Hot air cooling heat pipe device for hydrogen internal combustion aircraft
By employing lightweight and efficient heat pipe devices in hydrogen-powered internal combustion aircraft and internal combustion engine vehicles, and utilizing the design of spiral blades and U-shaped heat pipes, the problem of low cooling efficiency of hot air output from turbochargers has been solved, achieving lightweight design and efficient heat transfer.
Patent Information
- Application Number
- CN202423174023.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-23
- Publication Date
- 2025-11-25
- Estimated Expiration
- 2034-12-23
AI Technical Summary
In the existing technology, the turbocharger output hot air cooling device for hydrogen internal combustion aircraft and internal combustion engine automobiles has the problems of increasing aircraft load, high production cost and low heat transfer efficiency.
It employs a lightweight and efficient heat pipe device, including a cooling chamber, a fixed tube, spiral fins, and a U-shaped heat pipe. It utilizes the principle of working fluid phase change for heat transfer, and achieves rapid heat transfer from the high-temperature zone to the low-temperature zone through the design of the spiral fins and heat pipe.
It effectively reduces aircraft load, improves heat transfer efficiency, and provides a more efficient cooling solution.
Smart Images
Figure CN223596619U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the heat dissipation technical field, especially relate to a hydrogen internal combustion aircraft hot air cooling heat pipe device. BACKGROUND
[0002] The heat pipe is a closed evaporator-condenser system, which uses the evaporation and condensation of the working medium to transfer heat. It has high thermal conductivity, good isothermality, 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 aircraft, for hydrogen internal combustion aircraft, the hot air output by the turbocharger is cooled by a liquid cooler or an air cooler. In the field of domestic internal combustion engine vehicles, an air cooler or a water cooler is also used, but the liquid cooling device is heavy, which greatly increases the load of the aircraft and the cost of production, and the efficiency of the air cooling is not high and unstable. UTILITY MODEL CONTENT
[0004] In view of the above problems, the utility model provides a light and more efficient refrigeration device, which replaces the intercooler and becomes a better option for hydrogen internal combustion aircraft and internal combustion engine vehicles. Specifically, a hydrogen internal combustion aircraft hot air cooling heat pipe device is provided, which comprises,
[0005] The cooling cavity has a hot air inlet on one side and a hot air outlet on the other side.
[0006] The fixed tube is arranged in the cooling cavity.
[0007] The spiral fin is spirally arranged on the outer periphery of the fixed tube and extends along the length direction of the fixed tube. A plurality of horizontally corresponding holes are formed in the spiral fin.
[0008] The heat pipe is provided with a plurality of heat pipes. A part of the pipe body of the heat pipe is located in the cooling cavity, passes through the hole in the spiral fin and is fixed on the spiral fin. A part of the pipe body is located outside the cooling cavity.
[0009] Further, the spiral fin is a copper spiral fin.
[0010] Further, the heat pipe is arranged in a U shape. The plurality of heat pipes are divided into two groups arranged opposite to each other, and the spiral fins in the cooling cavity are grouped and penetrated. The cold ends of the two groups of heat pipes are aligned, and the hot ends are aligned.
[0011] Further, the cooling cavity is cylindrical, and the outer periphery of the spiral fin is attached to the cooling cavity.
[0012] Further, the heat pipe device is provided in multiple groups.
[0013] The scheme is to replace the intercooler refrigeration device of the existing turbocharger output hot air of hydrogen internal combustion aircraft and internal combustion engine automobile, solve the problem of increasing the load of the aircraft, thereby increasing the production cost and the unstable problem of low heat transfer efficiency. BRIEF DESCRIPTION OF DRAWINGS
[0014] Figure 1 It is the structure front view of the utility model;
[0015] Figure 2 It is the device sectional view of the utility model;
[0016] Figure 3 It is the device left view;
[0017] Figure 4 It is the internal structure of the cavity;
[0018] Figure 5 Positioning diagram of multiple sets of heat pipe cooling devices. DETAILED DESCRIPTION
[0019] The principles and characteristics of the utility model are described below in combination with the drawings, and the examples are only used to explain the utility model and are not used to limit the scope of the utility model.
[0020] Reference Figures 1-4 The utility model provides a light more efficient refrigeration device, replaces the intercooler, becomes a more optimal selection scheme for hydrogen internal combustion aircraft and internal combustion engine automobile, specifically provides a hydrogen internal combustion aircraft hot air cooling heat pipe device, comprising,
[0021] Cooling cavity 6, cylindrical, one side has hot air inlet 1, the other side has hot air outlet 5, the cylindrical design is advantageous to the gas formation cyclone, makes hot air and heat pipe hot end in the cooling cavity fully contact, and makes heat fully transfer.
