CN208901926U - A kind of aircraft radiator body and radiator - Google Patents
A kind of aircraft radiator body and radiator Download PDFInfo
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- CN208901926U CN208901926U CN201821420931.7U CN201821420931U CN208901926U CN 208901926 U CN208901926 U CN 208901926U CN 201821420931 U CN201821420931 U CN 201821420931U CN 208901926 U CN208901926 U CN 208901926U
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- heat
- dissipating pipe
- radiator
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- fin
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Abstract
The utility model discloses a kind of aircraft radiator bodies, including one or more heat-dissipating pipe and multiple fins, the heat-dissipating pipe in the shape of a spiral, is provided with more than one mounting hole on each fin, the quantity of the mounting hole on each fin and the quantity of heat-dissipating pipe are identical；Each fin passes through mounting hole and is sheathed on each heat-dissipating pipe and is fixed on heat-dissipating pipe.The invention also discloses a kind of aircraft radiator, including radiator fan, the side of the radiator fan is provided with aircraft radiator body as described above.The aircraft of the utility model radiator body and radiator all have the advantages that simple structure, good heat dissipation effect.
Description
Technical field
The utility model relates generally to aircraft technical field of heat dissipation, refers in particular to a kind of aircraft radiator body and heat dissipation
Device.
Background technique
The existing exhausted major part of engine radiator sold is rectangle or square etc. in the market, and is forced to radiator cold
But the fan overwhelming majority is circle, this just brings adverse effect to the radiating efficiency of radiator；Rectangle or pros simultaneously
For shape radiator for aircraft, aerodynamic performance is bad, is unfavorable for reducing air drag.
Utility model content
The technical problems to be solved in the utility model is that for technical problem of the existing technology, this is practical new
Type provides the aircraft radiator body and radiator that a kind of structure is simple, radiating efficiency is good.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
A kind of aircraft radiator body, including one or more heat-dissipating pipe and multiple fins, the heat-dissipating pipe is in spiral shell
Shape is revolved, is provided with more than one mounting hole on each fin, the quantity of the mounting hole on each fin and the quantity of heat-dissipating pipe are identical；
Each fin passes through mounting hole and is sheathed on each heat-dissipating pipe and is fixed on heat-dissipating pipe.
As a further improvement of the above technical scheme:
Each fin is evenly arranged on heat-dissipating pipe.
When the quantity of the heat-dissipating pipe is multiple, each heat-dissipating pipe parallel arrangement.
The same end of each heat-dissipating pipe is interconnected to form a plurality of liquid cooling loop parallel with one another.
Each heat-dissipating pipe dislocation connection is to form a liquid cooling loop.
The fin is welded on the heat-dissipating pipe.
The heat-dissipating pipe is aluminium alloy heat-dissipating pipe；The fin is aluminum alloy fin.
The invention also discloses a kind of aircraft radiator, including radiator fan, the sides of the radiator fan
It is provided with aircraft radiator body as described above.
As a further improvement of the above technical scheme:
The circumference of the radiator body is provided with the first protective cover；The radiator body is opposite with radiator fan
Side is provided with one or more support bar, and the both ends of support bar are connected with the first protective cover respectively.
The second protective cover is provided on the radiator fan, the circumference of the second protective cover is connected with the first protective cover.
Compared with the prior art, the advantages of the utility model are:
The aircraft radiator body of the utility model, it is spiral (in the form of annular discs) by the way that heat-dissipating pipe to be arranged,
Extend liquid cooling loop in range small as far as possible as far as possible, improves radiating efficiency, and spiral helicine heat-dissipating pipe is also convenient for and round wind
Fan matches；In addition, multiple fins are arranged on heat-dissipating pipe, the contact area of heat-dissipating pipe and air is increased, is further increased
Cooling effect.
The aircraft radiator of the utility model equally has the advantages that described in radiator body as above, and structure letter
It is single, be dismounted easily, good heat dissipation effect, windage it is small, light-weight.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of radiator body in the utility model.
Fig. 2 is the structural schematic diagram of heat-dissipating pipe in the utility model.
Fig. 3 is the structural schematic diagram of fin in the utility model.
Fig. 4 is the schematic perspective view of radiator in the utility model.
Fig. 5 is the decomposition texture schematic diagram of radiator in the utility model.
Fig. 6 is the structural schematic diagram of radiator fan in the utility model.
