CN212958869U

CN212958869U - Heat radiating fin for aero-engine

Info

Publication number: CN212958869U
Application number: CN202021739071.0U
Authority: CN
Inventors: 薛海洋
Original assignee: Dongguan Qiqin Precision Thermal Conduction Technology Co ltd
Current assignee: Dongguan Qiqin Precision Thermal Conduction Technology Co ltd
Priority date: 2020-08-19
Filing date: 2020-08-19
Publication date: 2021-04-13
Anticipated expiration: 2030-08-19

Abstract

The utility model discloses a radiator for an aeroengine, which comprises a central radiator group, side radiator groups and a bottom plate, wherein the top of the bottom plate is fixed with the central radiator group, the two sides of the central radiator group are symmetrically provided with the side radiator groups, one side of the side radiator groups, which is far away from the central radiator group, is provided with a side fixing mechanism which can further fixedly install the device through screws, an extending mechanism which can extend and rotate the side radiator is symmetrically arranged between the bottom plate of the side radiator groups and the bottom plate of the central radiator groups, the radiator for the aeroengine realizes the firmer and more stable installation of the radiator under the action of the side fixing mechanism, realizes the folding and structural shape change of the central radiator groups and the side radiator groups under the matching action of the side fixing mechanism and the extending mechanism, is convenient for transportation and use in different environments, compared with the prior art, the structure of the radiating fin is more convenient to install and change.

Description

Heat radiating fin for aero-engine

Technical Field

The utility model relates to a fin technical field specifically is a fin for aeroengine.

Background

The radiating fin is a device for radiating heat of electronic elements which are easy to generate heat in electrical appliances, and is made of aluminum alloy, brass or bronze into a plate shape, a sheet shape, a plurality of sheet shapes and the like, for example, a CPU (central processing unit) in a computer needs to use a relatively large radiating fin, and power tubes, row tubes and power amplifier tubes in a power amplifier in a television set need to use the radiating fin.

The existing radiating fin is welded and fixed on the surface, the shape cannot be changed, and the radiating fin is inconvenient to transport and apply in different environments.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a through folding fin for the air motor that changes fin group molding to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a fin for aeroengine, includes central fin group, side fin group and bottom plate, the bottom plate top is fixed with central fin group, central fin group bilateral symmetry is equipped with side fin group, side fin group keeps away from central fin group one side and is equipped with the side fixed establishment that accessible screw carries out further fixed mounting to the device, the symmetry is equipped with the extension mechanism that the side fin was rotated in the extensible between side fin group bottom plate and the central fin group bottom plate, be equipped with central filling area on the central fin group surface.

Preferably, the side fixing mechanism comprises a rotating side plate, auxiliary screw holes, an inserting plate and an inserting groove, the bottom of the rotating side plate is rotatably connected with the bottom plate of the bottom of the side radiating fin group through a rotating shaft, the rotating side plate is equidistantly provided with the auxiliary screw holes on the surface, the rotating side plate is symmetrically fixed with the inserting plate on two sides of the auxiliary screw holes on the surface, the inserting groove is formed in the position, corresponding to the inserting plate, of two sides of the bottom plate of the bottom of the side radiating fin group, and the inserting plate is in sliding insertion with the inserting groove.

Preferably, bolt holes are symmetrically formed in the surface of the rotating side plate close to one side of the inserting plate.

Preferably, extend the mechanism and include spout, connecting block, sliding block, first even board and second even board, the connecting block symmetry is established inside central fin group bottom plate both sides, and the connecting block both sides are fixed with the sliding block, the inside position that corresponds the sliding block of bottom plate has seted up the spout, the sliding block is sliding connection with the spout, the connecting block is close to side fin group one side and is fixed with first even board, and just first even board is worn out the bottom plate and is rotated through the pivot and be connected with the second even board, the second is even the board and is kept away from the one end of first even board and is rotated through the bottom plate of pivot and side fin group bottom and be connected.

Preferably, the bottom plate of the central fin group is equidistantly provided with positioning screw holes in the central filling area.

Preferably, a rubber pad is fixed at the bottom of the rotating side plate.

Compared with the prior art, the beneficial effects of the utility model are that:

when the heat radiating fin is installed, the rotary side plate is rotated to separate the inserting plate from the inserting groove, the position corresponding to the auxiliary screw hole is fixed, when the heat radiating fin needs to be folded and withdrawn, the rotary side plate is rotated in the direction to insert the inserting plate into the inserting groove to pull the side heat radiating fin group, the first connecting plate drives the second connecting plate and the connecting block to move, and the stable sliding is carried out under the action of the sliding groove and the sliding block, after the first connecting plate and the second connecting plate are pulled out, the side heat radiating fin group is folded by rotating, after the extension mechanism is matched and folded, the two extension mechanisms are fixed and limited, the heat radiating fin for the aero-engine realizes the firmer and more stable installation of the heat radiating fin under the action of the side fixing mechanism, and realizes the folding change of the structural shape of the central heat radiating fin group and the side heat radiating fin group under the matching action of the side fixing mechanism and, the transportation and the use of different environment are convenient, compared with the prior art, the installation and the change of the radiating fin structure are more convenient.

