Hot air cooling heat pipe device for hydrogen internal combustion aircraft

Abstract

The invention belongs to the technical field of heat dissipation, and particularly relates to a hot air cooling heat pipe device for a hydrogen internal combustion aircraft, which comprises a cooling cavity, a hot air inlet and a hot air outlet, the fixed pipe is arranged in the cooling cavity; the spiral piece is spirally arranged on the periphery of the fixed pipe and extends in the length direction of the fixed pipe; a plurality of horizontally corresponding holes are formed in the spiral sheet; the plurality of heat pipes are arranged; a part of a pipe body of the heat pipe is positioned in the cooling cavity, penetrates through the hole in the spiral sheet and is fixed on the spiral sheet; a part of the pipe body is located outside the cooling cavity. According to the scheme, an existing intercooler refrigerating device for outputting hot air through a turbocharger of a hydrogen internal combustion aircraft and an internal combustion engine automobile is replaced, and the problems that the production cost is increased and the heat transfer efficiency is not high and unstable due to the fact that the aircraft load is increased are solved.

Description

Technical Field

[0001] The invention belongs to the technical field of heat dissipation, and in particular relates to a heat pipe device for hot air cooling of a hydrogen internal combustion aircraft. Background Art

[0002] A heat pipe is a closed evaporator-condenser system that uses the evaporation and condensation of a working fluid to transfer heat. It has the advantages of high thermal conductivity, good isothermal properties, and long-distance heat transfer, and is often used in cooling areas, materials, and energy conversion systems.

[0003] At present, in the field of domestic light general aviation aircraft, for hydrogen internal combustion aircraft, the hot air output by the turbocharger is liquid-cooled or air-cooled by an intercooler. In the field of domestic internal combustion engine automobiles, intercoolers are also used for air-cooling or water-cooling. However, liquid cooling refrigeration devices are heavy, which greatly increases the load of the aircraft and increases the cost of production. In addition, the efficiency of air cooling is low and unstable. Summary of the invention

[0004] In view of the above problems, the present invention provides a lightweight and more efficient refrigeration device to replace the intercooler, becoming a better choice for hydrogen internal combustion aircraft and internal combustion engine vehicles. Specifically, a heat pipe device for hot air cooling of hydrogen internal combustion aircraft is provided, comprising:

[0005] A cooling cavity having a hot air inlet on one side and a hot air outlet on the other side;

[0006] A fixed pipe is arranged in the cooling cavity;

[0007] The spiral sheet is spirally arranged on the outer circumference of the fixed tube and extends along the length direction of the fixed tube; the spiral sheet is provided with a plurality of horizontal corresponding holes;

[0008] A plurality of heat pipes are provided; a portion of the heat pipe body is located in the cooling cavity and is fixed on the spiral sheet through the holes on the spiral sheet; a portion of the heat pipe body is located outside the cooling cavity.

[0009] Furthermore, the spiral blades are copper spiral blades.

[0010] Furthermore, the heat pipe is arranged in a U shape; the multiple heat pipes are divided into two groups arranged opposite to each other on the left and right, and the spiral sheets in the cooling cavity are grouped and penetrated; the cold ends of the two groups of heat pipes are aligned with each other, and the hot ends are aligned with each other.

[0011] Furthermore, the cooling cavity is cylindrical, and the outer circumference of the spiral blade fits the cooling cavity.

[0012] Furthermore, the heat pipe device is arranged in multiple groups.

[0013] The present invention aims to replace the intercooler refrigeration device for outputting hot air from the existing turbocharger of hydrogen internal combustion aircraft and internal combustion engine automobiles, thereby solving the problem of increasing the aircraft load, thereby increasing production costs and low and unstable heat transfer efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural front view of the present invention;

[0015] Figure 2 is a cross-sectional view of the device of the present invention;

[0016] Figure 3 It is the left side view of the device;

[0017] Figure 4 It is the internal structure of the cavity;

[0018] Figure 5 Schematic diagram of the location of multiple heat pipe cooling devices. DETAILED DESCRIPTION

[0019] The principles and features of the present invention are described below in conjunction with the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0020] refer to Figure 1-4 The present invention provides a lightweight and more efficient refrigeration device, which replaces the intercooler and becomes a better choice for hydrogen internal combustion aircraft and internal combustion engine vehicles. Specifically, a heat pipe device for hot air cooling of hydrogen internal combustion aircraft is provided, comprising:

[0021] The cooling cavity 6 is cylindrical, with a hot air inlet 1 on one side and a hot air outlet 5 on the other side; the cylindrical design is conducive to the formation of gas swirl, so that the hot air is in full contact with the hot end of the heat pipe in the cooling cavity and the heat is fully transferred.

