Energy pod based on supercritical co2 power generation technology and method of operation thereof

Abstract

The application belongs to the technical field of aviation electromechanical systems, and discloses an energy pod based on supercritical CO2 power generation technology and a running method thereof, wherein the pod comprises a closed cycle power generation unit, a fuel gas heat exchange unit, a power electronic unit and an aviation lithium battery, the closed cycle power generation unit is internally provided with a closed cycle heat exchange gas path, after the gas of the closed cycle heat exchange gas path obtains heat provided by the fuel gas heat exchange unit, the heat energy is converted into electric energy, and the electric energy is delivered to the aviation lithium battery and an on-board direct current bus through the power electronic unit; the fuel gas heat exchange unit is a mechanism for generating heat by burning fuel oil. The application can adapt to wider application requirements of airborne electrical equipment, can adapt to wider environmental pressure changes, and has the advantage of smaller output power attenuation with flight height changes of the aircraft compared with a traditional auxiliary power device.

Description

Technical Field

[0001] This invention belongs to the field of aviation electromechanical systems technology, and relates to an energy system for aircraft, specifically an energy pod based on supercritical CO2 power generation technology and its operation method. Background Technology

[0002] Electronic equipment, laser devices, and high-power airborne radar play a crucial role in modern aviation. Airborne power pods can provide onboard power for these devices. The pod's power generation system can be designed as an independent, detachable unit, featuring rapid loading and unloading, making it essential equipment for expanding aircraft applications and flexibly deploying missions. In practical aircraft use, pod products offer advantages such as convenient maintenance, minimal impact on the aircraft, and the ability to expand specific aircraft functions, making it a rapidly developing and important technology in recent years. Summary of the Invention

[0003] To address the aforementioned issues, this invention proposes an airborne energy pod technology based on supercritical carbon dioxide power generation, which can provide an extended package of onboard power for aircraft, while exhibiting minimal power attenuation with altitude changes, thus possessing significant application value.

[0004] Technical solution of the present invention:

[0005] An energy pod based on supercritical CO2 power generation technology includes a closed-loop power generation unit, a gas heat exchange unit, a power electronics unit, and an aviation lithium battery. The closed-loop power generation unit is equipped with a closed-loop heat exchange gas path. After the gas in the closed-loop heat exchange gas path receives heat from the gas heat exchange unit, it converts the thermal energy into electrical energy, which is then transmitted to the aviation lithium battery and the onboard DC bus through the power electronics unit. The gas heat exchange unit is a mechanism that generates heat by burning fuel.

[0006] Furthermore, the closed-loop power generation unit includes a high-speed starter / generator and an SCO2 power unit. The SCO2 power unit includes a heat exchanger, an SCO2 turbine, a regenerator, a cooling device, an SCO2 compressor, and a closed-loop heat exchange gas path. After the gas in the closed-loop heat exchange gas path acquires heat from the heat exchanger, it drives the SCO2 turbine to do work. Then, it enters the hot end of the regenerator, passes through the cooling device to dissipate heat, is pressurized by the SCO2 compressor, and returns to the heat exchanger through the cold end of the regenerator, completing the cycle. The SCO2 turbine is connected to and drives the high-speed starter / generator.

[0007] Furthermore, the high-speed starter / generator, SCO2 turbine, and SCO2 compressor are coaxial. During the start-up phase, the high-speed starter / generator acts as a starter motor to drive the SCO2 compressor.

[0008] Furthermore, the device includes a pod assembly, which comprises an outer wall and an inner wall. A closed-loop power generation unit, a gas heat exchange unit, a power electronics unit, and an aviation lithium battery are installed inside the inner wall of the pod assembly. An air inlet is provided at the front end of the pod assembly. The air inlet includes a ram cooling air inlet with a large inlet area. The rear end of the ram cooling air inlet contracts between the outer wall and the inner wall to form a ram duct. The cooling device for the closed-loop power generation unit is a ram duct cooler installed in the ram duct.

[0009] Furthermore, the air inlet also includes a cabin air inlet with a small inlet area located at the center of the ram cooling air inlet. The rear end of the cabin air inlet is expanded to connect with the interior of the inner wall, and a power electronics unit, a closed-loop power generation unit, a gas heat exchange unit, and an aviation lithium battery are respectively installed along the air flow direction.

