An integrated thermal management system for an aircraft based on a loop heat pipe

Abstract

The application discloses an airplane integrated thermal management system based on a loop heat pipe. A low-temperature liquid cooling loop is connected with a high-temperature liquid cooling loop through the loop heat pipe; the loop heat pipe comprises an evaporator (06), a capillary core is arranged in the evaporator (06), a cold edge outlet of the evaporator (06) is connected with a hot edge inlet of a condenser (08) through a gas transmission pipeline, a hot edge outlet of the condenser (08) is connected with a liquid reservoir (07), and the liquid reservoir (07) is connected with a cold edge inlet of the evaporator (06); a hot edge outlet and a hot edge inlet of the evaporator (06) are connected with the low-temperature liquid cooling loop, and a cold edge outlet and a cold edge inlet of the condenser (08) are connected with the high-temperature liquid cooling loop. The application effectively improves energy utilization.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to an integrated thermal management system for aircraft based on loop heat pipes. Background Technology

[0002] As aircraft performance improves, airborne electromechanical systems generate more heat, presenting both new opportunities and challenges for aircraft thermal management technology. Traditional thermal management systems suffer from low efficiency, heavy weight, and poor reliability. Loop heat pipes, as a highly efficient heat transfer technology, have already been applied in the aerospace field. However, in integrated aircraft thermal management systems, effectively integrating loop heat pipe technology (LHP) with the aircraft's various thermal requirements to achieve efficient, lightweight, and reliable thermal management remains a pressing issue. Existing technological solutions still have significant room for improvement in terms of integration, intelligence, and energy efficiency. Summary of the Invention

[0003] The purpose of this invention is to provide an integrated thermal management system for aircraft based on loop heat pipes. This invention effectively improves energy utilization.

[0004] Technical Solution: An integrated thermal management system for aircraft based on a loop heat pipe includes a cryogenic liquid cooling loop connected to a high-temperature liquid cooling loop via a loop heat pipe. The loop heat pipe includes an evaporator with a capillary wick inside. The cold-side outlet of the evaporator is connected to the hot-side inlet of a condenser via a gas transmission pipeline. The hot-side outlet of the condenser is connected to a liquid receiver, and the liquid receiver is connected to the cold-side inlet of the evaporator. The hot-side outlet and inlet of the evaporator are connected to the cryogenic liquid cooling loop, and the cold-side outlet and inlet of the condenser are connected to the high-temperature liquid cooling loop.

[0005] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the cryogenic liquid cooling loop includes a heat source component, which is connected in series with the cryogenic liquid cooling loop pump unit and then connected in series between the hot side inlet and outlet of the evaporator.

[0006] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the heat source components include a recirculating air heat exchanger and a galley cold plate connected in parallel; the recirculating air heat exchanger is used to cool the recirculated air in the aircraft cabin; the galley cold plate is used to provide refrigerant for the aircraft's galley catering cart.

[0007] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the recirculating air heat exchanger and the galley cold plate are respectively connected in series with a first flow regulating valve and a second flow regulating valve.

[0008] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the high-temperature liquid cooling loop includes a high-power controller cold plate assembly, a high-temperature liquid cooling loop pump set, and a cold source assembly; the high-power controller cold plate assembly is connected in parallel with the cold side of the condenser and then connected in series with the cold source assembly and the high-temperature liquid cooling loop pump set; the outlet of the cold source assembly is connected to the cold side inlet of the condenser and the inlet of the high-power controller cold plate assembly via the high-temperature liquid cooling loop pump set; the cold side outlet of the condenser and the outlet of the high-power controller cold plate assembly are connected to the inlet of the cold source assembly.

[0009] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the cold source components include a skin heat exchanger and a fan duct heat exchanger connected in parallel; the skin heat exchanger is arranged in the anti-icing area of ​​the aircraft wing to transfer the heat of the integrated thermal management system to the outer surface of the skin; the fan duct heat exchanger is arranged in the fan duct of the aircraft engine to transfer the heat of the integrated thermal management system to the fan duct air.

[0010] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the skin heat exchanger and the fan duct heat exchanger are connected in series with the wing anti-icing heating valve and the sixth flow regulating valve, respectively.

[0011] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the high-power controller cold plate assembly includes a first high-power controller cold plate and a second high-power controller cold plate connected in parallel; the first high-power controller cold plate and the second high-power controller cold plate are used to dissipate heat from the high-power equipment controllers of the aircraft.

