Heat exchanger, space radiation angle model and heat exchange efficiency evaluation method

Abstract

This invention discloses a heat exchanger, a space radiation angle model, and a method for evaluating heat exchange efficiency. The heat exchanger includes a main body and fins. The main body has a hollow chamber with a flow channel inside. The main body has an inlet and an outlet, both of which are connected to the flow channel. Fins are connected to opposite sides of the main body and protrude from the main body in opposite directions. Specifically, along the protrusion direction of the fins, the thickness of the side of the fin furthest from the main body is less than the thickness of the side closest to the main body. This invention can couple natural convection with space radiation cooling, improving heat dissipation efficiency and mitigating the urban heat island effect.

Description

Technical Field

[0001] This invention relates to the field of building energy management and thermal energy utilization, and in particular to a heat exchanger, a space radiation angle model, and a method for evaluating heat exchange efficiency. Background Technology

[0002] With the continuous increase in power density of modern industrial equipment and electronic devices, efficient heat dissipation has become one of the key factors in ensuring stable equipment operation. Currently, widely used heat dissipation devices mainly rely on natural or forced convection to directly dissipate heat into the surrounding environment, such as air-cooled heat exchangers, finned heat exchangers, and fan-assisted cooling systems. However, these traditional heat dissipation methods have many limitations.

[0003] Traditional heat exchangers primarily rely on convection for heat dissipation during operation, releasing a large amount of waste heat directly into the atmosphere. This causes significant thermal pollution in localized areas, exacerbating the urban heat island effect and impacting the ecological environment and residents' quality of life. Furthermore, due to factors such as the low thermal conductivity and limited heat transfer efficiency of air, conventional convection cooling methods struggle to meet the increasing heat dissipation demands in high heat flux density applications, leading to increased equipment temperature, decreased stability, and even safety hazards. Summary of the Invention

[0004] The main objective of this invention is to propose a heat exchanger, an aerospace radiation angle model, and a method for evaluating heat exchange efficiency, which can couple natural convection with aerospace radiation cooling to improve heat dissipation efficiency and alleviate the urban heat island effect.

[0005] To achieve the above objectives, some embodiments of the present invention provide a heat exchanger comprising:

[0006] The main body has a hollow cavity with a flow guide channel inside. The main body has an inlet and an outlet, both of which are connected to the flow guide channel.

[0007] Fins are connected to opposite sides of the main body and protrude from the main body in opposite directions.

[0008] In particular, along the convex direction of the fin, the thickness of the side of the fin away from the main body is less than the thickness of the side closer to the main body.

[0009] In some embodiments, the fins are spaced apart along the vertical direction.

[0010] In some embodiments, the fins protrude horizontally from the body portion.

[0011] In some embodiments, the thickness of the fins gradually increases along the vertical direction from the side of the fins furthest from the main body to the side closest to the main body.

[0012] In some embodiments, the region of the fin that is cut off by the vertical plane is an isosceles triangle; and / or,

[0013] The fins are conical with a slope ranging from 2.7 to 3.7.

[0014] In some embodiments, the length of the fin along the convex direction is y, and the distance from the fin to its adjacent fin below it is d. The relationship between y and d satisfies:

[0015] y = pd, where p is in the range of 0.8 ≤ p ≤ 1.2.

[0016] In some embodiments, the outlet is located below the inlet in the vertical direction.

[0017] In some embodiments, the hollow cavity is provided with multiple spaced isolation modules, which divide the flow channel into multiple flow branches, and the multiple flow branches are interconnected.

[0018] In some embodiments, the cross-section of the main body portion cut by the vertical plane is rectangular, and the fins protrude along the thickness direction of the main body portion. The relationship between the length a, width b, and thickness c of the main body portion satisfies:

[0019] 70c≤b≤a.

[0020] A second aspect of the present invention provides a heat dissipation system comprising the heat exchanger of any of the preceding claims. The heat dissipation system includes at least two relatively distributed heat exchangers, wherein the distance between the main bodies of the two heat exchangers along the direction from one heat exchanger to the other is [missing information]. 2l The height of the main body in the vertical direction is h The length of the fin along the convex direction is y satisfy:

[0021] y=q[h / (lm)x-hm / (1-m)] , q The range is 0.8≤q≤1.2 .

[0022] A third aspect of the present invention provides a calculation model for a heat exchanger system and the angle of solar radiation, for use when the sun partially irradiates the heat exchanger system. The model is characterized by including the heat dissipation system of claim 10. The calculation model for the heat exchanger system and the angle of solar radiation has S3 and S5 surfaces corresponding to two adjacent heat exchangers, and S1 and S2 surfaces that are parallel to each other and spaced apart between S3 and S5 surfaces. Surface S6 is coplanar with S2 surface and is located between S3 and S2 surfaces. Surfaces S6 and S3 are suitable for solar irradiation. Surfaces S3, S1, S5, S2, and S6 are sequentially connected end-to-end, and their outlines, when intercepted by a vertical plane, form a parallelogram. The calculation model for the heat exchanger system and the angle of solar radiation includes at least one of the following relationships:

[0023] X 1,2 This represents the percentage of heat radiated from surface S1 that falls onto surface S2.

[0024] ;

[0025] And / or, X 1,3 This represents the percentage of heat radiated from surface S1 that falls onto surface S3.

[0026] ;

[0027] And / or, X 1,5 This represents the percentage of heat radiated from surface S1 that falls onto surface S5.