Figure label indicates: 1, radiator body；101, heat-dissipating pipe；102, fin；1021, mounting hole；103, elbow；2,
First protective cover；201, trunnion；3, support bar；4, the second protective cover；5, fan.
Specific embodiment
The utility model is further described below in conjunction with Figure of description and specific embodiment.
As shown in Figure 1 to Figure 3, the aircraft radiator body of the present embodiment, including one or more 101 He of heat-dissipating pipe
Multiple fins 102, each heat-dissipating pipe 101 in the shape of a spiral, are provided with more than one mounting hole 1021, mounting hole on each fin 102
The shape size of 1021 shape size and heat-dissipating pipe 101 matches, specially rectangle (in other embodiments or
The other shapes such as circle), the quantity of the mounting hole 1021 on each fin 102 is identical as the quantity of heat-dissipating pipe 101；Each fin 102
It is sheathed on each heat-dissipating pipe 101 and is fixed on heat-dissipating pipe 101 by mounting hole 1021.The aircraft of the utility model, which is used, to be dissipated
Hot device ontology, it is spiral (in the form of annular discs) by the way that heat-dissipating pipe 101 to be arranged, extend liquid cooling as far as possible in range small as far as possible and returns
Radiating efficiency is improved on road, and spiral helicine heat-dissipating pipe 101 is also convenient for matching with Circular fan 5；In addition, in heat-dissipating pipe 101
The upper multiple fins 102 of setting, increase the contact area of heat-dissipating pipe 101 Yu air, further improve cooling effect.
In the present embodiment, each fin 102 is equidistant and is evenly arranged on heat-dissipating pipe 101；Specifically, by each fin 102 according to
It is secondary to be inserted on heat-dissipating pipe 101, then be welded on heat-dissipating pipe 101 by welding manners such as solderings, guarantee to be reliably connected.Wherein fin
102 and heat-dissipating pipe 101 be aluminum alloy material, it is light-weight, be suitable for aircraft on.
In the present embodiment, the quantity of heat-dissipating pipe 101 two, two 101 parallel side-by-side of heat-dissipating pipe arrangements, specifically such as Fig. 2 institute
Show.Certainly, in other embodiments, two heat-dissipating pipes 101 can also arrange (the combination side of similar mosquito-repellent incense in the same plane
Formula)；It is understood that not being defined herein to the quantity of heat-dissipating pipe 101, in other embodiments, can also use
Three, four or more heat-dissipating pipe 101, are selected with specific reference to actual conditions.
In the present embodiment, each dislocation of heat-dissipating pipe 101 connection is to form a liquid cooling loop.Specifically, as successively set in parallel
The heat-dissipating pipe 101 for the n# that is equipped with 1#, 2#, 3# ..., wherein the port at middle part is the end A, the port of circumference is the end B, then the A of 1# and 2#
End is connected, and 2# is connected with the end B of 3#, is sequentially connected, so that each series connection of heat-dissipating pipe 101 be made to form a liquid level circuit.Such as Fig. 2 institute
Show, it is preferable that using two heat-dissipating pipes 101 arranged side by side, the port B of two heat-dissipating pipes 101 is connected by elbow 103, thus in A
Port forms an inlet and a liquid outlet.Certainly, in other embodiments, the same end of each heat-dissipating pipe 101 mutually interconnects
It connects to form a plurality of liquid cooling loop parallel with one another.Specifically, such as 1#, 2#, 3# ..., the end A of the heat-dissipating pipe 101 of n# is connected with each other shape
At an inlet or liquid outlet；The end B of the heat-dissipating pipe 101 of 1#, 2#, 3# ... n# is interconnected to form liquid outlet or inlet,
It respectively enters to make each heat-dissipating pipe 101 form liquid cooling loop in parallel after liquid cooling medium enters from one end to each heat-dissipating pipe
101, then after each heat-dissipating pipe 101 is radiated, then the other end through each heat-dissipating pipe 101 converges.Specifically, each heat-dissipating pipe
101 end is connected with each other by elbow 103.
As shown in Figures 4 to 6, the invention also discloses a kind of aircraft radiators, including radiator fan 5, dissipate
The side of Hot-air fan 5 is provided with aircraft radiator body 1 as described above.Radiator fan 5 is carrying out pressure air discharging and radiating
When, coolant liquid in heat-dissipating pipe 101 is cooled down.The aircraft heat spreader structures of the utility model are simple, are dismounted easily, dissipate
Thermal effect is good, windage is small and light-weight.
