Kaleidoscope type skin inner flow channel structure

Abstract

The utility model relates to a kaleidoscope type skin inner flow channel structure, belongs to the technical field of liquid cooling heat dissipation of airborne equipment, and solves the problems that an existing skin inner flow channel is poor in heat exchange effect and obvious in local temperature rise. The kaleidoscope type skin inner flow channel structure comprises a cooling liquid inlet, a guide-in channel, a kaleidoscope flow channel, a cross-shaped guide-out channel and a cooling liquid outlet, the kaleidoscope flow channel comprises multiple layers of annular main paths which are arranged in a nested mode, and every two adjacent layers of annular main paths are communicated through multiple parallel branches which are connected in parallel. The lead-in channel is connected with the cooling liquid inlet and the outermost layer of the kaleidoscope flow channel; the cross-shaped guide-out channel is arranged in the middle of the kaleidoscope flow channel and communicates with the innermost layer of flow channel of the kaleidoscope flow channel. The cooling liquid outlet is formed in the center of the cross-shaped leading-out channel and used for leading out cooled cooling liquid. According to the utility model, rapid cooling of high-temperature cooling liquid is realized, and the phenomenon that local temperature rise of the skin is too fast is reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to airborne equipment liquid cooling heat dissipation technical field especially relates to a kaleidoscope type skin inner runner structure. BACKGROUND

[0002] In recent years, with the increasing degree of integration of electronic equipment, the heat power increases exponentially. At the same time, the volume and weight of electronic equipment are continuously compressed, and miniaturization and light weight are increasingly becoming the basic requirements of electronic equipment. The heat exchange capacity of active liquid circulation system is high, which has been increasingly widely used in electronic equipment heat dissipation system.

[0003] However, in practical application, the space of airborne equipment is small, and water cooling machine cannot be configured. At present, the mode of guiding the cooling liquid into the internal runner of the aircraft skin is adopted to cool the cooling liquid after heat absorption, thereby realizing the continuous cooling of electronic equipment. However, the inflow of high-temperature cooling liquid into the aircraft skin will cause serious local temperature rise of the skin, thereby affecting its structural performance, and the limited heat exchange surface of the internal runner of the skin will also lead to unsatisfactory heat exchange effect, thereby unable to guarantee the cooling effect of electronic equipment.

[0004] Therefore, it is necessary to provide a novel skin internal runner structure design to improve the heat exchange effect and guarantee the cooling liquid temperature, while avoiding the rapid local temperature rise of the skin affecting its structural performance. UTILITY MODEL CONTENT

[0005] In view of the above analysis, the utility model aims to provide a kaleidoscope type skin internal runner structure to solve the problems of unsatisfactory heat exchange effect of the internal runner of the existing skin cold plate and rapid temperature rise of the skin.

[0006] The purpose of the utility model is mainly realized through the following technical schemes:

[0007] A kaleidoscope type skin internal runner structure, comprising: a cooling liquid inlet, an import channel, a kaleidoscope runner, a cross-shaped export channel and a cooling liquid outlet;

[0008] The kaleidoscope runner comprises a plurality of annular main roads arranged in layers, and the adjacent two layers of annular main roads are communicated through a plurality of parallel branches arranged in parallel;

[0009] One end of the import channel is connected with the cooling liquid inlet, and the other end is connected with the outermost layer of the kaleidoscope runner; the cooling liquid inlet is used for guiding the cooling liquid after heat absorption and temperature rise;

[0010] The cross-shaped export channel is arranged in the middle of the kaleidoscope runner, and the four ports of the cross-shaped export channel are communicated with the innermost layer of the kaleidoscope runner;

[0011] The cooling liquid outlet is arranged at the center of the cross-shaped leading-out channel, and is used for leading out the cooling liquid cooled by the aircraft skin.

[0012] Further, the leading-in channels are arranged at intervals in the circumferential direction of the kaleidoscope flow channel, and the starting ends of the four leading-in channels are connected to one cooling liquid inlet.

[0013] Further, the multiple parallel branches are arranged at intervals in the circumferential direction of the annular main channel.

