Pre-cooling heat exchanger for aircraft and aircraft

Abstract

The present disclosure relates to the field of aircraft technology, and particularly provides a pre-cooling heat exchanger for an aircraft, comprising at least three stacked and spaced baffles to form an air flow channel arranged along a first direction of the baffles and a heat exchange working medium flow channel arranged along a second direction of the baffles; the baffle is a curved baffle, so that the heat exchange working medium flow channel is formed as a wave-shaped flow channel; the air flow channel is provided with a first heat exchange fin group and a second heat exchange fin group, the second heat exchange fin group comprises a plurality of evenly arranged flow uniformizing fins, the flow uniformizing fin comprises a heat exchange fin body supported in the air flow channel and a heat exchange working medium micro-channel arranged in the heat exchange fin body, an inlet end of the heat exchange working medium micro-channel is communicated with one of the heat exchange working medium flow channels adjacent to the air flow channel, and an outlet end of the heat exchange working medium micro-channel is communicated with another of the heat exchange working medium flow channels adjacent to the air flow channel, so as to improve the heat exchange efficiency.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft technology, and in particular to a precooling heat exchanger for aircraft and an aircraft. Background Technology

[0002] The high speed of aircraft has extremely important military and civilian value, but the aerodynamic heating effect generated by aircraft during high-speed flight limits the flight limits of aircraft.

[0003] Turbine engines are a crucial component of aircraft, providing propulsion for flight. To increase the flight speed of turbine engines, related technologies utilize pre-cooling heat exchangers to cool the ramjet intake air, lowering its temperature to partially offset the temperature rise caused by aerodynamic heating during high-speed flight. However, the heat exchange efficiency of these pre-cooling heat exchangers is relatively low. Summary of the Invention

[0004] In order to solve the above-mentioned technical problems, or at least partially solve the above-mentioned technical problems, this disclosure provides a precooling heat exchanger for aircraft and an aircraft to improve heat exchange efficiency.

[0005] In a first aspect, this disclosure provides a precooling heat exchanger for an aircraft, comprising at least three stacked and spaced-apart partitions. In every three adjacent partitions, an airflow channel is formed between two adjacent partitions, and a heat exchange medium flow channel is formed between another two adjacent partitions. The airflow channel is arranged along a first direction of the partitions, and the heat exchange medium flow channel is arranged along a second direction of the partitions; the first direction and the second direction are perpendicular to each other.

[0006] The baffle is a curved baffle, so that the heat exchange working fluid flow channel is formed into a wavy flow channel;

[0007] The airflow channel is provided with a first heat exchange fin group and a second heat exchange fin group. The first heat exchange fin group includes a plurality of heat exchange fins spaced apart in the airflow channel. The second heat exchange fin group includes a plurality of flow equalization fins spaced apart in the airflow channel. Each flow equalization fin includes a heat exchange fin body supported in the airflow channel and a heat exchange medium microchannel disposed in the heat exchange fin body. The inlet end of the heat exchange medium microchannel is connected to one of the heat exchange medium channels adjacent to the airflow channel, and the outlet end of the heat exchange medium microchannel is connected to another heat exchange medium channel adjacent to the airflow channel.

[0008] Optionally, the inlet end of the heat exchange medium microchannel contacts one of the baffles corresponding to the air flow channel, and the outlet end of the heat exchange medium microchannel contacts the other baffle corresponding to the air flow channel. Furthermore, both baffles of the air flow channel are provided with clearance holes at the positions corresponding to the heat exchange medium microchannel, so that the heat exchange medium microchannel can communicate with the corresponding heat exchange medium flow channel through the clearance holes.

[0009] Optionally, along the stacking direction of the partition, the flow equalization fins in two adjacent layers of the airflow channels are arranged correspondingly;

[0010] And / or, the heat exchange fin body is provided with a plurality of heat exchange medium microchannels, the plurality of heat exchange medium microchannels are arranged at intervals along the extension direction of the air flow channel and are arranged in parallel.

[0011] Optionally, the heat exchange fin body includes a first outer body surface and a second outer body surface disposed opposite to each other, the first outer body surface and the second outer body surface protruding in a direction away from each other to form a streamlined arc-shaped surface;

[0012] Along the extension direction of the airflow channel, one end of the first outer body surface is connected to one end of the second outer body surface, and the other end of the first outer body surface is connected to the other end of the second outer body surface.

