Refrigerant pack for aircraft environmental control system

Abstract

The application discloses a kind of aircraft environmental control system refrigeration package, mainly by first fuel air radiator, mixed radiator, air dynamic pressure bearing turbine cooler, outer ice protection heat shield, clamp and system pipeline etc. First fuel air radiator, mixed radiator are all aluminum alloy plate fin heat exchanger structure, air dynamic pressure bearing turbine cooler is a kind of boost turbine cooler. Second fuel air radiator, regenerator, condenser and high pressure water separator are integrated in mixed radiator, so as not to be installed in each corner of aircraft according to single component dispersion. In the application, first fuel air radiator, mixed radiator and air dynamic pressure bearing turbine cooler are connected by system pipeline, clamp etc., compared with traditional design scheme, weight reduction is at least 20% or more, manufacturing difficulty is reduced, post-maintenance is improved, and space occupation is greatly reduced.

Description

Technical Field

[0001] This invention belongs to the field of aircraft environmental control system technology, specifically relating to a refrigeration package structure, and particularly a highly integrated boost-type refrigeration package structure design. Background Technology

[0002] To meet the requirements for pressure, temperature, humidity, and ventilation within the cabin, an aircraft cabin air conditioning and pressurization system is required, and the refrigeration system is a crucial component. The refrigeration system ensures the cooling of the cabin and equipment compartments, and its form, composition, and operating principle often characterize the air conditioning system. The pressurized air supplied by the cabin pressurizer or engine compressor has very high pressure and temperature, making cabin heating relatively convenient. However, cooling this high-temperature, high-pressure air and maintaining a suitable cabin environment is often more complex.

[0003] Cooling packages are a crucial approach to the integrated and modular design of current and future aircraft environmental control systems. They integrate various previously disassembled components such as radiators and turbines into a single cooling module. During the overall aircraft design, only a certain amount of installation space needs to be reserved on the aircraft to install this cooling module; the corresponding interface on the module connects to the aircraft's environmental control piping. This simplifies the piping layout, minimizes aircraft weight, and facilitates system component management.

[0004] In traditional refrigeration systems, components are scattered throughout the aircraft, resulting in numerous and complex piping systems between components. This not only takes up a lot of space but also increases the weight and manufacturing difficulty, and makes maintenance difficult later on. Summary of the Invention

[0005] This invention aims to provide a refrigeration package for an aircraft environmental control system, which integrates a second fuel-air radiator, a regenerator, a condenser, a high-pressure water separator, etc., into a single hybrid radiator. The air dynamic bearing turbine cooler is arranged in the installation space between the hybrid radiator and the first fuel-air radiator. By using fewer connecting pipes and clamps, the first fuel-air radiator and the hybrid heat exchanger are effectively connected, reducing the number of pipes and clamps in the environmental control system and achieving a weight reduction of at least 20% compared to existing refrigeration systems.

[0006] Statistics on the failure rate of existing refrigeration systems show that turbine coolers account for more than 80% of failures. Therefore, it is necessary to design the turbine cooler in the refrigeration package as a field-replaceable unit to meet the needs of quick disassembly and assembly, and reduce the workload of field troubleshooting.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] Aircraft environmental control system cooling package, including,

[0009] First fuel-air radiator;

[0010] The mixing heat exchanger is mainly composed of a second fuel-air radiator, a regenerator and a condenser. The regenerator is located between the second fuel-air radiator and the condenser. The second fuel-air radiator, the regenerator and the condenser are an integrated structure that shares a heat-side flow channel of a radiator core. The air outlet of the second fuel-air radiator is connected to the inlet of the regenerator. A high-pressure water separator is installed at the inlet of the regenerator.

[0011] An air dynamic pressure bearing turbine cooler, comprising a turbine and a compressor, wherein the inlet of the turbine is fixedly connected to the outlet of the regenerator by a clamp, and the inlet of the compressor is fixedly connected to the air outlet of a first fuel-air radiator by a clamp.

[0012] The system piping has one end fixedly connected to the turbine outlet by a clamp, and the other end fixedly connected to the condenser inlet by a clamp.

