CN115484793A - Enhanced heat dissipation device - Google Patents
Enhanced heat dissipation device Download PDFInfo
- Publication number
- CN115484793A CN115484793A CN202211237335.6A CN202211237335A CN115484793A CN 115484793 A CN115484793 A CN 115484793A CN 202211237335 A CN202211237335 A CN 202211237335A CN 115484793 A CN115484793 A CN 115484793A
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- airfoil
- fin
- base plate
- fins
- heat dissipation
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- 230000017525 heat dissipation Effects 0.000 title claims abstract description 25
- 230000001965 increasing effect Effects 0.000 claims abstract description 23
- 230000000712 assembly Effects 0.000 claims abstract description 10
- 238000000429 assembly Methods 0.000 claims abstract description 10
- 241001669680 Dormitator maculatus Species 0.000 claims abstract description 7
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 claims abstract description 6
- 239000002826 coolant Substances 0.000 claims description 16
- 238000000034 method Methods 0.000 claims description 7
- 239000000758 substrate Substances 0.000 claims description 6
- 108010074506 Transfer Factor Proteins 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 4
- 230000008018 melting Effects 0.000 claims description 4
- 230000002708 enhancing effect Effects 0.000 claims description 2
- 238000004088 simulation Methods 0.000 description 6
- 238000004458 analytical method Methods 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012417 linear regression Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2039—Modifications to facilitate cooling, ventilating, or heating characterised by the heat transfer by conduction from the heat generating element to a dissipating body
- H05K7/20409—Outer radiating structures on heat dissipating housings, e.g. fins integrated with the housing
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- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The invention relates to the technical field of heat dissipation of electronic components, and particularly discloses a reinforced heat dissipation device which comprises a base plate, a plurality of rows of fin assemblies arranged on the base plate, and a cover plate positioned on the fin assemblies and matched with the base plate to form a hollow cavity; each row of the fin assembly comprises a plurality of groups of airfoil fins; the cross section of the airfoil fin is an NACA airfoil section, and the rib profile of the airfoil fin is a rib with unequal sections; the area of the cross section of the airfoil fin is sequentially increased from one side far away from the base plate to one side close to the base plate.
Description
Technical Field
The invention relates to the technical field of heat dissipation of electronic components, in particular to an enhanced heat dissipation device.
Background
During normal operation, heat generated by the electronic device must be dissipated to prevent junction temperature from exceeding its design operating temperature, resulting in performance rejection and reliability degradation. The method for enhancing the convection heat transfer mainly comprises the following steps: the turbulence degree is increased, the heat exchange area is increased, the thermophysical property of the fluid is improved, and the like. Especially for more compact devices with a trend toward increased power density, the heat dissipation device generally needs to be provided with fins to increase the heat exchange area due to the higher heat flow density.
By adopting the traditional enhanced heat transfer technology, various deformed fins are used on the heating surface of the channel, and the flow resistance is increased by adopting the measures of straight fins, corrugated fins, needle-shaped fins and the like, porous media and the like, so that the comprehensive thermodynamic coefficient is reduced. The surface area is increased, the material consumption and the processing complexity are increased while the surface area is increased by utilizing compact fins and the like, so that the cost is increased, the heat dissipation surface area is increased by increasing the height of the straight fins, the rib efficiency is reduced, and meanwhile, the rib is poor in heat exchange capacity at the top and low in rib efficiency because the thickness of the rib is usually thinner.
Patent CN110198615B describes a radial fin array structure, which uses straight fins to form a gradually enlarged flow channel, and the number of fins is increased according to the width of the flow channel in the flow direction. The design can break through the increased fins and the boundary layers on the surfaces of the fins, so that the heat dissipation performance is improved, but the problem is that the fins are irregular in shape and cannot utilize the whole effective heat dissipation area. Furthermore, the closer the channel is to the inlet, the more sparse the fins are, whereby the heat dissipation capacity is also greatly reduced, hot spots may be formed, whereas the closer the fins are to the outlet, the denser the pressure drop is increased.
