Pre-cooling heat exchange device and aircraft

Abstract

The invention belongs to the technical field of aviation aircrafts, and particularly relates to a pre-cooling heat exchange device and an aircraft. The device comprises a base and a plurality of rotating modules, wherein a fixing piece is arranged in the transverse axis direction of the base; each rotating module comprises a supporting outer ring, a supporting inner ring and a plurality of pre-cooling heat exchange pieces arranged between the supporting outer ring and the supporting inner ring, the supporting inner ring is arranged on the fixing piece in a sleeving mode, and the width of the section, in the radial direction of the supporting inner ring, of each pre-cooling heat exchange piece is smaller than the distance between every two adjacent pre-cooling heat exchange pieces; a fluid channel is arranged in the supporting outer ring, the supporting inner ring and the pre-cooling heat exchange piece, an opening for cooling fluid to flow in and / or flow out is formed in the supporting outer ring, and the opening is communicated with the fluid channel; when the pre-cooling heat exchange device is in an initial mode, the included angle between the corresponding single pre-cooling heat exchange pieces in every two adjacent rotating modules is 0 degree. The supporting outer ring is driven by external force to rotate so as to drive the pre-cooling heat exchange piece to rotate, and the pre-cooling heat exchange device is adjusted to be in different modes from the initial mode. Therefore, the device is simple in structure, the heat exchange mode can be matched with the flight speed with low machining cost, and the pressure loss can be close to zero.

Description

Technical Field

[0001] The present application relates to the technical field of aviation aircraft, and in particular to a pre-cooling heat exchange device and an aircraft. Background Art

[0002] The high-speed development of aircraft has extremely important military and civilian applications. However, the aerodynamic heating effect usually limits the flight limit of the aircraft engine to Mach number 2.5. To further increase the flight speed of the engine, the main solution is to use a pre-cooling heat exchanger structure to cool the ram air intake. The reduction in the engine's inlet air temperature can offset the increase in intake air temperature caused by the aerodynamic heating effect during high-speed flight, allowing the engine to fly at higher speeds. Although the pre-cooling heat exchanger structure can reduce the intake air temperature, it also increases the flow resistance. During low-speed flight, the heat exchanger is sensitive to flow losses, and lower flow losses and smaller heat transfer effects are required to meet the desired requirements. However, during high-speed flight, it is not sensitive to flow losses, and a pre-cooling heat exchanger with a larger heat transfer effect is required.

[0003] In the related art, if an additional pre-cooling heat exchanger structure is arranged in the engine flow channel to adapt to different flight speeds, it will not only increase the complexity of the structure and the processing cost, but also still have a certain pressure loss during use. Summary of the Invention

[0004] In view of the above problems, the present application is proposed. The present application provides a pre-cooling heat exchange device and an aircraft.

[0005] According to one aspect of the present application, a pre-cooling heat exchange device is provided, which is applied to an engine. The pre-cooling heat exchange device includes:

[0006] A base and multiple rotating modules, wherein a fixing member is provided in the transverse direction of the base; a single rotating module includes a supporting outer ring, a supporting inner ring, and multiple pre-cooling heat exchange members disposed between the supporting outer ring and the supporting inner ring, the supporting inner ring being sleeved on the fixing member, the width of a cross section of a single pre-cooling heat exchange member in the radial direction of the supporting inner ring being smaller than the distance between two adjacent pre-cooling heat exchange members; a fluid channel is provided in the supporting outer ring, the supporting inner ring, and the pre-cooling heat exchange member, and an opening is provided on the supporting outer ring for inflow and / or outflow of cooling fluid, the opening being connected to the fluid channel;

[0007] When the pre-cooling heat exchange device is in the initial mode, the angle between the corresponding single pre-cooling heat exchange elements in two adjacent rotating modules is 0°;

[0008] The supporting outer ring rotates under the driving force of an external force to drive the pre-cooling heat exchange component to rotate, so that the pre-cooling heat exchange device is adjusted from an initial mode to a different mode.