[0013] Optionally, the first outer body surface and / or the second outer body surface are covered with a hydrophobic coating.

[0014] Optionally, along the extension direction of the heat exchange medium microchannel, the heat exchange medium microchannel includes an inlet section, an intermediate section, and an outlet section connected in sequence.

[0015] The cross-sectional area of ​​the inlet section gradually decreases along the direction from the inlet section to the middle section; and the cross-sectional area of ​​the outlet section gradually increases along the direction from the middle section to the outlet section.

[0016] The cross-sectional area of ​​the intermediate section is equal everywhere in the direction from the inlet section to the outlet section.

[0017] Optionally, the precooling heat exchanger for the aircraft may further include a flow diverter;

[0018] The flow diverter's inlet is connected to the heat exchange medium supply pipeline, and the flow diverter has multiple diversion branches that are respectively connected to the flow diverter inlet, with each diversion branch corresponding to at least two layers of the heat exchange medium flow channels.

[0019] Optionally, the heat exchange medium channel is provided with lattice fins, and the lattice fins are supported between two adjacent partitions.

[0020] Optionally, the lattice fins include a plurality of support rods arranged radially;

[0021] The ends of the plurality of support rods that are close to each other are connected to a central meeting point, and the ends of the plurality of support rods that are away from the central meeting point respectively contact the corresponding partitions to provide support between two adjacent partitions.

[0022] Optionally, among all the support rods, at least two adjacent support rods are connected by a reinforcing rod between their ends away from the central confluence point, the reinforcing rod being arranged parallel to and in contact with the partition.

[0023] Secondly, this disclosure provides an aircraft including a precooling heat exchanger for an aircraft as described above.

[0024] The precooling heat exchanger and aircraft provided in this disclosure embodiment, by setting at least three stacked and spaced partitions, such that in every three adjacent partitions, an air flow channel is formed between two adjacent partitions, and a heat exchange working fluid flow channel is formed between the other two adjacent partitions, and the air flow channel and the heat exchange working fluid flow channel are arranged vertically, thereby improving the heat exchange efficiency.

[0025] By setting the baffles as curved baffles, the heat exchange medium flow channel is formed into a wavy flow channel. This increases the primary surface heat exchange area compared to a straight flow channel, thus improving the heat exchange efficiency of the heat exchange medium, while maintaining the same outer contour volume of the heat exchanger. Furthermore, by setting a first heat exchange fin group and a second heat exchange fin group in the air flow channel, the contact area between the air and the heat exchanger is increased, further improving heat exchange efficiency. Simultaneously, by making the second heat exchange fin group include multiple spaced-apart flow-equalizing fins, each of which includes a heat exchange fin body supported in the air flow channel and a heat exchange medium microchannel penetrating the fin body, with the microchannel connected to two adjacent heat exchange medium flow channels, the flow distribution of the heat exchange medium between heat exchanger layers is improved, enhancing heat exchange uniformity. The synergistic effect of the heat exchange medium flow channel and the flow-equalizing fins in heat exchange with the air further improves heat exchange efficiency. Furthermore, the flow equalization fins also provide some support to the airflow channel, improving the airflow channel's resistance to airflow and its stability, thereby enhancing the stability and service life of the precooling heat exchanger structure.

[0026] In addition, since the air flow channel is perpendicular to the corrugated heat exchange medium flow channel, the air can pass straight through the heat exchanger along the air flow channel between the two baffles, thereby reducing the pressure loss on the air side to a certain extent.

[0027] It should be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further illustration of the claimed technology. Attached Figure Description

[0028] The above and other objects, features, and advantages of this disclosure will become more apparent from the more detailed description of the embodiments thereof in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of this disclosure and form part of the specification. They are used together with the embodiments of this disclosure to explain the disclosure and do not constitute a limitation thereof. In the drawings, the same reference numerals generally represent the same components or steps.

[0029] Figure 1 This is a schematic diagram of the structure of a precooling heat exchanger for an aircraft provided in an embodiment of the present disclosure;

[0030] Figure 2 for Figure 1 The corresponding structural diagram after removing the first heat exchange fin group;

[0031] Figure 3 This is a schematic diagram of the flow equalization fins in a precooling heat exchanger for an aircraft provided in an embodiment of the present disclosure.