Especially for the heat dissipation of airborne electronic equipment, because the high altitude pressure is small, the air volume generated by the fan is also small, the existing radiating fins of the airborne electronic equipment are all straight fins or uniform-section pin fins, and meanwhile, the selection of the structural parameters of the performance required by the radiating fins does not have the existing empirical formula, so that the most suitable structural parameters cannot be selected intuitively, and therefore, the radiating fins with small wind resistance, high rib efficiency and light weight are urgently needed.
Disclosure of Invention
The technical problem to be solved by the invention is to provide an enhanced heat dissipation device; the method aims to solve the problems that the wind resistance of a fin structure is large, rib efficiency is low and performance parameters of the fin cannot be obtained in the prior art.
The technical problem to be solved by the invention is as follows:
a reinforced heat dissipation device comprises a base plate, a plurality of rows of fin components arranged on the base plate, and a cover plate which is positioned on the fin components and matched with the base plate to form a hollow cavity;
each row of the fin assembly comprises a plurality of groups of airfoil fins;
the cross section of the airfoil fin is an NACA airfoil section, and the rib type of the airfoil fin is a rib with unequal sections; the area of the cross section of the airfoil fin is gradually increased from the side far away from the base plate to the side close to the base plate.
In some possible embodiments, multiple rows of fin assemblies are distributed in staggered rows with equal intervals, and the interval between two adjacent rows of fin assemblies is A;
the airfoil fins in each row are distributed at equal intervals, and the interval between every two adjacent airfoil fins is D.
In some possible embodiments, the length of the side of the airfoil fin far from the base plate is x, and the length of the side of the airfoil fin close to the base plate is y, wherein x < y; the rib height of the airfoil fin is h.
In some possible embodiments, the substrate has a rectangular structure with a length L; the multiple rows of fin assemblies are arranged in the longitudinal direction of the substrate.
In some possible embodiments, the base plate and the airfoil fin satisfy the relations (1) and (2);
wherein,
j is a heat transfer factor;
f friction factor.
In some possible embodiments, a projection of each set of the airfoil fins on a plane in which the cooling medium flows is in a right-angled trapezoid shape;
the projection of each group of the wing fins on a plane which is vertical to the flowing direction of the cooling medium is in an isosceles trapezoid shape.
In some possible embodiments, the length of the upper base of the right trapezoid is 7-9mm, the length of the lower base is 10-12mm, and the distance between two adjacent sets of airfoil fins along the flow direction of the cooling medium is 7-11mm.
In some possible embodiments, the distance between two adjacent sets of airfoil fins in the same row is 3-3.8mm.
In some possible embodiments, two ends of the hollow chamber are respectively provided with an opening; the opening comprises an inlet and an outlet; the leading edge of the airfoil fin is disposed on a side proximate the inlet.
In some possible embodiments, the airfoil fin is made using a selective laser melting technique.
Compared with the prior art, the invention has the following beneficial effects:
the cross section of the airfoil fin is an NACA airfoil section, and the rib profile of the airfoil fin is a rib with unequal sections; the area of the cross section of the airfoil fin is sequentially increased from the side far away from the base plate to the side close to the base plate; airflow vortex is not easy to generate behind the ribs of the wing-shaped fins, so that the wind resistance is reduced, and the heat exchange efficiency of the wing-shaped fins is improved;
according to the invention, the most appropriate rib parameters can be found more conveniently and rapidly through the formula (1) and the formula (2) of the base plate and the airfoil fin;
the cooling device is simple in structure, and the cold area medium flows in the hollow cavity chamber to take away heat of the base plate and the wing-shaped fins, so that the purpose of cooling components is achieved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of a base plate and fin assembly according to the present invention;
FIG. 3 is a front view of the base plate and fin assembly connection of the present invention;
FIG. 4 is an enlarged schematic view at A in FIG. 3;
FIG. 5 is a side view of the base plate and fin assembly connection of the present invention;
FIG. 6 is an isometric view of an airfoil fin of the present invention;
FIG. 7 is a top view of an airfoil fin of the present invention;
FIG. 8 is a bottom view of an airfoil fin of the present invention;
FIG. 9 is a flow field diagram according to example 1 of the present invention;
FIG. 10 is a flow field diagram of comparative example 1;
wherein: 1. a substrate; 2. a fin assembly; 21. an airfoil fin; 3. and a cover plate.