[0014] Further, the annular main channel of the kaleidoscope flow channel comprises four annular flow channels arranged in layers, namely a first annular main channel, a second annular main channel, a third annular main channel and a fourth annular main channel.

[0015] Further, multiple first parallel branches are arranged between the first annular main channel and the second annular main channel to communicate; the multiple first parallel branches are arranged at intervals in the circumferential direction of the second annular main channel.

[0016] Further, multiple second parallel branches are arranged between the second annular main channel and the third annular main channel to communicate; the multiple second parallel branches are arranged at intervals in the circumferential direction of the third annular main channel.

[0017] Further, multiple third parallel branches are arranged between the third annular main channel and the fourth annular main channel to communicate; the multiple third parallel branches are arranged at intervals in the circumferential direction of the fourth annular main channel.

[0018] Further, concentric annular flow channels are arranged on the first parallel branches.

[0019] Further, the concentric annular flow channels comprise an outer annular flow channel and an inner annular flow channel arranged concentrically; the outer annular flow channel communicates with the first parallel branch, and the first parallel branch penetrates the outer annular flow channel to communicate with the inner annular flow channel.

[0020] Further, at least two circular annular flow channels are arranged in the second parallel branches.

[0021] The technical scheme of the kaleidoscope skin inner flow channel structure can at least achieve one of the following effects:

[0022] 1. The kaleidoscope skin inner flow channel structure is provided with leading-in channels on the outside of the kaleidoscope flow channel, and is provided with cross-shaped leading-out channels on the inside, multiple annular main channels and parallel branches arranged in layers, realizes the mutual parallel connection of the multiple parallel branches and the multi-layer nested conduction, and improves the heat exchange efficiency of the cooling liquid.

[0023] 2. The kaleidoscope-type internal flow channel structure of this utility model allows the coolant, after absorbing heat and heating up, to be introduced into the kaleidoscope flow channel through four inlet channels for heat exchange and cooling. Due to the design of multiple inlet channels, a ring main channel, and multiple parallel branch channels, the coolant can spread rapidly inside the aircraft skin, effectively reducing the temperature rise of the skin structure and avoiding the decrease in structural performance such as stiffness and strength caused by the temperature rise of the skin.

[0024] 3. In the kaleidoscope-type skin internal flow channel structure of this utility model, when the coolant flows in the annular main channel and the arc-shaped parallel branch channels, the overall flow channel structure is mostly arc-shaped and can be divided by multiple parallel branch channels, which can effectively reduce flow resistance and realize the smooth division and convergence of coolant. The flow channel design conforms to the principle of fluid dynamics, which is conducive to the smooth flow of coolant inside the kaleidoscope flow channel, thereby ensuring the heat exchange effect.

[0025] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages will become apparent from the description or be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained from the description and accompanying drawings, which are particularly pointed out. Attached Figure Description

[0026] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0027] Figure 1 This is a schematic diagram of the kaleidoscope-type skin internal flow channel structure of this utility model;

[0028] Figure 2 for Figure 1 A partial enlarged view of the first parallel branch of the kaleidoscope-shaped skin internal flow channel structure;

[0029] Figure 3 for Figure 1 A partial enlarged view of the second parallel branch of the kaleidoscope-shaped skin internal flow channel structure.

[0030] Figure label:

[0031] 1-Coolant inlet; 2-Inlet channel; 3-Kaleidoscope flow channel; 4-Cross-shaped outlet channel; 5-Coolant outlet; 31-First annular main path; 32-First parallel branch path; 33-Second annular main path; 34-Second parallel branch path; 35-Third annular main path; 36-Third parallel branch path; 37-Fourth annular main path; 320-Concentric annular flow channel; 321-Outer annular flow channel; 322-Inner annular flow channel; 31-First circular annular flow channel; 32-Second circular annular flow channel. Detailed Implementation

[0032] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0033] Example 1

[0034] A specific embodiment of this utility model discloses a kaleidoscope-type skin internal flow channel structure, such as... Figure 1 As shown, it includes: a coolant inlet 1, an inlet channel 2, a kaleidoscope-shaped flow channel 3, a cross-shaped outlet channel 4, and a coolant outlet 5. Specifically, one end of the inlet channel 2 is connected to the coolant inlet 1, and the other end is connected to the outermost flow channel of the kaleidoscope-shaped flow channel 3; the coolant inlet 1 is connected to a heat storage tank through a coolant pipeline, and is used to introduce the heat-exchanged and heated coolant into the inner flow channel of the aircraft skin.

