CN215881348U

CN215881348U - Aeroengine blade production is with processing fixed establishment

Info

Publication number: CN215881348U
Application number: CN202121658340.5U
Authority: CN
Inventors: 李维
Original assignee: Changsha Maosi Electromechanical Technology Co ltd
Current assignee: Changsha Maosi Electromechanical Technology Co ltd
Priority date: 2021-07-15
Filing date: 2021-07-15
Publication date: 2022-02-22
Anticipated expiration: 2031-07-15

Abstract

The utility model provides a machining fixing mechanism for producing an aircraft engine blade. Aeroengine blade production is with processing fixed establishment, including the operation panel, guide way and fixed slot have been seted up on the operation panel respectively, the arc slide rail has been seted up to the inside of guide way all is connected with the connecting frame through the pivot rotation. According to the processing and fixing mechanism for producing the blades of the aircraft engine, the blades can be guided to enter the fixing grooves through the arranged positioning wheels, the phenomenon that the blades collide with the front ends of the blades in the inserting and fixing process to deform the blades so as to influence the follow-up assembly of the blades is avoided, the angle of the connecting frame can be adjusted through the arranged electric telescopic rods, the sliding wheels on the connecting frame are enabled to contact the blades, the blades are convenient to take after detection, large friction between the blades and the fixing grooves in the taking process is avoided, and therefore the practicability of the mechanism is improved.

Description

Aeroengine blade production is with processing fixed establishment

Technical Field

The utility model relates to the technical field of aviation, in particular to a machining fixing mechanism for producing an aero-engine blade.

Background

The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine.

In the use process of an aircraft engine, the blade is used as a key component of the aircraft generator and needs to be detected in the production process so as to avoid certain defects in the machining process of the blade and avoid major accidents in use.

Among the correlation technique, need carry out the centre gripping to the blade when detecting and fix to be convenient for observe the condition of blade, wherein, before carrying out the centre gripping fixed, through inserting the blade in the fixed slot, fix spacingly afterwards, nevertheless at the male in-process, collide the front end of blade easily, make it take place to deform, thereby influence follow-up assembly to the blade.

Therefore, it is necessary to provide a machining and fixing mechanism for producing an aircraft engine blade to solve the technical problems.

SUMMERY OF THE UTILITY MODEL

The utility model provides a processing and fixing mechanism for producing an aircraft engine blade, which solves the technical problem that the blade is easy to collide with the front end of the blade to deform by inserting the blade into a fixing groove before clamping and fixing.

In order to solve the technical problem, the machining fixing mechanism for producing the blade of the aero-engine comprises an operating platform, the operating platform is respectively provided with a guide groove and a fixed groove, the guide groove is internally provided with an arc-shaped slide rail, and the insides of the guide grooves are respectively and rotatably connected with a connecting frame through a rotating shaft, the insides of the connecting frames are respectively and rotatably connected with a positioning wheel and a sliding wheel, the back surface of the positioning wheel is connected with the inner part of the arc-shaped slide rail in a sliding way, one side of the inner part of the guide groove is provided with an adjusting component, the adjusting component comprises an electric telescopic rod, the bottom end of the electric telescopic rod is arranged at one side of the inner part of the guide groove, and the top end of the electric telescopic rod is fixedly connected with a displacement block, one side of the displacement block is connected with one side in the guide groove in a sliding way, the displacement block is movably connected with a push rod, and one end of the push rod is movably connected with one side of the connecting frame.

Preferably, the guide groove communicates with the fixing groove.

Preferably, a sliding groove is formed in the operating platform, two sliding blocks are connected to the inside of the sliding groove in a sliding mode, one side of each sliding block penetrates through the fixing groove and extends to the outside of the fixing groove, and one side of each sliding block, which extends to the outside of the fixing groove, is fixedly connected with a fixing clamp.

Preferably, a cylinder is arranged on one side inside the sliding groove, and the telescopic end of the cylinder is fixed on one side of the sliding block.

Preferably, one side of the fixing clamp is fixedly connected with a marking block, a graduated scale is arranged on the fixing clamp, and one side of the marking block is slidably connected onto the graduated scale.

Preferably, a pressing plate is slidably connected between two sides of the inside of the fixing clamp, and one side of the pressing plate penetrates through the fixing clamp and extends to the outside of the fixing clamp.

Preferably, an elastic part is arranged on one side of the inside of the fixing clamp, and one side of the elastic part is arranged on the extrusion plate.

Compared with the prior art, the machining fixing mechanism for producing the blades of the aircraft engine provided by the utility model has the following beneficial effects:

the utility model provides a processing and fixing mechanism for producing an aircraft engine blade, which can play a role of guiding the blade entering a fixed groove through an arranged positioning wheel, so that the blade is prevented from colliding with the front end of the blade in the process of insertion and fixation to deform the front end of the blade, and further the follow-up assembly of the blade is influenced.