[0032] Figure 4 This is a partial structural cross-sectional view of an aircraft precooling heat exchanger provided in an embodiment of the present disclosure;

[0033] Figure 5 This is a schematic diagram of the structure of the lattice fins in an aircraft precooling heat exchanger provided in an embodiment of the present disclosure;

[0034] Figure 6 This is a schematic diagram of the flow diverter in a precooling heat exchanger for aircraft provided in an embodiment of the present disclosure.

[0035] Among them, 1. partition plate; 11. air flow channel; 12. heat exchange medium flow channel; 13. clearance hole; 2. first heat exchange fin group; 21. heat exchange fin; 3. second heat exchange fin group; 31. flow equalization fin; 311. heat exchange fin body; 312. first outer body surface; 313. second outer body surface; 314. heat exchange medium microchannel; 315. inlet section; 316. middle section; 317. outlet section; 4. matrix fin; 41. support rod; 42. central confluence point; 43. reinforcing rod; 5. flow guide and splitter; 51. flow guide inlet; 52. flow branch; 6. end plate; 61. inlet pipe; 62. outlet pipe. Detailed Implementation

[0036] To make the objectives, technical solutions, and advantages of this disclosure more apparent, exemplary embodiments according to this disclosure will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this disclosure, and not all embodiments of this disclosure. It should be understood that this disclosure is not limited to the exemplary embodiments described herein.

[0037] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to". The term "based on" means "at least partially based on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments". Definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc., used in this disclosure are only used to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0038] It should be noted that the terms "a" and "a plurality of" used in this disclosure are illustrative rather than restrictive, and those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0039] Reference Figures 1 to 5 As shown, this disclosure provides a precooling heat exchanger for aircraft, including at least three stacked and spaced-apart partitions 1.

[0040] In every three adjacent partitions 1, an air flow channel 11 is formed between two adjacent partitions 1, and a heat exchange medium flow channel 12 is formed between the other two adjacent partitions 1. The air flow channel 11 is arranged along a first direction of the partition 1, and the heat exchange medium flow channel 12 is arranged along a second direction of the partition 1. The first direction and the second direction are perpendicular to each other.

[0041] The first direction can be, for example, the width direction of partition 1, such as... Figure 1 and Figure 2 The direction indicated by XX in the diagram, the second direction could be, for example, the length direction of partition 1, for example... Figure 1 and Figure 2 The YY direction is shown in the diagram.

[0042] The partition 1 is made of a material that meets the requirements of high temperature resistance, corrosion resistance, and good thermal conductivity in aerospace applications, such as high-temperature alloys, high-temperature stainless steel, or titanium alloys. For example, the thickness of the partition 1 can be set to 0.5 mm.

[0043] In specific implementation, along the second direction mentioned above, end plates 6 are provided on both sides of the partition 1. The end plates 6 seal the ends of adjacent partitions 1 to form a sealed flow channel. An inlet pipe 61 is provided on one end plate 6, and an outlet pipe 62 is provided on the other end plate 6. The inlet pipe 61 is used to connect with an external heat exchange medium supply pipeline. The heat exchange medium supply pipeline introduces heat exchange medium into the heat exchange medium flow channel 12 through the inlet pipe 61. During the flow, the heat exchange medium exchanges heat with the air in the adjacent air flow channel 11, absorbing the heat from the air and cooling it. The heat exchange medium after heat exchange is finally discharged from the outlet pipe 62, and for example, after cooling, it re-enters the heat exchange medium supply pipeline, realizing the recycling of the heat exchange medium and saving costs.

[0044] For example, the heat exchange medium can be a high-boiling-point liquid metal, such as a gallium-indium alloy, specifically Ga... 68 In 20 Sn 12 Of course, the heat exchange medium can also be a sodium-potassium alloy, a lead-bismuth alloy, etc. In addition, the heat exchange medium can also be a gaseous heat exchange medium.

[0045] Specifically, the heat of the air entering the airflow channel 11 is transferred to the baffle 1, and then from the baffle 1 to the heat exchange medium in the adjacent heat exchange medium flow channel 12. After absorbing the heat of the air, the heat exchange medium flows out from the outlet of the heat exchange medium flow channel 12, thereby cooling the air. The cooled air in the airflow channel 11 eventually flows from the outlet end of the airflow channel 11 to the engine, and enters the engine from the engine's air intake, thereby cooling the engine's intake air temperature, ensuring the engine's performance, and thus ensuring that it can fly at higher speeds.