[0028] ;

[0029] And / or, X 1,6 This represents the percentage of heat radiated from surface S1 that falls onto surface S6.

[0030] ;

[0031] And / or, X 2,3 This represents the percentage of heat radiated from surface S2 that falls onto surface S3.

[0032] ;

[0033] And / or, X 2,5 This represents the percentage of heat radiated from surface S2 that falls onto surface S5.

[0034] ;

[0035] And / or, X 3,5 This represents the percentage of heat radiated from surface S3 that falls onto surface S5.

[0036] ;

[0037] And / or, X 3,6 This represents the percentage of heat radiated from surface S3 that falls onto surface S6.

[0038] ;

[0039] And / or, X 5,6 This represents the percentage of heat radiated from surface S5 that falls onto surface S6.

[0040] ;

[0041] in, It is the spacing of the heat exchanger2l and height h The ratio;

[0042] .

[0043] An embodiment of the fourth aspect of the present invention provides a calculation model for a heat exchanger system and the angle of aerospace radiation, for use when the sun is fully irradiated on the heat exchanger system. The model is characterized by including the heat dissipation system of claim 10. The calculation model for the heat exchanger system and the angle of aerospace radiation has two corresponding adjacent heat exchangers, one corresponding to surface S5, and the other corresponding to surfaces S3 and S4. Surfaces S3 and S4 are coplanar, wherein surface S3 is irradiated by the sun, surface S4 is not irradiated by the sun, surface S1 is sandwiched between surfaces S3 and S5, surface S2 is sandwiched between surfaces S4 and S5, and surfaces S4, S3, S1, S5, and S2 are sequentially connected end-to-end, and their outlines, intercepted by a vertical plane, form a parallelogram. The calculation model for the heat exchanger system and the angle of aerospace radiation includes at least one of the following relationships:

[0044] X 1,2 This represents the percentage of heat radiated from surface S1 that falls onto surface S2.

[0045] ;

[0046] And / or, X 1,3 This represents the percentage of heat radiated from surface S1 that falls onto surface S3.

[0047] ;

[0048] And / or, X 1,4 This represents the percentage of heat radiated from surface S1 that falls onto surface S4.

[0049] ;

[0050] And / or, X 1,5 This represents the percentage of heat radiated from surface S1 that falls onto surface S5.

[0051] ;

[0052] And / or, X 2,3 This represents the percentage of heat radiated from surface S2 that falls onto surface S3.

[0053] ;

[0054] And / or, X 2,4 This represents the percentage of heat radiated from surface S2 that falls onto surface S4.

[0055] ;

[0056] And / or, X 2,5 This represents the percentage of heat radiated from surface S2 that falls onto surface S5.

[0057] ;

[0058] And / or, X 3,5 This represents the percentage of heat radiated from surface S3 that falls onto surface S5.

[0059] ;

[0060] And / or, X 4,5 This represents the percentage of heat radiated from surface S4 that falls onto surface S5.

[0061] ;

[0062] in, It is the spacing of the heat exchanger 2l and height h The ratio;

[0063] ;

[0064] ;

[0065] ;

[0066] .

[0067] An embodiment of the fifth aspect of the present invention provides a method for evaluating the efficiency of a heat dissipation system, including the heat exchanger system of any of the above and a calculation model of the aerospace radiation angle.

[0068] According to the above embodiments, the beneficial effects of the present invention are:

[0069] The heat exchanger of the present invention includes a main body and fins. The main body serves as the base of the heat exchanger and is used to provide flow channels and connect the fins. The main body can be made of aluminum alloy, which has good thermal conductivity and lightweight properties. In some embodiments, the main body is a thin plate, for example, a plate with a length of 1m, a width of 1m, and a thickness of 1cm. The main body has a hollow chamber with flow channels inside to promote fluid flow and improve heat exchange efficiency. The main body has an inlet and an outlet, both of which are connected to the flow channels. Specifically, the inlet and outlet connect the flow channels to the external environment, ensuring smooth fluid flow to and from the heat exchanger.

[0070] The fins are connected to opposite sides of the main body and protrude from it in opposite directions. Along the protruding direction of the fins, the thickness of the side of the fin furthest from the main body is less than the thickness of the side closest to the main body. This thinner fin furthest from the main body facilitates faster heat transfer to the outer surface, improving surface temperature uniformity and thus enhancing radiation capacity. Furthermore, this design not only increases the structural stability of the heat exchanger but also optimizes the heat transfer path, allowing heat to be distributed more evenly across the fin surface, thereby achieving efficient heat dissipation through natural convection and radiative cooling.

[0071] In summary, the heat exchanger of this invention achieves efficient coupling of natural convection and aerospace radiative cooling through the synergistic structural design of the main body and fins. The main body incorporates flow channels to promote natural airflow within the hollow cavity, enhancing convective heat transfer efficiency. Simultaneously, the fins feature a gradient thinning design along the vertical direction, increasing the heat dissipation surface area and optimizing the heat transfer path to the surface, resulting in a more uniform heat distribution on the outer surface of the fins. This enhances their ability to emit infrared radiation into the sky, strengthening the aerospace radiative cooling effect. The combination of these two elements allows the heat exchanger to significantly improve overall heat dissipation efficiency without requiring additional energy consumption. Furthermore, when applied to buildings, this device effectively reduces building surface temperature and decreases heat emissions into the environment, thereby mitigating the urban heat island effect caused by dense building construction on an urban scale, resulting in significant ecological benefits. Therefore, the heat exchanger of this invention has a simple and reliable structure, a small unit footprint, effectively utilizes the aerospace radiative cooling process without additional energy consumption, significantly reduces building energy consumption and environmental heat hazards, and possesses excellent economic and practical value.