[0013] As an alternative, the aircraft environmental control system cooling package also includes an external anti-icing heat shield, which is wrapped around the outer surface of the system piping.

[0014] Furthermore, the external anti-icing and heat insulation cover includes an alumina ceramic inner liner, the outer surface of which is a steel skin, which is riveted to the alumina ceramic inner liner.

[0015] Furthermore, the skin is made of 1Cr18Ni9Ti steel strip rolled into a cross-shaped corrugation, and the cross-shaped corrugation is formed by energy storage spot welds.

[0016] Alternatively, the aircraft environmental control system cooling package also includes the air-to-air heat exchanger, the inlet of which is connected to the compressor outlet in the aerodynamic bearing turbine cooler, and the outlet of which is connected to the air inlet of the second fuel-air radiator.

[0017] Furthermore, the high-pressure water separator is installed inside the inlet gas collection hood of the regenerator.

[0018] Furthermore, the high-pressure water separator includes:

[0019] The water separator housing forms the housing of the regenerator inlet gas collection hood;

[0020] The inner shell of the water separator is located inside the outer shell of the water separator;

[0021] A stationary impeller, which is located in the outer shell of the water separator and positioned at the front end of the inlet of the inner shell of the water separator;

[0022] A water collection tank, which is connected to the housing of the water separator;

[0023] The drain pipe has its inlet connected to the water collection tank and its outlet connected to the vent hole of the air-to-air heat exchanger. It should be noted that the air-to-air heat exchanger here is not part of the refrigeration unit.

[0024] Furthermore, the air dynamic bearing turbine cooler is connected to the radiator core by screws.

[0025] Furthermore, the radiator core is an aluminum plate-fin structure, and the radiator core includes:

[0026] Side plates, the two side plates are arranged in parallel on the two end faces of the radiator core;

[0027] A partition, wherein multiple partitions are arranged in parallel and spaced apart between two side plates;

[0028] The hot edge fins (i.e., shared hot edge fins) and cold edge fins of the mixed radiator are installed on both sides of the same partition.

[0029] A hot edge seal and a cold edge seal for a hybrid radiator, wherein the hot edge seal is disposed on both sides of the hot edge fins of the hybrid radiator, and the cold edge seal is disposed on both sides of the cold edge fins of the hybrid radiator.

[0030] The cold edge fins of the mixed radiator corresponding to the same partition plate include fuel-air radiator fins, regenerator fins and condenser fins, and fuel-air radiator cold edge seals are provided between the fuel-air radiator fins and the regenerator fins, and regenerator seals are provided between the regenerator fins and the condenser fins.

[0031] Furthermore, the first fuel-air radiator and the mixing heat exchanger are arranged in a manner where two straight lines intersect perpendicularly. The air dynamic bearing turbine cooler is placed in the right-angle area formed by the two perpendicularly intersecting straight lines. The outlet axis direction of the first fuel-air radiator, the inlet axis direction of the compressor, the outlet axis direction of the turbine, the outlet axis direction of the regenerator, and the inlet axis direction of the condenser are parallel, wherein the outlet axis direction of the first fuel-air radiator, the inlet axis direction of the compressor, and the outlet axis direction of the turbine are coaxial.

[0032] In the refrigeration package of this invention, the outlet of the first fuel-air heat exchanger and the compressor inlet of the aerodynamic bearing turbine cooler are connected by clamps. After being pressurized by the compressor, the air outlet connects to an external air-to-air heat exchanger via the aircraft's environmental control piping. From the outlet of this heat exchanger, the air returns to the inlet of the mixing radiator, where it exchanges heat with the aircraft fuel. The cold air exiting the mixing radiator enters the high-pressure water separator in the inlet shroud of the regenerator for high-pressure water separation. The cold air then enters the regenerator and exchanges heat with the high-temperature air flowing through the regenerator section of the mixing radiator, thus increasing its temperature. The air exiting the regenerator enters the turbine inlet of the aerodynamic bearing turbine cooler, driving the turbine blades to rotate and generate power, which in turn drives the compressor blades of the turbine cooler to rotate, further pressurizing the air. The low-temperature air exiting the turbine exit enters the condenser through system piping for heating, and finally enters the aircraft cabin from the condenser outlet. To prevent the low-temperature air exiting the turbine from causing icing of the outside humid air on the outer wall of the system piping, an external anti-icing heat insulation cover is wrapped around the outer wall of the system piping.