Drawings

FIG. 1 is a schematic structural view of a first embodiment of a machining fixing mechanism for producing an aircraft engine blade, provided by the utility model;

FIG. 2 is a side view of the console shown in FIG. 1;

FIG. 3 is a schematic perspective view of the connection frame shown in FIG. 1;

FIG. 4 is a schematic perspective view of the fixing clip shown in FIG. 1;

fig. 5 is a schematic structural diagram of a second embodiment of the machining fixing mechanism for producing an aircraft engine blade provided by the utility model.

Reference numbers in the figures: 1. an operation table; 2. a guide groove; 3. fixing grooves; 4. an arc-shaped slide rail; 5. a connecting frame; 6. positioning wheels; 7. a sliding wheel; 8. an adjustment assembly; 81. an electric telescopic rod; 82. a displacement block; 83. a push rod; 9. a sliding groove; 10. a slider; 11. fixing the clamp; 12. a cylinder; 13. marking a block; 14. a graduated scale; 15. a pressing plate; 16. an elastic member.

Detailed Description

The utility model is further described with reference to the following figures and embodiments.

First embodiment

Referring to fig. 1, fig. 2, fig. 3 and fig. 4, fig. 1 is a schematic structural view of a first embodiment of a machining fixing mechanism for producing an aircraft engine blade according to the present invention; FIG. 2 is a side view of the console shown in FIG. 1; FIG. 3 is a schematic perspective view of the connection frame shown in FIG. 1; fig. 4 is a schematic perspective view of the fixing clip shown in fig. 1. The machining fixing mechanism for producing the blade of the aero-engine comprises an operating platform 1, wherein a guide groove 2 and a fixing groove 3 are respectively formed in the operating platform 1, an arc-shaped slide rail 4 is formed in the guide groove 2, the inside of the guide groove 2 is rotatably connected with a connecting frame 5 through a rotating shaft, the inside of the connecting frame 5 is rotatably connected with a positioning wheel 6 and a sliding wheel 7 respectively, the back face of the positioning wheel 6 is slidably connected with the inside of the arc-shaped slide rail 4, an adjusting assembly 8 is arranged on one side of the inside of the guide groove 2, the adjusting assembly 8 comprises an electric telescopic rod 81, the bottom end of the electric telescopic rod 81 is arranged on one side of the inside of the guide groove 2, a displacement block 82 is fixedly connected to the top end of the electric telescopic rod 81, one side of the displacement block 82 is slidably connected with one side of the inside of the guide groove 2, and a push rod 83 is movably connected to the displacement block 82, one end of the push rod 83 is movably connected to one side of the connecting frame 5;

the rotation of the connecting frame 5 can be limited by the arc-shaped sliding rail 4, so that the deviation is avoided, and the stability in the rotation process is improved;

the electric telescopic rod 81 is connected with an external power supply and a control switch;

the angle of the connecting frame 5 can be automatically adjusted through the arranged electric telescopic rod 81, so that the sliding wheel 7 contacts with the blade, and the blade is positioned when being taken;

the front end of the inserted blade can be positioned by the positioning wheel 6, so that the inserted blade can smoothly enter the fixing groove for fixing;

the locating wheel 6 and the sliding wheel 7 are made of rubber, and buffer protection is performed on the blades when the blades are inserted, so that the blades are prevented from colliding and being deformed.

The guide groove 2 communicates with the fixing groove 3.

The operating platform is characterized in that a sliding groove 9 is formed in the operating platform 1, two sliding blocks 10 are connected to the inside of the sliding groove 9 in a sliding mode, one side of each sliding block 10 penetrates through the corresponding fixing groove 3 and extends to the outside of the corresponding fixing groove 3, and the sliding blocks 10 extend to one side of the outside of the corresponding fixing groove 3 and are fixedly connected with fixing clamps 11.

An air cylinder 12 is arranged on one side inside the sliding groove 9, and the telescopic end of the air cylinder 12 is fixed on one side of the sliding block 10;

through the cylinder 12 who sets up, can promote the blade and carry out the centre gripping fixed, be convenient for detect.

One side of the fixed clamp 11 is fixedly connected with a marking block 13, a graduated scale 14 is arranged on the fixed clamp 11, and one side of the marking block 13 is connected to the graduated scale 14 in a sliding manner;

through scale 14 and the mark piece 13 that sets up, can carry out the measurement of thickness to the blade that detects, behind the 11 fixed blades of mounting fixture, at this moment, mark piece 13 stops the position on scale 14 and takes notes to obtain the thickness of blade, classify, the processing of the follow-up link of being convenient for.

