CN217572254U

CN217572254U - Aviation turbine blade flange plate damper machining tool

Info

Publication number: CN217572254U
Application number: CN202221090759.XU
Authority: CN
Inventors: 王刚
Original assignee: Chengdu Changding Aviation Technology Co ltd
Current assignee: Chengdu Changding Aviation Technology Co ltd
Priority date: 2022-05-09
Filing date: 2022-05-09
Publication date: 2022-10-14
Anticipated expiration: 2032-05-09

Abstract

The utility model discloses an aviation turbine blade flange attenuator processing frock belongs to aviation parts machining field. A machining tool for an aviation turbine blade flange damper comprises a machining table, wherein supports are symmetrically assembled at the top end of the machining table, and an operating part is assembled between the two supports; the limiting device is assembled on the processing table and used for fixing the turbine blade edge plate damper; the limiting device comprises a bottom plate connected with the processing table, a plurality of sliding grooves are formed in the surface of the bottom plate, arc-shaped blocks are slidably mounted on the inner wall of each sliding groove, and the peripheries of the turbine blade edge plate dampers are fixed through the arc-shaped blocks; the utility model discloses a plurality of arc pieces on the stop device are fixed the object, because the size of every specification object is all inequality to the arc is adjusted on the spout, makes the stable fixing of object of processing on the bottom plate, makes things convenient for the operating parts to process it.

Description

Aviation turbine blade flange plate damper machining tool

Technical Field

The utility model relates to an aviation parts machining technology field especially relates to an aviation turbine blade flange attenuator processing frock.

Background

The damper is a device for providing motion resistance and consuming motion energy, energy absorption and shock absorption by damping are not new technologies, various dampers are already applied to industries such as aerospace, aviation, war industry, firearms, automobiles and the like to absorb vibration and dissipate energy, and after the seventies of the twentieth century, people start to gradually transfer the technologies to structural engineering such as buildings, bridges, railways and the like, so that the development is very rapid, and meanwhile, a damper part processing device is also rapidly developed.

However, when the existing equipment is used for processing the damper of the edge plate of the turbine blade, the piston rods with different sizes are difficult to firmly fix, so that the damper is stressed and dislocated in the polishing process, the polishing effect is influenced, and due to the fact that the polishing disc is in close contact with the damper and rubs at high speed, a large amount of heat can be generated, the surface temperature of a blank rises, the brittleness of the surface part of the blank is increased, and the quality of the damper is influenced.

Furthermore, in order to improve the quality of the damper, the machining tool for the edge plate damper of the aviation turbine blade is developed.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the problem that the object takes place the dislocation when adding man-hour among the prior art, and the aviation turbine blade flange attenuator processing frock of proposing.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the machining tool for the damper of the aeroturbine blade flange plate comprises a machining table, wherein supports are symmetrically assembled at the top end of the machining table, and an operating piece is assembled between the two supports;

the limiting device is assembled on the processing table and used for fixing the turbine blade edge plate damper;

the limiting device comprises a bottom plate connected with the processing table, a plurality of sliding grooves are formed in the surface of the bottom plate, arc-shaped blocks are slidably mounted on the inner wall of each sliding groove, and the periphery of the damper of the edge plate of the turbine blade is fixed through the arc-shaped blocks.

Preferably, the inner cavity of the bottom plate is equipped with a driving device, and a rotating block is equipped at the output end of the driving device.

Preferably, one end of the rotating block is rotatably provided with a push rod, and the other end of the push rod is rotatably provided with a sliding block.

Preferably, both ends of the slider are equipped with female blocks, and both ends of the slider penetrate through the female blocks and extend into the interior thereof.

Preferably, one side of the concave block is provided with a groove, and the outer surface of the sliding block is connected with the inner wall of the groove in a sliding manner.

Preferably, a gear plate is slidably mounted on the inner wall of the concave block, and one end of the gear plate is connected with one end of the sliding block.

Preferably, the fixing rods are assembled on the periphery of the bottom plate, and the outer surfaces of the fixing rods are assembled with the full gears.

Preferably, the outer surface of the full gear meshes with one side of the gear plate.

Preferably, the top end of the all-gear is equipped with a telescopic rod, and the other end of the telescopic rod is equipped with a fixed block.