[0033] The hybrid radiator is a three-core aluminum alloy plate-fin heat exchanger structure. Through the rational combination of side plates, partitions, fuel-air radiator fins, fuel-air radiator cold edge seals, fuel-air radiator cold edge fins, hybrid radiator hot edge seals, regenerator seals, regenerator fins, condenser fins, and hybrid radiator hot edge fins, it achieves heat exchange between fuel and air, heat regeneration between air and air, and condensation between air and air in a single radiator core.

[0034] In the booster-type refrigeration package of the aircraft environmental control system designed in this invention, the hybrid radiator integrates a second fuel-air radiator, a regenerator, and a condenser. The second fuel-air radiator, regenerator, and condenser share a single heat dissipation core, and a high-pressure water separator is equipped in the regenerator inlet shroud. This minimizes the number of connecting pipes and clamps for each radiator, reducing the installation space and system weight of the refrigeration package. Both the first fuel-air radiator and the hybrid radiator employ an aluminum alloy plate-fin heat exchanger structure.

[0035] The inlet gas collection hood of the regenerator is designed with a high-pressure water separator. The stationary impeller inside the high-pressure water separator rotates the humid air entering the water separator along the inner shell of the water separator. The centrifugal force separates the moisture in the humid air and sends it along the outer shell of the water separator into the water collection tank. The water is then discharged into the air-to-air heat exchanger on the aircraft through the drain pipe and the pipeline on the aircraft to participate in heat exchange.

[0036] The air dynamic bearing turbine cooler is a core component of this refrigeration package and also one of the components with a relatively high failure rate. It is effectively connected to the first fuel-air radiator and the hybrid radiator via clamps and system piping. It is designed as a replaceable unit for field use. This design allows for field replacement and maintenance. An external anti-icing heat insulation cover is designed on the turbine cooler's outlet piping to prevent icing caused by low temperatures.

[0037] This invention effectively connects the fuel-air radiator, the hybrid radiator, the aerodynamic bearing turbine cooler, the system piping, and the connecting clamps, minimizing the number of connecting pipes and clamps for each radiator, reducing the installation space of the refrigeration package, and lightening the system weight of the refrigeration package. Furthermore, it designs the components with a high failure rate in the refrigeration package as a field-replaceable unit, reducing the maintenance difficulty of the refrigeration package.

[0038] This invention uses a direct connection between the outlet and inlet clamps, eliminating the need for pipe connections, significantly reducing the amount of pipe used, and thus reducing the system's weight.

[0039] Compared with existing technologies, the booster-type refrigeration package for the aircraft environmental control system of the present invention includes a first fuel-air radiator, a mixing radiator, an aerodynamic bearing turbine cooler, an external anti-icing heat shield, clamps, and system piping. This refrigeration package utilizes the installation space between the mixing radiator and the first fuel-air radiator to arrange the aerodynamic bearing turbine cooler, employing fewer connecting pipes and clamps to effectively connect the first fuel-air radiator and the mixing heat exchanger, reducing the number of pipes and clamps in the environmental control system, and reducing the weight of the refrigeration package by at least 20%. Furthermore, statistical analysis of the failure rate of existing refrigeration packages shows that the turbine cooler accounts for over 80% of failures. The refrigeration package of the present invention designs the turbine cooler as a replaceable unit for field use; turbine installation and removal can be completed simply by tightening and loosening four quick-release clamps and a few mounting screws, reducing the workload of field maintenance. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the refrigeration package structure of the present invention;

[0041] Figure 2 This is a schematic diagram of the hybrid heat sink structure of the present invention;

[0042] Figure 3 Schematic diagram of the working principle of the refrigeration package system of the present invention;