[0009] Compared to the prior art, the precooling and heat exchange device provided in this application includes a base and multiple rotating modules, with a fixed member disposed along the base's transverse axis. Each rotating module comprises an outer support ring, an inner support ring, and multiple precooling and heat exchange components disposed between the outer and inner support rings. The inner support ring is sleeved onto the fixed member, and the width of a single precooling and heat exchange component in the radial direction of the inner support ring is less than the distance between two adjacent precooling and heat exchange components. Fluid channels are defined within the outer support ring, the inner support ring, and the precooling and heat exchange components. The outer support ring has openings for the inflow and / or outflow of cooling fluid, which are connected to the fluid channels.

[0010] Therefore, the cooling fluid can flow into the fluid channel through the openings in the support outer ring and flow within the pre-cooling heat exchanger, thereby exchanging heat with the airflow from the engine's air intake. After the heat exchange is complete, the cooling fluid is discharged from the openings through the fluid channel. If the engine's flight speed is low, the pre-cooling heat exchanger can be maintained in its initial mode. During this process, the contact area between the individual pre-cooling heat exchanger elements and the airflow is minimized, ensuring engine thrust with minimal flow resistance and minimizing pressure loss. As the flight speed gradually increases, the support outer ring can be driven by an external force to rotate, driving the pre-cooling heat exchanger elements connected to the support outer ring to rotate accordingly, allowing the pre-cooling heat exchanger to adjust from the initial mode to a different mode. During this process, the angle between the corresponding individual pre-cooling heat exchanger elements in two adjacent rotating modules gradually increases, and the contact area between the individual pre-cooling heat exchanger elements and the airflow gradually increases, thereby gradually improving the heat exchange capacity of the pre-cooling heat exchanger, thereby reducing the intake air temperature and offsetting the aerodynamic heating effect.

[0011] It can be seen that the pre-cooling heat exchange device provided in the present application has a simple structure, can adapt the heat exchange mode to the flight speed at a relatively low processing cost, and can make the pressure loss close to 0.

[0012] According to another aspect of the present application, an aircraft is provided, comprising the above-mentioned pre-cooling heat exchange device.

[0013] Compared with the prior art, the beneficial effects of the aircraft provided by the present application are the same as those of the above-mentioned pre-cooling heat exchange device, and will not be described in detail here.

[0014] It is to be understood that both the foregoing general description and the following detailed description are exemplary, and are intended to provide further explanation of the technology as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The above and other purposes, features, and advantages of the present application will become more apparent through a more detailed description of the embodiments of the present application in conjunction with the accompanying drawings. The accompanying drawings are intended to provide a further understanding of the embodiments of the present application and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the present application and do not constitute a limitation of the present application. In the drawings, the same reference numerals generally represent the same components or steps.

[0016] Figure 1 A schematic structural diagram of a pre-cooling heat exchange device according to an embodiment of the present application is shown;

[0017] Figure 2 A schematic structural diagram of a rotation module according to an embodiment of the present application is shown;

[0018] Figure 3 A schematic diagram showing the structure of the pre-cooling heat exchange device of an embodiment of the present application in an intermediate mode is shown;

[0019] Figure 4 A schematic structural diagram of the pre-cooling heat exchange device of an embodiment of the present application when in the final mode is shown.

[0020] Reference numerals:

[0021] 100 - base; 200 - rotating module; 201 - supporting outer ring; 2011 - opening; 202 - supporting inner ring; 203 - pre-cooling heat exchange component; and 204 - fluid transmission pipeline. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solutions and advantages of this application more apparent, the following exemplary embodiments of this application will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of this application, rather than all the embodiments of this application, and it should be understood that this application is not limited to the exemplary embodiments described herein.

[0023] The high-speed development of aircraft has extremely important military and civilian applications. However, the aerodynamic heating effect usually limits the flight limit of the aircraft engine to Mach number 2.5. To further increase the flight speed of the engine, the main solution is to use a pre-cooling heat exchanger structure to cool the ram air intake. The reduction in the engine's inlet air temperature can offset the increase in intake air temperature caused by the aerodynamic heating effect during high-speed flight, allowing the engine to fly at higher speeds. Although the pre-cooling heat exchanger structure can reduce the intake air temperature, it also increases the flow resistance. During low-speed flight, the heat exchanger is sensitive to flow losses, and lower flow losses and smaller heat transfer effects are required to meet the desired requirements. However, during high-speed flight, it is not sensitive to flow losses, and a pre-cooling heat exchanger with a larger heat transfer effect is required.