[0072] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0073] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0074] Figure 1 This is a schematic diagram of a heat dissipation system in one embodiment of the present invention, which includes two heat exchangers arranged accordingly;

[0075] Figure 2 This is a three-dimensional structural diagram of a heat exchanger viewed from a first perspective in one embodiment of the present invention;

[0076] Figure 3This is a three-dimensional structural diagram of a heat exchanger viewed from a second perspective in one embodiment of the present invention;

[0077] Figure 4 This is a three-dimensional structural diagram of a heat exchanger viewed from a third-person perspective in one embodiment of the present invention;

[0078] Figure 5 This is a three-dimensional structural diagram of a heat exchanger viewed from a fourth perspective in one embodiment of the present invention;

[0079] Figure 6 This is a schematic cross-sectional view of the heat exchanger cut by the first plane in one embodiment of the present invention;

[0080] Figure 7 This is a schematic cross-sectional view of the heat exchanger cut by the second plane in one embodiment of the present invention;

[0081] Figure 8 This is a schematic cross-sectional view of the heat exchanger cut by a third plane in one embodiment of the present invention;

[0082] Figure 9 To observe from another perspective Figure 8 A schematic cross-sectional view of the heat exchanger.

[0083] Figure 10 This is a schematic diagram of different operating conditions corresponding to the calculation model of the heat exchanger system and the aerospace radiation angle in one embodiment of the present invention.

[0084] Explanation of icon numbers:

[0085] Heat exchanger 10;

[0086] Main body 100; flow guide channel 110; isolation module 120; outlet 130; inlet 140;

[0087] Fin 200;

[0088] Vertical direction Y; horizontal direction X.

[0089] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0090] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0091] It should be noted that if the embodiments of the present invention involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0092] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or," "and / or," or "and / or" throughout the text implies three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0093] In related technologies, heat exchanger 10 mainly relies on convective heat dissipation, directly discharging building waste heat into the environment, which exacerbates the urban heat island effect. The heat exchanger 10 has not been effectively designed to couple air-to-ground radiative cooling with natural convection.

[0094] The following is for reference. Figures 1 to 10 This invention describes a heat exchanger 10, a heat dissipation system, a calculation model for the heat exchanger system and the aerospace radiation angle, and a method for evaluating the efficiency of the heat dissipation system, according to embodiments of the present invention. The invention belongs to the field of building energy management and thermal energy utilization, and particularly relates to the structural design of a heat exchanger 10 combining natural convection and aerospace radiation cooling. (Refer to...) Figures 1 to 9 In some embodiments, the heat exchanger 10 of the present invention includes a main body 100 and fins 200. The main body 100 serves as the base of the heat exchanger 10 and is used to provide the flow channel 110 and connect the fins 200. The main body 100 can be made of aluminum alloy, which has good thermal conductivity and lightweight characteristics. In some embodiments, the main body 100 is a relatively thin plate, for example, a plate with a length of 1m, a width of 1m, and a thickness of 1cm. The main body 100 has a hollow chamber, in which the flow channel 110 is provided to promote fluid flow and improve heat exchange efficiency. The main body 100 has an inlet 140 and an outlet 130, both of which are connected to the flow channel 110. Specifically, the inlet 140 and the outlet 130 connect the flow channel 110 to the external environment, ensuring that the fluid can smoothly enter and exit, thereby facilitating heat exchange in the heat exchanger 10.

[0095] Fins 200 are connected to opposite sides of the main body 100 and protrude from the main body 100 in opposite directions. Specifically, along the protruding direction of the fins 200, the thickness of the side of the fins 200 away from the main body 100 is less than the thickness of the side closer to the main body 100. Regarding the thickness of the fins 200, it can be understood that the protruding direction of the fins 200 is its length direction, and the direction perpendicular to this direction is the thickness direction of the fins 200. The thinner side of the fins 200 away from the main body 100 helps heat transfer to the outer surface more quickly, improving surface temperature uniformity and thus enhancing radiation capacity. Furthermore, this design not only increases the structural stability of the heat exchanger 10 but also optimizes the heat transfer path, allowing heat to be distributed more evenly on the surface of the fins 200, thereby achieving efficient heat dissipation through natural convection and radiative cooling.

[0096] In summary, the heat exchanger 10 of the present invention achieves efficient coupling of natural convection and aerospace radiative cooling through the synergistic structural design of the main body 100 and the fins 200. The main body 100 has an internal flow channel 110 that promotes natural airflow within the hollow cavity, enhancing convective heat transfer efficiency. Simultaneously, the fins 200 feature a gradient thinning design along the vertical Y-direction, which not only increases the heat dissipation surface area but also optimizes the heat transfer path to the surface, resulting in a more uniform heat distribution on the outer surface of the fins 200. This enhances their ability to emit infrared radiation into the sky, strengthening the aerospace radiative cooling effect. The combination of these two features allows the heat exchanger 10 to significantly improve overall heat dissipation efficiency without requiring additional energy consumption. Furthermore, when this device is applied to buildings, it can effectively reduce building surface temperature and decrease heat emissions into the environment, thereby mitigating the urban heat island effect caused by dense building construction on an urban scale, resulting in significant ecological benefits. Therefore, the heat exchanger 10 of the present invention has a simple and reliable structure, a small unit footprint, can effectively utilize the aerospace radiation cooling process, requires no additional energy consumption, significantly reduces building energy consumption and environmental heat hazards, and has good economic efficiency and practicality.

