A temperature difference power generation device, power generation method, air intake and jet aircraft

Abstract

The present invention discloses a thermoelectric power generation device, a power generation method, an air intake and a jet aircraft. The device comprises an inner ring (1), the inner ring (1) is covered with an outer ring (4); the outer surface of the inner ring (1) is provided with thermoelectric power generation sheets (3) distributed along the circumferential direction, and the two ends of the thermoelectric power generation sheets (3) are electrically connected to a circuit (2) arranged on the outer surface of the inner ring (1); the inner surface of the outer ring (4) cooperates with the inner ring (1) on which the thermoelectric power generation sheets (3) are installed, and one or more annular flow channels (7) are arranged axially in the inner wall of the outer ring (4), and the outer surface is provided with an air intake port (5) and an air exhaust port (6), both of which are connected to the annular flow channel (7). The device has a simple structure, high reliability, light weight, and no adverse effect on engine performance. At the same time, the device can also cool the engine bleed air and reduce the heat dissipation pressure of the aircraft environmental control system.

Description

Technical Field

[0001] The present invention relates to the technical field of overall aircraft design, and in particular to a temperature difference power generation device, a power generation method, an air inlet and a jet aircraft. Background Art

[0002] Traditional aircraft power systems mainly use engine-driven generators as a power source. They have a complex structure, many moving parts, reliability risks, and require the extraction of engine shaft power, which has a negative impact on the performance of jet engines. In addition, they are equipped with backup power supply devices using batteries, but the energy density of batteries is low, which adds a lot of extra weight to the aircraft. Summary of the invention

[0003] The purpose of the present invention is to provide a temperature difference power generation device, a power generation method, an air intake and a jet aircraft. The present invention has a simple structure, high reliability, light weight, and no adverse effect on engine performance. At the same time, it can also cool the engine bleed air and reduce the heat dissipation pressure of the aircraft environmental control system.

[0004] Technical solution. A jet aircraft thermoelectric power generation device based on engine bleed air comprises an inner ring, an outer ring is arranged outside the inner ring; thermoelectric power generation sheets are distributed along the circumferential direction on the outer surface of the inner ring, and both ends of the thermoelectric power generation sheets are electrically connected to the circuit arranged on the outer surface of the inner ring; the inner surface of the outer ring cooperates with the inner ring with the thermoelectric power generation sheets installed, more than one annular flow channel is arranged axially inside the outer ring wall, and a bleed air inlet and a bleed air exhaust port are arranged on the outer surface, both of which are connected to the annular flow channel.

[0005] In the aforementioned jet aircraft temperature difference power generation device based on engine bleed air, the inner surface of the inner ring conforms to the inner profile of the aircraft's air inlet.

[0006] In the aforementioned jet aircraft temperature difference power generation device based on engine bleed air, the cross section of the inner surface of the outer ring is polygonal.

[0007] In the aforementioned jet aircraft temperature difference power generation device based on engine bleed air, the inner ring and the outer ring are both made of heat conductive material.

[0008] A power generation method for a jet aircraft thermoelectric power generation device based on engine bleed air as described above, taking the intake air of the air inlet as a cold source, cooling the inner surface of the thermoelectric power generation sheet through the inner surface of the inner ring; taking the engine bleed air as a heat source, entering the outer ring from the bleed air inlet, flowing along the annular flow channel for one circle and then flowing out from the bleed air exhaust port, heating the outer surface of the thermoelectric power generation sheet in the process; thereby forming a temperature difference between the inner and outer surfaces of the thermoelectric power generation sheet, generating electrical energy, which is then derived by the circuit.

[0009] In the aforementioned power generation method, the temperature of the engine bleed air is reduced after it leaves the bleed air exhaust port and is used to supply the rear-end environmental control system.

[0010] An air intake duct is provided with the above-mentioned jet aircraft temperature difference power generation device based on engine bleed air.

[0011] A jet aircraft is provided with the air inlet as described above.