[0010] Furthermore, the gas heat exchange unit includes an air compressor, a fuel pump, a gas turbine, a heat exchange burner, and a speed-regulating starter / generator. The air compressor and the gas turbine are coaxial, and the air compressor is driven by the speed-regulating starter / generator. Compressed air enters the heat exchange burner, mixes with fuel from the fuel pump, and then burns. The high-temperature, high-pressure gas flow after combustion exchanges heat with the closed-cycle power generation unit and then drives the gas turbine to operate, reducing the power consumption of the speed-regulating starter / generator. The heat exchange burner and the heat exchange device of the closed-cycle power generation unit are the same device.

[0011] Furthermore, the power electronics unit includes an AC / DC rectifier, a power divider, and a system controller. The electrical energy generated by the closed-cycle power generation unit enters the power divider after passing through the AC / DC rectifier, and the power divider connects to the aviation lithium battery and the DC bus. The system controller collects signals from the closed-cycle power generation unit, the gas heat exchange unit, and the aviation lithium battery, and controls the closed-cycle power generation unit and the gas heat exchange unit.

[0012] An operational method for an airborne energy pod based on supercritical carbon dioxide power generation technology is disclosed. When an aircraft needs to expand its energy supply, the aforementioned airborne energy pod based on supercritical carbon dioxide power generation technology is installed. During startup, a high-speed starter / generator acts as a starter motor to drive the compressor, causing the gas in the closed-loop heat exchanger circuit to circulate. A variable-speed starter / generator acts as a motor to drive the air compressor, and simultaneously, fuel supply begins, with the fuel pump operating to provide compressed air and fuel to the heat exchanger combustion chamber and ignite it. The high-temperature, high-pressure gas generated in the heat exchanger combustion chamber transfers heat to the gas in the closed-loop heat exchanger circuit, which drives the SCO2 turbine. When the SCO2 turbine speed reaches a set value, the high-speed starter / generator switches to power generation mode to provide power to the DC bus and charge the aviation lithium battery.

[0013] The beneficial effects of this invention are as follows:

[0014] 1. This invention provides an airborne energy pod based on supercritical carbon dioxide power generation technology. Through the configuration of lithium batteries, the system has the characteristics of energy storage and has a large peak-to-average power ratio, which can meet the application needs of a wider range of airborne electrical equipment.

[0015] 2. This invention adopts the closed-loop thermoelectric conversion technology principle, and the hot end adopts a heat exchange combustion unit. Its compressor speed is adjustable to adapt to a wider range of environmental pressure changes. Compared with traditional auxiliary power units, the output power has the advantage of less attenuation with the flight altitude of the aircraft.

[0016] 3. The high-speed starter / generator of the closed-loop power generation unit of this invention adopts high-speed direct drive technology, which saves the gearbox transmission mechanism compared with the traditional motor reduction arrangement, thereby reducing the system weight and improving the system efficiency.

[0017] 4. The bearing of this invention adopts a gas dynamic pressure bearing, which eliminates the oil lubrication mechanism of the rolling bearing in the traditional airborne turbine power system, reducing weight and achieving the requirement of maintenance-free operation.

[0018] 5. The supercritical carbon dioxide power generation technology of this invention has the characteristics of small turbine size and high efficiency, which has great benefits for the miniaturization and advancement of airborne equipment.

[0019] 6. The heat exchange combustion unit of this invention uses a turbine for energy recovery, which makes the onboard electrical efficiency higher. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this invention, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this invention and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the principle of an airborne energy pod based on supercritical CO2 power generation technology according to the present invention;

[0022] Figure 2 This is a schematic diagram of the principle of the SCO2 closed-loop power generation unit of the present invention;

[0023] Figure 3 This is a schematic diagram of the heat exchange combustion unit of the present invention;

[0024] Figure 4 This is a schematic diagram of the structure of an airborne energy pod based on supercritical carbon dioxide power generation technology according to the present invention;