[0046] The baffle 1 is a curved baffle, which forms a wavy flow channel 12 for the heat exchange medium. By setting the baffle 1 as a curved baffle, a wavy flow channel 12 for the heat exchange medium is formed, thereby increasing the primary surface heat exchange area and improving the heat exchange efficiency of the heat exchange medium. Since the air channel 11 is arranged perpendicular to the heat exchange medium flow channel 12, air passes straight through the heat exchanger along the air channel 11, thereby reducing the pressure loss on the air side. That is, while improving the heat exchange efficiency, the pressure loss on the air side is also reduced.

[0047] For example, the radius of curvature of the corrugated surface of the baffle 1 satisfies the condition that the heat exchange medium does not separate (e.g., radius of curvature R ≥ 5D, where D is the hydraulic diameter of the flow channel). For example, the radius of curvature of the corrugated baffle is R = 6D = 12mm.

[0048] Tests showed that the corrugated heat exchange medium channel 12 increases the surface heat exchange area by about 20% to 40% compared with the flat straight channel for the same volume.

[0049] The airflow channel 11 is provided with a first heat exchange fin group 2 and a second heat exchange fin group 3. The first heat exchange fin group 2 includes a plurality of heat exchange fins 21 arranged at intervals in the airflow channel 11. Specifically, the plurality of heat exchange fins 21 are arranged in parallel in the airflow channel 11. The presence of the heat exchange fins 21 increases the contact area between the air and the heat exchanger, thereby enhancing air-side heat exchange. Specifically, the heat of the air entering the airflow channel 11 is transferred to the baffle 1 and the heat exchange fins 21, and the heat is transferred to the heat exchange medium in the adjacent heat exchange medium flow channel 12 through the baffle 1 and the heat exchange fins 21, thereby achieving air cooling and improving heat exchange efficiency.

[0050] For example, the thickness of the heat exchange fin 21 can be set to 0.1 mm to 0.3 mm. The heat exchange fin 21 can be a straight fin or a serrated fin.

[0051] Specifically, the second heat exchange fin group 3 includes a plurality of flow equalization fins 31 spaced apart in the air flow channel 11. The flow equalization fin 31 includes a heat exchange fin body 311 supported in the air flow channel 11 and a heat exchange medium microchannel 314 disposed in the heat exchange fin body 311. The inlet end of the heat exchange medium microchannel 314 is connected to one of the heat exchange medium channels 12 adjacent to the air flow channel 11, and the outlet end of the heat exchange medium microchannel 314 is connected to another heat exchange medium channel 12 adjacent to the air flow channel 11.

[0052] This configuration increases the contact area between the air and the heat exchanger, thereby improving the heat exchange efficiency without increasing the outer contour of the heat exchanger. Moreover, by configuring the heat exchange medium microchannels 314 as described above, the flow distribution of the heat exchange medium between the heat exchanger layers is improved, achieving uniform flow and thus improving heat exchange uniformity. The heat exchange efficiency is further improved by the synergistic heat exchange of the air through the heat exchange medium flow channels 12 and the uniform flow fins 31.

[0053] By increasing the primary surface heat exchange area through the coordinated action of the curved baffle and the flow equalization fins 31, the heat transfer coefficient of the heat exchange medium is improved, thereby enhancing the overall heat exchange efficiency.

[0054] In practice, the baffle 1 and the heat exchange fin body 311 can both be made of nickel-based high-temperature alloys (such as Inconel 718 or GH3625) to improve the structural strength of the baffle 1 and the heat exchange fin body 311 and their corrosion resistance to the heat exchange medium.

[0055] The precooling heat exchanger for aircraft provided in this embodiment of the present disclosure is provided with at least three stacked and spaced partitions 1, such that in every three adjacent partitions 1, an air flow channel 11 is formed between two adjacent partitions 1, and a heat exchange working fluid flow channel 12 is formed between the other two adjacent partitions 1, and the air flow channel 11 and the heat exchange working fluid flow channel 12 are arranged perpendicularly, thereby improving the heat exchange efficiency.