[0012] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, the first high-power controller cold plate and the second high-power controller cold plate are respectively connected in series with the fourth flow regulating valve and the fifth flow regulating valve.

[0013] In the aforementioned integrated thermal management system for aircraft based on loop heat pipes, both the cryogenic liquid-cooled loop pump unit and the high-temperature liquid-cooled loop pump unit are designed with dual backups.

[0014] The present invention has achieved the following beneficial effects:

[0015] 1. The advantages of this invention, which uses a loop heat pipe instead of the traditional evaporative cooling cycle, are that it has high heat transfer efficiency, no moving mechanical parts, and no additional energy consumption; it has a compact structure, flexible design, and long transmission distance, which can better adapt to the airborne space and facilitate integration with aircraft components, making the layout of the aircraft's integrated thermal management system more flexible and convenient.

[0016] 2. Compared with traditional evaporative cooling, the loop heat pipe used in this invention has a simpler structure, higher reliability, and lighter weight. By reducing components such as compressors, compressor controllers, and expansion valves, the total weight reduction of the two integrated thermal management systems on the left and right sides of the aircraft can reach about 52 kg.

[0017] 3. This invention uses a loop heat pipe to transfer airborne waste heat from recirculated air, kitchen carts, high-power equipment controllers, etc., to the anti-icing area of ​​the aircraft wing skin and the fan duct. Compared with traditional engine bleed air anti-icing or electrothermal anti-icing, it significantly improves energy utilization.

[0018] 4. This invention uses the air in the aircraft's anti-icing area skin and fan duct as a heat sink, instead of the traditional ram air, which improves energy utilization and reduces fuel consumption and aerodynamic drag. Attached Figure Description

[0019] Figure 1 A schematic diagram of the structure of an aircraft integrated thermal management system based on a loop heat pipe provided by the present invention;

[0020] Among them: 01-Recirculating air heat exchanger, 02-Kitchen cold plate, 03-First flow regulating valve, 04-Second flow regulating valve, 05-Low temperature liquid cooling circuit pump set, 06-Evaporator, 07-Liquid receiver, 08-Condenser, 09-Third flow regulating valve, 10-First high-power controller cold plate, 11-Second high-power controller cold plate, 12-Fourth flow regulating valve, 13-Fifth flow regulating valve, 14-High temperature liquid cooling circuit pump set, 15-Skin heat exchanger, 16-Fan duct heat exchanger, 17-Wing anti-icing heating valve, 18-Sixth flow regulating valve. Detailed Implementation

[0021] Example 1. See also Figure 1 An integrated thermal management system for aircraft based on a loop heat pipe includes a recirculating air heat exchanger 01, a galley cold plate 02, a first flow regulating valve 03, a second flow regulating valve 04, a cryogenic liquid cooling loop pump set 05, an evaporator 06, a liquid receiver 07, a condenser 08, a third flow regulating valve 09, a first high-power controller cold plate 10, a second high-power controller cold plate 11, a fourth flow regulating valve 12, a fifth flow regulating valve 13, a high-temperature liquid cooling loop pump set 14, a skin heat exchanger 15, a fan duct heat exchanger 16, a wing anti-icing heating valve 17, and a sixth flow regulating valve 18, wherein:

[0022] It should be noted that the loop heat pipe includes an evaporator 06, a capillary wick, a liquid receiver 07, a condenser 08, and transmission lines. The evaporator 06 is thermally coupled with the low-temperature liquid cooling circuit to obtain heat. The internal fluid working medium is heated and evaporated. The generated vapor reaches the condenser 08 through the gas transmission line. The condenser 08 is thermally coupled with the high-temperature liquid cooling circuit. The internal vapor condenses and releases heat under the cooling effect of the heat sink. The condensate flows back to the liquid receiver 07 through the liquid transmission line under the action of capillary force. The liquid receiver 07 continuously supplies liquid to the evaporator 06, thereby completing the circulation of the fluid working medium and the transfer of heat.

[0023] It should be noted that the capillary wick is only arranged inside the evaporator 06, and the transmission pipeline and condenser 08 are both flexible tubes with smooth walls.