Preferably, the top end of the fixed block is connected with the bottom end of the arc-shaped block.

Compared with the prior art, the utility model provides an aviation turbine blade flange attenuator processing frock possesses following beneficial effect:

1. this aeroturbine blade flange attenuator processing frock fixes the object through a plurality of arc pieces on stop device, because the size of every specification object is all inequality to the arc is adjusted on the spout, makes the stable fixing of object that is processed on the bottom plate, makes things convenient for the operating parts to process it.

2. This aeroturbine blade flange attenuator processing frock, it makes two push pedal promotion sliders remove inside the recess on concave type piece to drive through drive arrangement changes the piece, and then makes concave type piece inner wall sliding connection's gear plate remove, and make the all-gear rotate, because the assembly support pole on the all-gear, and be connected with the arc piece through the fixed block of assembling on the bracing piece, and then make on the stable bottom plate that is in of object, and can not produce the slip, the quality of follow-up turbine blade flange attenuator has been guaranteed.

3. This aeroturbine blade flange attenuator processing frock through the telescopic link of fixed assembly on the bottom plate, makes the full gear fix and rotates in situ to make the bracing piece rotate round the full gear, and then make the fixed block remove along the direction of spout, and then make things convenient for operating personnel to place and take.

The device does not relate to the part all the same with prior art or can adopt prior art to realize, the utility model discloses a plurality of arc pieces on the stop device are fixed the object, because the size of every specification object is all inequality, thereby the arc is adjusted on the spout, make the stable fixing on the bottom plate of object of processing, make things convenient for the operating parts to process it, it makes two push pedal promotion sliders inside the recess on concave type piece move to drive the commentaries on classics piece simultaneously through drive arrangement, and then make concave type piece inner wall sliding connection's toothed plate move, and make the all-gear rotate, because the assembly support bar on the all-gear, and be connected with the arc piece through the fixed block of assembly on the bracing piece, and then make the stable bottom plate that is in of object, and can not produce the slip, the quality of follow-up turbine blade rim plate attenuator has been guaranteed.

Drawings

Fig. 1 is a schematic structural view of a machining tool for an aviation turbine blade flange damper provided by the present invention;

FIG. 2 is a schematic structural view of a limiting device of a machining tool for an aviation turbine blade flange damper provided by the present invention;

FIG. 3 is a schematic view of the internal structure of a limiting device of a machining tool for an aviation turbine blade flange damper according to the present invention;

fig. 4 is the utility model provides an aviation turbine blade flange attenuator processing frock stop device part schematic structure.

In the figure: 1. a processing table; 2. a limiting device; 11. a support; 12. an operating member; 21. a base plate; 22. a chute; 23. an arc-shaped block; 24. a drive device; 25. rotating the block; 26. a push rod; 27. a slider; 28. a concave block; 29. a gear plate; 31. a fixing rod; 32. all-gear; 33. a telescopic rod; 34. a fixed block; 35. and (4) a groove.

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.

In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Example (b): referring to fig. 1-4, the machining tool for the damper of the blade edge plate of the aviation turbine comprises a machining table 1, wherein two sides of the machining table 1 are provided with brackets 11, an operating part 12 is assembled between the two brackets 11 and used for machining multiple objects, and on the basis of not changing original equipment, a limiting device 2 is assembled at the top end of the machining table 1 and the objects are fixed through the limiting device 2.

Stop device 2 includes the bottom plate 21 of being connected with processing platform 1, and be equipped with drive arrangement 24 in the inner chamber of bottom plate 21, wherein drive arrangement 24 is the equipment that motor etc. have power take off, simultaneously with drive arrangement 24's output be equipped with and change piece 25, and all rotate at the both ends of changeing piece 25 and install push rod 26, and the one end that two push rods 26 kept away from each other all rotates and installs slider 27, because one side that two concave type pieces 28 are relative all seted up fluted 35, and slider 27's both ends all with the inner wall sliding connection of fluted 35, and then when push rod 26 promoted slider 27 to both sides, make slider 27 remove at the inner wall of recess 35.

