Pre-cooling heat exchanger for aircraft and aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to a pre-cooling heat exchanger for an aircraft and the aircraft, the pre-cooling heat exchanger for the aircraft comprises at least three partition plates which are stacked and arranged at intervals so as to form an air flow channel arranged in the first direction of the partition plates and a heat exchange working medium flow channel arranged in the second direction of the partition plates; the partition plate is a bent partition plate, so that the heat exchange working medium runner forms a wave-shaped runner; a first heat exchange fin set and a second heat exchange fin set are arranged in the air flow channel, the second heat exchange fin set comprises a plurality of flow equalizing fins arranged at intervals, and each flow equalizing 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. The inlet end of the heat exchange working medium micro-channel communicates with one heat exchange working medium flow channel adjacent to the air flow channel, and the outlet end of the heat exchange working medium micro-channel communicates with the other heat exchange working medium flow channel adjacent to the air flow channel, so that the heat exchange efficiency is improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and in particular to a pre-cooling heat exchanger for an aircraft and an aircraft. Background Art

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

[0003] Turbine engines are essential components of aircraft, providing propulsion. To increase the flight speed of turbine engines, conventional technologies use pre-cooling heat exchangers to cool the ram air intake, reducing the inlet air temperature and, to a certain extent, offsetting the temperature increase caused by aerodynamic heating during high-speed flight. However, the heat transfer efficiency of pre-cooling heat exchangers in conventional technologies is relatively low. Summary of the Invention

[0004] In order to solve the above technical problems or at least partially solve the above technical problems, the present disclosure provides a pre-cooling heat exchanger for an aircraft and an aircraft, so as to improve heat exchange efficiency.

[0005] In a first aspect, the present disclosure provides a pre-cooling heat exchanger for an aircraft, comprising at least three stacked and spaced-apart partitions, wherein an air flow channel is formed between two adjacent partitions of each three adjacent partitions, and a heat exchange medium flow channel is formed between another two adjacent partitions, wherein 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;

[0006] The partition is a curved partition, so that the heat exchange medium flow channel is formed into a wavy flow channel;

[0007] A first heat exchange fin group and a second heat exchange fin group are provided in the air flow channel, the first heat exchange fin group includes a plurality of heat exchange fins arranged at intervals in the air flow channel; the second heat exchange fin group includes a plurality of flow balancing fins arranged at intervals in the air flow channel, the flow balancing fins include a heat exchange fin body supported in the air flow channel and a heat exchange medium microchannel provided in the heat exchange fin body, the inlet end of the heat exchange medium microchannel is communicated with one of the heat exchange medium flow channels adjacent to the air flow channel, and the outlet end of the heat exchange medium microchannel is communicated with another heat exchange medium flow channel adjacent to the air flow channel.

[0008] Optionally, the inlet end of the heat exchange medium microchannel contacts one of the partitions corresponding to the air flow channel, and the outlet end of the heat exchange medium microchannel contacts another of the partitions corresponding to the air flow channel, and avoidance holes are provided at the positions of the two partitions of the air flow channel corresponding to the heat exchange medium microchannel, so that the heat exchange medium microchannel is connected with the corresponding heat exchange medium flow channel through the avoidance holes.

[0009] Optionally, along the stacking direction of the partitions, the flow balancing fins in two adjacent layers of the air flow channels are arranged correspondingly;

[0010] And / or, a plurality of the heat exchange medium microchannels are provided in the heat exchange fin body, and the plurality of the 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 main surface and a second outer main surface arranged opposite to each other, and the first outer main surface and the second outer main surface protrude in directions away from each other to form a streamlined arc surface;

[0012] In the extending direction of the air flow channel, one end of the first outer main body surface is connected to one end of the second outer main body surface, and the other end of the first outer main body surface is connected to the other end of the second outer main body surface.