In the present embodiment, the circumference of radiator body 1 is provided with the first protective cover 2, and the first protective cover 2 is by two semicircles
Shape cover is fastened by bolts, and the circumference of the first protective cover 2 is provided with multiple trunnions 201 with holes, part trunnion
201 with aircraft engine corresponding component for connecting；In addition it is arranged in the side opposite with radiator fan 5 of radiator body 1
There is one or more support bar 3, the both ends of support bar 3 are connected with the trunnion with holes 201 of the first protective cover 2 by bolt respectively.
Wherein each support bar 3 is arranged and is parallel to each other along the radial direction of radiator body 1, for undertaking weight when heat-dissipating pipe 101 works.
In the present embodiment, the second netted protective cover 4 is provided on radiator fan 5, the circumference of the second protective cover 4 passes through
Bolt is connected with the trunnion with holes 201 on the first protective cover 2.
Above are merely preferred embodiments of the utility model, the protection scope of the utility model is not limited merely to above-mentioned
Embodiment, technical solution belonging to the idea of the present invention belong to the protection scope of the utility model.It should be pointed out that pair
For those skilled in the art, several improvements and modifications without departing from the principle of the utility model,
It should be regarded as the protection scope of the utility model.
Claims (10)
1. a kind of aircraft radiator body, which is characterized in that including one or more heat-dissipating pipe (101) and multiple fins
(102), the heat-dissipating pipe (101) in the shape of a spiral, is provided with more than one mounting hole (1021), each wing on each fin (102)
The quantity of mounting hole (1021) on piece (102) is identical as the quantity of heat-dissipating pipe (101)；Each fin (102) passes through mounting hole
(1021) it is sheathed on each heat-dissipating pipe (101) and is fixed on heat-dissipating pipe (101).
2. aircraft radiator body according to claim 1, which is characterized in that each fin (102) is evenly arranged in
On heat-dissipating pipe (101).
3. aircraft radiator body according to claim 1 or 2, which is characterized in that when the heat-dissipating pipe (101)
When quantity is multiple, each heat-dissipating pipe (101) parallel arrangement.
4. aircraft radiator body according to claim 3, which is characterized in that the same end of each heat-dissipating pipe (101)
It is interconnected to form a plurality of liquid cooling loop parallel with one another.
5. aircraft radiator body according to claim 3, which is characterized in that each heat-dissipating pipe (101) dislocation connection
To form a liquid cooling loop.
6. aircraft radiator body according to claim 1 or 2, which is characterized in that the fin (102) is welded in
On the heat-dissipating pipe (101).
7. aircraft radiator body according to claim 1 or 2, which is characterized in that the heat-dissipating pipe (101) is aluminium
Alloy heat-sink pipe；The fin (102) is aluminum alloy fin.
8. a kind of aircraft radiator, which is characterized in that including radiator fan (5), the side of the radiator fan (5) is arranged
Just like aircraft described in any one of claim 1 to 7 with radiator body (1).
9. aircraft radiator according to claim 8, which is characterized in that the circumference of the radiator body (1)
It is provided with the first protective cover (2)；The radiator body and radiator fan (5) opposite side are provided with one or more support
Item (3), the both ends of support bar (3) are connected with the first protective cover (2) respectively.
10. aircraft radiator according to claim 9, which is characterized in that be provided on the radiator fan (5)
The circumference of two protective covers (4), the second protective cover (4) is connected with the first protective cover (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821420931.7U CN208901926U (en) | 2018-08-31 | 2018-08-31 | A kind of aircraft radiator body and radiator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821420931.7U CN208901926U (en) | 2018-08-31 | 2018-08-31 | A kind of aircraft radiator body and radiator |
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| Publication Number | Publication Date |
|---|---|
| CN208901926U true CN208901926U (en) | 2019-05-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821420931.7U Active CN208901926U (en) | 2018-08-31 | 2018-08-31 | A kind of aircraft radiator body and radiator |
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| CN (1) | CN208901926U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110822703A (en) * | 2019-11-23 | 2020-02-21 | 南京启景环境科技有限公司 | Electric heating circulation hot water warmer |
-
2018
- 2018-08-31 CN CN201821420931.7U patent/CN208901926U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110822703A (en) * | 2019-11-23 | 2020-02-21 | 南京启景环境科技有限公司 | Electric heating circulation hot water warmer |
| CN110822703B (en) * | 2019-11-23 | 2021-03-16 | 南京启景环境科技有限公司 | Electric heating circulation hot water warmer |
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