[0056] Furthermore, by setting the baffle 1 as a curved baffle, the heat exchange medium flow channel 12 is formed into a wavy flow channel. This increases the primary surface heat exchange area compared to a straight flow channel, while maintaining the same outer contour volume of the heat exchanger, thereby improving the heat exchange efficiency of the heat exchange medium. By setting the first heat exchange fin group 2 and the second heat exchange fin group 3 in the air flow channel 11, the contact area between the air and the heat exchanger is increased, further improving the heat exchange efficiency. Simultaneously, by making the second heat exchange fin group 3 include multiple... The spaced-apart flow equalization fins 31 comprise a heat exchange fin body 311 supported in the airflow channel 11 and heat exchange medium microchannels 314 penetrating the heat exchange fin body 311. The heat exchange medium microchannels 314 are connected to two adjacent heat exchange medium channels 12, thereby improving the flow evenness of the heat exchange medium between heat exchanger layers and enhancing heat exchange uniformity. Through the synergistic effect of the heat exchange medium channels 12 and the flow equalization fins 31, heat exchange efficiency is further improved. Furthermore, the flow equalization fins 31 also provide support to the airflow channel 11 to a certain extent, improving the airflow channel 11's resistance to airflow impact and stability, and enhancing the stability and service life of the pre-cooling heat exchanger structure.

[0057] In addition, since the air flow channel 11 is perpendicular to the corrugated heat exchange medium flow channel 12, air can pass straight through the heat exchanger along the air flow channel 11 between the two baffles 1, thereby reducing the pressure loss on the air side to a certain extent.

[0058] The precooling heat exchanger provided in this embodiment improves the heat transfer coefficient on the heat exchange medium side and reduces the air pressure drop through the above-mentioned settings, making it suitable for high heat flux density heat dissipation scenarios such as aviation and energy.

[0059] Combination Figure 1 , Figure 2 and Figure 4 As shown, in some embodiments, the flow equalization fins 31 in two adjacent airflow channels 11 are correspondingly arranged along the stacking direction of the partition 1.

[0060] In other words, a second heat exchange fin group 3 can be provided in each layer of air flow channel 11. The second heat exchange fin group 3 of each layer can include one or more flow equalization fins 31. When multiple flow equalization fins 31 are provided in each layer, the multiple flow equalization fins 31 are arranged at intervals in the air flow channel 11.

[0061] By aligning the flow equalization fins 31 in the two adjacent airflow channels 11, the overall structural strength of the heat exchanger is improved.

[0062] Reference Figure 4As shown, the inlet end of the heat exchange medium microchannel 314 is in contact with one of the baffles 1 corresponding to the air flow channel 11, and the outlet end of the heat exchange medium microchannel 314 is in contact with the other baffle 1 corresponding to the air flow channel 11. Both baffles 1 of the air flow channel 11 are provided with clearance holes 13 at the positions corresponding to the heat exchange medium microchannel 314, so that the heat exchange medium microchannel 314 can be connected to the corresponding heat exchange medium flow channel 12 through the clearance holes 13.

[0063] This configuration allows the two ends of the heat exchange medium microchannel 314 to be directly aligned and connected with the two adjacent heat exchange medium channels 12, eliminating the need for connecting pipes or similar structures. This enables the heat exchange medium to flow smoothly between the heat exchange medium channels 12 and the heat exchange medium microchannel 314, thereby improving heat exchange efficiency while simplifying the overall structure.

[0064] Reference Figures 1 to 3 As shown, in some embodiments, a plurality of heat exchange medium microchannels 314 are provided in the heat exchange fin body 311. The plurality of heat exchange medium microchannels 314 are arranged at intervals along the extension direction of the air flow channel 11 and are arranged in parallel.

[0065] This design improves the heat exchange effect at different locations in the airflow channel 11, further enhancing the uniformity of interlayer flow distribution and heat exchange efficiency. Moreover, even if a microchannel becomes blocked, the heat exchange medium can still flow between heat exchanger layers through other microchannels, ensuring the heat exchange effect.

[0066] Continue to refer to Figure 2 and Figure 3 As shown, in some embodiments, the heat exchange fin body 311 includes a first outer body surface 312 and a second outer body surface 313 disposed opposite to each other, the first outer body surface 312 and the second outer body surface 313 protruding in a direction away from each other to form a streamlined arc-shaped surface. Specifically, along the extension direction of the airflow channel 11, one end of the first outer body surface 312 and one end of the second outer body surface 313 are connected, and the other end of the first outer body surface 312 is connected to the other end of the second outer body surface 313.