[0012] Beneficial effects: The present invention is designed for jet aircraft equipped with an air intake and an environmental control system that uses engine bleed air as an energy source and air source. The heat exchange structure is used to use the engine bleed air going to the aircraft environmental control system as a heat source, the aircraft air intake cold air as a cold source, and the temperature difference power generation sheet is used as a heat exchange medium, thereby realizing temperature difference power generation. The device can achieve a highly reliable power generation function without extracting engine shaft power and has no effect on engine performance. The engine bleed air can also be cooled to reduce the heat dissipation pressure of the rear-end aircraft environmental control system, thereby reducing the weight of the environmental control system heat dissipation structure. Specifically, the advantages of the present invention are as follows:

[0013] The first is to provide an additional power source that is independent of the aircraft's existing power supply system and can provide sustainable power. Under normal circumstances, it can be used as a supplement to the aircraft's main power supply system to reduce the pressure on the main power supply system. In the event of a failure in the main power system, it can also be used as the aircraft's backup power supply system for emergency use. When used as a backup power supply system, compared to a backup power supply device using a battery, this device has the advantages of being able to work sustainably and not being limited by the battery capacity. Under the emergency power supply duration usually required by aircraft, the application of the present invention to replace a backup power supply device using a battery, or as a supplement to a backup power supply device using a battery, can significantly reduce the weight of the battery.

[0014] The second is to pre-cool the engine bleed air, thereby reducing the heat dissipation pressure of the rear-end aircraft environmental control system. Since the present invention is installed on the aircraft air inlet, the cold source uses the air in the air inlet, which can fully utilize the large flow of air in the air inlet for heat dissipation, and its cooling efficiency is high. Therefore, after the engine bleed air is pre-cooled by the present invention, the heat dissipation capacity requirement of the rear-end environmental control system can also be greatly reduced, thereby effectively saving the weight of the heat dissipation mechanism of the rear-end environmental control system.

[0015] In summary, the present invention can achieve significant benefits in terms of aircraft weight. At the same time, since the present invention integrates the two functions of power generation and heat dissipation in one device, it also effectively utilizes the space around the air inlet that is difficult for other equipment to use due to limited conditions such as fixed connection and disassembly and assembly access, and also has great benefits in saving the available space in the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of a jet aircraft temperature difference power generation device of the present invention;

[0017] Figure 2 It is a schematic diagram of the inner and outer ring structures;

[0018] Figure 3 It is a schematic diagram of the inner circle structure;

[0019] Figure 4 This is a cross-sectional view of a jet aircraft thermoelectric power generation device;

[0020] Figure 5 This is a schematic diagram of the working principle of the jet aircraft temperature difference power generation device;

[0021] Figure 6 This is a schematic diagram of the installation of the thermoelectric generator. DETAILED DESCRIPTION

[0022] Example 1. A jet aircraft temperature difference power generation device, see Figure 1-Figure 6 , consisting of an outer ring 4 and an inner ring 1. The inner ring 1 is made of a high thermal conductivity material, and its inner surface is a cylindrical surface that conforms to the inner profile of the aircraft air inlet. The outer surface is designed with grooves for arranging the circuit 2 and the thermoelectric power generation sheet 3, and the circuit 2 and the thermoelectric power generation sheet 3 are arranged thereon; the outer ring 4 is also made of a high thermal conductivity material, and its inner surface is designed as a polygonal structure, which cooperates with the inner ring 1 on which the thermoelectric power generation sheet 3 is installed; a plurality of annular flow channels 7 are arranged inside the outer ring 4, and an air inlet 5 and an air exhaust 6 are provided on the outer surface, which are connected to the annular flow channels 7. When the device is used on an aircraft, it is arranged on the aircraft air intake 8 as a part of the aircraft air intake. When the aircraft is flying, the air intake of the air intake 8 is used as a cold source, passing through the inner ring 1 to cool the inner surface of the thermoelectric generator sheet 3; the engine bleed air is used as a heat source, entering the outer ring 4 from the bleed air inlet 5, flowing along the annular flow channel 7 for one circle, and then flowing out from the bleed air exhaust port 6, heating the outer surface of the thermoelectric generator sheet 3 in the process; thus, a temperature difference is formed between the inner and outer surfaces of the thermoelectric generator sheet 3, generating electrical energy, which is derived from the device by the circuit 2. In addition, after the engine bleed air passes through the outer ring 4, the temperature will be reduced, which is used to supply the rear-end environmental control system, which can reduce the heat dissipation pressure of the aircraft environmental control system.