[0097] Understandably, in some embodiments, to further enhance heat dissipation, the main body 100 may be made of copper, which has a higher thermal conductivity than aluminum alloys. For example, using a copper main body 100, the internal flow channels 110 can be designed in a spiral shape, which not only increases the path length of fluid flow but also improves the heat exchange efficiency between the fluid and the inner wall of the main body 100. For the fins 200, in some embodiments, tiny protrusions or textures can be added to their surface to disrupt airflow and create more turbulent areas, thereby enhancing heat exchange between the air and the fins 200. For example, a series of parallel grooves can be machined on the surface of the fins 200, with the direction of these grooves perpendicular to the fluid flow direction. When air passes through these grooves, local vortices are formed, effectively improving heat dissipation efficiency.

[0098] Reference Figures 2 to 5 In some embodiments, viewed vertically in the Y direction, the fins 200 are designed in a spaced-out configuration. This arrangement not only optimizes the airflow path but also ensures that each fin 200 receives sufficient airflow, maximizing the use of natural convection for heat dissipation. Specifically, the spacing between the fins 200 creates an effective airflow channel as air enters between adjacent fins 200, promoting rapid heat dissipation from the fin surface. Furthermore, this spaced arrangement helps prevent increased airflow resistance due to overly dense fins 200, ensuring the overall efficiency of the heat exchanger 10. Combined with the flow channel 110 design within the main body 100, this spaced-out fin structure significantly improves the overall performance of the heat exchanger 10, achieving highly efficient heat dissipation while maintaining low operating costs and maintenance requirements.

[0099] Understandably, in some embodiments, the spacing between the fins 200 can be adjusted according to actual application requirements. For example, in applications requiring higher heat dissipation efficiency, the distance between the fins 200 can be reduced, while simultaneously increasing the height or width of the fins 200 to maintain sufficient airflow. Another extension is to introduce fins 200 of different shapes, such as wavy fins 200. This design not only increases the surface area but also further disrupts airflow, creating more turbulent zones, thereby improving heat dissipation efficiency.

[0100] It is understood that, in some embodiments, a high-reflectivity coating may be applied to the surface of the fin 200 to enhance the effect of aerospace radiation cooling, thereby reducing heat absorption by reflecting solar radiation and achieving better cooling.

[0101] Reference Figures 2 to 5 In some embodiments, the fins 200 of the heat exchanger 10 are designed to protrude from the body 100 in the horizontal direction X. This structural design not only maximizes space utilization and increases the air contact area, thereby improving heat dissipation efficiency, but also facilitates the coordinated operation of multiple heat exchangers 10.

[0102] In some embodiments, different materials are used to manufacture different parts of the fins 200. For example, a copper alloy with high thermal conductivity is used on the side closer to the main body 100, while a lightweight aluminum alloy with good mechanical strength is used on the side farther from the main body 100. This ensures efficient heat conduction while reducing overall weight. In some embodiments, a ceramic material with high thermal conductivity is used in the core part of the fins 200, while an outer layer of metal with good corrosion resistance is wrapped around it. This not only improves heat conduction efficiency but also extends service life.

[0103] Reference Figures 2 to 5 In some embodiments, the fins 200 of the heat exchanger 10 are designed with a gradually increasing thickness along the vertical direction Y. That is, the thickness of the fins 200 gradually increases from the side away from the main body 100 to the side closer to the main body 100. This design helps optimize the heat transfer path, allowing heat to flow more concentratedly to the thicker parts of the fins 200, thereby achieving efficient heat dissipation through natural convection and radiation cooling. Specifically, when heat diffuses from the main body 100 to both sides, due to the change in the thickness of the fins 200, heat tends to concentrate more near the main body 100, where the temperature is higher, which helps to accelerate heat dissipation. At the same time, the thinner ends of the fins 200 also help reduce air resistance, promote airflow, and further improve heat dissipation efficiency. This structural design enhances heat dissipation capacity while maintaining good economic efficiency.

[0104] Understandably, in some embodiments, the thickness variation of the fins 200 can be adjusted to further improve heat dissipation. For example, in addition to a linearly increasing thickness variation, a non-linear thickness distribution pattern, such as parabolic or exponential growth, can be adopted to more precisely control the heat transfer path. Such a design can optimize heat distribution according to specific heat dissipation requirements, allowing heat to be dissipated more evenly.

[0105] Reference Figures 2 to 5 In some embodiments, the area of ​​the heat exchanger 10's fins 200 cut by the vertical plane is an isosceles triangle. This design not only increases the airflow area but also maximizes heat dissipation efficiency within a limited space. Specifically, when air flows through the fins 200, due to their isosceles triangular shape, the air forms a more uniform flow path on the surface of the fins 200, reducing air resistance and allowing heat to be dissipated more effectively through natural convection and radiative cooling. Furthermore, the isosceles triangular design allows the fins 200 to gradually increase in thickness, helping to concentrate heat in the thicker sections, thereby improving overall heat dissipation performance.

