Vortex tube device applied to hydrogen energy aircraft

Abstract

The utility model relates to the technical field of hydrogen energy aircrafts, in particular to a vortex tube device applied to a hydrogen energy aircraft, which comprises a vortex tube, an internal combustion engine, an engine cooling component and a cockpit temperature adjusting component. The vortex tube comprises a high-speed airflow inlet, a vortex tube hot end and a vortex tube cold end, the high-speed airflow inlet is located above the vortex tube and used for enabling high-speed airflow to enter the vortex tube and separating cold airflow and hot airflow under the vortex effect, and the vortex tube hot end and the vortex tube cold end are arranged on the left side and the right side of the vortex tube respectively and used for discharging the hot airflow and the cold airflow; one end of the engine cooling assembly communicates with the vortex tube cold end, and the other end of the engine cooling assembly is arranged on the periphery of the aircraft internal combustion engine to cool the internal combustion engine. The input end of the cockpit temperature adjusting assembly communicates with the vortex tube hot end and the vortex tube cold end at the same time, and the output end of the cockpit temperature adjusting assembly is arranged in a cockpit.

Description

Technical Field

[0001] The utility model relates to the technical field of hydrogen energy aircraft, and specifically relates to a vortex tube device applied to a hydrogen energy aircraft. Background Technique

[0002] A vortex tube is a device that uses the action of a vortex tube to generate a vortex in a high-speed air flow, separating it into two cold and hot air flows, obtaining a refrigeration method by using the cold air flow, and obtaining a heating method by using the hot air flow.

[0003] Currently, in the field of domestic light general aviation aircraft, for hydrogen energy aircraft, its aircraft engine uses a liquid cooling device. However, the liquid cooling refrigeration device is relatively heavy, which greatly increases the burden on the aircraft's load and increases the cost for enterprises. In addition, in high-temperature or low-temperature weather, the temperature control system in the aircraft cockpit also has deficiencies and cannot effectively provide a comfortable environment for passengers.

[0004] Therefore, inventing a device with a very small load burden that can both refrigerate and heat at the same time has become a better alternative for general aviation light aircraft. Content of the Utility Model

[0005] The purpose of the utility model is to provide a vortex tube device applied to a hydrogen energy aircraft, which can refrigerate the engine of the hydrogen energy aircraft and adjust the temperature of the cockpit according to the climate, thereby solving the technical problems in the background technique.

[0006] To achieve the above purpose, the utility model provides the following technical solution: a vortex tube device applied to a hydrogen energy aircraft, including a vortex tube, an internal combustion engine, an engine cooling component, and a cockpit temperature adjustment component;

[0007] The vortex tube includes a high-speed air flow inlet, a hot end of the vortex tube, and a cold end of the vortex tube. The high-speed air flow inlet is located above the vortex tube and is used to allow high-speed air flow to enter the vortex tube and separate into cold and hot air flows under the action of the vortex. The hot end of the vortex tube and the cold end of the vortex tube are respectively arranged on the left and right sides of the vortex tube and are used to discharge the hot air flow and the cold air flow;

[0008] One end of the engine cooling component is connected to the cold end of the vortex tube, and the other end is arranged around the aircraft internal combustion engine to cool the internal combustion engine;

[0009] The input end of the cockpit temperature adjustment component is simultaneously connected to the hot end of the vortex tube and the cold end of the vortex tube, and its output end is arranged inside the cockpit.

[0010] Further, the engine cooling component includes a cold air inlet, a spiral cooling cavity, a cold air outlet, and heat sinks; the cold air inlet is connected to the cold end of the vortex tube, the spiral cooling cavity is connected to the cold air inlet and the cold air outlet, and the heat sinks are installed on both sides of the internal combustion engine and embedded in the spiral cooling cavity.