[0067] By setting the heat exchange fin body 311 to the above-mentioned streamlined structure, the smoothness of air flow during the air flow channel 11 is improved, the pressure loss is further reduced, and the contact area between air and heat exchange fin body 311 is increased while the area of ​​the baffle 1 remains unchanged, thereby further improving the heat exchange efficiency.

[0068] In some embodiments, both the first outer body surface 312 and the second outer body surface 313 are covered with a hydrophobic coating. By covering the first outer body surface 312 and the second outer body surface 313 with a hydrophobic coating, the deposition of pollutants in the air on the heat exchange fin body 311 can be reduced to a certain extent, thereby further improving the heat exchange effect between the air and the uniform flow fins 31.

[0069] For example, the hydrophobic coating may be polytetrafluoroethylene. Of course, the hydrophobic coating may also be made of other materials such as silicone resin-based coatings, and the embodiments disclosed herein are not limited thereto.

[0070] Alternatively, a hydrophobic coating may be applied only to the first outer body surface 312, or only to the second outer body surface 313.

[0071] In some embodiments, refer to Figure 4 As shown, along the extension direction of the heat exchange medium microchannel 314, the heat exchange medium microchannel 314 includes an inlet section 315, an intermediate section 316, and an outlet section 317 connected in sequence.

[0072] In the direction from inlet section 315 to intermediate section 316, the cross-sectional area of ​​inlet section 315 gradually decreases to reduce flow velocity. In the direction from intermediate section 316 to outlet section 317, the cross-sectional area of ​​outlet section 317 gradually increases to balance pressure.

[0073] As mentioned above, by compensating for the flow channel resistance gradient, the uniformity of flow distribution between layers is further achieved, thereby improving the heat transfer uniformity and thus further improving the heat transfer efficiency.

[0074] In particular, the cross-sectional area of ​​the intermediate section 316 is equal everywhere along the direction from the inlet section 315 to the outlet section 317. This improves the pressure balance in the heat exchange medium microchannel 314, thereby improving the smoothness of the heat exchange medium flow.

[0075] For example, in the direction from the middle section 316 to the entrance section 315, the area expansion ratio of the entrance section 315 can be set to 1:1.5, and in the direction from the exit section 317 to the middle section 316, the area contraction ratio of the exit section 317 can be set to 1.2:1.

[0076] For example, the flow channel length ratio of the heat exchange medium microchannel 314 is 1:3:1 (inlet section 315: middle section 316: outlet section 317), the average diameter is 1 mm, and its height on the air side is 4 mm.

[0077] The flow-equalizing fins 31 have a streamlined shape and a finely constructed internal heat exchange medium microchannel 314. Specifically, by precisely controlling the area, shape, and orientation of the microchannels, the inertial effect and viscous resistance of the heat exchange medium, such as liquid metal, are fully considered. A flow resistance gradient compensation strategy is introduced to achieve uniform distribution of liquid metal flow between layers. Based on this flow-equalizing design, the traditional head structure is abandoned, making the precooling heat exchanger structure more streamlined and lightweight.

[0078] Reference Figure 6 As shown, in some embodiments, the precooling heat exchanger for aircraft further includes a flow diverter 5. The flow diverter 5 has a flow inlet 51 connected to a heat exchange medium supply pipe, and has multiple diversion branches 52 each connected to the flow inlet 51. The number of diversion branches can be, for example, four or five, etc., and this disclosure does not specifically limit the number. Each diversion branch 52 corresponds to at least two layers of heat exchange medium flow channels 12.

[0079] This configuration further improves the interlayer flow uniformity of the heat exchanger, thereby further improving the heat exchange uniformity and ultimately the heat exchange efficiency.

[0080] By combining the heat exchange medium microchannels 314 within the flow equalization fins 31 with the flow diverter 5, the interlayer flow equalization and the increase of the primary heat exchange area are further realized. This eliminates the need for traditional bulky and space-consuming end caps, which is conducive to the compact and lightweight development of heat exchangers. This makes the heat exchanger particularly suitable for applications such as aerospace where size and weight are extremely sensitive.