[0013] Optionally, the first outer main body surface and / or the second outer main body surface is 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, a middle section and an outlet section connected in sequence;

[0015] In the direction from the inlet section to the middle section, the cross-sectional area of ​​the inlet section gradually decreases; in the direction from the middle section to the outlet section, the cross-sectional area of ​​the outlet section gradually increases;

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

[0017] Optionally, the aircraft pre-cooling heat exchanger further includes a flow diverter;

[0018] The diversion inlet of the diversion diverter is connected to the heat exchange medium supply pipeline, and the diversion diverter has a plurality of diversion branches respectively connected to the diversion inlet, and each of the diversion branches corresponds to at least two layers of the heat exchange medium flow channels.

[0019] Optionally, a lattice fin is provided in the heat exchange medium flow channel, and the lattice fin is supported between two adjacent partitions.

[0020] Optionally, the lattice fin comprises 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 convergence point, and the ends of the plurality of support rods that are away from the central convergence point are in contact with corresponding partitions respectively to be supported between two adjacent partitions.

[0022] Optionally, among all the support rods, a reinforcing rod is connected between the ends of at least two adjacent support rods away from the central confluence point, and the reinforcing rod is arranged parallel to the partition and fits with the partition.

[0023] In a second aspect, the present disclosure provides an aircraft, comprising the aircraft pre-cooling heat exchanger as described above.

[0024] The aircraft pre-cooling heat exchanger and aircraft provided in the embodiments of the present disclosure are provided with at least three stacked and spaced partitions, so that among every three adjacent partitions, an air flow channel is formed between two adjacent partitions, and a heat exchange medium flow channel is formed between the other two adjacent partitions. The air flow channel and the heat exchange medium flow channel are arranged perpendicularly, thereby improving heat exchange efficiency.

[0025] By setting the partition as a curved partition, the heat exchange medium flow channel is formed into a wavy flow channel. In this way, when the outer contour volume of the heat exchanger remains unchanged, the wavy flow channel increases the primary surface heat exchange area compared to the straight flow channel, thereby improving the heat exchange efficiency of the heat exchange medium; by setting the first heat exchange fin group and the second heat exchange fin group in the air flow channel, the contact area between the air and the heat exchanger is increased, and the heat exchange efficiency is further improved; at the same time, by making the second heat exchange fin group include a plurality of spaced flow-equalizing fins, the flow-equalizing fins include a heat exchange fin body supported in the air flow channel and a heat exchange medium microchannel set through the heat exchange fin body, and the heat exchange medium microchannel is respectively connected to the two adjacent heat exchange medium flow channels, thereby improving the flow distribution of the heat exchange medium between the heat exchanger layers, improving the uniformity of heat exchange, and exchanging heat with the air through the cooperation of the heat exchange medium flow channel and the flow-equalizing fins, thereby further improving the heat exchange efficiency. Moreover, the flow-balancing fins also support the air flow channel to a certain extent, thereby improving the impact resistance and stability of the air flow channel to the airflow, thereby improving the stability and service life of the pre-cooling heat exchanger structure.

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

[0027] 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

[0028] The above and other purposes, features, and advantages of the present disclosure will become more apparent through a more detailed description of the embodiments of the present disclosure in conjunction with the accompanying drawings. The accompanying drawings are intended to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and are not intended to limit the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0029] Figure 1 A schematic structural diagram of a pre-cooling heat exchanger for an aircraft according to an embodiment of the present disclosure;

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

[0031] Figure 3 A schematic structural diagram of a flow-sharing fin in a pre-cooling heat exchanger for an aircraft according to an embodiment of the present disclosure;

[0032] Figure 4 A partial structural cross-sectional view of a pre-cooling heat exchanger for an aircraft provided in one embodiment of the present disclosure;

[0033] Figure 5 A schematic structural diagram of a lattice fin in a pre-cooling heat exchanger for an aircraft according to an embodiment of the present disclosure;

[0034] Figure 6 This is a schematic structural diagram of a flow guide and diverter in a pre-cooling heat exchanger for an aircraft provided in one embodiment of the present disclosure.

