Cooler, cooling structure, and aircraft

Abstract

The application relates to a cooler, a cooling structure and an aircraft. The cooler comprises an inlet liquid collecting chamber, an outlet liquid collecting chamber and flat tubes. The inlet liquid collecting chamber and the outlet liquid collecting chamber are arranged at two ends of the outer periphery of the cooler. The two ends of the plurality of flat tubes are communicated with the inlet liquid collecting chamber and the outlet liquid collecting chamber. Adjacent flat tubes are arranged at intervals to form heat dissipation gaps for passing air flow. The inlet liquid collecting chamber and the outlet liquid collecting chamber are arranged to form an air guide opening. The plurality of flat tubes are bent and protruded towards the same side of the air guide opening to form a heat dissipation groove communicated with the air guide opening. The windward surface area of the heat dissipation groove is greater than the flow area of the air guide opening. The cooler, the cooling structure and the aircraft provided by the application solve the problems of small heat dissipation area, large volume and large weight of the oil cooler.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a cooler, a cooling structure, and an aircraft. Background Technology

[0002] In existing rotorcraft, the cooling of the rotor (propeller) electric drive system (which can be simply understood as an electric drive system that integrates motors, reducers, controllers, etc. into one unit) mainly utilizes oil coolers for single-phase oil cooling. The oil cooler is usually located inside the rotor nacelle and is wrapped on the outside of the rotor nacelle skin. In addition, an auxiliary electric fan is also installed inside the rotor nacelle to cool the oil cooler.

[0003] One type of oil cooler (the first type) is usually ring-shaped and surrounds the perimeter of the cabin, while the other type of oil cooler (the second type) is disc-shaped and located at the air outlet of the electric fan. The first type of oil cooler has a smaller heat dissipation area (the middle part is occupied by the cabin), which leads to lower heat dissipation efficiency. The second type of oil cooler adds an electric fan, which increases its size and weight, which is not conducive to the lightweight and compact design of the aircraft. Utility Model Content

[0004] Therefore, it is necessary to provide a cooler, a cooling structure, and an aircraft to solve the problems of existing oil coolers having a small heat dissipation area and large size and weight.

[0005] The cooler provided in this application includes an inlet manifold, an outlet manifold, and flat tubes. The inlet manifold and outlet manifold are respectively located at both ends of the outer periphery of the cooler. The two ends of multiple flat tubes are respectively connected to the inlet manifold and the outlet manifold. Adjacent flat tubes are spaced apart to form a heat dissipation gap for airflow. The inlet manifold and outlet manifold are defined to form an air guide. Multiple flat tubes are bent and protruded towards the same side of the air guide to form a heat dissipation groove that connects to the air guide. The windward surface area of ​​the heat dissipation groove is larger than the flow area of ​​the air guide.

[0006] In one embodiment, the cooler is spherical and bowl-shaped, with the inlet and outlet manifolds and the flat tubes all being arc-shaped. The inlet and outlet manifolds are located at the opening edge of the bowl-shaped cooler, the air vents form the bowl mouth of the bowl-shaped cooler, and multiple flat tubes surround the bowl body of the bowl-shaped cooler.

[0007] This application also provides a cooling structure, which includes an electric drive device, a shroud, and a cooler as described in any of the above embodiments. The cooler is disposed on one side of the electric drive device, and the flat tube of the cooler is bent away from the electric drive device. The shroud is disposed on the side of the electric drive device facing the cooler and protrudes towards the cooler. The inner surface of the heat dissipation groove and the protruding surface of the shroud are spaced apart to form a rectifier cavity that connects the heat dissipation gap.

[0008] In one embodiment, the cooling structure further includes a guide ring, a housing, and a propeller. The electric drive unit is installed inside the housing, the propeller is connected to the output end of the electric drive unit, the cooler is located on the leeward side of the electric drive unit, one end of the guide ring is connected to and fitted on the outer periphery of the inlet and outlet liquid collection chambers, and the other end extends toward the direction close to the electric drive unit and is fitted on the outer periphery of the housing. The guide ring and the housing are spaced apart to form an external flow guide gap that connects to the rectifier cavity, and the propeller is located on the windward side of the external flow guide gap.

[0009] In one embodiment, the air guide ring is a heat-conducting element so that the heat of the heat-conducting medium in the cooler can be transferred to the atmospheric environment through the air guide ring.