[0106] The main body 100 has an internal flow channel 110, which is connected to the inlet 140 and the outlet 130 to ensure smooth flow of the medium (such as coolant). After entering the main body 100, the medium is distributed to various parts through the flow channel 110, carrying away heat and transferring it to the surface of the fins 200 for heat dissipation. The isosceles triangular structure of the fins 200 further enhances the heat dissipation effect, because the thicker side is closer to the main body 100 and can better conduct heat, while the thinner side is conducive to air circulation and reduces thermal resistance.

[0107] Reference Figures 2 to 5The fins 200 are conical with a slope ranging from 2.7 to 3.7, such as 2.7, 3.0, 3.125, 3.3, and 3.7, with 3.125 being preferred to achieve the best heat dissipation effect.

[0108] It is understandable that in some embodiments, in order to further optimize heat dissipation performance, other geometries besides isosceles triangles can be considered. For example, the fins 200 can be designed as trapezoidal or fan-shaped. For trapezoidal fins 200, the larger base is located on the side closer to the main body 100. This design also helps to concentrate heat conduction and provides more surface area for heat dissipation. For example, for fan-shaped fins 200, the heat dissipation efficiency can be adjusted by changing the angle of the fan, which is particularly advantageous in applications requiring directional heat dissipation.

[0109] Reference Figure 1 In some embodiments, the length of the fins 200 of the heat exchanger 10 along the convex direction is y, and the distance from the fin 200 to its adjacent fin 200 below it is d. The relationship between y and d satisfies: y = pd, where p ranges from 0.8 to 1.2, for example, p is 0.8, 0.9, 1.0, 1.1, or 1.2, preferably p is 1, that is, the length y of the fins 200 along the convex direction of the heat exchanger 10 is equal to the distance d from the fin 200 to its adjacent fin 200 below it. This design ensures that the spacing between the fins 200 is moderate, neither too dense to obstruct airflow nor too sparse to affect heat dissipation efficiency. Specifically, when the p value is close to 1, a balance is reached between the length and spacing of the fins 200, which helps to form an optimal airflow path and promotes effective heat dissipation. When the p-value is less than 1, the distance between the fins 200 is relatively large, suitable for applications requiring rapid heat dissipation; while when the p-value is greater than 1, the distance between the fins 200 is relatively small, suitable for applications with limited space but requiring high heat dissipation density. The flow channel 110 inside the main body 100 works in conjunction with the fins 200 to achieve efficient heat dissipation. During the flow of the medium within the flow channel 110, heat is carried to the surface of the fins 200, and then heat is exchanged with the surrounding environment through the fins 200. The reasonable layout and size ratio of the fins 200 ensure that heat can be dissipated quickly and evenly, thereby effectively utilizing the aerospace radiation cooling process and reducing building energy consumption and environmental heat hazards.

[0110] It is understandable that, in some embodiments, the ratio of fin length y to spacing d can be adjusted to adapt to different application scenarios. For example, when applied in a high-temperature environment, the p value can be appropriately increased to reduce the spacing between fins 200, thereby increasing the heat dissipation capacity per unit area. Conversely, in a low-temperature environment, the p value can be decreased to increase the spacing between fins 200, thereby reducing air resistance and improving heat dissipation efficiency.

[0111] It is understood that in some embodiments, an adjustable fin design 200 is introduced, meaning that the length or spacing of the fins 200 is dynamically adjusted according to actual operating conditions. For example, the ambient temperature and heat dissipation requirements can be monitored in real time by mechanical devices or intelligent control systems, thereby automatically adjusting the position or shape of the fins 200 to achieve optimal heat dissipation. For example, in some high-performance computing devices, the state of the heat exchanger 10 can be dynamically adjusted according to the processor's workload to ensure that it is always within the optimal operating temperature range.

[0112] Reference Figure 2 as well as Figures 6 to 8 In some embodiments, the main body 100 of the heat exchanger 10 is provided with an inlet 140 and an outlet 130, wherein the outlet 130 is located below the inlet 140 along the vertical direction Y. This layout design helps to utilize the principle of natural convection, allowing the cooling medium to flow naturally under the action of gravity. Specifically, when the cooling medium enters the main body 100 through the inlet 140, it first contacts the top area. As heat is absorbed, the temperature rises and the density decreases, causing the cooling medium to gradually rise and eventually flow to the bottom outlet 130. Since the outlet 130 is located below the inlet 140, this layout allows the cooling medium to flow naturally downward along the guide channel 110 inside the main body 100 without the need for an additional power device to drive the medium circulation, thereby achieving efficient heat dissipation without energy consumption.

[0113] The airflow channel 110 inside the main body 100 works in conjunction with the design of the fins 200 to jointly improve heat dissipation efficiency. The thickness of the fins 200 on the side away from the main body 100 is less than that on the side closer to the main body 100, forming a gradual transition structure from thin to thick. This design not only increases the airflow area but also improves heat transfer efficiency. As the cooling medium passes through the airflow channel 110, it transfers heat to the fins 200, which then dissipate the heat through natural convection and radiative cooling processes. Therefore, the entire heat dissipation system can effectively reduce building energy consumption and environmental thermal hazards without consuming additional energy, demonstrating good economic efficiency and practicality.

