring is fixed in the box body by arranging a retainer (5) at the bottom of the spring.

6. The aircraft engine blade flexible clamping tool of claim 5, characterized in that: the box body comprises a main box body (6) and a lower box body (7) which can be separated, and the retainer is arranged in the lower box body.

7. The flexible clamping tool for the aero-engine blade according to claim 6, wherein: the pressing device comprises a pressing block (8), the pressing block is located on the side face of the box body, extends from the side face to the inside of the box body, and can extrude the movable rod in the box body.

8. The aircraft engine blade flexible clamping tool of claim 7, characterized in that: the pressing degree of the movable rod by the pressing block is adjusted through a bolt.

9. The aircraft engine blade flexible clamping tool of claim 8, characterized in that: the clamping tool comprises two clamping devices, the movable bodies of the two clamping devices are opposite, and the two clamping devices move relatively under the action of the air cylinder (2).