Drawings

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

FIG. 2 is a schematic view of the connection between the central fin group and the side fin group of the present invention;

FIG. 3 is a schematic view of the extension mechanism and the side fin set of the present invention;

FIG. 4 is a schematic view of the structure of the extending mechanism of the present invention;

FIG. 5 is a schematic structural view of the side fixing mechanism of the present invention;

fig. 6 is a schematic view of the connection between the side fixing mechanism and the bottom plate of the present invention.

In the figure: 1. a central fin group; 11. a center-fill region; 2. a side radiating fin group; 3. a side fixing mechanism; 31. rotating the side plate; 32. bolt holes; 33. an auxiliary screw hole; 34. a plugboard; 35. inserting grooves; 4. a base plate; 41. positioning screw holes; 5. an extension mechanism; 51. a chute; 52. connecting blocks; 53. A slider; 54. a first connecting plate; 55. and a second connecting plate.

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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1 and 2, a heat sink for an aircraft engine in the drawings includes a central heat sink set 1, side heat sink sets 2 and a bottom plate 4, the top of the bottom plate 4 is fixed with the central heat sink set 1, the two sides of the central heat sink set 1 are symmetrically provided with the side heat sink sets 2, one side of the side heat sink set 2, which is far away from the central heat sink set 1, is provided with a side fixing mechanism 3 capable of further fixing and mounting the device by screws, an extending mechanism 5 capable of extending and rotating the side heat sink is symmetrically arranged between the bottom plate 4 of the side heat sink set 2 and the bottom plate 4 of the central heat sink set 1, the surface of the central heat sink set 1 is provided with a central filling area 11, under the action of the side fixing mechanism 3, the effect of more firmly and stably mounting the heat sink is achieved, under the cooperation effect of the side, the folding of central fin group 1 and side fin group 2 has been realized and structural shape has been changed, convenient transportation and the use of different environment.

Referring to fig. 5 and 6, the side fixing mechanism 3 includes a rotating side plate 31, an auxiliary screw hole 33, a socket plate 34 and a socket groove 35, the bottom of the rotating side plate 31 is rotatably connected with the bottom plate 4 at the bottom of the side cooling fin group 2 through a rotating shaft, auxiliary screw holes 33 are equidistantly formed in the surface of the rotating side plate 31, insertion plates 34 are symmetrically fixed on the surface of the rotating side plate 31 on two sides of the auxiliary screw holes 33, and the two sides of the bottom plate 4 at the bottom of the side cooling fin group 2 corresponding to the position of the inserting plate 34 are provided with inserting grooves 35, the inserting plate 34 is inserted into the inserting groove 35 in a sliding manner, when the heat sink is installed, the rotating side plate 31 is rotated to separate the inserting plate 34 from the inserting groove 35, the position corresponding to the auxiliary screw hole 33 is fixed, when it needs to be folded and retracted, the rotating side plate 31 is rotated in the direction to insert the inserting plate 34 into the inserting groove 35.

Referring to fig. 2 and 3, bolt holes 32 are symmetrically formed in the surface of the rotating side plate 31 near the insertion plate 34, and after the matching extension mechanisms 5 are folded, the two extension mechanisms 5 are fixed and limited.

Referring to fig. 3 and 4, the extending mechanism 5 includes a sliding slot 51, a connecting block 52, sliding blocks 53, a first connecting plate 54 and a second connecting plate 55, the connecting block 52 is symmetrically disposed inside two sides of a bottom plate 4 at the bottom of the central fin group 1, the sliding blocks 53 are fixed on two sides of the connecting block 52, the sliding slot 51 is disposed at a position corresponding to the sliding block 53 inside the bottom plate 4, the sliding block 53 is slidably connected to the sliding slot 51, the first connecting plate 54 is fixed on one side of the connecting block 52 close to the side fin group 2, the first connecting plate 54 penetrates through the bottom plate 4 and is rotatably connected to the second connecting plate 55 through a rotating shaft, one end of the second connecting plate 55 far from the first connecting plate 54 is rotatably connected to the bottom plate 4 at the bottom of the side fin group 2 through the rotating shaft, the side fin group 2 is pulled, the first connecting plate 54 drives the second connecting plate 55 and the connecting block 52 to move, and slide stably under the, after first link plate 54 and second link plate 55 are pulled out, the rotation causes side fin group 2 to be folded.