[0024] In the related art, if an additional pre-cooling heat exchanger structure is arranged in the engine flow channel to adapt to different flight speeds, it will not only increase the complexity of the structure and the processing cost, but also still have a certain pressure loss during use.

[0025] In response to the above problems, the present application provides a pre-cooling heat exchange device, which has a simple structure, can adapt to different flight speeds at a lower processing cost, and can minimize pressure loss. Figure 1 The schematic diagram of the structure of the pre-cooling heat exchange device of the embodiment of the present application is shown. Figure 1 The intermediate precooling heat exchange device is in the initial mode. Figure 2 FIG. 1 shows a schematic diagram of the structure of the rotation module according to an embodiment of the present application. Figure 1 and Figure 2 As shown, the pre-cooling heat exchange device includes a base 100 and a plurality of rotating modules 200. A fixed part is provided in the horizontal axis direction of the base 100. A single rotating module 200 includes a supporting outer ring 201, a supporting inner ring 202 and a plurality of pre-cooling heat exchange parts 203 arranged between the supporting outer ring 201 and the supporting inner ring 202. The supporting inner ring 202 is sleeved on the fixed part. The width of the cross section of a single pre-cooling heat exchange part 203 in the radial direction of the supporting inner ring 202 is smaller than the distance between two adjacent pre-cooling heat exchange parts 203; the supporting outer ring 201, the supporting inner ring 202 and the pre-cooling heat exchange part 203 have fluid channels, and the supporting outer ring 201 is provided with an opening 2011 for the cooling fluid to flow in and / or out, and the opening 2011 is connected to the fluid channel.

[0026] When the pre-cooling heat exchange device is in the initial mode, the angle between the corresponding individual pre-cooling heat exchange components 203 in two adjacent rotating modules 200 is 0°. Driven by an external force, the support outer ring 201 rotates, driving the pre-cooling heat exchange components 203 to rotate, allowing the pre-cooling heat exchange device to adjust from the initial mode to a different mode.

[0027] It is understandable that in order to better illustrate the structure of the rotating module 200 in the pre-cooling heat exchange device, Figure 1 The fixing member is omitted. The fixing member can be rectangular or conical in shape. When the rotating module 200 rotates, it can effectively reduce the shaking or deviation of the supporting inner ring 202, ensuring the stable rotation of the rotating module 200 around the fixing member, thereby ensuring the structural stability of the entire pre-cooling heat exchange device during operation and reducing the risk of failure due to structural instability.

[0028] During specific implementation, the cooling fluid can flow into the fluid channel through the opening 2011 of the support outer ring 201 and flow inside the pre-cooling heat exchanger 203, thereby performing heat exchange with the airflow of the engine's air intake. After the heat exchange is completed, the cooling fluid will be discharged from the opening 2011 through the fluid channel. If the flight speed of the engine is low, the pre-cooling heat exchange device can be kept in the initial mode. During this process, the contact area between each pre-cooling heat exchanger 203 and the airflow is minimized, and the thrust of the engine can be guaranteed with minimal flow resistance, so that the pressure loss approaches 0. As the flight speed gradually increases, the support outer ring 201 can be driven by an external force to rotate, so as to drive the pre-cooling heat exchanger 203 connected to the support outer ring 201 to rotate accordingly, so that the pre-cooling heat exchange device can be adjusted from the initial mode to a different mode. During this process, the angle between the corresponding single pre-cooling heat exchange components 203 in the two adjacent rotating modules 200 gradually increases, and the contact area between the single pre-cooling heat exchange component 203 and the airflow gradually increases, so that the heat exchange capacity of the pre-cooling heat exchange device gradually increases, so as to achieve the effect of lowering the intake air temperature and offsetting the aerodynamic heating effect.

[0029] It can be seen that the pre-cooling heat exchange device provided in the present application has a simple structure, can adapt the heat exchange mode to the flight speed at a relatively low processing cost, and can make the pressure loss close to 0.

[0030] In practical applications, the opening 2011 includes a cooling fluid inlet and a cooling fluid outlet, and the specific location of the opening 2011 is not limited here, as long as it is provided on the supporting outer ring 201 .