[0010] In one embodiment, the air guide ring is welded to the outer periphery of the inlet and outlet liquid collection chambers.

[0011] In one embodiment, the air guide ring is bonded to the outer periphery of the inlet and outlet liquid collection chambers via a thermal interface material layer.

[0012] In one embodiment, the cooling structure further includes a housing portion, an electric drive unit and a cooler are respectively installed in the housing portion, the cooler is disposed on the windward side of the electric drive unit, and an annular internal flow guide gap is provided between the housing portion and the electric drive unit so that the airflow passing through the cooler can be guided into the internal flow guide gap through the surface of the shroud.

[0013] In one embodiment, the periphery of the housing portion is provided with a side vent, so that airflow passing through the internal guide gap can enter the atmospheric environment through the side vent.

[0014] In one embodiment, the tail end of the housing is provided with a tail vent so that airflow passing through the internal guide gap can enter the atmospheric environment through the tail vent.

[0015] This application also provides an aircraft that includes the cooling structure described in any of the above embodiments.

[0016] Compared with existing technologies, the cooler, cooling structure, and aircraft provided in this application, specifically, have a cooling medium that is diverted from the inlet manifold to each flat tube. As it flows through the flat tubes, it exchanges heat with the external airflow and finally converges into the outlet manifold. The heat dissipation grooves formed by the bending of the flat tubes create a diffusion zone in the airflow path. The airflow velocity decreases after entering the air guide, creating turbulence within the heat dissipation grooves to enhance heat exchange. The design of the heat dissipation groove surface area being larger than the air guide area allows the airflow to diffuse within the grooves, extending the residence time and improving heat exchange efficiency. The heat dissipation gaps between adjacent flat tubes form parallel flow channels, ensuring full contact between the airflow and the flat tube surface as it passes through, achieving multi-channel synchronous heat dissipation.

[0017] Compared to existing technologies, annular oil coolers are limited by the cabin structure, which restricts the expansion of the central heat dissipation area. This solution uses bent flat tubes to form a three-dimensional heat dissipation structure, achieving a larger effective heat dissipation surface area within the same projected area. Unlike disc-shaped oil coolers that rely on forced convection from fans, this solution utilizes the natural airflow generated by the aircraft's motion to achieve efficient heat dissipation, significantly reducing system weight by eliminating the need for fan components. The air vents formed by the bent flat tubes and the heat dissipation slots constitute a continuous flow channel, avoiding airflow separation issues associated with traditional planar layouts and improving aerodynamic heat transfer efficiency.

[0018] Through the above technical solution, this application effectively improves the heat dissipation efficiency of the cooler by optimizing the spatial arrangement of the cooling structure without the need for additional auxiliary heat dissipation devices. The heat dissipation grooves formed by the bent flat tubes expand the airflow contact area, and together with the synergistic effect of the air guide and heat dissipation gaps, enhance the natural convection heat transfer effect. This structure is particularly suitable for space-constrained aircraft scenarios, achieving efficient heat dissipation while maintaining a compact size, and resolving the contradiction between insufficient heat dissipation area and bulky system of traditional oil coolers. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application or the conventional technology, the drawings used in the description of the embodiments or the conventional technology will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A schematic diagram of the structure of a cooler according to an embodiment of this application;

[0021] Figure 2 This is a schematic diagram of the cooling structure of Embodiment 1 provided in this application;

[0022] Figure 3 A side view of the cooling structure of Embodiment 1 provided in this application;

[0023] Figure 4 for Figure 3 A partial sectional view at point AA shown;

[0024] Figure 5 This is a schematic diagram of the cooling structure of Embodiment 2 provided in this application;

[0025] Figure 6 A partial cross-sectional view of the cooling structure of Embodiment 2 provided in this application.