[0035] Among them, 1. partition; 11. air flow channel; 12. heat exchange medium flow channel; 13. avoidance hole; 2. first heat exchange fin group; 21. heat exchange fin; 3. second heat exchange fin group; 31. flow balancing fin; 311. heat exchange fin body; 312. first outer main body surface; 313. second outer main body surface; 314. heat exchange medium microchannel; 315. inlet section; 316. middle section; 317. outlet section; 4. lattice fin; 41. support rod; 42. central confluence point; 43. reinforcement rod; 5. diverter; 51. diverter inlet; 52. diversion branch; 6. end plate; 61. inlet pipe; 62. outlet pipe. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the present disclosure more apparent, the following will describe in detail exemplary embodiments of the present disclosure with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described herein.

[0037] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". The relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0038] It should be noted that the modifications of "one" and "multiple" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, they should be understood as "one or more".

[0039] Reference Figures 1 to 5 As shown, an embodiment of the present disclosure provides a pre-cooling heat exchanger for an aircraft, comprising at least three stacked and spaced partitions 1 .

[0040] Among 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 partitions 1, and the heat exchange medium flow channel 12 is arranged along a second direction of the partitions 1. The first direction and the second direction are perpendicular.

[0041] The first direction may be, for example, the width direction of the partition 1, such as Figure 1 and Figure 2 The second direction may be the length direction of the partition 1, for example Figure 1 and Figure 2 The direction shown by YY in .

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

[0043] In a specific implementation, end plates 6 are provided on both sides of the partition 1 along the second direction, and the ends of the adjacent partitions 1 are sealed by the end plates 6 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 communicate 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 process, the heat exchange medium exchanges heat with the air in the adjacent air flow channel 11, absorbs the heat of the air, and cools the air. The heat exchange medium after heat exchange is finally discharged from the outlet pipe 62, for example, after cooling, it re-enters the heat exchange medium supply pipeline, thereby realizing the recycling of the heat exchange medium and saving costs.

[0044] For example, the heat exchange medium may 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 may also be a sodium-potassium alloy, a lead-bismuth alloy, etc. In addition, the heat exchange medium may also be a gaseous heat exchange medium, etc.

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

[0046] Partition 1 is curved, forming a wavy heat exchange medium flow path 12. By creating a curved partition 1, the wavy heat exchange medium flow path 12 increases the primary surface heat exchange area and improves the heat exchange efficiency of the heat exchange medium. Because air flow path 11 is perpendicular to heat exchange medium flow path 12, air flows straight through the heat exchanger along air flow path 11, reducing air-side pressure loss. This improves heat exchange efficiency while also reducing air-side pressure loss.

[0047] For example, the curvature radius of the wavy surface of the partition 1 satisfies the condition of non-separation of the heat exchange medium flow (eg, curvature radius R≥5D, where D is the hydraulic diameter of the flow channel). For example, the curvature radius of the wavy partition is R=6D=12 mm.

[0048] According to tests, the wavy heat exchange medium flow channel 12 increases the primary surface heat exchange area by about 20% to 40% compared with the straight flow channel at the same volume.

[0049] The air flow 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 air flow channel 11. Specifically, the plurality of heat exchange fins 21 are arranged in parallel in the air flow 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 air flow channel 11 is transferred to the partition 1 and the heat exchange fins 21. The heat is then transferred to the heat exchange medium in the adjacent heat exchange medium flow channel 12 through the partition 1 and the heat exchange fins 21, thereby cooling the air and improving the heat exchange efficiency.

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

[0051] Specifically, the second heat exchange fin group 3 includes a plurality of flow-balancing fins 31 arranged at intervals in the air flow channel 11, and the flow-balancing fins 31 include a heat exchange fin body 311 supported in the air flow channel 11 and a heat exchange medium microchannel 314 arranged 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 flow 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 flow channel 12 adjacent to the air flow channel 11.