[0023] The installation method of the temperature difference power generation sheet 3 on the inner ring 1 is as follows Figure 6 As shown, the temperature difference power generation sheet 3 is composed of a three-layer structure, the middle part is the power generation sheet body 32, and the upper and lower surfaces are respectively pasted with a soft upper phase change thermal conductive sheet 31 and a lower phase change thermal conductive sheet 33, whose function is to cover and fill the gap between the inner ring 1, the power generation sheet body 32, and the outer ring 4 to increase the thermal conductivity; a positioning pin 11 is arranged on the inner ring 1, and corresponding positioning holes are arranged on the power generation sheet body 32, the upper phase change thermal conductive sheet 31 and the lower phase change thermal conductive sheet 33 for fixing the power generation sheet during installation.

[0024] In order to ensure full contact between the inner ring 1, the power generation sheet 3, and the outer ring 4, the inner diameter of the outer ring 4 is designed to be slightly smaller than the overall outer diameter of the power generation sheet 3 after installation on the inner ring 1. During installation, the outer ring 4 must first be placed in a hot environment to expand its overall size due to heat until the inner diameter is larger than the overall outer diameter of the power generation sheet 3 after installation on the inner ring 1. Then the inner ring 1 and the outer ring 4 are fitted together and then placed at room temperature for cooling. After the outer ring 4 cools and shrinks, it will be pressed against the power generation sheet 3 and the inner ring 1. This design and installation method does not require the use of a large number of connectors to press the outer ring 4 against the power generation sheet 3 and the inner ring 1, and also maintains the integrity of the inner and outer rings, improves the rigidity and strength of the device, and effectively reduces the overall weight of the device; it also avoids the uneven pressure at various locations that may result in poor contact due to forced installation of connectors, which damages the thermal conductivity inside the device, and improves the power generation and heat dissipation performance of the device.

Claims

1. A jet aircraft temperature difference power generation device based on engine bleed air, characterized in that: The invention comprises an inner ring (1), wherein the inner ring (1) is covered with an outer ring (4); the outer surface of the inner ring (1) is provided with temperature difference power generation sheets (3) distributed along the circumferential direction, and the two ends of the temperature difference power generation sheets (3) are electrically connected to a circuit (2) arranged on the outer surface of the inner ring (1); the inner surface of the outer ring (4) cooperates with the inner ring (1) on which the temperature difference power generation sheets (3) are installed, and one or more annular flow channels (7) are arranged axially in the inner wall of the outer ring (4), and the outer surface is provided with an air intake port (5) and an air exhaust port (6), both of which are connected to the annular flow channel (7).

2. The jet aircraft temperature difference power generation device based on engine bleed air according to claim 1, characterized in that: The inner surface of the inner ring (1) conforms to the inner profile of the air inlet (8) of the aircraft.

3. The jet aircraft temperature difference power generation device based on engine bleed air according to claim 1, characterized in that: The cross section of the inner surface of the outer ring (4) is polygonal.

4. The jet aircraft temperature difference power generation device based on engine bleed air according to claim 1, characterized in that: The inner ring (1) and the outer ring (4) are both made of heat-conducting material.

5. A method for generating electricity using a jet aircraft temperature difference power generation device based on engine bleed air as claimed in any one of claims 1 to 4, characterized in that: The air intake of the air intake duct (8) is used as a cold source to cool the inner surface of the thermoelectric power generation sheet (3) through the inner surface of the inner ring (1); the engine bleed air is used as a heat source to enter the outer ring (4) through the bleed air inlet (5), flow along the annular flow channel (7) for one circle, and then flow out from the bleed air outlet (6), during which the outer surface of the thermoelectric power generation sheet (3) is heated; thereby, a temperature difference is formed between the inner and outer surfaces of the thermoelectric power generation sheet (3), generating electrical energy, which is then conducted out by the circuit (2).

6. The power generation method according to claim 1, characterized in that: The engine bleed air is cooled down after passing through the bleed air exhaust port (6) and is used to supply the rear-end environmental control system.

7. An air intake duct, characterized in that: A jet aircraft temperature difference power generation device based on engine bleed air as described in any one of claims 1 to 4 is installed.

8. A jet aircraft, characterized in that: The air intake duct according to claim 7 is installed.

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