[0024] It should be noted that the cryogenic liquid cooling circuit includes a recirculating air heat exchanger 01, a kitchen cold plate 02, a first flow regulating valve 03, a second flow regulating valve 04, a cryogenic liquid cooling circuit pump set 05, and liquid cooling pipelines.

[0025] It should be noted that the high-temperature liquid cooling circuit includes the third flow regulating valve 09, the first high-power controller cold plate 10, the second high-power controller cold plate 11, the fourth flow regulating valve 12, the fifth flow regulating valve 13, the high-temperature liquid cooling circuit pump group 14, the skin heat exchanger 15, the fan duct heat exchanger 16, the wing anti-icing heating valve 17, the sixth flow regulating valve 18, and the liquid cooling pipeline.

[0026] Furthermore, the recirculated air heat exchanger 01 cools the recirculated air in the aircraft cabin to ensure the overall cooling capacity of the aircraft's environmental control system.

[0027] Furthermore, the kitchen cooling plate 02 provides refrigerant at the appropriate temperature for the aircraft's kitchen cart.

[0028] Furthermore, the opening degrees of the first flow regulating valve 03, the second flow regulating valve 04, the third flow regulating valve 09, the fourth flow regulating valve 12, the fifth flow regulating valve 13, and the sixth flow regulating valve 18 are adjusted based on the temperature feedback of the object being cooled.

[0029] Furthermore, both the cryogenic liquid-cooled circuit pump unit 05 and the high-temperature liquid-cooled circuit pump unit 14 consist of two pumps, one of which is a standby pump.

[0030] Furthermore, evaporator 06 is a flat-plate evaporator, using stainless steel as the evaporator shell material.

[0031] Furthermore, the receiver 07 acts as a liquid reservoir for the loop, accommodating excess liquid flowing from the transmission lines and condenser 08 during the LHP startup process of the loop heat pipe. In addition, the receiver provides sufficient liquid to the capillary wick as needed to ensure its wettability. The housing of receiver 07 is made of stainless steel.

[0032] Furthermore, condenser 08 is a shell-and-tube heat exchanger, with coolant flowing through the shell to complete heat exchange. The shell of condenser 08 is made of copper coil with an inner diameter of 2mm and a wall thickness of 0.5mm.

[0033] It should be noted that, to accommodate the confined airborne space, smooth, flexible circular pipes are generally selected for the gas-liquid transmission lines, and the length of the lines is determined by the distance between the heat source and the cold source. The gas-liquid transmission lines and the condenser 08 are made of the same material and have the same pipe diameter, which helps to achieve the integrity of the circuit.

[0034] Furthermore, the first high-power controller cold plate 10 and the second high-power controller cold plate 11 dissipate heat for the aircraft's high-power equipment controllers, and finally dissipate the heat to the aircraft skin or engine fan duct through the skin heat exchanger 15 or the fan duct heat exchanger 16.

[0035] Furthermore, the skin heat exchanger 15 is arranged in the anti-icing area of ​​the aircraft wing to transfer heat from the integrated thermal management system to the outer surface of the skin, achieving the dual purpose of airborne waste heat dissipation and anti-icing.

[0036] Furthermore, the fan duct heat exchanger 16 is arranged in the fan duct of the aircraft engine to transfer heat from the integrated thermal management system to the fan duct air, thereby improving energy utilization.

[0037] Furthermore, the wing anti-icing heating valve 17 is adjusted to connect or disconnect the skin heat exchanger 15, thereby enabling the on / off functionality of the wing anti-icing system. When anti-icing is required in the wing anti-icing area, the wing anti-icing heating valve 17 is opened, and the heat from the integrated thermal management system is transferred to the leading edge of the aircraft wing through the skin heat exchanger 15, thus achieving anti-icing. When anti-icing is not required in the wing anti-icing area, the wing anti-icing heating valve 17 is closed, and the heat from the integrated thermal management system is transferred to the fan duct air through the fan duct heat exchanger 16.

