Heat exchanger based on periodic porous structure and heat dissipation system with same

Abstract

The invention belongs to the technical field of heat exchange, and particularly relates to a heat exchanger based on a periodic porous structure and a heat dissipation system with the heat exchanger, the heat exchanger comprises a shell, a side plate, a bottom plate, heat exchange fluid and a heat exchange fin structure, the side plate is connected between the shell and the bottom plate, and the shell, the side plate and the bottom plate form a heat exchange flow channel through which the heat exchange fluid flows; a heat exchange fin structure composed of a plurality of single-layer repeated fin structure units is filled in a heat exchange flow channel, a body-centered cubic structure unit, an oval nail column structure unit and a three-period minimum curved surface TPMS structure unit are adopted, and compared with a traditional fin structure, the heat exchange fin structure has the high mechanical strength and the high specific surface area.

Description

Technical Field

[0001] The present application belongs to the field of heat exchange technology, and in particular relates to a heat exchanger based on a periodic porous structure and a heat dissipation system having the same. Background Art

[0002] In recent years, with the development of electronic components and aerospace power equipment towards miniaturization, high transmission capacity, and high power density, the heat dissipation and temperature control problems of high-power and high-heat flux equipment have become increasingly serious. In order to meet higher heat exchange requirements, the development of lightweight, efficient, and compact heat exchangers is the key to achieving efficient and stable operation of high-temperature equipment. Traditional heat exchangers have large volume and mass increments, low heat exchange efficiency, and it is difficult to balance flow resistance and heat transfer performance. In addition, whether from a design or manufacturing perspective, it is difficult to achieve local performance regulation of the heat exchange structure of the heat exchanger.

[0003] The heat exchanger provided by the present invention is a type of plate-fin heat exchanger, and has enhanced heat exchange fin tubes inside. The fin tubes can effectively increase the heat transfer area and heat transfer coefficient. The fin types of traditional plate-fin heat exchangers include straight, serrated, corrugated and louvered types. However, for the above-mentioned fin types, there are problems such as low design freedom, inability to balance high heat exchange capacity and low flow resistance, weak heat exchange adaptive adjustment ability, and inability to adapt to complex space layout. The compactness, flow resistance and heat exchange efficiency of the heat exchanger still need to be further improved. Summary of the invention

[0004] In order to solve the above problems, the present application provides a heat exchanger, comprising:

[0005] The shell, the side plate, the bottom plate, the heat exchange fluid and the heat exchange fin structure, the side plate is connected between the shell and the bottom plate, the shell, the side plate and the bottom plate form a heat exchange channel through which the heat exchange fluid flows; the heat exchange channel is filled with a single layer of heat exchange fin structure composed of several repeated fin structure units.

[0006] Preferably, the fin structure unit includes a body-centered cubic structure unit, an elliptical nail column structure unit, and a three-period minimum surface TPMS structure unit.

[0007] Preferably, the three-period minimum surface TPMS structural unit includes an I-WP type structure, a Gyroid type structure, a Primative type structure and a Diamond type structure.

[0008] Preferably, the surface equation of the I-WP type structure is:

[0009] f(x,y,z)=2*(cos(x)*cos(y)+cos(y)*cos(z)+cos(z)*cos(x))-(cos(2*x)+cos(2*y)+cos

[0010] (2*z))=0.

[0011] Where D is the size of the TPMS unit and q is the parameter that controls the porosity of the TPMS.

[0012] Preferably, the surface equation of the Gyroid structure is:

[0013] f(x,y,z)=cos(x)*sin(y)+cos(y)*sin(z)+cos(z)*sin(x)=0.

[0014] Preferably, the surface equation of the Primative structure is:

[0015] f(x,y,z)=cos(x)+cos(y)+cos(z)=0.

[0016] Preferably, the surface equation of the Diamond structure (10) is:

[0017] f(x,y,z)=sin(x)*sin(y)*sin(z)+sin(x)*cos(y)*cos(z)+cos(x)*sin(y)*cos(z)+cos(x)*cos(y)*sin(z)=0.

[0018] A heat dissipation device for a formula racing car, a heat exchange device, a pump, a transmission pipeline, and the heat exchanger based on the periodic porous structure;

[0019] The shell of the heat exchanger has an external coating for corrosion protection on the outside, and the external coating is in contact with the external airflow. The inlet of the heat exchange flow channel has two inlet pipes, and the two inlet pipes are connected to the inlet header. The outlet has two outlet pipes, and the two outlet pipes are connected to the outlet header. The heat exchange device is installed on the formula racing engine, and its outlet is connected to the inlet header, and its inlet is connected to the outlet header. The heat exchange fluid circulates between the heat exchange device and the heat exchanger through a pump. The fin structure unit of the heat exchanger adopts an IWP structure, and its surface equation is as follows: f(x,y,z)=2*(cos(p*x)*cos(p*y)+cos(p*y)*cos(p*z)+cos(p*z)*cos(p*x)

[0020] )-(cos(2*p*x)+cos(2*p*y)+cos(2*p*z))+q;

[0021] Among them, the parameters p and q are used to control the unit length and solid fraction of the IWP structure, respectively;

[0022] The heat exchanger uses high-strength aluminum powder and uses a 3D printer to integrate the heat exchange fin structure and the shell.