[0026] Reference numerals: 110, shell section; 111, tail exhaust port; 112, internal flow guide gap; 120, electric drive unit; 200, cooler; 210, inlet liquid collection chamber; 220, outlet liquid collection chamber; 230, flat tube; 240, heat dissipation gap; 250, fin; 260, air guide; 270, heat dissipation groove; 280, rectifier cavity; 300, propeller; 400, flow guide shroud; 500, air guide ring; 510, external flow guide gap; 600, rectifier shroud. Detailed Implementation

[0027] Please see Figures 1-6 This application provides a cooling structure for dissipating heat from the electric drive system of various aircraft such as UAVs. The cooling structure includes an electric drive bay, a cooler 200, a fairing 600, a wind deflector 500, a propeller 300, and a fairing 400. The electric drive bay includes a housing portion 110 and an electric drive device 120. The electric drive device 120 is the power source that drives the propeller 300 to rotate. The electric drive device 120 is installed in the housing portion 110, which is cylindrical or flat cylindrical in shape. The electric drive device 120 mainly includes a drive motor, a reducer, and a controller. Among these, the stator of the drive motor generates the most heat. Therefore, the cooler 200 mainly dissipates heat from the stator of the drive motor. Of course, it can also dissipate heat from other heat sources (including but not limited to IGBT modules, SiC MOSFETs, reducers, controllers, and other parts of the drive motor). The fairing 400 is located at the front of the electric drive bay (i.e., the front of the aircraft, the end closest to the windward side), serving to reduce wind resistance and protect the front-end components (including various sensors). The propeller 300 is connected to the output end of the electric drive bay (i.e., the electric drive unit 120) so that the electric drive unit 120 can drive the propeller 300 to rotate.

[0028] Cooler 200 refers to a heat exchange device, specifically a finned radiator 250, which is fixed to the aircraft by welding or bolting. Specifically, the working principle of cooler 200 is as follows: a heat-conducting medium directly or indirectly contacts the heat source (such as the stator winding of a drive motor, IGBT module, or semiconductor power switching devices like SiC MOSFETs) within the electric drive unit 120, absorbing the heat generated by the heat source. Then, the heat-conducting medium (mainly heat-conducting oil, but also deionized water, ethylene glycol aqueous solution, or other novel heat-conducting media) is pumped into cooler 200. The heat-conducting medium circulates between cooler 200 and the heat source of electric drive unit 120 to transfer heat from electric drive unit 120 to cooler 200. Furthermore, cooler 200 can utilize the oncoming airflow generated during flight or the airflow generated by propeller 300 to dissipate the heat in the heat-conducting medium into the atmosphere. The cooled heat-conducting medium then circulates back into the heat source of electric drive unit 120 to continue absorbing heat.

[0029] like Figure 1 , Figure 4 and Figure 6 As shown, the cooler 200 includes an inlet manifold 210, an outlet manifold 220, and flat tubes 230. The inlet manifold 210 is located at one end of the outer periphery of the cooler 200, and the outlet manifold 220 is located at the other end of the outer periphery of the cooler 200. The two ends of the multiple flat tubes 230 are respectively connected to the inlet manifold 210 and the outlet manifold 220. The heat-conducting medium in the inlet manifold 210 enters the outlet manifold 220 through the multiple flat tubes 230. Adjacent flat tubes 230 are spaced apart to form heat dissipation gaps 240 for airflow. In order to enhance the heat dissipation effect, the heat dissipation gaps 240 are also provided with multiple fins 250 arranged at intervals along the extension direction of the flat tubes 230. Furthermore, the inlet manifold 210 and the outlet manifold 220 are defined to form an air guide 260. Multiple flat tubes 230 are bent and protruded towards the same side of the air guide 260 to form a heat dissipation groove 270 communicating with the air guide 260. The windward surface area of ​​one side of the heat dissipation groove 270 is larger than the flow area of ​​the air guide 260. It should be noted that along the direction from the inlet manifold 210 to the outlet manifold 220, each flat tube 230 first extends away from the air guide 260, and then extends towards the air guide 260. Furthermore, the degree of bending of each flat tube 230 is different; the flat tubes 230 in the middle region have a greater degree of bending, while the flat tubes 230 on both sides have a smaller degree of bending.

[0030] Specifically, the cooling medium is diverted from the inlet manifold 210 to each flat tube 230. As it flows through the flat tubes 230, it exchanges heat with the external airflow and finally converges in the outlet manifold 220. The heat dissipation grooves 270 formed by the bends of the flat tubes 230 create a diffusion zone in the airflow path. After entering the air guide 260, the airflow velocity decreases, creating turbulence within the heat dissipation grooves 270 to enhance heat exchange. The design of the heat dissipation grooves 270 having a larger surface area than the air guide 260 allows the airflow to diffuse within the grooves, extending the residence time and improving heat exchange efficiency. The heat dissipation gaps 240 between adjacent flat tubes 230 form parallel flow channels, ensuring full contact between the airflow and the surface of the flat tubes 230 as it passes through, achieving multi-channel synchronous heat dissipation.