[0035] Preferably, such as Figure 1 As shown, four inlet channels 2 are equally spaced along the circumference of the kaleidoscope flow channel 3, and each of the four inlet channels 2 is connected to a coolant inlet 1 at its starting end, allowing coolant to flow into the kaleidoscope flow channel 3 through the four inlet channels 2 for heat exchange with the aircraft skin. Furthermore, the coolant inlets 1 are connected to the coolant inlet pipes via four skin inlet pipes and a five-way pipe structure, allowing the coolant after heat exchange with electronic equipment to be diverted by the five-way pipe structure to the four skin inlet pipes, and then flow into the kaleidoscope flow channel 3 through the four inlet channels 2 for heat exchange and cooling with the aircraft skin.

[0036] In this embodiment, the kaleidoscope-type parallel flow channel is designed with multiple coolant inlets 1 in the inlet section to introduce coolant into the kaleidoscope flow channel 3 in multiple ways for heat exchange and cooling. Furthermore, by setting multiple first parallel branches 32 as branch branches, the multiple branch branches are connected in parallel with each other, which can improve the uniformity and stability of coolant flow in the aircraft skin.

[0037] Specifically, the kaleidoscope flow channel 3 has a multi-layered nested annular structure; the cross-shaped outlet channel 4 is located in the middle of the kaleidoscope flow channel 3, and all four ports of the cross-shaped outlet channel 4 are connected to the innermost flow channel of the kaleidoscope flow channel 3; the coolant outlet 5 is located in the center of the cross-shaped outlet channel 4, and is connected to the kaleidoscope flow channel 3 through the four branches of the cross-shaped outlet channel 4, so that the coolant after being cooled by the aircraft skin can be discharged through the coolant outlet 5.

[0038] like Figure 1As shown, the kaleidoscope flow passage 3 comprises a plurality of annular main channels arranged in layers, and the adjacent two layers of annular main channels are communicated through a plurality of parallel branches arranged in parallel, and the plurality of parallel branches are arranged at equal intervals along the circumferential direction of the annular main channel.

[0039] Preferably, as Figure 1 As shown, the annular main channel of the kaleidoscope flow passage 3 comprises four annular flow channels arranged in layers, which are respectively: a first annular main channel 31, a second annular main channel 33, a third annular main channel 35 and a fourth annular main channel 37.

[0040] Specifically, a plurality of first parallel branches 32 are arranged between the first annular main channel 31 and the second annular main channel 33 for communication; the plurality of first parallel branches 32 are arranged at equal intervals along the circumferential direction of the second annular main channel 33; preferably, the first parallel branch 32 is an arc-shaped flow channel.

[0041] Specifically, a plurality of second parallel branches 34 are arranged between the second annular main channel 33 and the third annular main channel 35 for communication; the plurality of second parallel branches 34 are arranged at equal intervals along the circumferential direction of the third annular main channel 35; preferably, the second parallel branch 34 is an arc-shaped flow channel.

[0042] Specifically, a plurality of third parallel branches 36 are arranged between the third annular main channel 35 and the fourth annular main channel 37 for communication; the plurality of third parallel branches 36 are arranged at equal intervals along the circumferential direction of the fourth annular main channel 37; preferably, the third parallel branch 36 is an arc-shaped flow channel.

[0043] Further, the end of the introduction channel 2 is communicated with the first annular main channel 31, and the four introduction channels 2 are arranged at intervals of 90° along the outer side of the first annular main channel 31. The four liquid inlet ports of the cross-shaped outlet channel 4 are communicated with the inner side of the fourth annular main channel 37, and the four branches of the cross-shaped outlet channel 4 are communicated with each other at the middle part.