Detailed Description
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; they may be connected directly or indirectly through intervening media, or they may be interconnected within two or more other elements or in a relationship between two or more other elements. Reference herein to "first," "second," and similar words, does not denote any order, quantity, or importance, but rather are used to distinguish one element from another. Also, the use of the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. In the implementation of the present application, "and/or" describes an association relationship of associated objects, which means that there may be three relationships, for example, a and/or B, which may mean: a exists alone, A and B exist simultaneously, and B exists alone. In the description of the embodiments of the present application, the meaning of "a plurality" means two or more groups unless otherwise specified. For example, the positioning posts refer to two or more sets of positioning posts. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
The present invention will be described in detail below.
As shown in fig. 1-10:
a kind of enhanced heat dissipating double-fuselage, including the base plate 1, the multi-row is installed on the fin assembly 2 on the base plate 1, and locate on fin assembly 2 and cooperate with base plate 1 to form the blind flange 3 of the hollow chamber; the hollow cavity is used for cooling medium to flow; the fin assembly 2 is positioned in the hollow cavity; each row of the fin assembly 2 comprises a plurality of sets of airfoil fins 21; an inlet and an outlet are arranged at the two ends of the hollow cavity; the inlet is connected with the cooling medium supply device, and the outlet is connected with the cooling medium recovery device; the base plate 1 is in direct contact with the surface of an electronic component serving as a heating source, and a cooling medium flows through a channel formed by the wing fins 21 and takes away heat on the fin base plate 1 and the wing fins 21, so that the purpose of cooling the component is achieved.
The cross section is a NACA airfoil section, the rib profile of the airfoil fin 21 is a rib with unequal sections, namely the rib of the airfoil fin 21 adopts a structure with a large upper part and a large lower part; the area of the cross section of the airfoil fin 21 increases gradually from the side far away from the base plate 1 to the side close to the base plate 1 of the base plate 1.
By adopting the structural arrangement of the airfoil fins 21, airflow vortices are not easily generated on the rear edges of the airfoil fins 21, so that the pressure drop of the fins is greatly reduced; the wing fins 21 are positioned on the base plate 1, the tops of the fins also support the upper cover plate 3, and the wing fins are uniformly distributed in the hollow cavity.
The structure that the wing-shaped fins 21 are small at the upper part and large at the lower part is adopted, the contact area between the wing-shaped fins and the base plate 1 is increased while the height of the ribs is increased, so that the heat exchange surface area is increased, and the heat dissipation efficiency and the convection heat exchange coefficient of the ribs are improved;
because the windward area of the fins is reduced, the windward side is close to the incoming flow side of the cooling medium, and the wing section is used as the cross section, the generation of air vortex is reduced, and the pressure drop of the fins is greatly reduced.
In some possible embodiments, the fin assemblies 2 in multiple rows are distributed in staggered rows with equal intervals, and the interval between two adjacent rows of fin assemblies 2 is a;
the airfoil fins 21 in each row are distributed at equal intervals, and the interval between two adjacent groups of airfoil fins 21 is D.
In some possible embodiments, the length of the side of the airfoil fin 21 away from the base plate 1 is x, and the length of the side of the airfoil fin 21 close to the base plate 1 is y, where x < y; the rib height of the airfoil fin 21 is h.
In some possible embodiments, the substrate 1 has a rectangular structure with a length L; the plurality of rows of fin elements 2 are arranged in the longitudinal direction of the base plate 1.