[0031] Compared to existing technologies, annular oil coolers are limited by the cabin structure, which restricts the expansion of the central heat dissipation area. This solution uses a bent flat tube 230 to form a three-dimensional heat dissipation structure, achieving a larger effective heat dissipation surface within the same projected area. Unlike disc-shaped oil coolers that rely on forced convection from fans, this solution utilizes the natural airflow generated by the aircraft's motion to achieve efficient heat dissipation, significantly reducing system weight by eliminating the need for a fan assembly. The air vent 260 formed by the bending of the flat tube 230 and the heat dissipation slot 270 constitute a continuous flow channel, avoiding airflow separation issues common in traditional planar layouts and improving aerodynamic heat transfer efficiency.

[0032] Through the above technical solution, this application effectively improves the heat dissipation efficiency of the cooler 200 by optimizing the spatial arrangement of the cooling structure without adding auxiliary heat dissipation devices. The heat dissipation groove 270 formed by the bent flat tube 230 expands the airflow contact area, and in conjunction with the synergistic effect of the air guide 260 and the heat dissipation gap 240, it enhances the natural convection heat transfer effect. This structure is particularly suitable for space-constrained aircraft scenarios, achieving efficient heat dissipation while maintaining a compact size, and solving the contradiction between insufficient heat dissipation area and bulky system of traditional oil coolers.

[0033] Specifically, in one embodiment, the cooler 200 is spherical bowl-shaped, and the liquid inlet manifold 210, the liquid outlet manifold 220 and the flat tube 230 are all arc-shaped (including but not limited to circular arc, elliptical arc or other curved shape). The liquid inlet manifold 210 and the liquid outlet manifold 220 are located at the opening edge of the bowl-shaped cooler 200, the air guide 260 forms the bowl mouth of the bowl-shaped cooler 200, and the multiple flat tubes 230 surround to form the bowl body of the bowl-shaped cooler 200.

[0034] Specifically, the spherical bowl-shaped structure arranges the inlet manifold 210 and outlet manifold 220 at the edge of the opening, allowing the flat tube 230 to extend along a curved surface to form the bowl body. After entering the flat tube 230 from the inlet manifold 210, the liquid flows along an arc-shaped path to the outlet manifold 220, during which heat is transferred through the wall of the flat tube 230 to the heat dissipation gap 240. The air guide 260, acting as the bowl opening, is directly connected to the external airflow, which carries away heat as it passes through the heat dissipation gap 240. The arc-shaped arrangement of the flat tubes 230 creates a continuous curved channel in the heat dissipation gap 240, increasing the airflow path length and ensuring a uniform flow velocity distribution.

[0035] Compared with existing technologies, this solution uses a bowl-shaped structure to cover the entire curved surface area with the flat tube 230, significantly increasing the heat dissipation area. The bowl-shaped structure effectively increases the arrangement space of the flat tube 230 through curved surface extension, and the continuous heat dissipation gap 240 formed by the arc-shaped flat tube 230 optimizes airflow distribution. The edge layout of the liquid inlet collection chamber 210 and the liquid outlet collection chamber 220 reduces the occupation of the central area, achieving higher heat dissipation efficiency in the same volume, while avoiding the addition of extra components and meeting the lightweight requirements of the aircraft.

[0036] However, this is not the only one. In other embodiments, the inlet manifold 210 and the outlet manifold 220 may also be polygonal, which can be adjusted according to the specific situation. The cooler 200 may also be cubic or other shapes, which will not be listed here.

[0037] In one embodiment, such as Figure 4 and Figure 6 As shown, the cooler 200 is located on one side of the electric drive unit 120. The flat tube 230 of the cooler 200 is bent away from the electric drive unit 120. The shroud 600 covers the side of the electric drive unit 120 facing the cooler 200 and protrudes towards the cooler 200. Furthermore, the inner surface of the heat dissipation groove 270 of the cooler 200 and the protruding surface of the shroud 600 are spaced apart to form a rectification cavity 280 between the shroud 600 and the cooler 200. When both the cooler 200 and the shroud 600 are spherical, the rectification cavity 280 is also spherical with one side concave and the other side convex.