The working principle of the machining fixing mechanism for producing the blades of the aero-engine provided by the utility model is as follows:

the first step is as follows: when the blade is fixed, in order to avoid the deformation of the blade when the blade is inserted into the operating platform 1, the positioning wheel 6 is arranged in the guide groove 2 in the operating platform 1, when the front end of the blade is inserted into the notch of the guide groove 2, the front end of the blade is contacted with the positioning wheel 6, and under the rotation of the positioning wheel 6, the front end of the blade is pushed into the fixing groove 3, so that the guiding and positioning effects of the blade when the blade is inserted are achieved;

the second step is that: then, by starting the cylinder 12, the sliding block 10 is pushed to slide in the sliding groove 9, and the fixing clamp 11 is driven to move, so that the blade is clamped and fixed, and the detection of the blade is facilitated;

the third step: in order to conveniently take the blade from the fixed groove 3, the electric telescopic rod 81 is started, the displacement block 82 is pushed to slide in the guide groove 2, the push rod 83 is driven to rotate the connecting frame 5, the sliding wheel 7 is close to the notch of the fixed groove 3, the blade is taken afterwards, the sliding is carried out on the outer surface of the sliding wheel 7, the blade can be taken smoothly, the blade is prevented from being taken, large friction is generated between the blade and the fixed groove 3, and the practicability of the mechanism is improved.

through the locating wheel 6 that sets up, can enter into the effect that plays the direction in the fixed slot 3 to the blade, avoid inserting fixed in-process, lead to colliding the front end of blade, make it take place deformation, thereby influence the follow-up assembly to the blade, and through the electric telescopic handle 81 that sets up, can adjust the angle of splice frame 5, make movable pulley 7 on the splice frame 5 contact the blade, thereby be convenient for take after the detection, avoid taking the in-process, make to produce great friction between blade and the fixed slot 3.

Second embodiment

Referring to fig. 5 in combination, a second embodiment of the present application provides another machining and fixing mechanism for producing an aircraft engine blade, based on the machining and fixing mechanism for producing an aircraft engine blade provided in the first embodiment of the present application. The second embodiment is only the preferred mode of the first embodiment, and the implementation of the second embodiment does not affect the implementation of the first embodiment alone.

Specifically, the difference of the machining fixing mechanism for producing the aircraft engine blade provided by the second embodiment of the present application lies in that: a pressing plate 15 is slidably connected between two sides of the inside of the fixing clamp 11, and one side of the pressing plate 15 penetrates through the fixing clamp 11 and extends to the outside of the fixing clamp 11.

An elastic piece 16 is arranged on one side inside the fixing clamp 11, and one side of the elastic piece 16 is arranged on the extrusion plate 15;

in this embodiment, the elastic member 16 is a spring. It is understood that in other embodiments, the elastic member 16 may be other elastic members, such as elastic rubber and disc-shaped elastic pieces;

through the resilience of the elastic piece 16, the extrusion plate 15 is pushed to fix the blade, and the fixing firmness is improved.

The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims

1. The utility model provides an aeroengine blade production is with processing fixed establishment, includes the operation panel, its characterized in that: the utility model discloses a sliding mechanism of electric telescopic handle, including operation panel, guide way and fixed slot, arc slide rail has been seted up to the inside of guide way all rotates through the pivot and is connected with the carriage, the inside of carriage rotates respectively and is connected with locating wheel and movable pulley, the back sliding connection of locating wheel in the inside of arc slide rail, one side of the inside of guide way is provided with adjusting part, adjusting part includes electric telescopic handle, electric telescopic handle's bottom set up in one side of the inside of guide way to electric telescopic handle's top fixedly connected with displacement piece, one side sliding connection of displacement piece in one side of the inside of guide way, swing joint has the push rod on the displacement piece, the one end swing joint of push rod in one side of carriage.

2. The aircraft engine blade production machining fixing mechanism as claimed in claim 1, wherein the guide groove is communicated with the fixing groove.

3. The aircraft engine blade production is with processing fixed establishment of claim 1, characterized in that, the operation panel is seted up sliding groove, sliding groove's inside sliding connection has two sliding blocks, one side of sliding block runs through the fixed slot and extends to the outside of fixed slot, the sliding block extends to the fixed clamp of one side fixedly connected with outside the fixed slot.

4. A machining fixing mechanism for producing an aircraft engine blade according to claim 3, wherein a cylinder is arranged on one side inside the sliding groove, and a telescopic end of the cylinder is fixed to one side of the sliding block.

5. The aircraft engine blade production is with processing fixed establishment of claim 3, characterized in that, a mark piece is fixedly connected with one side of mounting fixture, be provided with the scale on the mounting fixture, one side of mark piece sliding connection is in on the scale.

6. The aircraft engine blade production is with processing fixed establishment of claim 3, characterized in that, sliding connection has the stripper plate between the inside both sides of mounting fixture, and one side of the stripper plate runs through mounting fixture and extends to the outside of mounting fixture.

7. The aircraft engine blade production is with processing fixed establishment of claim 6, characterized in that, the inside one side of mounting fixture all is provided with the elastic component, one side of elastic component sets up on the stripper plate.