A circular heat exchanger structure adapted to the motor of a low-altitude aircraft

Abstract

This invention discloses a circular heat exchanger structure adapted to the motor of a low-altitude aircraft, relating to the field of heat exchanger technology. It includes a left and right liquid collection pipe as liquid collection components. Both the left and right liquid collection pipes are arc-shaped structures with internal liquid collection chambers, adapted to the pre-set inner wall of the motor fairing. Multiple sets of parallel flat pipes are connected between the left and right liquid collection pipes. This invention eliminates the corner dead zones generated by traditional square heat exchangers in a circular space by designing the heat exchanger core to fit snugly against the inner wall of the motor fairing, maximizing the use of limited space and contributing to the overall lightweight and compact design of the aircraft. Simultaneously, the circular shape makes the windward area distribution of the heat exchanger core more uniform, allowing cooling air to flow more smoothly and evenly across the core surface, avoiding the generation of corner eddies, thereby improving the overall heat exchange efficiency and temperature distribution uniformity.

Description

Technical Field

[0001] This invention relates to the field of heat exchanger technology, and more particularly to a circular heat exchanger structure adapted to the motor of a low-altitude aircraft. Background Technology

[0002] In low-altitude aircraft, the motor is the core power component, which generates heat during operation. To ensure flight safety, heat management of the motor is necessary, and heat sinks are used to dissipate heat from the motor.

[0003] Most existing heat exchangers for low-altitude aircraft motors have a square structure, such as... Figure 1 and Figure 2 As shown, the main body includes an inlet and outlet liquid collecting pipe 1 and a return liquid collecting pipe 4. Several heat-conducting pipes 2 and fins 6 are installed alternately between the inlet and outlet liquid collecting pipes 1 and the return liquid collecting pipe 4. On the side of the inlet and outlet liquid collecting pipes 1 away from the return liquid collecting pipe 4, from top to bottom, an inlet pressure plate 10, an upper left mounting bracket 9, an outlet pressure plate 8, and a lower left mounting bracket 7 are installed sequentially. On the side of the return liquid collecting pipe 4 away from the inlet and outlet liquid collecting pipes 1, from top to bottom, an upper right mounting bracket 3 and a lower right mounting bracket 5 are installed sequentially. Cooling oil enters the inlet and outlet liquid collecting pipes 1 from the inlet pressure plate 10, passes through the heat-conducting pipes 2 and enters the return liquid collecting pipe 4, and then enters the inlet and outlet liquid collecting pipes 1 again through the heat-conducting pipes 2, and is discharged from the outlet pressure plate 8 after cooling. In this cycle, the cooling oil in the corner area of ​​the heat exchanger is prone to stagnation and cannot effectively participate in heat exchange, resulting in low heat exchange efficiency.

[0004] The aforementioned square heat exchanger has obvious drawbacks in actual use: the fluid is prone to generating eddies at the four corners of the square heat exchanger, resulting in uneven fluid flow rate, which in turn leads to large differences in heat exchange efficiency on the heat exchanger surface and local high temperature. This not only reduces the overall heat dissipation performance but also affects the stable operation of the motor. Summary of the Invention

[0005] To overcome the shortcomings of existing technologies, the purpose of this invention is to provide a circular heat exchanger structure adapted to the motor of a low-altitude aircraft. The heat exchanger core is designed to be circular and fits in close to the inner wall of the motor shroud, eliminating the corner dead zone generated by the traditional square heat exchanger in the circular space and achieving the purpose of stable heat exchange.

[0006] To address the problems of the prior art, the technical solution of the present invention is as follows: A circular heat exchanger structure adapted to a low-altitude aircraft motor includes a left and a right liquid collecting pipe as liquid collecting components. Both the left and right liquid collecting pipes are arc-shaped structures with internal liquid collecting cavities, and are adapted to the pre-designed inner wall of the motor fairing. Multiple sets of parallel flat tubes are connected between the left and right liquid collecting pipes. The length of the flat tubes gradually decreases from the middle to the outside, and the width of the flat tubes is set between 22-38 mm. Single-row or double-row flat tubes can be selected. Fins are arranged between adjacent flat tubes. The two ends are connected to the left and right liquid collection pipes respectively. The end faces of the left and right liquid collection pipes are respectively equipped with left and right pressure plates for connecting external pipelines. The left pressure plate, right pressure plate, left liquid collection pipe, right liquid collection pipe, flat tube and fins together form the heat dissipation core. The opposite sides of the left and right liquid collection pipes are connected to the mounting brackets by brazing. The mounting brackets are used to install the heat dissipation core inside the motor fairing. No complex transition structure is required, the assembly is simple and the weight is light, which meets the requirements of lightweight and high reliability of aircraft.