[0023] An aircraft thermal management system, a heat exchange device, a pump, a transmission pipeline, and the heat exchanger based on the periodic porous structure;

[0024] The heat exchange device is connected to the high-temperature component of the aircraft, the outlet of the heat exchange device is connected to the inlet of the heat exchanger through a pipeline, the inlet of the heat exchange device is connected to the outlet of the heat exchanger, the heat exchange fluid circulates between the heat exchange device and the heat exchanger through a pump, the fin structure unit of the heat exchanger adopts a single-layer SC-BCC lattice structure, and the heat exchanger is placed between the aircraft skin and the aircraft wall panel.

[0025] Advantages of this application include:

[0026] (1) The internal structure of the heat exchange channel can adopt a SC-BCC lattice structure, which has higher mechanical strength and higher specific surface area than the traditional fin structure.

[0027] (2) The internal structure of the heat exchange channel can adopt a nail column structure, which has a simple structure and convenient design. The cross-row arrangement can enhance the fluid disturbance and strengthen the heat exchange process.

[0028] (3) The TPMS structure can be used inside the heat exchange channel, and its surface structure can be represented by an implicit function of f(x, y, z) = 0, which has the characteristics of convenient modeling, high design freedom, large specific surface area and low flow resistance.

[0029] (4) The internal fin structure of the heat exchange channel adopts the selective laser melting (SLM) metal powder 3D printing technology to achieve the integrated molding of the skin and the fin. Compared with traditional technology, it can realize the molding of complex fin structures and effectively avoid the problems of thermal resistance, strength and leakage caused by welds.

[0030] (5) The internal fin structure of the heat exchange channel adopts the selected laser melting (SLM) metal powder 3D printing technology, which can realize conformal design for complex curved shapes and achieve integrated design of heat exchanger structure and function.

[0031] (6) The inlet and outlet channels can adopt a single-inlet and single-outlet or multiple-inlet and multiple-outlet mode according to the actual size of the curved surface to ensure uniform flow in the channel. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the structure of a heat exchanger.

[0033] Figure 2 It is a schematic diagram of specific embodiment 1 of the present invention.

[0034] Figure 3 It is a side view of specific embodiment 1 of the present invention.

[0035] Figure 4 It is a schematic diagram of specific embodiment 2 of the present invention.

[0036] Figure 5 It is a cross-sectional view of specific embodiment 2 of the present invention.

[0037] Figure 6 It is an exploded view of specific embodiment 2 of the present invention.

[0038] Among them: 1-coating, 2-shell, 3-flow channel, 13-side plate, 4-bottom plate, 5-fluid inlet, 6-fluid outlet, 8-TPMS porous structure, 9-elliptical nail column, 10-SC-BCC lattice structure, 11-inlet header; 12-outlet header; 13-side plate. DETAILED DESCRIPTION

[0039] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0040] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0041] A heat exchanger, comprising:

[0042] The shell, the side plate, the bottom plate, the heat exchange fluid and the heat exchange fin structure, the side plate is connected between the shell and the bottom plate, the shell, the side plate and the bottom plate form a heat exchange channel through which the heat exchange fluid flows; the heat exchange channel is filled with a single layer of heat exchange fin structure composed of several repeated fin structure units.

[0043] The fin structure unit includes a body-centered cubic structure unit, an elliptical nail column structure unit, and a three-period minimum surface TPMS structure unit.

[0044] The three-period minimum surface TPMS structural units include I-WP type structure, Gyroid type structure, Primative type structure and Diamond type structure (10).

[0045] The surface equation of the I-WP structure is:

[0046] f(x,y,z)=2*(cos(x)*cos(y)+cos(y)*cos(z)+cos(z)*cos(x))-(cos(2*x)+cos(2*y)+cos

[0047] (2*z))=0.

[0048] Where D is the size of the TPMS unit and q is the parameter that controls the porosity of the TPMS.

[0049] The surface equation of the Gyroid structure is:

[0050] f(x,y,z)=cos(x)*sin(y)+cos(y)*sin(z)+cos(z)*sin(x)=0.

[0051] The surface equation of the Primative structure is:

[0052] f(x,y,z)=cos(x)+cos(y)+cos(z)=0.