[0043] Figure 4 This is a schematic diagram of the structure of the heat sink core in the hybrid heat sink of the present invention;

[0044] Figure 5 This is a schematic diagram of the high-pressure water separator structure in this invention;

[0045] Figure 6 This is a schematic diagram of the external anti-icing and heat insulation cover structure in this invention;

[0046] Figure 7 for Figure 4 CC section view;

[0047] Figure 8 for Figure 4 Cross-sectional view of the middle section (BB);

[0048] In the diagram, 1-First fuel-air radiator, 2-Mixer radiator, 3-Air dynamic bearing turbine cooler, 4-Clamp, 5-System piping, 6-External anti-icing heat shield, 21-Second fuel-air radiator, 22-Regenerator, 23-Condenser, 211-Radiator core, 221-High-pressure water separator, 21101-Side plate, 21102-Baffle, 21103-Fuel-air radiator fins, 21104-Fuel-air radiator 21105-Hot edge seal of radiator, 21106-Regenerator seal, 21107-Regenerator fins, 21108-Condenser fins, 21109-Hot edge fins of radiator, 22101-Stationary impeller, 22102-Water separator inner shell, 22103-Water separator outer shell, 22104-Water sump, 22105-Drain pipe, 601-Inner liner, 602-Skin, 603-Rivet. Detailed Implementation

[0049] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0050] like Figure 1 As shown, the booster cooling pack of the aircraft environmental control system mainly consists of a first fuel-air radiator 1, a mixing radiator 2, an aerodynamic bearing turbine cooler 3, an external anti-icing heat shield 6, clamps 4, and system piping 5.

[0051] The hybrid radiator 2 integrates a second fuel-air radiator 21, a regenerator 22, and a condenser 23. The heat dissipation core of these three radiators is designed as a single unit, a three-core aluminum alloy plate-fin structure. Through a rational combination of side plates 21101, partitions 21102, fuel-air radiator fins 21103, fuel-air radiator cold edge seals 21104, hybrid radiator hot edge seals 21105, regenerator seals 21106, regenerator fins 21107, condenser fins 21108, and hybrid radiator hot edge fins 21109, the three different heat dissipation technologies of the second fuel-air radiator 21, regenerator 22, and condenser 23 are achieved within a single radiator core 211. After the components of the radiator core 211 are machined, they are assembled according to design requirements and then brazed in a vacuum brazing furnace in a single operation.

[0052] The hybrid radiator 2 has a high-pressure water separator 221 designed at the inlet gas collection hood of the regenerator 22. Inside the water separator are a stationary impeller 22101, an inner shell 22102, an outer shell 22103, a water collection tank 22104, and a drain pipe 22105. The outer shell 22103 of the water separator is also the outer shell of the inlet gas collection hood of the regenerator 22. The high-pressure water separator 221 is welded to the radiator core 211 of the hybrid radiator 2 at the inlet of the regenerator 22 by argon arc welding, forming a regenerator inlet gas collection hood with a water separator.

[0053] The air dynamic bearing turbine cooler 3 is a booster turbine with an air dynamic bearing as its core. The turbine inlet is connected to the outlet of the regenerator 22 in the mixing radiator 2 by a clamp 4. The high-temperature, high-pressure air from the regenerator 22 drives the turbine to rotate, which in turn drives the turbine compressor to do work, converting thermal energy into mechanical energy. The compressor inlet of the air dynamic bearing turbine cooler 3 is connected to the air outlet of the first fuel-air radiator 1 by a clamp 4. The air from the first fuel-air radiator 1 is pressurized by the compressor impeller and used for air-to-air radiators outside this refrigeration package (in this invention). Figure 1 The air-to-air radiator (not shown in the diagram) exchanges heat to further reduce the air temperature. The air dynamic bearing turbine cooler 3 is mounted on the side plate 21101 of the hybrid radiator 2 with screws.