[0007] Preferably, the left and right liquid collecting pipes adopt an integrated molding structure, which is formed by bending extruded pipe into an arc shape. The structure has high strength and good pressure resistance. The diameter of the heat exchanger is 280mm-350mm to adapt to different performance and flow resistance requirements.

[0008] Preferably, the left and right liquid collecting pipes adopt a split molding structure, which is formed by stacking and welding two sets of pipes. It has two liquid collecting cavities inside, which effectively increases the cross-sectional area of ​​the liquid collecting pipes and reduces fluid resistance while ensuring the arc shape of the left and right liquid collecting pipes.

[0009] Preferably, the left and right liquid collecting pipes adopt a split molding structure, which includes a cover plate and a main plate. Both ends of the main plate extend downward and bend upward to form a buckle. The cover plate has an n-shaped cross-section, and both ends of the cover plate extend downward to form an insertion part. The insertion part is fitted into the buckle. The cover plate, buckle, main plate, and insertion part together form a liquid collecting cavity. The split molding structure of the left and right liquid collecting pipes facilitates processing and welding. At the same time, it allows for rapid development and iteration based on the existing product platform, greatly reducing the development cycle, cost, and risk of new products.

[0010] Preferably, the end of the sleeve away from the motherboard is bent to form a guide arc edge. The insertion part is positioned and stably inserted into the sleeve by the guide arc edge. The guide arc edge can improve the assembly positioning accuracy and welding reliability.

[0011] Preferably, the flat tube is provided with a flow disturbance mechanism to guide the cross-flow of cooling oil. The flow disturbance mechanism includes a flow channel and a flow disturbance plate inside the flat tube. The cross-section of the flow disturbance plate is W-shaped, and there are several flow disturbance plates. If the flow disturbance plates are arranged at equal intervals inside the flat tube, the flow channel will be separated.

[0012] Preferably, the baffle plate has staggered guide ports on its inclined surfaces along the flow direction of the cooling oil, through which the cooling oil is transported to adjacent partition channels, so that the cooling oil flows alternately in the adjacent channels.

[0013] Preferably, the guide port is a hollow cone shape, and the inner diameter of the guide port gradually decreases along the flow direction of the cooling oil. The cooling oil velocity through the guide port increases, enhancing the fluid flushing effect, avoiding flow dead zones and local overheating, making the temperature of the entire flat tube heat exchange surface more uniform, and improving the operating stability and service life of the heat exchanger.

[0014] Preferably, the fins are louvered aluminum fins with a fin density of 15-25 FPI and a louver opening angle of 30°-45° to adapt to different wind resistance and heat exchange performance requirements. The fins at the inclined angle guide the airflow to fully impact the flat tube, thereby achieving rapid heat conduction.

[0015] Preferably, both the left and right liquid collection pipes are made of aluminum alloy, which has high thermal conductivity and low density, ensuring stable heat dissipation of the radiator while meeting the requirements for lightweighting of low-altitude aircraft.

[0016] Compared with the prior art, the advantages of the present invention are as follows: 1. This invention eliminates the corner dead zone generated by the traditional square heat sink in the circular space by designing the heat sink core to fit the inner wall of the motor rectifier shell, so as to maximize the use of limited space and facilitate the overall lightweight and compact design of the aircraft.

[0017] 2. The circular shape of this invention makes the windward area of ​​the radiator core more uniform, and the cooling air can flow more smoothly and evenly across the surface of the core, avoiding the generation of corner eddies, thereby improving the overall heat exchange efficiency and temperature distribution uniformity.

[0018] 3. The present invention, through the arc-shaped liquid collection pipe and core structure, enables the radiator to be installed directly or through a simpler bracket against the inner wall of the motor rectifier housing, which simplifies the installation structure and reduces assembly difficulty and cost.

[0019] 4. This invention is not only applicable to aircraft motor fairings, but can also be extended to heat exchange equipment with circular, arc-shaped or narrow irregular installation spaces.