[0031] In one optional embodiment, the number of rotating modules in the present application is 3 to 6. Within this range, the heat exchange effect of the pre-cooling heat exchange device can be guaranteed to be as expected, while also ensuring the structural stability of the pre-cooling heat exchange device. If the number of rotating modules exceeds 6, not only will the production cost increase, but the complexity and weight of the structure will also increase, resulting in a decrease in overall structural stability and possible coordination difficulties between the modules. If the number of rotating modules is less than 3, it will not be able to meet the heat exchange requirements under complex working conditions.

[0032] On this basis, the embodiments of this application limit the number of pre-cooling heat exchange components within each rotating module to 4 to 16. Within this range, sufficient heat exchange area is ensured while also ensuring the structural strength of the module itself. For example, during rotation, a moderate number of pre-cooling heat exchange components can ensure more even force distribution across the module, reducing the risk of deformation or damage caused by uneven force distribution and extending the device's service life.

[0033] Exemplarily, the modes of the pre-cooling heat exchange device in the embodiment of the present application also include an intermediate mode and a final mode. Figure 3 FIG. 1 shows a schematic diagram of the structure of the pre-cooling heat exchange device of the embodiment of the present application when it is in the intermediate mode. Figure 3 As shown, when the pre-cooling heat exchange device is in the intermediate mode, the included angle of the corresponding single pre-cooling heat exchange elements 203 in two adjacent rotary modules 200 is greater than 0° and less than 30° to 60°. Figure 4 FIG. 1 shows a schematic diagram of the structure of the pre-cooling heat exchange device of the embodiment of the present application in the final mode. Figure 4 As shown, when the pre-cooling heat exchange device is in the final mode, the angle between the corresponding single pre-cooling heat exchange elements 203 in two adjacent rotating modules 200 is 30° to 60°. It can be seen that the pre-cooling heat exchange device in the embodiment of the present application can provide multiple flight modes and can realize multiple intermediate modes based on the number of rotating modules 200, that is, multiple intermediate gears can be set as needed.

[0034] It is understandable that in order to better illustrate the structure of the rotating module 200 in the pre-cooling heat exchange device, Figure 3 and Figure 4 Fixings omitted.

[0035] In specific implementation, as the flight speed gradually increases, each support outer ring 201 can be driven by an external force to rotate, thereby driving the pre-cooling heat exchange element 203 connected to the support outer ring 201 to rotate accordingly, so that the angle between the corresponding single pre-cooling heat exchange elements 203 in two adjacent rotating modules 200 is greater than 0° and less than 30° to 60°, thereby adjusting the pre-cooling heat exchange device from the initial mode to the intermediate mode. At this time, it is possible to ensure that the pre-cooling heat exchange device has a certain heat exchange effect while controlling the flow resistance at a reasonable level. Moreover, when the angle between the corresponding single pre-cooling heat exchange elements 203 in two adjacent rotating modules 200 is 30° to 60°, the pre-cooling heat exchange device adjusts from the intermediate mode to the final mode. At this time, the total contact area between the cooling fluid in the pre-cooling heat exchange element 203 and the external airflow (i.e., the airflow at the engine air intake) reaches the maximum value, and the heat exchange efficiency is significantly improved. During high-speed flight, it can fully offset the aerodynamic heating effect, effectively reduce the intake temperature, meet the engine's strict requirements on intake temperature in high-temperature environments, and ensure stable and efficient operation of the engine.

[0036] For example, when the engine's flight Mach number is less than or equal to 2, the pre-cooling heat exchange device is in the initial mode. During low-speed flight, the engine is more sensitive to flow losses and has a relatively low demand for heat exchange. The initial mode significantly reduces flow resistance while maintaining a certain level of heat exchange. This indicates that the pre-cooling heat exchange device meets the engine's operating requirements under low-speed conditions, helping to improve engine efficiency and reduce energy consumption during low-speed flight.

[0037] When the engine's flight Mach number is greater than 2 and less than 3.5, the pre-cooling heat exchange device is in the intermediate mode, thereby ensuring a certain heat exchange effect while controlling the flow resistance within a reasonable range to adapt to the changes in the engine intake temperature and pressure under this operating condition.