[0038] Specifically, when the cooler 200 is arranged on the side of the electric drive unit 120, the curved flat tube 230 forms a bowl-shaped heat dissipation groove 270 structure, and the raised surface of the shroud 600 and the inner wall of the heat dissipation groove 270 form a tapered flow channel. When the airflow enters the air guide 260, it is guided by the rectifier cavity 280 and diffuses evenly along the heat dissipation gap 240. At the same time, the curved shape of the flat tube 230 increases the effective contact area of ​​the heat dissipation surface. The curved design of the shroud 600 can reduce airflow separation and avoid pressure loss caused by local eddies.

[0039] Example 1

[0040] In this embodiment, as Figures 1-4 As shown, the cooler 200 is located on the leeward side of the electric drive unit 120 (that is, the rear end of the electric drive unit 120, where the airflow passes through the electric drive unit 120 first and then through the cooler 200). One end of the air guide ring 500 is connected to and sleeved on the outer periphery of the liquid inlet collection chamber 210 and the liquid outlet collection chamber 220, and the other end extends toward the direction close to the electric drive unit 120 and is sleeved on the outer periphery of the housing portion 110. Furthermore, the air guide ring 500 and the housing portion 110 are spaced apart to form an external flow guide gap 510 that connects to the rectifier cavity 280. The propeller 300 is located on the windward side of the external flow guide gap 510.

[0041] Specifically, the high-speed airflow generated when the propeller 300 rotates first enters the external guide gap 510 and flows along the annular channel between the guide ring 500 and the housing 110. This airflow then enters the rectifying cavity 280, where it forces convection cooling of the flat tube 230 through the heat dissipation gap 240. The cooler 200 is located on the leeward side of the electric drive unit 120 to avoid interference from the propeller 300's wake, while simultaneously utilizing the high-pressure area on the front of the propeller 300 to enhance intake efficiency.

[0042] Through the above technical solution, this application achieves efficient cooling of the electric drive device 120, using the airflow of the propeller 300 itself to replace the traditional electric fan, thus reducing the system weight while ensuring heat dissipation performance. The cooperative design of the air guide ring 500 and the housing part 110 forms a continuous airflow channel, avoiding energy loss caused by airflow separation, and enabling the cooling airflow to uniformly cover the surface of the flat tube 230, thereby improving heat exchange efficiency.

[0043] Furthermore, in one embodiment, the air guide ring 500 is a heat-conducting component (specifically, it can be made of metal or thermally conductive ceramic materials, etc., which will not be listed here one by one) so that the heat of the heat-conducting medium in the cooler 200 can be transferred to the atmospheric environment through the air guide ring 500.

[0044] Specifically, the air guide ring 500 is fixed to the outer periphery of the inlet manifold 210 and the outlet manifold 220 by welding or a thermal interface material layer, forming a stable heat conduction path. When the heat-conducting medium in the cooler 200 flows through the flat tube 230, heat is transferred through the wall of the flat tube 230 to the inlet manifold 210 and the outlet manifold 220, and then diffused to its outer surface by the high thermal conductivity of the air guide ring 500. Since the air guide ring 500 extends and is fitted onto the outer periphery of the housing portion 110, its exposed portion is directly exposed to the external airflow, allowing heat to dissipate quickly through natural convection or forced airflow, without relying on additional cooling fans or complex heat dissipation structures.

[0045] Compared with existing technologies, this solution designs the air guide ring 500 as a heat-conducting component, utilizing its own structure to achieve heat transfer without the need to add a fan or increase the size of the heat sink, which simplifies the cooling structure and improves heat dissipation efficiency.

[0046] Specifically, in one embodiment, the air guide ring 500 is welded to the outer periphery of the liquid inlet manifold 210 and the liquid outlet manifold 220.

[0047] In another embodiment, the air guide ring 500 is bonded to the outer periphery of the liquid inlet manifold 210 and the liquid outlet manifold 220 through a thermal interface material layer (including but not limited to thermally conductive silicone grease, thermally conductive adhesive, etc., which are not listed here). At the same time, in order to enhance the connection strength, the air guide ring 500 and the cooler 200 are also connected and reinforced by fasteners.