[0011] Further, the cockpit temperature control component includes a hot air duct, a cold air duct, a total hot and cold air control valve, a small refrigeration and heating air conditioner, and air diffuser vanes;

[0012] The input end of the hot air duct is connected to the hot end of the vortex tube, and the other end is connected to the small refrigeration and heating air conditioner after passing through the total hot and cold air control valve;

[0013] The input end of the cold air duct is connected to the cold end of the vortex tube, and the other end is connected to the small refrigeration and heating air conditioner after passing through the total hot and cold air control valve;

[0014] The total hot and cold air control valve is connected to the small refrigeration and heating air conditioner; the total hot and cold air control valve is used to control the air flow in the hot air duct and the cold air duct to enter the small refrigeration and heating air conditioner;

[0015] The small refrigeration and heating air conditioner is of a hollow structure, and its interior serves as a heat exchange space for hot and cold air flows, so that the hot and cold air flows are fused to form a suitable temperature;

[0016] The air diffuser vanes are arranged at the output end of the small refrigeration and heating air conditioner on the small refrigeration and heating air conditioner.

[0017] Further, the cockpit temperature control component further includes a temperature control valve, and two temperature control valves are respectively arranged on the hot air duct and the cold air duct; the temperature control valve is located between the total hot and cold air control valve and the small refrigeration and heating air conditioner; the temperature control valve is used to adjust the flow rates of the cold air and the hot air according to the temperature of the cockpit.

[0018] Further, the spiral cooling cavity is spiral-shaped, providing space for the cold air flow to cool the heat sinks.

[0019] Beneficial effects

[0020] Compared with the traditional liquid cooling device, the vortex tube device adopted by the present utility model has a simpler and lighter structure, effectively reducing the overall weight of the aircraft and alleviating the load burden.

[0021] The present utility model improves the engine cooling effect: through the specially designed engine cooling component, the cold air flow generated by the vortex tube is used to cool the engine, improving the cooling efficiency, which helps to extend the service life of the engine and improve its performance.

[0022] The present utility model optimizes the temperature regulation in the cockpit: the cockpit temperature regulation component can accurately adjust the proportion of cold and hot airflows according to different climate conditions and the actual temperature in the cockpit, creating a comfortable environment for pilots and passengers.

[0023] The present utility model is energy-saving and environmentally friendly: during the operation of the vortex tube device, no additional energy input is required. Without consuming electrical energy, it only relies on the energy of the high-speed airflow to separate cold and hot airflows, achieving efficient utilization of energy and environmental protection and energy conservation. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments recorded in the present utility model. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings.

[0025] Figure 1 is a schematic diagram of the vortex tube structure of the vortex tube device disclosed by the present utility model;

[0026] Figure 2 is a schematic diagram of the engine cooling component of the vortex tube device disclosed by the present utility model;

[0027] Figure 3 is a schematic diagram of the cockpit temperature regulation component of the vortex tube device disclosed by the present utility model;

[0028] Figure 4 is a schematic diagram of the vortex tube device disclosed by the present utility model.

[0029] In the figure:

[0030] 1, cold air inlet; 2, spiral cooling cavity; 3, cold air outlet; 4, and heat sink; 5, internal combustion engine; 6, temperature control valve; 7, hot air duct; 8, air diffusing blades; 9, cold air duct; 10, total cold and hot air control valve; 11, small refrigeration and heating air conditioner; 12, high-speed air inlet; 13, hot end of the vortex tube; 14, cold end of the vortex tube. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model with reference to the drawings in the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, rather than all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0032] To achieve the above object, the present utility model provides the following technical solutions. As Figures 1-4 shown, a vortex tube device applied to a hydrogen energy aircraft includes a vortex tube, an internal combustion engine 5, an engine cooling assembly, and a cockpit temperature control assembly;

[0033] The vortex tube includes a high-speed air inlet 12, a hot end 13 of the vortex tube, and a cold end 14 of the vortex tube. The high-speed air inlet 12 is located above the vortex tube and is used to allow high-speed air to enter the vortex tube and separate into cold and hot airflows under the action of the vortex. The hot end 13 and the cold end 14 of the vortex tube are respectively arranged on the left and right sides of the vortex tube and are used to discharge the hot airflow and the cold airflow;

[0034] One end of the engine cooling assembly is connected to the cold end 14 of the vortex tube, and the other end is arranged around the aircraft internal combustion engine 5 to cool the internal combustion engine 5;

[0035] The input end of the cockpit temperature control assembly is simultaneously connected to the hot end 13 and the cold end 14 of the vortex tube, and its output end is arranged inside the cockpit.