[0038] When the engine's flight Mach number is greater than or equal to 3.5, the pre-cooling heat exchanger is in its final mode. During high-speed flight, the engine intake air is subjected to intense aerodynamic heating. The fully deployed mode fully utilizes the heat exchange function, efficiently transferring heat from the intake air to the cooling fluid, effectively reducing the intake air temperature and meeting the engine's stringent intake air temperature requirements in high-temperature environments.

[0039] In an optional embodiment, the pre-cooling heat exchanger in the embodiment of the present application is plate-shaped, which can provide a large surface area for contact with the fluid and can also guide the airflow at the engine's air intake. In addition, because the plate-shaped pre-cooling heat exchanger is internally provided with a fluid channel for the circulation of the cooling fluid, the high-temperature airflow can directly exchange heat with the cooling fluid when it contacts the wall of the pre-cooling heat exchanger, resulting in a high heat exchange efficiency. In addition, the width of the cross-section of the pre-cooling heat exchanger in the embodiment of the present application in the radial direction of the supporting inner ring is 2mm to 10mm, which can ensure the flow rate and flow of the cooling fluid in the heat exchanger, thereby improving the heat exchange efficiency. If the width is less than 2mm, the flow rate of the cooling fluid will be restricted, resulting in an inability to fully absorb heat. If the width is greater than 10mm, the volume of the pre-cooling heat exchanger will be greatly increased, thereby increasing the difficulty of installing the pre-cooling heat exchanger in actual scenarios.

[0040] For example, the material of the pre-cooling heat exchanger in the embodiments of the present application includes at least one of titanium alloy, stainless steel, and steel alloy. When the pre-cooling heat exchanger is made of titanium alloy, it can withstand the pressure and stress during the pre-cooling heat exchange process, ensuring the structural stability of the heat exchanger. In addition, titanium alloy has excellent corrosion resistance and can resist erosion by substances such as moisture and oxygen in the cooling medium and air. It can operate stably for a long time even in humid or corrosive environments, extending the service life of the pre-cooling heat exchanger and reducing maintenance and replacement costs. When the pre-cooling heat exchanger is made of stainless steel, the smooth surface and low roughness of stainless steel help reduce the flow resistance of the fluid on the heat exchanger surface, improve the fluid flow performance, and thus enhance the heat exchange effect. At the same time, the smooth surface is also less prone to scaling and dust accumulation, making it easier to clean and maintain. When the pre-cooling heat exchanger is made of steel alloy, due to its good thermal conductivity, it can quickly transfer heat, allowing the pre-cooling heat exchanger to quickly achieve heat exchange during operation and improve heat exchange efficiency.

[0041] For example, the cooling fluid in the embodiments of the present application includes supercritical helium, supercritical hydrogen, supercritical carbon dioxide, liquid metal, water, kerosene, or ethylene glycol. The liquid metal may include sodium potassium alloy, gallium indium tin alloy, lead bismuth alloy, or mercury.

[0042] For example, Figures 1 to 4 As shown, the rotary module 200 in the embodiment of the present application also includes a fluid transmission pipe 204, which is provided at the opening 2011. The Shore hardness of the fluid transmission pipe 204 is 60HA to 80HA. This hardness range makes the fluid transmission pipe 204 relatively flexible, capable of adapting to the vibration of the device, thermal expansion and contraction, and slight deformation during installation. This reduces the risk of rupture or loosening of the fluid transmission pipe 204 due to stress concentration, thereby improving the reliability and stability of the entire pre-cooling heat exchange device. Furthermore, the fluid transmission pipe 204 within this hardness range can bend and twist accordingly with the rotation of the rotary module 200, ensuring the stability and sealing of the connection of the fluid transmission pipe 204 during rotation.

[0043] In actual applications, since the Shore hardness of the fluid transmission pipeline is 60HA~80HA and it is bendable and deformable, even if there is a certain deviation in the installation position of the upstream and downstream main pipelines, or a slight displacement occurs due to thermal expansion and contraction during the operation of the pre-cooling heat exchange device, the fluid transmission pipeline can still achieve a good connection through its own deformation, ensuring smooth transmission of the fluid.

[0044] The present application also provides an aircraft, including the above-mentioned pre-cooling heat exchange device, which can ensure the safe operation of the aircraft under various flight conditions with lower cost and pressure loss.