The relationship among the heat transfer factor, the friction factor and each structural parameter is obtained by carrying out simulation analysis on models with different levels and different factors and processing data by using a multiple linear regression method; the base plate 1, the airfoil fins 21, the heat transfer factor and the friction factor satisfy relational expressions (1) and (2);
wherein,
j is a heat transfer factor;
f friction factor.
The relationships (1) and (2) will enable the design involving the airfoil fin 21 described above to more easily find the most appropriate rib parameters by need.
In some possible embodiments, the projection of each set of airfoil fins 21 on the plane of the flow direction of the cooling medium is a right trapezoid; i.e. a right-angled trapezoid as seen in a direction perpendicular to the cooling medium;
the projection of each group of airfoil fins 21 on a plane which is vertical to the flow direction of the cooling medium is isosceles trapezoid; i.e. an isosceles trapezoid as seen in the direction of flow of the cooling medium.
In some possible embodiments, the hollow chamber is provided with openings at both ends thereof; the opening comprises an inlet and an outlet; the leading edge of the airfoil fin 21 is disposed on the side near the inlet.
In some possible embodiments, the airfoil fin 21 is made using a selective laser melting technique. The selective laser melting technology is adopted, so that the use of manufacturing materials is reduced, and the radiator has light weight and high radiating efficiency;
in some possible embodiments, the length of the upper bottom of the right trapezoid is 7-9mm, the length of the lower bottom is 10-12mm, and the distance between two adjacent sets of airfoil fins 21 in the flow direction of the cooling medium is 7-11mm; namely x is 7-9mm, y is 10-12mm, and A is 7-11mm.
In some possible embodiments, the distance between two adjacent sets of airfoil fins 21 in the same row is 3-3.8mm; namely D is 3-3.8mm; the upper bottom width and the lower bottom width of the isosceles trapezoid are determined by the upper bottom surface length, the lower bottom surface length and the naca wing shape of the right-angle trapezoid.
Example 1:
in this embodiment, the rib height h of the airfoil fin 21 is 7mm, the length L of the base plate 1 is 340mm, the horizontal distance D between the ribs is 3mm, the vertical distance a between the ribs is 7mm, the length x of the upper top surface of the airfoil fin 21 is 7mm, and the length y of the lower top surface thereof is 10mm.
Numerical simulation is carried out on a row unit by using numerical simulation software fluent, the result is obtained, the flow field of the airfoil fin 21 is shown in figure 9 when the Reynolds number is 600, and simulation analysis is carried out to obtain that the heat flux is 471W/m 2 The inlet-outlet pressure difference was 38Pa.
Comparative example 1:
the fins in the comparative example are straight rib fins with equal sections, and the rib height, the plate length, the horizontal distance, the vertical distance and the length and width of the lower bottom surface of the fins are all 10mm;
numerical simulation is carried out on a row unit by using numerical simulation software fluent, the result is obtained, the flow field of the fin is shown in figure 10 when the Reynolds number is 600, and simulation analysis is carried out to obtain that the heat flux is 421W/m 2 The inlet-outlet differential pressure was 143Pa.
Therefore, the numerical simulation result can compare that under the condition of the same Reynolds number, the heat dissipation capacity of the unequal cross sections is 11.9% larger than that of the equal cross section straight rib, and the pressure difference is 73.4% smaller, so that compared with the equal cross section fin in the prior art, the invention increases the heat dissipation and reduces the wind resistance.
Therefore, by adopting the wing-shaped fin, the contact area between the fin and the base plate 1 is increased while the height of the rib is increased, so that the heat exchange surface area is increased, and the heat dissipation efficiency and the convection heat exchange coefficient of the rib are improved; and because the windward area is reduced, and the cross section is the NACA airfoil section, the generation of air vortex is reduced, so that the pressure drop of the fins is greatly reduced.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (10)
1. A reinforced heat dissipation device is characterized by comprising a base plate, a plurality of rows of fin components arranged on the base plate, and a cover plate which is positioned on the fin components and matched with the base plate to form a hollow cavity; each row of the fin assembly comprises a plurality of groups of airfoil fins;
the cross section of the airfoil fin is an NACA airfoil section, and the rib profile of the airfoil fin is a rib with unequal sections; the area of the cross section of the airfoil fin is gradually increased from the side far away from the base plate to the side close to the base plate.