[0022] A fixed pipe is arranged in the cooling cavity 6;

[0023] The spiral piece 4 is a copper spiral piece spirally arranged on the outer circumference of the fixed tube and extends along the length direction of the fixed tube; the spiral piece 4 is provided with a plurality of horizontal corresponding holes;

[0024] There are multiple U-shaped heat pipes. Part of the heat pipe body is located in the cooling cavity and is fixed on the spiral sheet through the holes on the spiral sheet. Part of the heat pipe body is located outside the cooling cavity. This U-shaped structure is more suitable for the cylindrical cooling cavity. It uses the phase change principle of the working fluid to transfer heat. In the evaporation section (heating section) of the heat pipe, the heat input causes the working fluid in the pipe to absorb heat and evaporate, changing from liquid to gas. Due to the difference in vapor pressure, the gaseous working fluid will move to the condensation section (heat dissipation section) of the heat pipe. In the condensation section, the gaseous working fluid releases heat and condenses back into liquid. Under the capillary action of the liquid wick, the liquid working fluid flows back to the evaporation section, and the cycle is repeated to achieve rapid heat transfer from the high temperature area (evaporation section) to the low temperature area (condensation section).

[0025] As an improvement of the scheme, the heat pipe is set in a U shape; multiple heat pipes are divided into two groups arranged opposite to each other on the left and right, and the spiral sheets in the cooling cavity are grouped and penetrated; the two groups of heat pipes are aligned with each other. That is, on the outside, the cold end 2 of a heat pipe in one group is aligned with the cold end 2 of the heat pipe in the other group; inside the cooling cavity, the hot end 3 of the heat pipe in one group is aligned with the hot end 3 of the heat pipe in the other group, and the cold ends 2 of the heat pipes are neatly and orderly arranged on the outer surface of the cooling cavity, so that the air cooling efficiency is higher and the heat can be taken away more easily.

[0026] As an improvement to the solution, the cooling cavity is cylindrical, and the outer periphery of the spiral blade fits into the cooling cavity. This design divides the internal space of the cooling cavity by the spiral blade to form a spiral space, so that the hot air entering the cooling cavity can swirl through the spiral path, thereby achieving full contact and heat transfer between the hot air and the hot end of the heat pipe.

[0027] As an improvement of the solution, refer to Figure 5 During use, the heat pipe device is set to be used in parallel with two groups, and the hot air is divided into two flow pipes through the hot air inlet, which enter the heat pipe device separately and then merge at the hot air outlet.

[0028] After turbocharging, the air density increases, the temperature rises, and it enters the cylindrical cooling cavity 6 through the hot air inlet 1. The copper spiral sheet 4 is embedded in the cylindrical cavity 6 and fixed. The copper spiral sheet 4 has multiple horizontal corresponding holes. The hot end of the U-shaped heat pipe is inserted into the copper spiral sheet 4 along the horizontal holes. The copper spiral sheet 4 forms a spiral path inside the cylindrical cooling cavity 6. The heat of the hot air is absorbed by the hot end 3 of the heat pipe and transferred to the cold end 2 of the heat pipe through the heat pipe. Finally, the heat is dissipated through heat transfer with the external air, achieving the effect of cooling the gas in the cavity. Finally, the temperature of the hot air passing through the cylindrical cooling cavity 6 is reduced and flows to the hot air outlet 5.

[0029] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A heat pipe device for hot air cooling of a hydrogen internal combustion aircraft, characterized in that: include, A cooling cavity having a hot air inlet on one side and a hot air outlet on the other side; A fixed pipe is arranged in the cooling cavity; The spiral sheet is spirally arranged on the outer circumference of the fixed tube and extends along the length direction of the fixed tube; the spiral sheet is provided with a plurality of horizontal corresponding holes; A plurality of heat pipes are provided; a portion of the heat pipe body is located in the cooling cavity and is fixed on the spiral sheet through the holes on the spiral sheet; a portion of the heat pipe body is located outside the cooling cavity.

2. A heat pipe device for hot air cooling of a hydrogen internal combustion aircraft as claimed in claim 1, characterized in that: The spiral blades are copper spiral blades.

3. A heat pipe device for hot air cooling of a hydrogen internal combustion aircraft as claimed in claim 1, characterized in that: The heat pipe is arranged in a U shape; the multiple heat pipes are divided into two groups arranged opposite to each other on the left and right, and the spiral sheets in the cooling cavity are grouped and penetrated; the cold ends of the two groups of heat pipes are aligned with each other, and the hot ends are aligned with each other.

4. A heat pipe device for hot air cooling of a hydrogen internal combustion aircraft as claimed in claim 1, characterized in that: The cooling cavity is cylindrical, and the outer circumference of the spiral sheet fits the cooling cavity.

5. A heat pipe device for hot air cooling of a hydrogen internal combustion aircraft as claimed in claim 1, characterized in that: The heat pipe device is arranged in multiple groups.

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