[0048] Specifically, when the air guide ring 500 is fixedly connected to the collector chamber via welding or a thermal interface material layer, the metallurgical interface formed by welding can directly transfer the heat of the heat-conducting medium in the cooler 200 to the air guide ring 500, while the thermal interface material layer improves heat conduction efficiency by filling the microscopic gaps in the contact surface. Both connection methods ensure a stable heat conduction path between the air guide ring 500 and the collector chamber, allowing the heat of the cooling medium to quickly diffuse to the external environment through the surface of the air guide ring 500.

[0049] Example 2

[0050] In this embodiment, as Figure 1 , Figure 5 and Figure 6 As shown, the cooler 200 is located on the windward side of the electric drive unit 120 (i.e., at the front end of the electric drive unit 120, where airflow first passes through the cooler 200 and then through the electric drive unit 120). The cooler 200 is housed within the housing portion 110, and an annular internal guide gap 112 is provided between the housing portion 110 and the electric drive unit 120 to allow airflow passing through the cooler 200 to be guided into the internal guide gap 112 through the surface of the fairing 600. It should be noted that the propeller 300 is located on the outer periphery of the internal guide gap 112, and the portion of the housing portion 110 connected to the propeller 300 can rotate synchronously with the propeller 300, while the other parts of the housing portion 110 remain stationary.

[0051] Specifically, the cooler 200 is positioned on the windward side of the electric drive unit 120. When the aircraft is in operation, the external airflow first impacts the air vent 260 of the cooler 200 and enters the heat dissipation slot 270. It then passes through the heat dissipation gap 240 between the flat tubes 230 to carry away heat. After passing through the heat dissipation gap 240, the airflow impacts the raised surface of the fairing 600 and, guided by it, enters the annular internal flow guide gap 112 between the housing portion 110 and the electric drive unit 120. This gap allows the airflow to flow circumferentially along the electric drive unit 120, thereby further absorbing the heat generated by the electric drive unit 120. Finally, the airflow is discharged to the external environment through the side exhaust port or tail exhaust port 111 of the housing portion 110.

[0052] Compared with the existing technology, this solution not only expands the heat dissipation area by directly arranging the cooler 200 on the windward side and utilizing the flow guide gap in the housing 110, but also eliminates auxiliary equipment such as electric fans, thereby significantly reducing the weight and volume of the overall structure while ensuring heat dissipation efficiency.

[0053] Furthermore, in one embodiment, the periphery of the housing portion 110 is provided with one or more side vents (not shown) to allow airflow passing through the internal guide gap 112 to enter the atmospheric environment through the side vents on the side wall of the housing portion 110. Specifically, the cooling airflow enters the rectifying cavity 280 after flowing through the heat dissipation gap 240 of the cooler 200, and is then guided into the annular internal guide gap 112 between the housing portion 110 and the electric drive device 120. During its flow along the internal guide gap 112, the airflow absorbs heat generated by the electric drive device 120 and is finally discharged to the atmospheric environment through the side vents on the side wall of the housing portion 110. The position of the side vents matches the side profile of the housing portion 110, ensuring that the hot air exhaust path is consistent with the direction of aircraft movement, thus preventing airflow from stagnating within the housing portion 110.

[0054] In another embodiment, the tail of the housing portion 110 is provided with one or more tail exhaust ports 111, so that the airflow passing through the internal guide gap 112 can enter the atmospheric environment through the tail exhaust ports 111 at the tail of the housing portion 110. Specifically, the cooling airflow enters the rectifying cavity 280 after flowing through the heat dissipation gap 240 of the cooler 200, and is then guided into the annular internal guide gap 112 between the housing portion 110 and the electric drive device 120. As the airflow flows along the internal guide gap 112, it absorbs the heat generated by the electric drive device 120, and is finally discharged to the atmospheric environment through the tail exhaust ports 111 at the tail of the housing portion 110. The position of the tail exhaust ports 111 matches the end profile of the housing portion 110, for example, it can be evenly distributed circumferentially or concentrated in a specific area, so that the hot air exhaust path is consistent with the direction of aircraft movement, and the airflow is prevented from stagnating in the housing portion 110.

[0055] This application also provides an aircraft that includes the cooling structure described in any of the above embodiments.