[0052] This arrangement 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 setting the heat exchange medium microchannel 314 as above, the flow distribution of the heat exchange medium between the heat exchanger layers is improved, and uniform flow is achieved, thereby improving the heat exchange uniformity. The heat exchange of the air is carried out through the cooperation of the heat exchange medium flow channel 12 and the flow equalizing fin 31, further improving the heat exchange efficiency.

[0053] The curved partitions and the flow-balancing fins 31 cooperate to increase the primary surface heat exchange area, thereby improving the heat transfer coefficient on the heat exchange medium side and enhancing the overall heat exchange efficiency.

[0054] In specific implementation, the partition 1 and the heat exchange fin body 311 can be made of nickel-based high-temperature alloy (such as Inconel718, GH3625) to improve the structural strength of the partition 1 and the heat exchange fin body 311 and the corrosion resistance to the heat exchange medium.

[0055] The aircraft pre-cooling heat exchanger provided in the embodiment of the present disclosure is provided with at least three stacked and spaced partitions 1, so that among 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 another two adjacent partitions 1. The air flow channel 11 and the heat exchange medium flow channel 12 are arranged perpendicularly, thereby improving heat exchange efficiency.

[0056] Moreover, by setting the partition 1 as a curved partition, the heat exchange medium flow channel 12 is formed into a wavy flow channel. In this way, when the outer contour volume of the heat exchanger remains unchanged, the wavy flow channel increases the primary surface heat exchange area compared with the straight flow channel, 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, and the heat exchange efficiency is further improved; at the same time, by making the second heat exchange fin group 3 include multiple The flow-balancing fins 31 are arranged at intervals, so that the flow-balancing fins 31 include a heat exchange fin body 311 supported in the air flow channel 11 and a heat exchange medium microchannel 314 provided through the heat exchange fin body 311. The heat exchange medium microchannel 314 is connected to two adjacent heat exchange medium flow channels 12, thereby improving the flow distribution of the heat exchange medium between the heat exchanger layers and improving the uniformity of heat exchange. The heat exchange efficiency is further improved by the coordinated heat exchange of air through the heat exchange medium flow channels 12 and the flow-balancing fins 31. In addition, the flow-balancing fins 31 also play a supporting role for the air flow channel 11 to a certain extent, improving the impact resistance and stability of the air flow channel 11 to the airflow, and improving 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 wavy heat exchange medium flow channel 12, the air can pass through the heat exchanger straight along the air flow channel 11 between the two partitions 1, thereby reducing the pressure loss on the air side to a certain extent.

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

[0059] Combine Figure 1 、 Figure 2 and Figure 4 As shown, in some embodiments, along the stacking direction of the partition 1 , the flow balancing fins 31 in two adjacent layers of air flow channels 11 are arranged correspondingly.

[0060] That is to say, a second heat exchange fin group 3 can be set in each layer of the air flow channel 11, and the second heat exchange fin group 3 of each layer can include one or more flow balancing fins 31. When multiple flow balancing fins 31 are set in each layer, the multiple flow balancing fins 31 are arranged at intervals in the air flow channel 11.

[0061] By arranging the flow balancing fins 31 in two adjacent layers of air flow channels 11 in correspondence, 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 contacts one of the partitions 1 corresponding to the air flow channel 11, and the outlet end of the heat exchange medium microchannel 314 contacts the other partition 1 corresponding to the air flow channel 11, and the two partitions 1 of the air flow channel 11 are provided with avoidance holes 13 at the positions corresponding to the heat exchange medium microchannel 314, so that the heat exchange medium microchannel 314 is connected with the corresponding heat exchange medium flow channel 12 through the avoidance holes 13.