[0036] Further, the engine cooling assembly includes a cold air intake 1, a spiral cooling cavity 2, a cold air outlet 3, and heat sinks 4; one end of the engine cooling assembly is connected to the cold end 14 of the vortex tube through the cold air intake 1. The cold air enters the spiral cooling cavity 2, and the heat sinks are installed on both sides of the internal combustion engine 5 and embedded in the spiral cooling cavity 2. The function of the heat sinks is to absorb the heat generated by the internal combustion engine 5 and achieve the cooling of the internal combustion engine 5 through heat exchange with the cold air. The cooled cold air is discharged from the cold air outlet 3.

[0037] Further, the cockpit temperature control assembly includes a hot air duct 7, a cold air duct 9, a total hot and cold air control valve 10, a refrigeration and heating small air conditioner 11, and air diffuser vanes 8; the input end of the cockpit temperature control assembly is respectively connected to the hot end 13 and the cold end 14 of the vortex tube through the hot air duct 7 and the cold air duct 9.

[0038] Specifically, the input end of the hot air duct 7 is connected to the hot end 13 of the vortex tube, and the other end is connected to the refrigeration and heating small air conditioner 11 after passing through the total hot and cold air control valve 10; the input end of the cold air duct 9 is connected to the cold end 14 of the vortex tube, and the other end is connected to the refrigeration and heating small air conditioner 11 after passing through the total hot and cold air control valve 10;

[0039] The total hot and cold air control valve 10 is connected to the refrigeration and heating small air conditioner 11; the total hot and cold air control valve 10 is used to control the airflows in the hot air duct 7 and the cold air duct 9 to enter the refrigeration and heating small air conditioner 11;

[0040] The small air conditioner 11 for refrigeration and heating has a hollow structure, and the hollow structure of the small air conditioner 11 provides a place for the heat exchange of cold and hot airflows, enabling the cold and hot airflows to merge to reach a temperature suitable for the cockpit.

[0041] The air-diffusing blades 8 are arranged at the position of the output end of the small air conditioner 11 for refrigeration and heating on the small air conditioner 11 for refrigeration and heating. The air-diffusing blades 8 can evenly distribute the airflow with adjusted temperature into the cockpit.

[0042] Furthermore, the cockpit temperature adjustment component further includes a temperature control valve 6. The temperature control valve 6 has two parts respectively arranged on the hot air duct 7 and the cold air duct 9; the temperature control valve 6 is located between the total control valve 10 for cold and hot airflows and the small air conditioner 11 for refrigeration and heating; the temperature control valve 6 is used to adjust the flow rates of the cold airflow and the hot airflow according to the temperature of the cockpit to achieve more precise temperature control.

[0043] Furthermore, the spiral cooling cavity 2 is spiral-shaped. The spiral design of the spiral cooling cavity 2 extends the flow path of the cold airflow therein, providing sufficient time and space for sufficient cooling.

[0044] The working principle and process are as follows:

[0045] When the high-speed airflow enters the inside of the vortex tube through the high-speed airflow inlet 12 above the vortex tube, due to the internal structure of the vortex tube, the airflow will generate a strong vortex motion. Under the action of the vortex, the energy of the high-speed airflow is separated to form two cold and hot airflows with different temperatures. The cold airflow is discharged from the cold end 14 of the vortex tube, and the hot airflow is discharged from the hot end 13 of the vortex tube.

[0046] The engine cooling component uses the cold airflow generated by the vortex tube to cool the internal combustion engine 5. The cold airflow enters the spiral cooling cavity 2 from the cold end 14 of the vortex tube through the cold airflow inlet 1, fully contacts the heat dissipation fins embedded therein in the spiral cavity, absorbs the heat generated by the internal combustion engine 5, and is discharged from the cold airflow outlet 3 after cooling.

[0047] The cockpit temperature adjustment component provides a suitable temperature for the cockpit by adjusting and mixing the cold and hot airflows generated by the vortex tube. The hot airflow passes through the hot air duct 7, and the cold airflow passes through the cold air duct 9. After the flow rates are adjusted by the temperature control valves 6 on their respective pipes, they then enter the small air conditioner 11 for refrigeration and heating through the total control valve 10 for cold and hot airflows. In the hollow structure of the small air conditioner 11 for refrigeration and heating, the cold and hot airflows conduct heat exchange and merge into an airflow with a suitable temperature, and finally are evenly distributed into the cockpit through the air-diffusing blades 8.