[0025] Among them, 1-high-speed starter / generator, 2-SCO2 power unit, 3-closed-cycle power generation unit, 4-system controller, 5-power electronics unit, 6-lithium battery, 7-power distributor, 8-starter, 9-AC / DC rectifier, 10-hot end heat exchanger, 11-SCO2 turbine, 12-SCO2 compressor, 13-bearing, 14-closed-cycle power generation unit, 15-cooler, 16-regenerator, 17-gas turbine, 18-gas heat exchange unit, 19-fuel pump, 20-air compressor, 21-pod device, 22-speed-regulating starter / generator. Detailed Implementation

[0026] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0027] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are based on the orientation or positional relationships in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or case referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0028] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; they can refer to mechanical connections or point connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0029] Example 1:

[0030] This invention can form an integrated airborne power pod, providing airborne power expansion for electronic equipment, high-power radar, and laser devices, enabling the application expansion and flexible configuration of airborne power packs. The power provided by this invention exhibits minimal power attenuation with flight altitude, demonstrating superior high-altitude characteristics and significant potential application scope.

[0031] An airborne energy pod based on supercritical CO2 power generation technology includes a closed-loop power generation unit 3, a gas heat exchange unit 18, a power electronics unit 5, and an aviation lithium battery 6. The closed-loop power generation unit 3 is equipped with a closed-loop heat exchange gas path. After the gas in the closed-loop heat exchange gas path receives heat from the gas heat exchange unit 18, it converts the thermal energy into electrical energy, which is then transmitted to the aviation lithium battery 6 and the onboard DC bus through the power electronics unit 5. The gas heat exchange unit 18 is a mechanism that generates heat by burning fuel.

[0032] The closed-loop power generation unit 3 includes a high-speed starter / generator 1 and an SCO2 power unit 2. The SCO2 power unit 2 includes a heat exchange device, an SCO2 turbine 11, a regenerator 16, a cooling device, an SCO2 compressor 12, and a closed-loop heat exchange gas path. After the gas in the closed-loop heat exchange gas path acquires heat from the heat exchange device, it drives the SCO2 turbine 11 to do work. Then, it enters the hot end of the regenerator 16, and is cooled by the cooling device. After being pressurized by the SCO2 compressor 12, it returns to the heat exchange device through the cold end of the regenerator 16 to complete the cycle. The SCO2 turbine 11 is connected to and drives the high-speed starter / generator 1.

[0033] The high-speed starter / generator 1, SCO2 turbine 11 and SCO2 compressor 12 are coaxial. During the start-up phase, the high-speed starter / generator 1 acts as a starter to drive the SCO2 compressor 12.

[0034] The device includes a pod device 21, which has an outer wall and an inner wall. A closed-loop power generation unit 3, a gas heat exchange unit 18, a power electronics unit 5, and an aviation lithium battery 6 are installed inside the inner wall of the pod device 21. The pod device 21 has an air inlet at its front end, which includes a ram cooling air inlet with a large inlet area. The rear end of the ram cooling air inlet contracts between the outer wall and the inner wall to form a ram duct. The cooling device for the closed-loop power generation unit 3 is a ram duct cooler 15 installed in the ram duct.

[0035] The air inlet also includes a cabin air inlet with a small inlet area located in the center of the ram cooling air inlet. The rear end of the cabin air inlet is expanded to connect to the interior of the inner wall. Along the air flow direction, a power electronics unit 5, a closed-loop power generation unit 3, a gas heat exchange unit 18, and an aviation lithium battery 6 are respectively installed.

[0036] The gas heat exchange unit 18 includes an air compressor 20, a fuel pump 19, a gas turbine 17, a heat exchange burner 10, and a speed-regulating starter / generator 22. The air compressor 20 and the gas turbine 17 are coaxial. The air compressor 20 is driven by the speed-regulating starter / generator 22. Compressed air enters the heat exchange burner 10 and mixes with fuel from the fuel pump 19 before combustion. The high-temperature and high-pressure gas flow after combustion exchanges heat with the closed-loop power generation unit 3 and then drives the gas turbine 17 to operate, reducing the power consumption of the speed-regulating starter / generator 22. The heat exchange burner 10 and the heat exchange device of the closed-loop power generation unit 3 are the same device.

[0037] The power electronics unit 5 includes an AC / DC rectifier 9, a power distributor 7, and a system controller 4. The electrical energy generated by the closed-loop power generation unit 3 enters the power distributor 7 after passing through the AC / DC rectifier 9. The power distributor 7 connects the aviation lithium battery 6 and the DC bus. The system controller 4 collects signals from the closed-loop power generation unit 3, the gas heat exchange unit 18, and the aviation lithium battery 6. The system controller 4 controls the closed-loop power generation unit 3 and the gas heat exchange unit 18.