[0022] Fixed pipe, set up in cooling cavity 6,
[0023] Spiral piece 4, for copper spiral piece spiral setting in the outer periphery of fixed pipe, along the length direction of fixed pipe extension, multiple horizontal corresponding holes are opened on spiral piece 4,
[0024] U-shaped heat pipes are provided; a part of the pipe body of the heat pipe is located in the cooling cavity and is fixed on the spiral sheet through the hole on the spiral sheet; another part of the pipe body is located outside the cooling cavity; the U-shaped structure can better match the cylindrical cooling cavity; the heat pipe utilizes the phase change principle of the working medium to transfer heat; in the evaporation section (heated section) of the heat pipe, heat is transferred into the pipe to make the working medium absorb heat and evaporate from liquid to gas; due to the difference in steam pressure, the gaseous working medium moves to the condensation section (heat dissipation section) of the heat pipe; in the condensation section, the gaseous working medium releases heat and condenses into liquid again; under the capillary action of the wick, the liquid working medium flows back to the evaporation section, thus realizing the 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 arranged in a U shape; a plurality of heat pipes are divided into two groups arranged oppositely to the left and right, and the spiral sheets in the cooling cavity are penetrated by the two groups; the two groups of heat pipes are aligned two by two. That is, externally, the cold end 2 of a heat pipe in one group is aligned with the cold end 2 of a heat pipe in the other group; internally in the cooling cavity, the hot end 3 of a heat pipe in one group is aligned with the hot end 3 of a heat pipe in the other group, and the cold end 2 of the heat pipe is arranged in order on the outer surface of the cooling cavity, so that the efficiency of air cooling is higher and heat can be more easily taken away.
[0026] As an improvement of the scheme, the cooling cavity is cylindrical, and the outer periphery of the spiral sheet is attached to the cooling cavity. This design divides the internal space of the cooling cavity by the spiral sheet to form a spiral space, so that the hot air entering the cooling cavity realizes rotational flow through the spiral path, thereby realizing sufficient contact and heat transfer between the hot air and the hot end of the heat pipe.
[0027] As an improvement of the scheme, reference Figure 5 In use, the heat pipe device is arranged in two groups and used in parallel, and the hot air is divided into two flow channels at the hot air inlet and then enters the heat pipe device and is combined at the hot air outlet.
[0028] After turbocharging, the air density increases and the temperature rises, and the air enters the cylindrical cooling cavity 6 through the hot air inlet 1. The copper spiral sheet 4 is embedded in the cylindrical cooling cavity 6 and is fixed. The copper spiral sheet 4 has a plurality of horizontal corresponding holes, the hot end of the U-shaped heat pipe is inserted into the copper spiral sheet 4 along the horizontal holes, and the copper spiral sheet 4 forms a spiral path in the cylindrical cooling cavity 6. The heat of the hot air is absorbed by the hot end 3 of the heat pipe and is transferred to the cold end 2 of the heat pipe through the action of the heat pipe, and finally the heat is dissipated through the heat transfer between the cold end 2 and 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 merely describes preferred embodiments of the present application and is not intended to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims
1. A hydrogen internal combustion aircraft hot air cooled heat pipe apparatus, characterized by, The application relates to a heat pipe device. The cooling cavity is provided with a hot air inlet on one side and a hot air outlet on the other side; The fixed tube is arranged in the cooling cavity; The spiral piece is spirally arranged on the outer periphery of the fixed tube and extends along the length direction of the fixed tube; a plurality of horizontally corresponding holes are formed in the spiral piece; The heat pipe is arranged in multiple; one part of the pipe body of the heat pipe is located in the cooling cavity, penetrates through the hole in the spiral piece and is fixed on the spiral piece; and the other part of the pipe body is located outside the cooling cavity.
2. A hydrogen-fueled aircraft hot air cooled heat pipe apparatus as defined in claim 1 wherein, The spiral piece is made of copper.
3. A hydrogen-fueled aircraft hot air cooled heat pipe apparatus as described in claim 1 wherein, The heat pipe is arranged in a U shape; the multiple heat pipes are divided into two groups which are oppositely arranged on the left and right sides, penetrate the spiral piece in the cooling cavity in groups and are oppositely arranged; the cold ends of the two groups of heat pipes are aligned, and the hot ends are aligned.
4. A hydrogen-fueled aircraft hot air cooled heat pipe apparatus as described in claim 1 wherein, The cooling cavity is in a cylindrical shape, and the outer periphery of the spiral piece is attached to the cooling cavity.
5. A hydrogen fueled aircraft hot air cooled heat pipe apparatus as described in claim 1 wherein, The heat pipe device is arranged in multiple groups.