[0054] The turbine outlet of the aerodynamic bearing turbine cooler 3 is calculated to have an air temperature between -80 and -75 degrees Celsius. The outlet air returns to the condenser 23 in the mixing radiator 2 via clamp 4 and system piping 5, where it participates in heat exchange, lowering the air temperature in the mixing radiator 2 and raising the air temperature entering the cabin. Calculations show the final temperature entering the cabin is between -20 and -15 degrees Celsius. To prevent icing of the outside humid air outside the system piping 5 due to the low temperature of the turbine outlet air (-80–-75 degrees Celsius), an external anti-icing heat insulation cover 6 is wrapped around the outer wall of the system piping 5.

[0055] The external anti-icing and heat insulation cover 6 uses a high-performance alumina ceramic inner liner 601. The outer surface of the alumina ceramic inner liner 601 is made of steel strip 1Cr18Ni9Ti-0.1-R-N0.2D-GB4239-91 rolled into a cross-shaped corrugated skin 602, and the intersections are sewn using an energy storage spot welding method. Rivets 603 are riveted to the corresponding dimensions of the skin 602 and are secured to the outer wall of the system pipeline 5 with locking wire to prevent the outer wall of the system pipeline 5 from freezing due to heat exchange with the outside air.

[0056] The connecting clamps 4 consist of two specifications. One set of 3HB8093-50 clamp assembly is used for the compressor inlet of the air dynamic bearing turbine cooler 3 and the first fuel air radiator 1, as well as the turbine inlet and the outlet of the regenerator 22. One set of GJB3821-3-65 clamp is used for the turbine outlet and the inlet of the system pipeline 5, as well as the outlet of the system pipeline 5 and the inlet of the condenser 23. A total of 4 sets are used.

[0057] like Figure 3 The diagram shown is a schematic of the aircraft environmental control booster refrigeration package system described in this invention, wherein the air-to-air radiator is not included. Figure 1 The system is shown in the diagram. It contains two fuel-air radiators (first fuel-air radiator 1 and second fuel-air radiator 21), a regenerator 22, a condenser 23, a high-pressure water separator 221, and an air dynamic bearing turbine cooler 3. System calculations and index allocation are performed iteratively by continuously revising the operating point parameters of each component.

[0058] like Figure 1 The diagram shown is a schematic of the aircraft environmental control booster refrigeration package structure of the present invention. Figure 3 The various components are integrated into a single design, forming a primary fuel-air radiator 1, a hybrid radiator 2, an aerodynamic bearing turbine cooler 3, an external anti-icing heat shield 6, four sets of clamps 4, and a system piping system 5. Through effective connection, the system completes... Figure 3The functions of each component are integrated into a single hybrid radiator 2, comprising the second fuel-air radiator 21, the regenerator 22, the condenser 23, and the high-pressure water separator 221 in the system design.

[0059] like Figure 4 , Figure 7 and Figure 8 The diagram shows the structure of the radiator core 211 of the hybrid radiator 2 in the aircraft environmental control booster refrigeration package of the present invention. The radiator core 211 is an aluminum alloy plate-fin radiator core structure. Through the reasonable arrangement of the side plate 21101, partition 21102, fuel-air radiator fins 21103, fuel-air radiator cold edge seal 21104, hybrid radiator hot edge seal 21105, regenerator seal 21106, regenerator fins 21107, condenser fins 21108, and hybrid radiator hot edge fins 21109, the fuel-air radiator 21, regenerator 22, and condenser 23 share a common core. The core assembly, including side plate 21101, partition plate 21102, hot edge seal of the mixing radiator 21105, and hot edge fins of the mixing radiator 21109, is shared by the three heat exchangers: the second fuel-air radiator 21, the regenerator 22, and the condenser 23. The remaining components—fuel-air radiator fins 21103, cold edge seal of the fuel-air radiator 21104, regenerator seal 21106, regenerator fins 21107, and condenser fins 21108—are designed with corresponding dimensions based on performance calculations for the three heat exchangers, but it is necessary to ensure consistent fin wave heights. For example… Figure 4 The 21103 fuel-air radiator fins of the Chinese fuel oil radiator adopt a dual-flow design.