[0038] Example 2:

[0039] An operational method for an airborne energy pod based on supercritical carbon dioxide power generation technology is disclosed. When an aircraft needs to expand its energy supply, the aforementioned airborne energy pod based on supercritical carbon dioxide power generation technology is installed. During startup, a high-speed starter / generator acts as a starter motor to drive the compressor, causing the gas in the closed-loop heat exchanger circuit to circulate. A variable-speed starter / generator acts as a motor to drive the air compressor, and simultaneously, fuel supply begins, with the fuel pump operating to provide compressed air and fuel to the heat exchanger combustion chamber and ignite it. The high-temperature, high-pressure gas generated in the heat exchanger combustion chamber transfers heat to the gas in the closed-loop heat exchanger circuit, which drives the SCO2 turbine. When the SCO2 turbine speed reaches a set value, the high-speed starter / generator switches to power generation mode to provide power to the DC bus and charge the aviation lithium battery.

[0040] After the pod receives the aircraft's power supply command, the system controller 4 controls the aviation lithium battery 6 to supply power to the DC bus through the power divider 7. When the aviation lithium battery 6's charge is less than 30%, the system controller 4 controls the closed-loop power generation unit 3 to start.

[0041] The pod system controller can also receive start commands from the aircraft's closed-cycle power generation unit 3, at which time the closed-cycle power generation unit 3 supplies power to the DC bus or supplies power to the aviation lithium battery 6.

[0042] The startup procedure for the generator pod is as follows:

[0043] System controller 4 controls the operation of high-speed starter / generator 22, which drives compressor 20 and turbine 17 to operate synchronously. After compressor 20 starts operating, it provides high-pressure compressed air and supplies it to heat exchange burner 10. When high-speed starter / generator 22 reaches a certain speed, generally about 40% of the rated speed, system controller 4 controls fuel pump 19 to supply fuel to heat exchange burner and ignite it. The exhaust gas from heat exchange burner 10 is exhausted through turbine 17 and the exhaust gas energy is recovered.

[0044] Simultaneously with the start-up of the gas heat exchange unit 18, the system controller 4 controls the first high-speed generator 1 to operate, driving the SCO2 compressor 12 and the SCO2 turbine 11, which in turn drives the flow of the working fluid within the closed-cycle power generation unit 14. When the speed of the first high-speed generator 1 reaches 45% of the rated speed of the closed-cycle power generation unit 14, the system controller 4 controls the first high-speed generator 1 to switch to power generation mode. The flowing supercritical CO2 working fluid, after being heated by the heat exchange burner 10, drives the SCO2 turbine 11 to rotate. The rotational energy provided by the rotation drives the SCO2 compressor 12 and the first high-speed generator 1, completing the start-up of the closed-cycle power generation unit 14.

[0045] The AC power provided by the first high-speed generator 1 enters the power distributor 7 through the AC / DC rectifier 9, and the power distributor 7 supplies power to the DC bus and the aviation lithium battery 6.

[0046] The power control startup procedure for the generator pod is as follows:

[0047] When the output power of the pod system 21 is lower than the demand, the system controller 4 increases the speed of the second starter / generator 22 to provide more compressed air. Simultaneously, the system controller 4 increases the flow rate of the fuel pump 19 to provide more fuel. The fuel flow rate is related to the compressor's gas delivery volume, with its equivalence ratio controlled at approximately 0.8. Therefore, the combustion heat temperature of the heat exchange burner 10 increases. The increased gas temperature transfers more heat to the circulating working fluid in the closed-cycle power generation unit 14, further increasing the working fluid temperature. As the temperature increases, the SCO2 turbine 11 provides more output power to the rotating shaft, thus increasing the output power of the pod system 21. The speed of the second starter / generator 22 and the fuel pump 19 increase until the power demand of the pod system 21 is reached or the exhaust temperature of the gas heat exchange unit 18 reaches the upper limit of the specified value, at which point the increase stops.