[0053] The surface equation of the Diamond structure is:

[0054] f(x,y,z)=sin(x)*sin(y)*sin(z)+sin(x)*cos(y)*cos(z)+cos(x)*sin(y)*cos(z)+co s(x)*cos(y)*sin(z)=0.

[0055] Example 1

[0056] Racing engines must pursue maximum performance under the premise that the rules allow. Although the hybrid engine displacement of the current F1 racing car is only 1.6t, it can generate about 1,000 horsepower, so it will inevitably generate huge heat during operation, which is much higher than that of a civilian car engine. If the heat is not dissipated in a timely and effective manner, the heat will cause the expansion and deformation of the metal parts of the racing car power unit (Power Unit), as well as the loosening and leakage of various pipe connection positions, and ultimately cause the power unit to be unable to output power normally. Therefore, the heat dissipation capacity of the F1 racing car is extremely important. However, due to the higher heat generation and extremely small mechanical installation space of the racing car, the operating environment of the cooling system is very harsh and the working tasks are more arduous. In order to meet the above challenges, the present embodiment complies with the above technical solution and provides a heat dissipation device for a formula racing car, such as Figures 2 to 3 As shown, when the equipment is running, efficient heat exchange between the internal heat transfer fluid and the external air is achieved through the heat exchanger.

[0057] In this embodiment, the IWP structure in the TPMS structure is used as the heat exchange fin structure, and its surface equation is as follows:

[0058] f(x,y,z)=2*(cos(p*x)*cos(p*y)+cos(p*y)*cos(p*z)+cos(p*z)*cos(p*x)

[0059] )-(cos(2*p*x)+cos(2*p*y)+cos(2*p*z))+q

[0060] The parameters p and q are used to control the unit length and solid phase fraction of the TPMS porous structure 8, respectively.

[0061] After the models of the TPMS porous structure 8 and the coating 1 are established by the 3D modeling software, the obtained solid model is sliced ​​and layered by the slicing software, and the TPMS porous structure 8 and the coating 1 are integrated by the laser melting (SLM) 3D printer, and the molding material is high-strength aluminum powder. The outer shell 2 of the coating 1 is used to protect the coating 1 from corrosion. The bottom and side surfaces of the heat exchanger are welded with the bottom plate 6 and the side plate 13 as support, respectively. The heat exchanger inlet and outlet adopt a double-inlet and double-outlet design. Two inlets are designed at the inlet to ensure flow uniformity, and are connected to the inlet header 11 through a ferrule interface. Two outlets are also designed at the outlet to connect to the outlet header 12.

[0062] The working process of this embodiment is as follows:

[0063] When the equipment equipped with the heat exchange device is working, the heat generated by the racing engine is taken away by the cooling medium through the heat exchanger and pumped to the inlet of the heat exchanger in this embodiment, and then divided through the inlet header 11, and enters the flow channel 3 inside the heat exchanger from two inlets, in which the single-layer TPMS structure 7 is filled to enhance the heat exchange efficiency and ensure high fluidity and low flow resistance. Due to the speed difference between the equipment and the external fluid, forced convection is formed outside the shell 2, and heat exchange is generated with the cooling medium in the flow channel 3, and the heat is taken away by the external air. The cooled cooling medium flows to the outlet header 12 through two outlets, and finally re-enters the racing engine cooling system for heat exchange to cool the engine.

[0064] Example 2

[0065] The aircraft thermal management system is closely related to the overall structure and other subsystems, and the heat dissipation of equipment is an important factor affecting the overall layout. Therefore, the space heat exchanger with the characteristics of compact structure, high heat exchange efficiency, safe and reliable operation and long service life has become one of the core components of the aircraft thermal management system. Based on the above technical solution, the present embodiment provides an aircraft heat exchanger. The low-temperature cooling medium changes into a high-temperature fluid after exchanging heat with the high-temperature components. The high-temperature fluid flows through the heat exchanger and radiates and convects through the shell to the outer space to dissipate heat, and the low-temperature cooling medium re-enters the aircraft to work. The fin structure of this embodiment adopts an SC-BCC lattice structure, and the heat exchanger structure is as follows: Figure 4-Figure 6 As shown. After the models of the SC-BCC lattice structure 10 and the shell 2 are established by the three-dimensional modeling software, the obtained solid model is sliced ​​and layered by the slicing software, and the SC-BCC lattice structure 10 and the shell 2 are integrated by metal 3D printing technology, and the molding material is high-strength aluminum powder. The coating 1 on the outside of the shell 2 is used to enhance the radiation heat transfer without corrosion. The bottom and side surfaces of the heat exchanger are welded with the bottom plate 4 and the side plate 13 as support, respectively. The heat exchanger inlet and outlet adopt a single inlet and single outlet design, and are connected to the bottom plate through a card sleeve interface.