[0114] Understandably, in some embodiments, the specific positions and shapes of the inlet 140 and outlet 130 can be adjusted to further optimize heat dissipation. For example, the inlet 140 can be designed in a funnel or horn shape to increase air intake and reduce fluid resistance. Furthermore, a collection tank or pipe can be provided at the outlet 130 to facilitate the recovery and reuse of the cooling medium. This improvement not only enhances the overall heat dissipation performance of the system but also reduces resource waste.

[0115] Understandably, in some embodiments, an intelligent temperature control system is introduced. This system can monitor temperature changes inside and around the heat exchanger 10 in real time using sensors, and automatically adjust the opening of the inlet 140 and outlet 130 as needed. For example, in high-temperature environments, the system can automatically increase the opening of the inlet 140 to accelerate the inflow of the cooling medium, thereby improving heat dissipation efficiency; while in low-temperature environments, the opening can be appropriately reduced to save energy.

[0116] Reference Figure 8 and Figure 9 In some embodiments, the hollow cavity of the heat exchanger 10 is provided with multiple spaced-apart isolation modules 120. These isolation modules 120 divide the flow channel 110 into multiple flow branches, which are interconnected. This design facilitates fluid flow within the hollow cavity and effectively increases the contact area between the cooling medium and the wall of the heat exchanger 10, thereby improving heat exchange efficiency. Each isolation module 120 serves to separate and guide, ensuring uniform distribution of the cooling medium along different paths. In this way, the cooling medium can effectively exchange heat over a wider area, improving the overall heat dissipation effect.

[0117] It is understandable that, in some embodiments, different design schemes for the isolation module 120 can be adopted to further optimize heat dissipation performance. For example, the isolation module 120 can be designed with a structure containing micropores, which can ensure the connectivity between the various flow branches and increase the turbulence effect of the medium flow, thereby improving heat exchange efficiency. Alternatively, the isolation module 120 can be manufactured using multilayer composite materials, such as using a high thermal conductivity material in the core and wrapping it with a material with good corrosion resistance, which can ensure efficient heat conduction and extend service life.

[0118] It is understood that in some embodiments, an adjustable isolation module 120 is introduced. Through mechanical devices or intelligent control systems, the position or shape of the isolation module 120 can be dynamically adjusted according to actual operating conditions to adapt to different heat dissipation requirements. For example, in some high-performance computing devices, the state of the isolation module 120 can be automatically adjusted according to the processor's workload to ensure it is always in optimal heat dissipation condition. For instance, when the processor load is high, the system can automatically increase the number or width of the heat dissipation branches to improve heat dissipation capacity; while under low load conditions, the number or width of the heat dissipation branches can be appropriately reduced to save space and cost.

[0119] Reference Figures 1 to 5 as well as Figure 9In some embodiments, the main body 100 of the heat exchanger 10 has a rectangular cross-section when cut by a vertical plane. The main body 100 has a hollow chamber inside, within which a flow channel 110 is provided. Both the inlet 140 and the outlet 130 are connected to the flow channel 110, ensuring smooth flow of the cooling medium. The fins 200 protrude along the thickness direction of the main body 100, allowing heat to be effectively dissipated through natural convection and radiative cooling. The length a, width b, and thickness c of the main body 100 satisfy 70c≤b≤a. For example, the main body 100 may be a cuboid with a length of 1m, a width of 1m, and a thickness of 1cm. This proportional design ensures sufficient heat dissipation area without occupying excessive space.

[0120] In some embodiments, a temperature sensor is added inside the main body 100 to monitor the temperature changes of the cooling medium in real time. Based on this data, the opening of the inlet 140 and the outlet 130 can be automatically adjusted by an intelligent control system to optimize heat dissipation. For example, in high-temperature environments, the system can automatically increase the opening of the inlet 140 to accelerate the inflow of the cooling medium, while in low-temperature environments, the opening can be appropriately reduced to save energy.

[0121] A second aspect of the present invention provides a heat dissipation system. (Refer to...) Figure 1 In some embodiments, the heat dissipation system includes at least two relatively distributed heat exchangers 10. Each heat exchanger 10 includes a main body 100, a flow channel 110, and fins 200 connected to its two sides. The distance between the two heat exchangers 10 is 2l, the height of the main body 100 is h, and the length of the fins 200 in the convex direction is y. The relationship between y and h and l satisfies... y=q[h / (lm)x-hm / (1-m)] The range of q is 0.8 ≤ q ≤ 1.2, for example, q is 0.8, 1.0, 1.2, with 1.0 being preferred. This layout design makes full use of the principles of natural convection and aerospace radiation cooling, so that a good airflow path is formed between the two heat exchangers 10, thereby improving the overall heat dissipation efficiency.

[0122] In practical applications, the distance 2l between the two heat exchangers 10 can be adjusted according to specific needs to achieve the best heat dissipation effect. For example, when high-efficiency heat dissipation is required, the value of 2l can be appropriately reduced, allowing the two heat exchangers 10 to be arranged more closely together, thereby enhancing the turbulence effect of airflow. Conversely, when space is limited, the value of 2l can be appropriately increased to adapt to different installation environments. By reasonably adjusting these parameters, the heat dissipation system can effectively reduce building energy consumption and environmental thermal hazards without consuming additional energy, demonstrating good economic efficiency and practicality.