[0048] When the output power of the pod system 21 exceeds the demand, the system controller 4 reduces the speed of the second high-speed starter / generator 22 to decrease the supply of compressed air. Simultaneously, the system controller 4 reduces the fuel flow rate of the fuel pump 19. The fuel flow rate is related to the compressor's gas delivery volume, and its equivalence ratio is controlled at approximately 0.8. Therefore, the combustion heat temperature of the heat exchange burner 10 decreases. The lower gas temperature transfers less heat to the circulating working fluid in the closed-cycle power generation unit 14, further reducing the working fluid temperature. As the temperature decreases, the SCO2 turbine 11 provides less output power to the rotating shaft, thus reducing the output power of the pod system 21. The speed of the second starter / generator 22 and the fuel flow rate of the fuel pump 19 decrease until the power demanded by the pod system 21 is reached, at which point the reduction stops.

[0049] When the pod system 21 requires higher power output, the closed-cycle power generation unit 14 and the aviation lithium battery 6 can simultaneously supply power to the aircraft DC bus to achieve a higher peak-to-average power ratio. Specifically, the aviation lithium battery 6 supplies power to the power divider 7, and the first high-speed starter / generator 1 of the closed-cycle power generation unit 14 supplies power to the power divider 7 via AC / DC. At this time, the power divider 7 has a greater capacity to supply power to the aircraft DC bus.

[0050] The working principle of the closed-loop thermoelectric conversion unit is as follows: The hot-end heat exchanger heats the working fluid in the closed loop. The heated working fluid is then expanded by an SCO2 turbine for power conversion. The turbine expansion work simultaneously drives the compressor to compress the working fluid and the generator to generate electricity. After expansion by the SCO2 turbine, the working fluid becomes a low-pressure working fluid, which then enters the hot end of the regenerator to exchange heat with the working fluid gas flow from the compressor outlet, thus recovering energy. The low-pressure working fluid has a significantly reduced temperature after passing through the regenerator, and then enters the cold-end heat exchanger for cooling until it meets the compressor inlet conditions. It is then compressed by the compressor into a high-pressure working fluid flow, with the compressor powered by the turbine rotation. The high-pressure working fluid flow from the compressor outlet absorbs heat from the hot-end low-pressure flow through the cold end of the regenerator. After absorbing heat, the working fluid is in a higher energy state and then enters the hot-end heat exchanger, thus completing a full power cycle.

[0051] Technical advantages:

[0052] 1. In a closed-loop system, the working fluid circulates entirely within the system during the cycle and does not come into contact with the ambient atmospheric pressure. Therefore, it is not affected by environmental pressure and can achieve stable power output at different flight altitudes of the aircraft. In contrast, the output power of a traditional APU decreases significantly with increasing altitude.

[0053] 2. Closed-cycle uses high-pressure supercritical CO2 working fluid for circulation. The density of CO2 working fluid is greatly increased under high pressure. Therefore, the actual physical size of the closed-cycle power generation unit is very small, about 1 / 25 of that of a traditional gas turbine, which plays an important role in the miniaturization of aircraft.

[0054] 3. The compressor compresses the CO2 working fluid near the critical point, at which point the compression work is very small. In a traditional gas turbine, the compression work accounts for about 2 / 3 of the turbine output work, while in a closed-cycle power generation unit, the compressor output work accounts for about 1 / 3 of the turbine output work. Therefore, the closed-cycle power generation unit is very efficient.

[0055] 4. The closed-loop power generation unit recovers and utilizes aircraft waste heat, saving aircraft fuel.

[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.

Claims

1. An energy pod based on supercritical CO2 power generation technology, characterized in that, It includes a closed-loop power generation unit (3), a gas heat exchange unit (18), a power electronics unit (5), and an aviation lithium battery (6). The closed-loop power generation unit (3) is equipped with a closed-loop heat exchange gas path. After the gas in the closed-loop heat exchange gas path obtains the heat provided by the gas heat exchange unit (18), it converts the heat energy into electrical energy and transmits it to the aviation lithium battery (6) and the onboard DC bus through the power electronics unit (5). The gas heat exchange unit (18) is a mechanism that generates heat by burning fuel.