[0081] For example, the flow diverter 5 can be configured as a tapered-expanding circular pipe, with helical guide vanes arranged on the wall of the expanding section to generate a circumferential velocity component in the heat exchange medium, suppressing flow fluctuations caused by pumping pulsations. Multiple outlets are arranged circumferentially at the outlet of the guide vane section, connecting to each diversion branch 52. The orifice sizes of the multiple outlets are different, optimized using Computational Fluid Dynamics (CFD), taking into account factors such as the conveying length and bend arrangement of each downstream diversion branch 52 to ensure that the flow rates of each diversion branch 52 are essentially the same.

[0082] In some embodiments, the heat exchange medium flow channel 12 is provided with lattice fins 4, and the lattice fins 4 are supported between two adjacent partitions 1.

[0083] This allows the lattice fins 4 to provide stable support for the heat exchange medium flow channel 12, improving the structural strength of the heat exchange medium flow channel 12, avoiding the risk of damage to the baffle 1 corresponding to the heat exchange medium flow channel 12 under the pressure and flow impact of the heat exchange medium, and extending the service life of the precooling heat exchanger.

[0084] In practice, multiple lattice fins 4 can be set in the heat exchange medium flow channel 12, and the multiple lattice fins 4 are arranged at intervals in the heat exchange medium flow channel 12.

[0085] Combination Figure 4 and Figure 5 As shown, in some embodiments, the lattice fins 4 include a plurality of support rods 41 arranged radially.

[0086] Among them, the ends of the multiple support rods 41 that are close to each other are connected to the central meeting point 42, and the ends of the multiple support rods 41 that are away from the central meeting point 42 respectively contact the corresponding partition 1 to support between two adjacent partitions 1.

[0087] This configuration allows the lattice fins 4 to form a spatial grid structure, which gives the fins extremely high rigidity, enabling them to remain stable under the pressure and flow impact of the heat exchange medium, and making them less prone to deformation and structural failure. This provides better stability support for the heat exchange medium flow channel 12, thereby ensuring that the baffle 1 operates stably and reliably under harsh fluid conditions and extending the service life of the precooling heat exchanger.

[0088] For example, the unit cell size of the lattice fin 4 is no greater than 2mm×2mm×2mm, the rod diameter of the support rod 41 is, for example, no greater than 0.5mm, and the porosity of the lattice fin 4 can be 85%. It can be integrally formed in the heat exchange medium channel 12 by 3D printing.

[0089] Furthermore, continue to refer to Figure 5 As shown, in some embodiments, at least two adjacent support rods 41 are connected by a reinforcing rod 43 at their ends away from the central meeting point 42. The reinforcing rod 43 is arranged parallel to the partition 1 and is attached to the partition 1.

[0090] This configuration further enhances the structural strength of the lattice fins 4, thereby improving the support effect of the lattice fins 4 on the heat exchange medium flow channel 12. At the same time, it enables the heat exchange medium to rapidly transfer heat with the air, further improving the heat exchange efficiency.

[0091] For example, high-precision metal 3D printing (layer resolution ≤20μm) can be used, such as laser selective melting (SLM) and laser powder bed fusion (LPBF), to create integrated heat exchangers. Leveraging the advantages of additive manufacturing technology, the limitations of traditional welding processes on complex structures can be overcome, enabling the structural integration of the corrugated baffle 1, lattice fins 4, and flow equalization fins 31.

[0092] This disclosure also provides an aircraft, including an engine and a precooling heat exchanger. The precooling heat exchanger is located on the engine's intake side and is used to cool the intake air, reducing the engine's inlet air temperature and offsetting the increase in intake air temperature caused by aerodynamic heating during high-speed flight, thus enabling the engine to fly at higher speeds.

[0093] The specific structure and implementation principle of the precooling heat exchanger in this embodiment are the same as those of the precooling heat exchanger for aircraft provided in the above embodiments, and can bring the same or similar technical effects. They will not be described in detail here, but can be referred to the description of the above embodiments.

[0094] The above description is merely an embodiment of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features disclosed in this disclosure that have similar functions.

[0095] While specific embodiments of this disclosure have been described in detail by way of example, those skilled in the art should understand that the examples are for illustrative purposes only and not intended to limit the scope of this disclosure. Those skilled in the art should understand that modifications can be made to the above embodiments without departing from the scope and spirit of this disclosure. The scope of this disclosure is defined by the appended claims.