[0044] In this embodiment, by designing the cross-shaped outlet channel 4, a cooling liquid outlet 5 is arranged at the center of the cross-shaped outlet channel 4, and the cooling liquid cooled in the kaleidoscope flow passage 3 is gathered to the cooling liquid outlet 5 position, and the cooling liquid flows into the heat dissipation structure again to absorb heat. In this embodiment, by arranging the introduction channel 2 on the outer side of the kaleidoscope flow passage 3 and the cross-shaped outlet channel 4 on the inner side, the parallel connection of the plurality of parallel branches and the multi-layer nested conduction are realized, the heat exchange efficiency of the cooling liquid is improved, and the rapid spreading of the cooling liquid in the aircraft skin effectively reduces the temperature rise of the skin structure, avoiding the decline of the structural performance such as stiffness and strength caused by the temperature rise of the skin.

[0045] In practice, coolant flows into the first annular main channel 31 through four inlet channels 2, and is then branched from the first annular main channel 31 into multiple first parallel branches 32. The coolant then flows from the multiple first parallel branches 32 into the second annular main channel 33. Further, the coolant is branched from the second annular main channel 33 into multiple second parallel branches 34, and then flows from the multiple second parallel branches 34 into the third annular main channel 35. The coolant in the third annular main channel 35 is branched into multiple third parallel branches 36, and then flows into the fourth annular main channel 37. Finally, the coolant in the fourth annular main channel 37 flows into the coolant outlet 5 through the cross-shaped outlet channel 4, and can also flow into the coolant internal flow channel 203 of the heat dissipation structure through the skin outlet pipe, thus dissipating heat for the heat dissipation structure and electronic equipment.

[0046] In this embodiment, when the coolant inside the aircraft skin flows through the annular main channel and the arc-shaped parallel branch channels, the overall flow channel structure is mostly arc-shaped, which can reduce flow resistance and realize the smooth diversion and convergence of coolant. The flow channel design conforms to the principles of fluid dynamics, which is conducive to the smooth flow of coolant inside the kaleidoscope flow channel 3, thereby ensuring the heat exchange effect.

[0047] Furthermore, to enhance the heat exchange effect between the coolant and the aircraft skin structure, in this embodiment, a concentric circulation channel 320 is provided on the first parallel branch 32. For example... Figure 2 As shown, the concentric circulation channel 320 includes an outer circulation channel 321 and an inner circulation channel 322 arranged concentrically. Specifically, the outer circulation channel 321 is connected to the first parallel branch 32, and the first parallel branch 32 passes through the outer circulation channel 321 and connects with the inner circulation channel 322. The coolant flows into the outer circulation channel 321 and the inner circulation channel 322 from the first parallel branch 32 and then flows back into the first parallel branch 32, and flows into the second annular main channel 33 via the first parallel branch 32.

[0048] In this embodiment, the coolant is further divided into two annular outer ring flow channels 321 and inner ring flow channels 322 in the first parallel branch 32 as heat dissipation sub-flow channels. The number and size of the sub-flow channels can be adjusted as needed to adjust the heat dissipation capacity of the aircraft skin, thereby improving the adaptability of the cooling system of this utility model.

[0049] In this embodiment, as Figure 3 As shown, the second parallel branch 34 is provided with at least two annular flow channels in parallel; preferably, the second parallel branch 34 is provided with a first annular flow channel 31 and a second annular flow channel 32 in parallel.

[0050] Specifically, the first annular flow channel 31 and the second annular flow channel 32 are connected in series to the second parallel branch 34, such as Figure 3The cooling liquid flows into the third annular main path 35 after being shunted by the second annular main path 33 to the multiple second parallel branches 34 and then sequentially flowing through the first circular flow channel 31 and the second circular flow channel 32.