2. The energy pod based on supercritical CO2 power generation technology according to claim 1, characterized in that, The closed-loop power generation unit (3) includes a high-speed starter / generator (1) and an SCO2 power unit (2). The SCO2 power unit (2) includes a heat exchange device, an SCO2 turbine (11), a regenerator (16), a cooling device, an SCO2 compressor (12), and a closed-loop heat exchange gas path. After the gas in the closed-loop heat exchange gas path acquires heat from the heat exchange device, it drives the SCO2 turbine (11) to do work. Then, it enters the hot end of the regenerator (16), and is cooled by the cooling device. After being pressurized by the SCO2 compressor (12), it returns to the heat exchange device through the cold end of the regenerator (16) to complete the cycle. The SCO2 turbine (11) is connected to and drives the high-speed starter / generator (1).

3. The energy pod based on supercritical CO2 power generation technology according to claim 2, characterized in that, The high-speed starter / generator (1), SCO2 turbine (11) and SCO2 compressor (12) are coaxial. During the start-up phase, the high-speed starter / generator (1) acts as a starter to drive the SCO2 compressor (12) to run.

4. The energy pod based on supercritical CO2 power generation technology according to claim 1, characterized in that, The pod device (21) includes an outer wall and an inner wall. The closed-loop power generation unit (3), the gas heat exchange unit (18), the power electronics unit (5) and the aviation lithium battery (6) are installed inside the inner wall of the pod device (21). The pod device (21) has an air inlet at the front end. The air inlet includes a ram cooling air inlet with a large inlet area. The rear end of the ram cooling air inlet contracts between the outer wall and the inner wall to form a ram duct. The cooling device of the closed-loop power generation unit (3) is a ram duct cooler (15) installed in the ram duct.

5. An energy pod based on supercritical CO2 power generation technology according to claim 4, characterized in that, The air inlet also includes a cabin air inlet with a small inlet area located at the center of the ram cooling air inlet. The rear end of the cabin air inlet is expanded to connect to the interior of the inner wall. A power electronics unit (5), a closed-loop power generation unit (3), a gas heat exchange unit (18), and an aviation lithium battery (6) are respectively arranged along the air flow direction.

6. An energy pod based on supercritical CO2 power generation technology according to claim 5, characterized in that, The gas heat exchange unit (18) includes an air compressor (20), a fuel pump (19), a gas turbine (17), a heat exchange burner (10), and a speed-regulating starter / generator (22). The air compressor (20) and the gas turbine (17) are coaxial. The air compressor (20) is driven by the speed-regulating starter / generator (22). Compressed air enters the heat exchange burner (10) and mixes with fuel from the fuel pump (19) for combustion. The high-temperature and high-pressure gas flow after combustion exchanges heat with the closed-loop power generation unit (3) and drives the gas turbine (17) to operate, reducing the power consumption of the speed-regulating starter / generator (22). The heat exchange burner (10) and the heat exchange device of the closed-loop power generation unit (3) are the same device.

7. An energy pod based on supercritical CO2 power generation technology according to claim 5, characterized in that, The power electronics unit (5) includes an AC / DC rectifier (9), a power divider (7), and a system controller (4). The electrical energy generated by the closed-loop power generation unit (3) enters the power divider (7) after passing through the AC / DC rectifier (9). The power divider (7) connects the aviation lithium battery (6) and the DC bus. The system controller (4) collects signals from the closed-loop power generation unit (3), the gas heat exchange unit (18), and the aviation lithium battery (6). The system controller (4) controls the closed-loop power generation unit (3) and the gas heat exchange unit (18).

8. A method for operating an energy pod based on supercritical CO2 power generation technology, wherein when an aircraft needs to expand its energy supply, an energy pod based on supercritical CO2 power generation technology as described in any one of claims 1-7 is installed. During startup, a high-speed starter / generator acts as a starter motor to drive the compressor, causing the gas in the closed-loop heat exchanger circuit to circulate. A variable-speed starter / generator acts as a motor to drive the air compressor, and simultaneously, fuel supply begins, the fuel pump operates, providing compressed air and fuel to the heat exchanger combustion chamber and igniting it. The high-temperature, high-pressure gas generated in the heat exchanger combustion chamber transfers heat to the gas in the closed-loop heat exchanger circuit, which drives the SCO2 turbine. When the SCO2 turbine speed reaches a set value, the high-speed starter / generator switches to power generation mode to provide power to the DC bus and charge the aviation lithium battery.

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