[0063] This arrangement allows the two ends of the heat exchange medium microchannel 314 to be directly aligned and connected with the two adjacent heat exchange medium flow channels 12, without the need to set up structures such as connecting pipes, so that the heat exchange medium can flow smoothly between the heat exchange medium flow channels 12 and the heat exchange medium microchannel 314, thereby improving the heat exchange efficiency and 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 , and 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 arrangement improves the heat exchange effect at different locations of the air flow channel 11, further enhancing the uniformity of flow distribution between layers and the heat exchange efficiency. Furthermore, even if a microchannel becomes clogged, the heat exchange medium can flow between the 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 main surface 312 and a second outer main surface 313 disposed opposite each other. The first outer main surface 312 and the second outer main surface 313 protrude away from each other to form a streamlined arc-shaped surface. In the direction extending along the air flow channel 11, one end of the first outer main surface 312 is connected to one end of the second outer main surface 313, and the other end of the first outer main surface 312 is connected to the other end of the second outer main surface 313.

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

[0068] In some embodiments, a hydrophobic coating is applied to both the first outer surface 312 and the second outer surface 313. By applying the hydrophobic coating to the first outer surface 312 and the second outer surface 313, 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 flow balancing fins 31.

[0069] For example, the hydrophobic coating may be made of polytetrafluoroethylene, but the hydrophobic coating may also be made of other materials such as a silicone resin-based coating, and the embodiments of the present disclosure are not limited thereto.

[0070] In addition, the hydrophobic coating may be applied only on the first outer main surface 312 or only on the second outer main surface 313 .

[0071] In some embodiments, reference 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 , a middle section 316 and an outlet section 317 that are connected in sequence.

[0072] The cross-sectional area of ​​the inlet section 315 gradually decreases from the inlet section 315 to the middle section 316 to reduce the flow rate, while the cross-sectional area of ​​the outlet section 317 gradually increases from the middle section 316 to the outlet section 317 to balance the pressure.

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

[0074] The cross-sectional area of ​​the middle section 316 is uniform 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 inlet section 315 , the area expansion ratio of the inlet section 315 can be set to 1:1.5), and in the direction from the outlet section 317 to the middle section 316 , the area contraction ratio of the outlet section 317 can be set to 1.2:1.

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

[0077] The flow-balancing fins 31 feature a streamlined shape and finely structured heat exchange medium microchannels 314. By precisely controlling the area, shape, and orientation of the microchannels, and taking into account the relationship between the inertial effect and viscous resistance of the heat exchange medium, such as liquid metal, a flow channel resistance gradient compensation strategy is introduced to achieve uniform distribution of liquid metal flow between layers. This flow-balancing design eliminates the need for traditional head structures, resulting in a more streamlined and lightweight pre-cooling heat exchanger.

[0078] Reference Figure 6 As shown, in some embodiments, the aircraft pre-cooling heat exchanger further includes a flow diverter 5. The flow diverter inlet 51 of the flow diverter 5 is connected to the heat exchange medium supply pipeline, and the flow diverter 5 has multiple flow diversion branches 52, each connected to the flow diversion inlet 51. The number of flow diversion branches can be four or five, for example, and is not specifically limited in the present embodiment. Each flow diversion branch 52 corresponds to at least two layers of heat exchange medium flow channels 12.

[0079] This arrangement further improves the inter-layer flow uniformity of the heat exchanger, thereby further improving the uniformity of heat exchange and further improving the heat exchange efficiency.

[0080] By combining the heat exchange medium microchannel 314 in the flow-balancing fin 31 and the flow diverter 5, the inter-layer flow distribution and the increase of the primary heat exchange area are further achieved. There is no need for the traditional bulky head that occupies a large space, which is conducive to the compact and lightweight development of the heat exchanger, making the heat exchanger particularly suitable for application scenarios such as aerospace that are extremely sensitive to size and quality.

[0081] For example, the flow guide and diverter 5 can be configured as a converging-diverging circular tube, with spiral guide vanes arranged on the wall of the diverging section to impart a circumferential velocity component to the heat exchange medium, suppressing flow fluctuations caused by pumping pulsation. Multiple outlets are arranged circumferentially at the outlet of the guide vane section, connecting to each diversion branch 52. The apertures of these multiple outlets vary and are optimized using computational fluid dynamics (CFD), taking into account factors such as the delivery length and elbow layout of each downstream diversion branch 52 to ensure that the flow rate of each diversion branch 52 is substantially uniform.