[0038] In summary, this invention provides an integrated aircraft thermal management system based on a loop heat pipe (LHP), comprising a loop heat pipe (LHP), a cryogenic liquid cooling loop, and a high-temperature liquid cooling loop. The loop heat pipe includes an evaporator 06, a capillary wick, a reservoir 07, a condenser 08, and transfer lines. The evaporator 06 is thermally coupled to the cryogenic liquid cooling loop, acquiring heat from the recirculated air heat exchanger 01 and the galley cooling plate 02 to cool the recirculated air and galley cart. The condenser 08 is thermally coupled to the high-temperature liquid cooling loop, transferring heat from the high-power device controller and the loop heat pipe to the aircraft skin or engine fan duct via the skin heat exchanger 15 and the fan duct heat exchanger 16. By effectively combining loop heat pipe technology with the various thermal requirements of the aircraft, efficient, lightweight, and reliable thermal management is achieved. Utilizing onboard waste heat for wing leading-edge anti-icing and employing fan duct air as a heat sink effectively improves energy utilization.

[0039] 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 integrated thermal management system for aircraft based on loop heat pipes, characterized in that, It includes a cryogenic liquid cooling circuit, which is connected to a high-temperature liquid cooling circuit via a loop heat pipe; the loop heat pipe includes an evaporator with a capillary wick inside; the cold-side outlet of the evaporator is connected to the hot-side inlet of the condenser via a gas transmission pipeline; the hot-side outlet of the condenser is connected to a liquid receiver; and the liquid receiver is connected to the cold-side inlet of the evaporator; the hot-side outlet and inlet of the evaporator are connected to the cryogenic liquid cooling circuit, and the cold-side outlet and inlet of the condenser are connected to the high-temperature liquid cooling circuit.

2. The aircraft integrated thermal management system based on loop heat pipes according to claim 1, characterized in that, The cryogenic liquid cooling circuit includes a heat source component, which is connected in series with the cryogenic liquid cooling circuit pump set and then connected in series together between the hot side inlet and outlet of the evaporator.

3. The aircraft integrated thermal management system based on loop heat pipes according to claim 2, characterized in that, The heat source components include a recirculating air heat exchanger and a galley cold plate connected in parallel; the recirculating air heat exchanger is used to cool the recirculated air in the aircraft cabin; the galley cold plate is used to provide refrigerant for the aircraft's galley catering cart.

4. The integrated aircraft thermal management system based on loop heat pipes according to claim 3, characterized in that, The recirculating air heat exchanger and the kitchen cold plate are connected in series with a first flow regulating valve and a second flow regulating valve, respectively.

5. The integrated aircraft thermal management system based on loop heat pipes according to claim 1, characterized in that, The high-temperature liquid cooling circuit includes a high-power controller cold plate assembly, a high-temperature liquid cooling circuit pump set, and a cold source assembly; the high-power controller cold plate assembly is connected in parallel with the cold side of the condenser and then connected in series with the cold source assembly and the high-temperature liquid cooling circuit pump set; the outlet of the cold source assembly is connected to the cold side inlet of the condenser and the inlet of the high-power controller cold plate assembly via the high-temperature liquid cooling circuit pump set; the cold side outlet of the condenser and the outlet of the high-power controller cold plate assembly are connected to the inlet of the cold source assembly.

6. The integrated aircraft thermal management system based on loop heat pipes according to claim 5, characterized in that, The cold source components include a skin heat exchanger and a fan duct heat exchanger connected in parallel; the skin heat exchanger is arranged in the anti-icing area of ​​the aircraft wing to transfer heat from the integrated thermal management system to the outer surface of the skin; the fan duct heat exchanger is arranged in the fan duct of the aircraft engine to transfer heat from the integrated thermal management system to the fan duct air.

7. The integrated aircraft thermal management system based on loop heat pipes according to claim 6, characterized in that, The skin heat exchanger and the fan duct heat exchanger are connected in series with an airfoil anti-icing heating valve and a sixth flow regulating valve, respectively.

8. The integrated aircraft thermal management system based on loop heat pipes according to claim 5, characterized in that, The high-power controller cold plate assembly includes a first high-power controller cold plate and a second high-power controller cold plate connected in parallel; the first high-power controller cold plate and the second high-power controller cold plate are used to dissipate heat from the high-power equipment controller of the aircraft.

9. The integrated aircraft thermal management system based on loop heat pipes according to claim 8, characterized in that, The first and second high-power controller cold plates are connected in series with the fourth and fifth flow regulating valves, respectively.

10. The integrated aircraft thermal management system based on loop heat pipes according to claim 2 or 5, characterized in that, Both the cryogenic liquid-cooled circuit pump set and the high-temperature liquid-cooled circuit pump set are designed with dual backups.

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