[0060] like Figure 4 The diagram shown is a structural schematic of the high-pressure water separator 221 in an aircraft environmental control booster refrigeration package according to the present invention. Figure 3 In terms of system principle, the high-pressure water separator 221 needs to be arranged between the hot air outlet of the condenser 23 and the inlet of the regenerator 22, which can form a single accessory. This invention directly integrates the high-pressure water separator 221 with the regenerator 22, designing the water separator shell 22103 of the high-pressure water separator 221 as part of the inlet gas collection hood of the regenerator 22. This component includes a stationary impeller 22101, a water separator inner shell 22102, a water collection tank 22104, and... The drain pipe 22105 allows humid air to pass through the stationary impeller, forming a high-speed rotation of the humid air on the inner shell 22102 of the water separator. Under the action of centrifugal force, the water in the humid air is separated and flows into the water collection tank 22104 through the gap between the inner shell 22102 and the outer shell 22103 of the water separator. The water is then discharged through the drain pipe 22105 on the water collection tank 22104 into the air-to-air radiator's pressurized air vent, participating in the heat exchange of the air-to-air radiator. Figure 3 The air-to-air radiator is shown in the image.

[0061] like Figure 5 The diagram shows the structure of the external anti-icing heat insulation cover 6 wrapped around the system piping 5 in the aircraft environmental control booster refrigeration package of the present invention. The system piping 5 connects the turbine outlet and the condenser 23 inlet. The turbine outlet air temperature is calculated to be between -80 and -75 degrees Celsius. To prevent the outside humid air from freezing on the outer wall of the system piping 5 due to the low temperature of the turbine outlet air (-80 to -75 degrees Celsius), an external anti-icing heat insulation cover 6 is wrapped around the outer wall of the system piping 5. The external anti-icing heat insulation cover 6 uses a high-performance alumina ceramic inner liner 601 and an outer skin 602 made of steel strip 1Cr18Ni9Ti-0.1-R-N0.2D-GB4239-91 rolled into a cross-shaped corrugated pattern, and is sewn using an energy storage spot welding method. Rivets 603 are riveted to the corresponding dimensions of the skin 602 and are secured to the outer wall of the system pipe 5 with locking wire to prevent the outer wall of the system pipe 5 from exchanging heat with the outside air and thus preventing the outer wall from freezing.

[0062] Through the above technical solution, the six functional components in the principle of the aircraft environmental control booster cooling package system are effectively integrated to form three major accessories: the first fuel-air radiator 1, the hybrid radiator 2, and the aerodynamic bearing turbine cooler 3, which reduces the difficulty of scientific research and management.

[0063] The three major accessories are connected by clamps 4, system piping 5, and an external anti-icing and heat insulation cover 6. The air dynamic bearing turbine cooler 3 is mounted on the side plate 21101 of the hybrid radiator 2 with four screws. The compressor is connected to the first fuel-air radiator 1 via clamps 4, and the turbine outlet is connected to the system piping 5 via clamps 4. The design fully considers the high failure rate of the air dynamic bearing turbine cooler 3, making it a replaceable unit for the field. Turbine assembly and disassembly can be completed simply by tightening and loosening the connecting bolts and clamps 4, reducing the intensity of daily maintenance. The integration of the hybrid radiator 2 reduces the number of covers, piping, and clamps for the second fuel-air radiator 21, regenerator 22, and condenser 23, achieving a system weight reduction of over 20% on the existing basis.

[0064] The above embodiments are not intended to limit the scope of protection of the present invention. Any modifications, alterations or equivalent substitutions made based on the technical solutions of the present invention shall fall within the scope of protection of the present invention.