One end and the slider 27 of gear plate 29 are connected, and then when slider 27 removes, because the other end and the full gear 32 meshing of gear plate 29, when making gear plate 29 slide on concave type piece 28, full gear 32 rotates on dead lever 31, and will fix telescopic link 33 on full gear 32 and rotate round full gear 32, a plurality of spouts 22 have been seted up on the top of bottom plate 21 simultaneously, and even distribution is on the top of bottom plate 21, there is arc piece 23 in the inner wall slidable mounting of spout 22, and the bottom of arc piece 23 is passed through fixed block 34 and is connected with telescopic link 33, make telescopic link 33 when rotating along full gear 32, drive arc piece 23 through fixed block 34 and remove on spout 22, and then fix the surface of object, make it keep stable man-hour adding.

The utility model discloses in, the object that will process is placed on bottom plate 21, and start drive arrangement 24, make drive arrangement 24 drive commentaries on classics piece 25 and rotate, drive two push rods 26 on changeing piece 25 simultaneously and remove to both sides, and then make the recess 35 inner wall of the slider 27 at push rod 26 both ends slide on concave type piece 28, and because slider 27 is connected with toothed plate 29, make toothed plate 29 slide on concave type piece 28, thereby it rotates to drive full gear 32, because dead lever 31 fixes inside bottom plate 21, make full gear 32 fix and rotate in situ, make the telescopic link 33 of assembly rotate round dead lever 31 on full gear 32, and then drive fixed block 34 on telescopic link 33 and rotate, because fixed block 34 is connected with arc piece 23, and the inner wall sliding connection of arc piece 23 and spout 22, make fixed block 34 drive the flower box piece slide in the direction of spout 22 inner wall regulation, and fix the object.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides an aeronautical turbine blade flange attenuator processing frock which characterized in that includes:

the machining device comprises a machining table (1), wherein supports (11) are symmetrically assembled at the top end of the machining table (1), and operating parts (12) are assembled between the two supports (11);

the limiting device (2) is assembled on the processing table (1) and is used for fixing the damper of the turbine blade edge plate through the limiting device (2);

wherein stop device (2) include with bottom plate (21) that processing platform (1) are connected, just a plurality of spout (22) have been seted up to the surface dress of bottom plate (21), simultaneously the inner wall slidable mounting of spout (22) has arc piece (23), and is through a plurality of arc piece (23) are fixed all around turbine blade flange attenuator.

2. The machining tool for the aero turbine blade flange damper as claimed in claim 1, wherein an inner cavity of the bottom plate (21) is provided with a driving device (24), and a rotating block (25) is arranged at an output end of the driving device (24).

3. The machining tool for the aero-turbine blade flange damper as claimed in claim 2, wherein a push rod (26) is rotatably mounted at one end of the rotating block (25), and a sliding block (27) is rotatably mounted at the other end of the push rod (26).

4. The machining tool for the aviation turbine blade flange damper as claimed in claim 3, wherein both ends of the sliding block (27) are provided with concave blocks (28), and both ends of the sliding block (27) penetrate through the concave blocks (28) and extend into the concave blocks.

5. The machining tool for the aviation turbine blade flange damper as claimed in claim 4, wherein a groove (35) is formed in one side of the concave block (28), and meanwhile the outer surface of the sliding block (27) is in sliding connection with the inner wall of the groove (35).

6. The machining tool for the aero turbine blade flange damper as claimed in claim 4, wherein a gear plate (29) is slidably mounted on the inner wall of the concave block (28), and one end of the gear plate (29) is connected with one end of the sliding block (27).

7. The tooling for machining the damper of the air turbine blade rim according to claim 1, wherein the fixing rods (31) are assembled on the periphery of the bottom plate (21), and the full gear (32) is assembled on the outer surface of each fixing rod (31).

8. The machining tool for the aero turbine blade flange damper as claimed in claim 7, wherein an outer surface of the full gear (32) is meshed with one side of the gear plate (29).

9. The machining tool for the aero turbine blade flange damper as claimed in claim 7, wherein a top end of the full gear (32) is provided with an expansion link (33), and the other end of the expansion link (33) is provided with a fixing block (34).

10. The machining tool for the aviation turbine blade flange damper as claimed in claim 9, wherein the top end of the fixing block (34) is connected with the bottom end of the arc-shaped block (23).