[0048] Meanwhile, the temperature sensor in the cockpit monitors the temperature in real time. When the temperature is too high, the temperature control valve 6 increases the cold air flow rate in the cold air duct 9 and reduces the hot air flow rate in the hot air duct 7, allowing more cold air to enter the mini air conditioner 11 for cooling and heating, and mixing to produce a lower temperature air flow to cool the cockpit. Conversely, when the temperature is too low, the temperature control valve 6 adjusts the cold and hot air flow rate ratio, increases the supply of hot air, and mixes to produce a higher temperature air flow to warm the cockpit, thus providing a comfortable environment for the cockpit.

[0049] The embodiments of the present utility model are given for purposes of illustration and description, and are not exhaustive or limit the present utility model to the disclosed form. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are chosen and described in order to better explain the principles and practical applications of the present utility model, and enable those of ordinary skill in the art to understand the present utility model and design various embodiments with various modifications suitable for specific purposes.

Claims

1. A vortex tube device applied to a hydrogen energy aircraft, characterized in that: It includes a vortex tube, an internal combustion engine (5), an engine cooling assembly, and a cockpit temperature control assembly; The vortex tube includes a high-speed air inlet (12), a hot end (13) of the vortex tube, and a cold end (14) of the vortex tube. The high-speed air inlet (12) is located above the vortex tube and is used to allow high-speed air to enter the vortex tube and separate into cold and hot airflows under the action of the vortex. The hot end (13) of the vortex tube and the cold end (14) of the vortex tube are respectively arranged on the left and right sides of the vortex tube and are used to discharge the hot airflow and the cold airflow; One end of the engine cooling assembly is connected to the cold end (14) of the vortex tube, and the other end is arranged around the internal combustion engine (5) to cool the internal combustion engine (5); The input end of the cockpit temperature control assembly is simultaneously connected to the hot end (13) of the vortex tube and the cold end (14) of the vortex tube, and its output end is arranged inside the cockpit.

2. The vortex tube device applied to a hydrogen energy aircraft according to claim 1, wherein: The engine cooling assembly includes a cold air inlet (1), a spiral cooling cavity (2), a cold air outlet (3), and heat sinks (4); the cold air inlet (1) is connected to the cold end (14) of the vortex tube, the spiral cooling cavity (2) is connected to the cold air inlet (1) and the cold air outlet (3), and the heat sinks (4) are installed on both sides of the internal combustion engine (5) and are embedded in the spiral cooling cavity (2).

3. The vortex tube device applied to a hydrogen energy aircraft according to claim 1, characterized in that: The cockpit temperature control assembly includes a hot air duct (7), a cold air duct (9), a total hot and cold air control valve (10), a small refrigeration and heating air conditioner (11), and air diffuser vanes (8); The input end of the hot air duct (7) is connected to the hot end (13) of the vortex tube, and the other end is connected to the small refrigeration and heating air conditioner (11) after passing through the total hot and cold air control valve (10); The input end of the cold air duct (9) is connected to the cold end (14) of the vortex tube, and the other end is connected to the small refrigeration and heating air conditioner (11) after passing through the total hot and cold air control valve (10); The total hot and cold air control valve (10) is connected to the small refrigeration and heating air conditioner (11); the total hot and cold air control valve (10) is used to control the airflow in the hot air duct (7) and the cold air duct (9) to enter the small refrigeration and heating air conditioner (11); The small refrigeration and heating air conditioner (11) is of a hollow structure, and its interior serves as a heat exchange space for hot and cold airflows; The air diffuser vanes (8) are arranged at the position of the output end of the small refrigeration and heating air conditioner (11) on the small refrigeration and heating air conditioner (11).

4. The vortex tube device applied to a hydrogen energy aircraft according to claim 1, wherein: The cockpit temperature control assembly further includes a temperature control valve (6), and two temperature control valves (6) are respectively arranged on the hot air duct (7) and the cold air duct (9); the temperature control valve (6) is located between the total hot and cold air control valve (10) and the small refrigeration and heating air conditioner (11); the temperature control valve (6) is used to adjust the flow rates of the cold airflow and the hot airflow according to the temperature of the cockpit.

5. Applied to a hydrogen energy aircraft according to claim 2 The vortex tube device is characterized in that: The spiral cooling cavity (2) is spiral-shaped and provides space for the cold airflow to cool the heat sinks (4).

Images