2. The enhanced heat dissipation device of claim 1, wherein the plurality of rows of fin assemblies are distributed in staggered rows with equal spacing, and the spacing between two adjacent rows of fin assemblies is a;
the airfoil fins in each row are distributed at equal intervals, and the interval between every two adjacent airfoil fins is D.
3. The apparatus as claimed in claim 2, wherein the airfoil fin has a length x on a side thereof away from the base plate and a length y on a side thereof close to the base plate, wherein x < y; the rib height of the airfoil fin is h.
4. The apparatus as claimed in claim 3, wherein the substrate has a rectangular shape with a length L; the multiple rows of fin assemblies are arranged in the length direction of the substrate.
5. The enhanced heat dissipation device of claim 4, wherein the base plate and the airfoil fin satisfy the relations (1) and (2);
wherein,
j is a heat transfer factor;
f friction factor.
6. The apparatus according to claim 5, wherein each of the airfoil fins has a right-angled trapezoid projection on a plane in which a flow direction of the cooling medium is located;
the projection of each group of the wing fins on a plane which is vertical to the flowing direction of the cooling medium is in an isosceles trapezoid shape.
7. The enhanced heat dissipation device of claim 6, wherein the length of the upper base of the right trapezoid is 7-9mm, the length of the lower base of the right trapezoid is 10-12mm, and the distance between two adjacent sets of airfoil fins along the flow direction of the cooling medium is 7-11mm.
8. The enhanced heat dissipation device of claim 7, wherein the distance between two adjacent sets of airfoil fins in the same row is 3-3.8mm.
9. The device for enhancing heat dissipation of any one of claims 1-8, wherein the hollow chamber has openings at both ends; the opening comprises an inlet and an outlet; the leading edge of the airfoil fin is disposed on a side proximate the inlet.
10. The enhanced heat dissipation device of claim 9, wherein the airfoil fin is formed using selective laser melting techniques.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211237335.6A CN115484793A (en) | 2022-10-10 | 2022-10-10 | Enhanced heat dissipation device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211237335.6A CN115484793A (en) | 2022-10-10 | 2022-10-10 | Enhanced heat dissipation device |
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| CN115484793A true CN115484793A (en) | 2022-12-16 |
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| CN202211237335.6A Pending CN115484793A (en) | 2022-10-10 | 2022-10-10 | Enhanced heat dissipation device |
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Citations (9)
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|---|---|---|---|---|
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| JP2010210202A (en) * | 2009-03-12 | 2010-09-24 | Aisin Aw Co Ltd | Heat exchange body |
| JP2013024468A (en) * | 2011-07-20 | 2013-02-04 | Kanazawa Univ | Heat transfer tube array structure for heat exchanger |
| US20140318755A1 (en) * | 2009-04-09 | 2014-10-30 | General Electric Company | Shaped heat sinks to optimize flow |
| CN108180773A (en) * | 2018-01-29 | 2018-06-19 | 西安热工研究院有限公司 | A kind of interruption fin structure printed circuit board heat exchanger core body |
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| CN111335963A (en) * | 2020-02-20 | 2020-06-26 | 西安交通大学 | Wing section spoiler column structure and turbine blade |
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| CN113613440A (en) * | 2021-08-17 | 2021-11-05 | 珠海格莱克科技有限公司 | Enhanced heat dissipation device using array heat dissipation fins |
-
2022
- 2022-10-10 CN CN202211237335.6A patent/CN115484793A/en active Pending
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| CN108180773A (en) * | 2018-01-29 | 2018-06-19 | 西安热工研究院有限公司 | A kind of interruption fin structure printed circuit board heat exchanger core body |
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