[0056] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0057] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the scope of protection of this application. Therefore, the patent protection scope of this application should be determined by the appended claims.

[0058] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0059] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0060] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0061] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0062] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0063] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the specification of this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

Claims

1. A cooler (200), characterized in that, The device includes an inlet manifold (210), an outlet manifold (220), and flat tubes (230). The inlet manifold (210) and the outlet manifold (220) are respectively located at both ends of the outer periphery of the cooler (200). The two ends of a plurality of flat tubes (230) are respectively connected to the inlet manifold (210) and the outlet manifold (220). Adjacent flat tubes (230) are spaced apart to form a heat dissipation gap (240) for airflow. The inlet manifold (210) and the outlet manifold (220) are defined to form an air guide (260). The plurality of flat tubes (230) are bent and protruded toward the same side of the air guide (260) to form a heat dissipation groove (270) that connects to the air guide (260). The windward surface area of ​​the heat dissipation groove (270) is larger than the flow area of ​​the air guide (260).

2. The cooler (200) according to claim 1, characterized in that, The cooler (200) is spherical bowl-shaped. The liquid inlet collection chamber (210), the liquid outlet collection chamber (220) and the flat tube (230) are all arc-shaped. The liquid inlet collection chamber (210) and the liquid outlet collection chamber (220) are located at the opening edge of the bowl-shaped cooler (200). The air guide (260) forms the bowl mouth of the bowl-shaped cooler (200). The multiple flat tubes (230) surround and form the bowl body of the bowl-shaped cooler (200).

3. A cooling structure, characterized in that, The device includes an electric drive unit (120), a shroud (600), and a cooler (200) as described in any one of claims 1 and 2. The cooler (200) is disposed on one side of the electric drive unit (120). The flat tube (230) of the cooler (200) is bent away from the electric drive unit (120). The shroud (600) covers the side of the electric drive unit (120) facing the cooler (200). The shroud (600) protrudes towards the cooler (200). The inner surface of the heat dissipation groove (270) and the protruding surface of the shroud (600) are spaced apart to form a rectifier cavity (280) communicating with the heat dissipation gap (240).

4. The cooling structure according to claim 3, characterized in that, It also includes a guide ring (500), a housing (110) and a propeller (300). The electric drive device (120) is installed inside the housing (110). The propeller (300) is connected to the output end of the electric drive device (120). The cooler (200) is located on the leeward side of the electric drive device (120). One end of the guide ring (500) is connected to and sleeved on the outer periphery of the liquid inlet collection chamber (210) and the liquid outlet collection chamber (220). The other end extends toward the direction close to the electric drive device (120) and is sleeved on the outer periphery of the housing (110). The guide ring (500) and the housing (110) are spaced apart to form an external flow guide gap (510) that connects to the rectifier cavity (280). The propeller (300) is located on the windward side of the external flow guide gap (510).

5. The cooling structure according to claim 4, characterized in that, The air guide ring (500) is a heat-conducting component, so that the heat of the heat-conducting medium in the cooler (200) can be transferred to the atmospheric environment through the air guide ring (500).

6. The cooling structure according to claim 4, characterized in that, The air guide ring (500) is welded to the outer periphery of the liquid inlet collection chamber (210) and the liquid outlet collection chamber (220); Alternatively, the air guide ring (500) is bonded to the outer periphery of the liquid inlet manifold (210) and the liquid outlet manifold (220) through a thermal interface material layer.

7. The cooling structure according to claim 3, characterized in that, It also includes a housing (110), in which the electric drive device (120) and the cooler (200) are respectively installed. The cooler (200) is located on the windward side of the electric drive device (120). An annular internal flow guide gap (112) is provided between the housing (110) and the electric drive device (120) so that the airflow passing through the cooler (200) can be guided into the internal flow guide gap (112) through the surface of the shroud (600).

8. The cooling structure according to claim 7, characterized in that, The periphery of the housing part (110) is provided with a side air outlet so that the airflow passing through the internal guide gap (112) can enter the atmospheric environment through the side air outlet.

9. The cooling structure according to claim 7, characterized in that, The tail of the housing part (110) is provided with a tail outlet (111) so that the airflow passing through the internal guide gap (112) can enter the atmospheric environment through the tail outlet (111).

10. An aircraft, characterized in that, Includes the cooling structure as described in any one of claims 3-9.

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