[0051] The kaleidoscope type liquid internal flow channel is arranged inside the aircraft skin, and comprises multiple parallel branches and multiple layers of nested annular main paths, and the multiple layers of annular main paths are communicated through the multiple parallel branches; the rotating and converging flow channel structure in the kaleidoscope flow channel 3 can realize the rapid shunting of the cooling liquid to the multiple parallel branches, and realize the sequential flow of the cooling liquid between the multiple layers of nested annular main paths through the multiple parallel branches; on the one hand, the level heat exchange and cooling of the cooling liquid are realized, the cooling liquid can rapidly spread on the outside of the annular structure kaleidoscope flow channel 3, and the high-temperature cooling liquid is prevented from being retained at a local position of the aircraft skin, which is beneficial to improving the heat exchange efficiency; on the other hand, the flow velocity of the cooling liquid is slowed down when flowing into the outer annular main path and the parallel branch with a large flow area, the heat exchange time with the aircraft skin can be prolonged, and the heat exchange effect is improved.

[0052] The above merely describes a preferred specific embodiment of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application.

Claims

1. A kaleidoscope type skin internal runner structure, characterized by, The application relates to a cooling liquid cooling device for an aircraft skin. The cooling liquid cooling device comprises a cooling liquid inlet (1), an import channel (2), a kaleidoscope flow channel (3), a cross-shaped export channel (4) and a cooling liquid outlet (5). The kaleidoscope flow channel (3) comprises multiple layers of annular main channels arranged in a nested mode, and adjacent two layers of annular main channels are communicated through multiple parallel branches arranged in parallel. One end of the import channel (2) is connected with the cooling liquid inlet (1), and the other end is connected with the outermost flow channel of the kaleidoscope flow channel (3); the cooling liquid inlet (1) is used for importing the cooling liquid after heat absorption and temperature rise. The cross-shaped export channel (4) is arranged in the middle of the kaleidoscope flow channel (3), and four ports of the cross-shaped export channel (4) are communicated with the innermost flow channels of the kaleidoscope flow channel (3). The cooling liquid outlet (5) is arranged in the center of the cross-shaped export channel (4), and the cooling liquid outlet (5) is used for exporting the cooling liquid after aircraft skin cooling and temperature drop.

2. The kaleidoscope skin internal flow passage structure according to claim 1, characterized by, Four paths of the import channel (2) are arranged at equal intervals in the circumferential direction of the kaleidoscope flow channel (3), and the starting ends of the four paths of the import channel (2) are connected with one cooling liquid inlet (1).

3. The kaleidoscope skin internal runner structure according to claim 1 or 2, characterized in that, Multiple parallel branches are arranged at equal intervals in the circumferential direction of the annular main channel.

4. The kaleidoscope skin internal runner structure of claim 3, wherein, The annular main channel of the kaleidoscope flow channel (3) comprises four layers of annular flow channels arranged in a nested mode, namely a first annular main channel (31), a second annular main channel (33), a third annular main channel (35) and a fourth annular main channel (37).

5. The kaleidoscope skin internal flow channel structure according to claim 4, characterized by, Multiple first parallel branches (32) are arranged between the first annular main channel (31) and the second annular main channel (33) to communicate; the multiple first parallel branches (32) are arranged at equal intervals in the circumferential direction of the second annular main channel (33).

6. The kaleidoscope skin internal flow channel structure according to claim 5, characterized by, Multiple second parallel branches (34) are arranged between the second annular main channel (33) and the third annular main channel (35) to communicate; the multiple second parallel branches (34) are arranged at equal intervals in the circumferential direction of the third annular main channel (35).

7. The kaleidoscope skin internal flow channel structure according to claim 6, characterized by, Multiple third parallel branches (36) are arranged between the third annular main channel (35) and the fourth annular main channel (37) to communicate; the multiple third parallel branches (36) are arranged at equal intervals in the circumferential direction of the fourth annular main channel (37).

8. A kaleidoscope skin internal flow channel structure according to any one of claims 5-7, characterized in that, A concentric ring flow channel (320) is arranged on the first parallel branch (32).

9. The kaleidoscope skin internal flow channel structure according to claim 8, characterized by, The concentric ring flow channel (320) comprises an outer ring flow channel (321) and an inner ring flow channel (322) arranged in a concentric mode; the outer ring flow channel (321) is communicated with the first parallel branch (32), and the first parallel branch (32) penetrates the outer ring flow channel (321) and is communicated with the inner ring flow channel (322).

10. The kaleidoscope skin internal flow channel structure according to claim 6, characterized by, At least two circular ring flow channels are arranged in the second parallel branch (34).

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