Claims

1. A precooling heat exchanger for aircraft, characterized in that, It includes at least three stacked and spaced partitions. In every three adjacent partitions, an air flow channel is formed between two adjacent partitions, and a heat exchange medium flow channel is formed between another two adjacent partitions. The air flow channel is arranged along a first direction of the partitions, and the heat exchange medium flow channel is arranged along a second direction of the partitions. The first direction and the second direction are perpendicular to each other. The baffle is a curved baffle, so that the heat exchange working fluid flow channel is formed into a wavy flow channel; The airflow channel is provided with a first heat exchange fin group and a second heat exchange fin group. The first heat exchange fin group includes a plurality of heat exchange fins spaced apart in the airflow channel. The second heat exchange fin group includes a plurality of flow equalization fins spaced apart in the airflow channel. Each flow equalization fin includes a heat exchange fin body supported in the airflow channel and a heat exchange medium microchannel disposed in the heat exchange fin body. The inlet end of the heat exchange medium microchannel is connected to one of the heat exchange medium channels adjacent to the airflow channel, and the outlet end of the heat exchange medium microchannel is connected to another heat exchange medium channel adjacent to the airflow channel. Along the extension direction of the heat exchange medium microchannel, the heat exchange medium microchannel includes an inlet section, an intermediate section and an outlet section connected in sequence; The cross-sectional area of ​​the inlet section gradually decreases along the direction from the inlet section to the middle section; and the cross-sectional area of ​​the outlet section gradually increases along the direction from the middle section to the outlet section. The cross-sectional area of ​​the intermediate section is equal everywhere in the direction from the inlet section to the outlet section.

2. The precooling heat exchanger for aircraft according to claim 1, characterized in that, The inlet end of the heat exchange medium microchannel is in contact with one of the baffles corresponding to the air flow channel, and the outlet end of the heat exchange medium microchannel is in contact with the other baffle corresponding to the air flow channel. Both baffles of the air flow channel are provided with clearance holes at the positions corresponding to the heat exchange medium microchannel, so that the heat exchange medium microchannel can communicate with the corresponding heat exchange medium flow channel through the clearance holes.

3. The precooling heat exchanger for aircraft according to claim 1, characterized in that, Along the stacking direction of the partition, the flow equalization fins in two adjacent layers of the airflow channel are arranged correspondingly; And / or, the heat exchange fin body is provided with a plurality of heat exchange medium microchannels, the plurality of heat exchange medium microchannels are arranged at intervals along the extension direction of the air flow channel and are arranged in parallel.

4. The precooling heat exchanger for aircraft according to claim 1, characterized in that, The heat exchange fin body includes a first outer body surface and a second outer body surface arranged opposite to each other, and the first outer body surface and the second outer body surface protrude in a direction away from each other to form a streamlined arc surface; Along the extension direction of the airflow channel, one end of the first outer body surface is connected to one end of the second outer body surface, and the other end of the first outer body surface is connected to the other end of the second outer body surface.

5. The precooling heat exchanger for aircraft according to claim 4, characterized in that, The first outer body surface and / or the second outer body surface are covered with a hydrophobic coating.

6. The precooling heat exchanger for aircraft according to any one of claims 1 to 5, characterized in that, The precooling heat exchanger for aircraft also includes a flow guide and splitter; The flow diverter's inlet is connected to the heat exchange medium supply pipeline, and the flow diverter has multiple diversion branches that are respectively connected to the flow diverter inlet, with each diversion branch corresponding to at least two layers of the heat exchange medium flow channels.

7. The precooling heat exchanger for aircraft according to any one of claims 1 to 5, characterized in that, The heat exchange medium flow channel is provided with lattice fins, and the lattice fins are supported between two adjacent partitions.

8. The precooling heat exchanger for aircraft according to claim 7, characterized in that, The lattice fins include multiple support rods arranged radially; The ends of the plurality of support rods that are close to each other are connected to a central meeting point, and the ends of the plurality of support rods that are away from the central meeting point respectively contact the corresponding partitions to support the rods between two adjacent partitions. Of all the support rods, at least two adjacent support rods are connected by a reinforcing rod between their ends away from the central meeting point. The reinforcing rod is arranged parallel to the partition and is in contact with the partition.

9. An aircraft, characterized in that, Includes the precooling heat exchanger for aircraft as described in any one of claims 1 to 8.

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