[0123] The following describes a specific embodiment of the heat exchanger 10 and heat dissipation system of this application. Specifically, refer to... Figure 1 When the spacing between the main body 100 of the vertical heat exchanger 10 is 2l and the height is h, the length of the heat dissipation fins 200 should meet the following requirements. y=h / (lm)x-hm / (1-m) This arrangement has been demonstrated to provide heat exchanger 10 with a better spherical radiation angle, thereby enhancing radiative heat dissipation. The heat exchanger 10 uses parallel piping, meaning the branches of the flow guide channel 110 are interconnected. This arrangement has been verified to have good heat transfer efficiency. When h is 2, 4, and 8 times l, m should satisfy 0.207h, 0.061h, and 0.0158h, respectively. Under these conditions, both the heat exchanger 10 itself and its bottom roof have a superior spherical radiation angle. The fins 200 are tapered, wider at the bottom and gradually decreasing in size along the height, with a slope of 3.125. The spacing between the fins 200 is equal to the height of the nearest upper fin 200. The flow guide channels are arranged in parallel, with the inlet 140 and outlet 130 positioned diagonally to ensure uniform internal fluid flow.

[0124] Furthermore, when the heat exchanger 10 requires a certain installation angle due to installation requirements, the calculation of radiative heat transfer needs to take into account the influence of the solar radiation incident angle. Figure 10 A common installation method is given (heat exchanger 10 is arranged vertically). Sometimes the angle of solar incidence is different, so the inventor devised a method to divide the entire plate area into different spaces, see [link to relevant documentation]. Figure 10 In the first diagram on the left, surfaces S3 and S6 are exposed to sunlight, resulting in different temperatures in these areas, which is used to define the regions. Surface S3 radiates to surfaces S6, S2, S5, and S1. The radiation angle coefficient is mainly used to calculate how much heat is transferred from surface S3 to surface S5, etc. In the middle diagram, sunlight only reaches surface S3. In this case, only surfaces S1, S3, S2, and S5 are present, but surface S6 is absent. In the rightmost diagram, the area of ​​surface S3 becomes smaller, and a portion of heat exchanger 10 is not exposed to sunlight. In this case, surface S4 is added. The formula for calculating the entire radiation angle, as described later, considers all three different operating conditions, thus obtaining the percentage of radiation between different surfaces, and the calculation area of ​​the radiation angle between heat exchangers 10 under this installation condition. Based on the law of conservation of energy, this patent provides a calculation model for the aerospace radiation angle associated with the heat exchanger 10 under different operating conditions, see... Figure 10 ( Figure 10 Condition 1 indicates that at noon, some sunlight reaches the roof, affecting S6 surfaces; Condition 2 indicates that in the morning or afternoon, sunlight only reaches part of the panels, and no sunlight reaches the roof as it is blocked by the panels. a,bThis represents the percentage of heat radiated from surface a that falls onto surface b; in other words, how much heat travels from surface a to surface b. X a,b The calculation results are decimals, such as 0.7 or 0.5, with a maximum of 1. This calculation model can assist in the rapid efficiency evaluation of specific engineering projects.

[0125] Specifically, refer to Figure 1 and Figure 10 The third aspect of this invention proposes a calculation model for a heat exchanger system and the aerospace radiation angle, see [link to relevant documentation]. Figure 10 The relevant content for condition 1. Specifically, this embodiment is used for solar partial irradiation of the heat exchanger 10 system, including the heat dissipation system of any of the above. The calculation model of the heat exchanger system and the aerospace radiation angle has S3 and S5 surfaces corresponding to two adjacent heat exchangers 10 respectively, and S1 and S2 surfaces that are parallel to each other and spaced apart between S3 and S5 surfaces. S6 surface is coplanar with S2 surface and is located between S3 and S2 surfaces. S6 surface and S3 surface are suitable for solar irradiation. S3 surface, S1 surface, S5 surface, S2 surface and S6 surface are connected end to end in sequence, and their outlines intercepted by the vertical plane form a parallelogram. The calculation model of the heat exchanger system and the aerospace radiation angle includes at least one of the following relationships:

[0126] X 1,2 This represents the percentage of heat radiated from surface S1 that falls onto surface S2.

[0127] ;

[0128] And / or, X 1,3 This represents the percentage of heat radiated from surface S1 that falls onto surface S3.

[0129] ;

[0130] And / or, X 1,5 This represents the percentage of heat radiated from surface S1 that falls onto surface S5.

[0131] ;

[0132] And / or, X 1,6 This represents the percentage of heat radiated from surface S1 that falls onto surface S6.

[0133] ;

[0134] And / or, X 2,3 This represents the percentage of heat radiated from surface S2 that falls onto surface S3.

[0135] ;

[0136] And / or, X 2,5 This represents the percentage of heat radiated from surface S2 that falls onto surface S5.

[0137] ;

[0138] And / or, X 3,5 This represents the percentage of heat radiated from surface S3 that falls onto surface S5.

[0139] ;

[0140] And / or, X 3,6 This represents the percentage of heat radiated from surface S3 that falls onto surface S6.

[0141] ;

[0142] And / or, X 5,6 This represents the percentage of heat radiated from surface S5 that falls onto surface S6.

[0143] ;

[0144] in, It is the spacing of the heat exchanger 2l and height h The ratio;

[0145] .