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

[0083] This enables the lattice fins 4 to stably support the heat exchange medium flow channel 12, improves the structural strength of the heat exchange medium flow channel 12, avoids the risk of damage to the partition 1 corresponding to the heat exchange medium flow channel 12 under the pressure and flow impact of the heat exchange medium, and extends the service life of the pre-cooling heat exchanger.

[0084] In a specific implementation, a plurality of lattice fins 4 may be provided in the heat exchange medium flow channel 12 , and the plurality of lattice fins 4 are arranged at intervals in the heat exchange medium flow channel 12 .

[0085] Combine Figure 4 and Figure 5 As shown, in some embodiments, the lattice fin 4 includes a plurality of support rods 41 arranged in a radial pattern.

[0086] The ends of the support rods 41 that are close to each other are connected to the central convergence point 42 , and the ends of the support rods 41 that are away from the central convergence point 42 are in contact with the corresponding partitions 1 respectively to be supported between two adjacent partitions 1 .

[0087] This arrangement enables 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 not prone to deformation and structural failure, thereby providing better stable support for the heat exchange medium flow channel 12, thereby ensuring stable and reliable operation of the partition 1 under harsh fluid conditions and extending the service life of the pre-cooling heat exchanger.

[0088] For example, the unit cell size of the lattice fin 4 is not greater than 2mm×2mm×2mm, the rod diameter of the support rod 41 is, for example, not 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 flow channel 12 by, for example, 3D printing.

[0089] Further, continue to refer to Figure 5 As shown, in some embodiments, among all the support rods 41, at least two adjacent support rods 41 are further connected with a reinforcing rod 43 between their ends away from the central convergence point 42, and the reinforcing rod 43 is arranged parallel to the partition 1 and fits with the partition 1.

[0090] This arrangement further improves the structural strength of the lattice fins 4, thereby further improving the supporting effect of the lattice fins 4 on the heat exchange medium flow channel 12, while enabling the heat exchange medium to quickly transfer heat to the air, further improving the heat exchange efficiency.

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

[0092] The present disclosure also provides an aircraft comprising an engine and a pre-cooling heat exchanger. The pre-cooling heat exchanger is located on the engine's air intake side and is used to cool the intake air, thereby reducing the temperature of the engine's inlet airflow. This offsets the increase in intake air temperature caused by aerodynamic heating during high-speed flight, allowing the engine to fly at higher speeds.

[0093] The specific structure and implementation principle of the pre-cooling heat exchanger in this embodiment are the same as those of the pre-cooling heat exchanger for aircraft provided in the above embodiment, and can bring the same or similar technical effects. They will not be described one by one here, and please refer to the description of the above embodiment for details.

[0094] The above descriptions are merely some embodiments of the present disclosure and an illustration of the technical principles employed. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above-mentioned technical features, but also encompasses other technical solutions formed by any combination of the above-mentioned technical features or their equivalents without departing from the above-mentioned disclosed concepts. For example, a technical solution formed by replacing the above-mentioned features with (but not limited to) technical features with similar functions disclosed in the present disclosure.

[0095] Although some specific embodiments of the present disclosure have been described in detail by way of examples, those skilled in the art will appreciate that the above examples are for illustrative purposes only and are not intended to limit the scope of the present disclosure. Those skilled in the art will appreciate that modifications may be made to the above embodiments without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A pre-cooling heat exchanger for an aircraft, characterized in that: The invention comprises at least three stacked and spaced partitions, wherein an air flow channel is formed between two adjacent partitions of each three adjacent partitions, and a heat exchange medium flow channel is formed between another two adjacent partitions, wherein 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; The partition is a curved partition, so that the heat exchange medium flow channel is formed into a wavy flow channel; A first heat exchange fin group and a second heat exchange fin group are provided in the air flow channel, the first heat exchange fin group includes a plurality of heat exchange fins arranged at intervals in the air flow channel; the second heat exchange fin group includes a plurality of flow balancing fins arranged at intervals in the air flow channel, the flow balancing fins include a heat exchange fin body supported in the air flow channel and a heat exchange medium microchannel provided in the heat exchange fin body, the inlet end of the heat exchange medium microchannel is communicated with one of the heat exchange medium flow channels adjacent to the air flow channel, and the outlet end of the heat exchange medium microchannel is communicated with another heat exchange medium flow channel adjacent to the air flow channel.