Referring to fig. 1, positioning screw holes 41 are equidistantly formed in the central filling area 11 of the bottom plate 4 of the central fin group 1, so that the bottom plate 4 can be conveniently installed and fixed.

Referring to fig. 6, a rubber pad is fixed at the bottom of the rotating side plate 31 to prevent the rotating side plate 31 from wearing the surface of the component during installation.

In the scheme, when the heat sink is installed, the rotating side plate 31 is rotated to enable the inserting plate 34 to be separated from the inserting groove 35 and fixed corresponding to the position of the auxiliary screw hole 33, when the heat sink needs to be folded and retracted, the rotating side plate 31 is rotated in the direction to insert the inserting plate 34 into the inserting groove 35, the side heat sink set 2 is pulled, the first connecting plate 54 drives the second connecting plate 55 and the connecting block 52 to move and slide stably under the action of the sliding groove 51 and the sliding block 53, after the first connecting plate 54 and the second connecting plate 55 are pulled out, the side heat sink set 2 is folded by rotating, after the matched extension mechanism 5 is folded, the two extension mechanisms 5 are fixed and limited, under the action of the side fixing mechanism 3, the effect of firmer and more stable installation of the heat sink is realized, under the matching action of the side fixing mechanism 3 and the extension mechanisms 5, the folding change structure shape of the central radiating fin group 1 and the side radiating fin group 2 is realized, the transportation and the use in different environments are convenient, and compared with the prior art, the folding change structure of the central radiating fin group and the side radiating fin group is more convenient to install and change the radiating fin structure.

It is noted that, herein, relational terms such as first and second, and the like may be 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. Also, 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 invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a fin for aeroengine, includes central fin group (1), side fin group (2) and bottom plate (4), bottom plate (4) top is fixed with central fin group (1), central fin group (1) bilateral symmetry is equipped with side fin group (2), its characterized in that: the side heat sink group (2) is far away from one side of the central heat sink group (1) and is provided with a side fixing mechanism (3) capable of further fixedly mounting the device through screws, an extending mechanism (5) capable of extending and rotating the side heat sink is symmetrically arranged between a bottom plate (4) at the bottom of the side heat sink group (2) and a bottom plate (4) of the central heat sink group (1), and a central filling area (11) is arranged on the surface of the central heat sink group (1).

2. A fin for an aircraft engine according to claim 1, wherein: side fixed establishment (3) are including rotating curb plate (31), supplementary screw hole (33), plugboard (34) and inserting groove (35), it rotates through pivot and bottom plate (4) of side fin group (2) bottom to rotate curb plate (31) bottom and is connected, rotate curb plate (31) and seted up supplementary screw hole (33) at the equidistance on the surface, it is fixed with plugboard (34) to rotate curb plate (31) and lie in supplementary screw hole (33) bilateral symmetry on the surface, and inserting groove (35) have been seted up to the position that bottom plate (4) both sides of side fin group (2) bottom correspond plugboard (34), plugboard (34) are pegged graft for sliding with inserting groove (35).

3. A fin for an aircraft engine according to claim 2, wherein: bolt holes (32) are symmetrically formed in one side, close to the insertion plate (34), of the surface of the rotating side plate (31).

4. A fin for an aircraft engine according to claim 1, wherein: the extension mechanism (5) comprises a sliding groove (51), a connecting block (52), a sliding block (53), a first connecting plate (54) and a second connecting plate (55), the connecting blocks (52) are symmetrically arranged inside two sides of the bottom base plate (4) of the central radiating fin group (1), sliding blocks (53) are fixed on two sides of the connecting block (52), sliding grooves (51) are arranged in the bottom plate (4) at positions corresponding to the sliding blocks (53), the sliding block (53) is in sliding connection with the sliding groove (51), a first connecting plate (54) is fixed on one side of the connecting block (52) close to the side radiating fin group (2), the first connecting plate (54) penetrates through the bottom plate (4) and is rotationally connected with a second connecting plate (55) through a rotating shaft, one end of the second connecting plate (55) far away from the first connecting plate (54) is rotatably connected with the bottom plate (4) at the bottom of the side radiating fin group (2) through a rotating shaft.

5. A fin for an aircraft engine according to claim 1, wherein: and the bottom plate (4) at the bottom of the central cooling fin group (1) is positioned in the central filling area (11) at equal intervals and is provided with positioning screw holes (41).

6. A fin for an aircraft engine according to claim 2, wherein: and a rubber pad is fixed at the bottom of the rotating side plate (31).