[0146] Reference Figure 1 and Figure 10 The fourth aspect of this invention proposes a calculation model for a heat exchanger system and the aerospace radiation angle, see [link to relevant documentation]. Figure 10 The relevant content for condition 2 is as follows. Specifically, this embodiment is used for a heat exchanger 10 system where the sun shines on all of the heat exchangers, including any of the above-mentioned heat dissipation systems. The calculation model of the heat exchanger system and the aerospace radiation angle has two corresponding adjacent heat exchangers 10, one of which corresponds to surface S5, and the other heat exchanger 10 corresponds to surfaces S3 and S4. Surfaces S3 and S4 are coplanar, where surface S3 can be illuminated by the sun, surface S4 is not illuminated by the sun, surface S1 is sandwiched between surfaces S3 and S5, and surface S2 is sandwiched between surfaces S4 and S5. Surfaces S4, S3, S1, S5, and S2 are connected end to end in sequence, and their outlines, intercepted by a vertical plane, form a parallelogram. The calculation model of the heat exchanger system and the aerospace radiation angle includes at least one of the following relationships:

[0147] X 1,2 This represents the percentage of heat radiated from surface S1 that falls onto surface S2.

[0148] ;

[0149] And / or, X 1,3 This represents the percentage of heat radiated from surface S1 that falls onto surface S3.

[0150] ;

[0151] And / or, X 1,4 This represents the percentage of heat radiated from surface S1 that falls onto surface S4.

[0152] ;

[0153] And / or, X 1,5 This represents the percentage of heat radiated from surface S1 that falls onto surface S5.

[0154] ;

[0155] And / or, X 2,3 This represents the percentage of heat radiated from surface S2 that falls onto surface S3.

[0156] ;

[0157] And / or, X 2,4 This represents the percentage of heat radiated from surface S2 that falls onto surface S4.

[0158] ;

[0159] And / or, X 2,5 This represents the percentage of heat radiated from surface S2 that falls onto surface S5.

[0160] ;

[0161] And / or, X 3,5 This represents the percentage of heat radiated from surface S3 that falls onto surface S5.

[0162] ;

[0163] And / or, X 4,5 This represents the percentage of heat radiated from surface S4 that falls onto surface S5.

[0164] ;

[0165] in, It is the spacing of the heat exchanger 2l and height h The ratio;

[0166] ;

[0167] ;

[0168] ;

[0169] .

[0170] Note: Regarding the embodiments of the third and fourth aspects described above, X ab The proportion of energy radiated from surface a that falls onto surface b.

[0171] A fifth aspect of this invention provides a method for evaluating the efficiency of a heat dissipation system, including a calculation model of the heat exchanger system and the aerospace radiation angle as described above. This method collects and analyzes the heat radiation ratio (e.g., X) of each surface of the heat dissipation system. 1,2 X 1,3 This method, combined with specific environmental conditions (such as the angle of solar incidence), evaluates the overall system's heat dissipation efficiency. This approach helps to gain a deeper understanding of the performance of each component in actual operation and allows for optimization adjustments.

[0172] In practical applications, by calculating the heat transfer ratio between each surface based on these parameters, the optimal design of the heat dissipation system's layout and dimensions can be determined. For example, X 1,2 This represents the percentage of heat radiated from surface S1 that falls onto surface S2. By measuring and calculating this value, we can understand the heat distribution within the system. This approach not only improves the overall efficiency of the cooling system but also significantly reduces building energy consumption and environmental thermal hazards. For example, in large data centers or industrial plants, proper cooling system design and evaluation methods can help maintain optimal equipment performance while reducing energy consumption and carbon emissions.

[0173] The above are merely preferred embodiments of the present invention and do not limit the scope of the patent. Any equivalent structural transformations made using the contents of the specification and drawings of the present invention under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the scope of patent protection of the present invention.

Claims

1. A heat exchanger, characterized in that, include: The main body has a hollow cavity, and a flow guide channel is provided in the hollow cavity. The main body has an inlet and an outlet, and the inlet and the outlet are both connected to the flow guide channel. Fins are connected to opposite sides of the main body and protrude from the main body in opposite directions. Wherein, along the protruding direction of the fin, the thickness of the side of the fin away from the main body is less than the thickness of the side closer to the main body; The fins protrude horizontally from the main body. Along the vertical direction, the thickness of the fins gradually increases from the side away from the main body to the side closer to the main body; The region of the fin intercepted by the vertical plane is an isosceles triangle; and / or, The fins are conical with a slope ranging from 2.7 to 3.

7. The length of the fin along the convex direction is: y The distance from the fin to the adjacent fin below it is d, y and d The relationship satisfies: y=pd ,in, p The range is 0.8≤p≤1.2 ; The hollow cavity is provided with multiple spaced isolation modules, which divide the flow channel into multiple flow branches, and the multiple flow branches are interconnected.

2. The heat exchanger according to claim 1, characterized in that, The fins are spaced apart along the vertical direction.

3. The heat exchanger according to claim 1, characterized in that, Along the vertical direction, the outlet is located below the inlet.

4. The heat exchanger according to claim 1, characterized in that, The cross-section of the main body portion cut by the vertical plane is rectangular, and the fins protrude along the thickness direction of the main body portion. The length of the main body portion is... a ,width b ,thickness c The relationship satisfies: 70c≤b≤a 。 5. A heat dissipation system, characterized in that, The heat dissipation system includes at least two of the heat exchangers that are distributed opposite to each other, comprising the heat exchanger according to any one of claims 1 to 4.

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