Claims

1. A cooling package for an aircraft environmental control system, characterized in that: include, First fuel-air radiator (1); The mixing heat exchanger (2) is mainly composed of a second fuel air radiator (21), a regenerator (22) and a condenser (23). The regenerator (22) is located between the second fuel air radiator (21) and the condenser (23). The second fuel air radiator (21), the regenerator (22) and the condenser (23) are an integrated structure sharing a heat flow channel of a radiator core (211). The air outlet of the second fuel air radiator (21) is connected to the inlet of the regenerator (22). A high-pressure water separator (221) is installed at the inlet of the regenerator (22). Air dynamic bearing turbine cooler (3), the air dynamic bearing turbine cooler (3) includes a turbine and a compressor, wherein the inlet of the turbine is fixedly connected to the outlet of the regenerator (22) by a clamp (4), and the inlet of the compressor is fixedly connected to the air outlet of the first fuel air radiator (1) by a clamp (4). System pipeline (5), one end of which is fixedly connected to the outlet of the turbine by a clamp (4), and the other end of which is fixedly connected to the inlet of the condenser (23) by a clamp (4); The radiator core (211) is an aluminum plate-fin structure, and the radiator core (211) includes: Side plates (21101), the two side plates (21101) are arranged in parallel on the two end faces of the radiator core (211); A partition (21102), wherein multiple partitions (21102) are arranged in parallel and spaced apart between two side plates (21101); The hot edge fins (21109) and cold edge fins of the mixed radiator are respectively installed on both sides of the same partition plate (21102). The hot edge seal (21105) and cold edge seal of the mixed radiator are provided on both sides of the hot edge fins (21109) of the mixed radiator. The cold edge fins of the mixed radiator corresponding to the same partition (21102) include fuel-air radiator fins (21103), regenerator fins (21107) and condenser fins (21108), and a fuel-air radiator cold edge seal (21104) is provided between the fuel-air radiator fins (21103) and the regenerator fins (21107), and a regenerator seal (21106) is provided between the regenerator fins (21107) and the condenser fins (21108).

2. The aircraft environmental control system cooling package according to claim 1, characterized in that: It also includes an external anti-icing and heat insulation cover (6), which is wrapped around the outer surface of the system pipeline (5).

3. The aircraft environmental control system cooling package according to claim 2, characterized in that: The external anti-icing and heat insulation cover (6) includes an alumina ceramic inner liner (601), the outer surface of which is a steel skin (602), and the skin (602) is riveted to the alumina ceramic inner liner (601).

4. The aircraft environmental control system cooling package according to claim 3, characterized in that: The skin (602) is made of 1Cr18Ni9Ti steel strip rolled into a cross-shaped corrugated pattern, and the cross is formed by energy storage spot welds.

5. The aircraft environmental control system cooling package according to claim 1, characterized in that: It also includes an air-to-air heat exchanger, the inlet of which is connected to the compressor outlet of the air dynamic bearing turbine cooler (3), and the outlet of which is connected to the air inlet of the second fuel air radiator (21).

6. The aircraft environmental control system cooling package according to claim 1, characterized in that: The high-pressure water separator (221) is installed inside the inlet gas collection hood of the regenerator (11).

7. The aircraft environmental control system cooling package according to claim 1, characterized in that: The high-pressure water separator (221) includes: The water separator housing (22103) forms the housing of the inlet gas collection hood of the regenerator (22); The water separator inner shell (22102) is located inside the water separator outer shell (22103); A stationary impeller (22101) is located in the outer shell (22103) of the water separator and is positioned at the inlet front end of the inner shell (22102) of the water separator; A water collection tank (22104) is connected to the housing (22103) of the water separator; The drain pipe (22105) has its inlet connected to the water sump (22104) and its outlet connected to the pressurized air vent of the air-to-air heat exchanger.

8. The aircraft environmental control system cooling package according to claim 1, characterized in that: The air dynamic bearing turbine cooler (3) is connected to the radiator core (211) by screws.

9. The aircraft environmental control system cooling package according to claim 1, characterized in that: The first fuel-air radiator (1) and the mixing heat exchanger (2) are arranged in a manner where two straight lines intersect perpendicularly. The air dynamic bearing turbine cooler (3) is placed in the right-angle area formed by the two perpendicularly intersecting straight lines. The outlet axis direction of the first fuel-air radiator (1), the inlet axis direction of the compressor, the outlet axis direction of the turbine, the outlet axis direction of the regenerator (22), and the inlet axis direction of the condenser (23) are parallel. The outlet axis direction of the first fuel-air radiator (1), the inlet axis direction of the compressor, and the outlet axis direction of the turbine are coaxial.

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