[0045] In practical applications, the pre-cooling heat exchange device can be arranged in the external casing to further improve the stability of the installation of the pre-cooling heat exchange device in the aircraft.

[0046] The above description is only a specific embodiment of the present application. Obviously, various modifications and combinations can be made thereto without departing from the spirit and scope of the present application. Accordingly, this specification and the drawings are merely exemplary illustrations of the present application as defined by the appended claims, and are deemed to have covered any and all modifications, variations, combinations or equivalents within the scope of the present application. Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include these changes and variations. Any person skilled in the art who can easily think of changes or substitutions within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

[0047] It should also be noted that in the apparatus and method of the present application, each component or each step can be decomposed and / or recombined, and such decomposition and / or recombination should be regarded as equivalent solutions of the present application.

[0048] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present application. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present application. Therefore, the present application is not intended to be limited to the aspects shown herein, but rather to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0049] The above description has been provided for the purpose of illustration and description. Furthermore, this description is not intended to limit the embodiments of the present application to the forms disclosed herein. Although several example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. A pre-cooling heat exchange device, characterized in that: Applied to an engine, the pre-cooling heat exchange device comprises: A base and a plurality of rotating modules, wherein a fixing member is provided in the transverse direction of the base; a single rotating module comprises a supporting outer ring, a supporting inner ring, and a plurality of pre-cooling heat-exchanging members arranged between the supporting outer ring and the supporting inner ring, the supporting inner ring being sleeved on the fixing member, and a width of a cross section of a single pre-cooling heat-exchanging member in the radial direction of the supporting inner ring being smaller than a distance between two adjacent pre-cooling heat-exchanging members; a fluid channel is provided in the supporting outer ring, the supporting inner ring, and the pre-cooling heat-exchanging member, and an opening is provided on the supporting outer ring for cooling fluid to flow in and / or out, the opening being in communication with the fluid channel; When the pre-cooling heat exchange device is in the initial mode, the included angle between the corresponding single pre-cooling heat exchange elements in two adjacent rotating modules is 0°; The supporting outer ring rotates under the driving force of an external force, so as to drive the pre-cooling heat exchange component to rotate, so that the pre-cooling heat exchange device is adjusted from an initial mode to a different mode.

2. The precooling heat exchange device according to claim 1, characterized in that: The number of the rotating modules is 3 to 6, and the number of pre-cooling heat exchange components included in each rotating module is 4 to 16.

3. The precooling heat exchange device according to claim 2, characterized in that: The modes of the pre-cooling heat exchange device also include an intermediate mode and a final mode; when the pre-cooling heat exchange device is in the intermediate mode, the angle between the corresponding single pre-cooling heat exchange elements in two adjacent rotating modules is greater than 0° and less than 30°~60°; when the pre-cooling heat exchange device is in the final mode, the angle between the corresponding single pre-cooling heat exchange elements in two adjacent rotating modules is 30°~60°.

4. The precooling heat exchange device according to claim 3, characterized in that: When the engine's flight Mach number is less than or equal to 2, the pre-cooling heat exchange device is in the initial mode; when the engine's flight Mach number is greater than 2 and less than 3.5, the pre-cooling heat exchange device is in the intermediate mode; when the engine's flight Mach number is greater than or equal to 3.5, the pre-cooling heat exchange device is in the final mode.

5. The precooling heat exchange device according to any one of claims 1 to 4, characterized in that: The pre-cooling heat exchange component is in a plate shape, and the width of the cross section of the pre-cooling heat exchange component in the radial direction of the supporting inner ring is 2 mm to 10 mm.

6. The precooling heat exchange device according to claim 5, characterized in that: The material of the pre-cooling heat exchange component includes at least one of titanium alloy, stainless steel and steel alloy.

7. The precooling heat exchange device according to claim 5, characterized in that: The cooling fluid includes supercritical helium, supercritical hydrogen, supercritical carbon dioxide, liquid metal, water, kerosene or ethylene glycol.

8. The pre-cooling heat exchange device according to claim 5, characterized in that: The rotating module further includes a fluid transmission pipeline, which is arranged on the opening and has a Shore hardness of 60HA to 80HA.

9. An aircraft, characterized in that: include: The precooling heat exchange device according to any one of claims 1 to 8.

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