2. The aircraft pre-cooling heat exchanger according to claim 1, characterized in that: The inlet end of the heat exchange medium microchannel contacts one of the partitions corresponding to the air flow channel, and the outlet end of the heat exchange medium microchannel contacts the other of the partitions corresponding to the air flow channel, and avoidance holes are provided at the positions of the two partitions of the air flow channel corresponding to the heat exchange medium microchannel, so that the heat exchange medium microchannel is connected with the corresponding heat exchange medium flow channel through the avoidance holes.

3. The aircraft pre-cooling heat exchanger according to claim 1, characterized in that: In the stacking direction of the partitions, the flow balancing fins in two adjacent layers of the air flow channels are arranged correspondingly; And / or, a plurality of the heat exchange medium microchannels are provided in the heat exchange fin body, and the plurality of the heat exchange medium microchannels are arranged at intervals along the extension direction of the air flow channel and are arranged in parallel.

4. The aircraft pre-cooling heat exchanger according to claim 1, characterized in that: The heat exchange fin body comprises a first outer main surface and a second outer main surface arranged opposite to each other, wherein the first outer main surface and the second outer main surface protrude in directions away from each other to form a streamlined arc surface; In the extending direction of the air flow channel, one end of the first outer main body surface is connected to one end of the second outer main body surface, and the other end of the first outer main body surface is connected to the other end of the second outer main body surface.

5. The aircraft pre-cooling heat exchanger according to claim 4, characterized in that: The first outer main body surface and / or the second outer main body surface is covered with a hydrophobic coating.

6. The aircraft pre-cooling heat exchanger according to claim 1, characterized in that: In the extension direction of the heat exchange medium microchannel, the heat exchange medium microchannel includes an inlet section, a middle section and an outlet section connected in sequence; In the direction from the inlet section to the middle section, the cross-sectional area of ​​the inlet section gradually decreases; in the direction from the middle section to the outlet section, the cross-sectional area of ​​the outlet section gradually increases; The cross-sectional area of ​​the intermediate section is equal everywhere along the direction from the inlet section to the outlet section.

7. The aircraft pre-cooling heat exchanger according to any one of claims 1 to 6, characterized in that: The aircraft pre-cooling heat exchanger further includes a flow guide and diverter; The diversion inlet of the diversion diverter is connected to the heat exchange medium supply pipeline, and the diversion diverter has a plurality of diversion branches respectively connected to the diversion inlet, and each of the diversion branches corresponds to at least two layers of the heat exchange medium flow channels.

8. The aircraft pre-cooling heat exchanger according to any one of claims 1 to 6, characterized in that: A lattice fin is provided in the heat exchange medium flow channel, and the lattice fin is supported between two adjacent partitions.

9. The aircraft pre-cooling heat exchanger according to claim 8, characterized in that: The lattice fin comprises a plurality of support rods arranged in a radial shape; The ends of the plurality of support rods that are close to each other are connected to a central convergence point, and the ends of the plurality of support rods that are away from the central convergence point are respectively in contact with corresponding partitions to support between two adjacent partitions; Among all the support rods, at least two adjacent support rods are further connected with a reinforcing rod between their ends away from the central convergence point. The reinforcing rod is arranged parallel to the partition and fits with the partition.

10. An aircraft, characterized in that: The invention comprises the aircraft pre-cooling heat exchanger according to any one of claims 1 to 9.

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