[0066] The working process of this embodiment is as follows:

[0067] When the equipment equipped with the heat exchange device is working, the heat generated by the high-temperature parts of the aircraft is taken away by the cooling medium through the heat exchanger and pumped to the inlet of the heat exchanger of this embodiment, and enters the internal flow channel of the heat exchanger through the fluid inlet 5, in which a single-layer SC-BCC lattice structure 10 is filled to enhance the heat exchange efficiency and ensure high fluidity and low flow resistance. Due to the speed difference between the equipment and the external fluid, forced convection is formed on the outside of the coating 1, and heat exchange is generated with the cooling medium in the flow channel, and the heat is taken away by the external air. The cooled cooling medium flows out through the fluid outlet 6, and finally re-enters the aircraft high-temperature parts cooling system for heat exchange to cool the high-temperature parts.

[0068] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A heat exchanger based on a periodic porous structure, characterized in that: include: The shell, the side plate, the bottom plate, the heat exchange fluid and the heat exchange fin structure, the side plate is connected between the shell and the bottom plate, the shell, the side plate and the bottom plate form a heat exchange channel through which the heat exchange fluid flows; the heat exchange channel is filled with a single layer of heat exchange fin structure composed of several repeated fin structure units.

2. The heat exchanger based on the periodic porous structure according to claim 1, characterized in that: The fin structure unit includes a body-centered cubic structure unit, an elliptical nail column structure unit, and a three-period minimum surface TPMS structure unit.

3. The heat exchanger based on the periodic porous structure according to claim 1, characterized in that: The three-period minimum surface TPMS structural units include I-WP type structure, Gyroid type structure, Primative type structure and Diamond type structure (10).

4. The heat exchanger based on the periodic porous structure according to claim 3, characterized in that: The surface equation of the I-WP structure is: f(x,y,z)=2*(cos(x)*cos(y)+cos(y)*cos(z)+cos(z)*cos(x))-(cos(2*x)+cos(2*y)+cos(2*z))=0. Where D is the size of the TPMS unit and q is the parameter that controls the porosity of the TPMS.

5. The heat exchanger based on the periodic porous structure according to claim 2, characterized in that: The surface equation of the Gyroid structure is: f(x,y,z)=cos(x)*sin(y)+cos(y)*sin(z)+cos(z)*sin(x)=0.

6. The heat exchanger based on the periodic porous structure according to claim 2, characterized in that: The surface equation of the Primative structure is: f(x,y,z)=cos(x)+cos(y)+cos(z)=0.

7. The heat exchanger based on the periodic porous structure according to claim 2, characterized in that: The surface equation of the Diamond structure is: f(x,y,z)=sin(x)*sin(y)*sin(z)+sin(x)*cos(y)*cos(z)+cos(x)*sin(y)*cos(z)+cos(x)*cos(y)*sin(z)=0.

8. A heat dissipation device for a formula car, characterized in that: A heat exchange device, a pump, a transmission pipeline, and a heat exchanger based on a periodic porous structure as claimed in claim 1; The shell of the heat exchanger has an external coating for corrosion protection, and the external coating is in contact with the external airflow. The inlet of the heat exchange flow channel has two inlet pipes, and the two inlet pipes are connected to the inlet header. The outlet has two outlet pipes, and the two outlet pipes are connected to the outlet header. The heat exchange device is installed on the formula racing engine, and its outlet is connected to the inlet header, and its inlet is connected to the outlet header. The heat exchange fluid circulates between the heat exchange device and the heat exchanger through a pump. The fin structure unit of the heat exchanger adopts an IWP structure, and its surface equation is as follows: f(x,y,z)=2*(cos(p*x)*cos(p*y)+cos(p*y)*cos(p*z)+cos(p*z)*cos(p*x))-(cos(2*p*x)+cos(2*p*y)+cos(2*p*z))+q; Among them, the parameters p and q are used to control the unit length and solid fraction of the IWP structure, respectively; The heat exchanger uses high-strength aluminum powder and uses a 3D printer to integrate the heat exchange fin structure and the shell.

9. An aircraft thermal management system, characterized in that: A heat exchange device, a pump, a transmission pipeline, and a heat exchanger based on a periodic porous structure as claimed in claim 1; The heat exchange device is connected to the high-temperature component of the aircraft, the outlet of the heat exchange device is connected to the inlet of the heat exchanger through a pipeline, the inlet of the heat exchange device is connected to the outlet of the heat exchanger, the heat exchange fluid circulates between the heat exchange device and the heat exchanger through a pump, the fin structure unit of the heat exchanger adopts a single-layer SC-BCC lattice structure, and the heat exchanger is placed between the aircraft skin and the aircraft wall panel.

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