[0020] 5. This invention divides the internal flow channel of the flat tube into multiple independent small flow channels by using a W-shaped baffle, which greatly increases the contact area between the cooling oil and the tube wall. At the same time, it forces the cooling oil to form a turbulent state, effectively destroys the laminar boundary layer, greatly improves the heat transfer coefficient between the cooling oil and the flat tube, and quickly removes the heat from the motor. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the existing technology.

[0022] Figure 2 This is a simplified assembly diagram of the existing technology.

[0023] Figure 3 This is a schematic diagram of the structure of the present invention.

[0024] Figure 4 This is a simplified assembly diagram of the present invention.

[0025] Figure 5 This is a schematic diagram of the structure of the left and right liquid collection tubes in this embodiment of the present invention.

[0026] Figure 6 This is a schematic diagram of the first split molding structure according to another embodiment of the present invention.

[0027] Figure 7 This is a schematic diagram of a second split-type molding structure according to another embodiment of the present invention.

[0028] Figure 8 This is a schematic diagram of an optional embodiment of the present invention.

[0029] Figure 9 This is a schematic diagram of the flat tube section of the present invention.

[0030] Figure 10 This is a cross-sectional view of the flat tube section of the present invention.

[0031] Figure 11 This is a simplified schematic diagram of the cooling oil flow direction inside the flat tube of the present invention; Figure 12 This is a simplified schematic diagram of the dual cooling oil circulation system in this invention.

[0032] Figure label: 1. Inlet and outlet liquid collecting pipes; 2. Heat conducting pipes; 3. Upper right mounting bracket; 4. Return liquid collecting pipe; 5. Lower right mounting bracket; 6. Fins; 7. Lower left mounting bracket; 8. Outlet pressure plate; 9. Upper left mounting bracket; 10. Inlet pressure plate; 21. Left collection tube; 211. Cover plate; 212. Insertion part; 213. Main board; 214. Snap sleeve; 215. Guide arc edge; 22. Flat tube; 23. Mounting bracket; 24. Left pressure plate; 25. Right collection tube; 26. Right pressure plate; 27. Fin; 30. Air guide hole; 40. Collection chamber; 50. Flow channel; 51. Baffle plate; 52. Guide port. Detailed Implementation

[0033] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0034] In this embodiment, as Figure 3 , Figure 5 , Figure 9 , Figure 10 and Figure 11 As shown, a circular heat exchanger structure adapted to a low-altitude aircraft motor includes a left liquid collecting pipe 21 and a right liquid collecting pipe 25 as liquid collecting components. Both the left liquid collecting pipe 21 and the right liquid collecting pipe 25 are arc-shaped structures with an internal liquid collecting chamber 40, and are adapted to the preset inner wall of the motor fairing. Multiple sets of parallel flat tubes 22 are connected between the left liquid collecting pipe 21 and the right liquid collecting pipe 25. The length of the multiple sets of flat tubes 22 gradually decreases from the middle to the outside. The width of the flat tubes 22 is set between 22-38mm. Single-row or double-row flat tubes 22 can be selected to adapt to the arc-shaped left liquid collecting pipe 21 and right liquid collecting pipe 25. During use, cooling air flows more smoothly through the flat tubes 22. Fins are arranged between adjacent flat tubes 22. 27. The two ends of the fin 27 are connected to the left liquid collection pipe 21 and the right liquid collection pipe 25 respectively. The end faces of the left liquid collection pipe 21 and the right liquid collection pipe 25 are respectively equipped with a left pressure plate 24 and a right pressure plate 26 for connecting external pipelines. The left pressure plate 24, the right pressure plate 26, the left liquid collection pipe 21, the right liquid collection pipe 25, the flat pipe 22 and the fin 27 together form a heat dissipation core. The opposite sides of the left liquid collection pipe 21 and the right liquid collection pipe 25 are connected to the mounting bracket 23 by brazing. The surface of the mounting bracket 23 is provided with through holes. The heat dissipation core is installed inside the motor fairing by bolts or screws in conjunction with the through holes on the mounting bracket 23. No complex transition structure is required, the assembly is simple and the weight is light, which meets the requirements of lightweight and high reliability of aircraft. The left liquid collecting pipe 21 and the right liquid collecting pipe 25 adopt an integrated molding structure, which is formed by bending the extruded pipe into an arc shape. The structure has high strength and good pressure resistance. The diameter of the heat exchanger is 280mm-350mm to adapt to different performance and flow resistance requirements.

[0035] like Figure 3 and Figure 5As shown, through the aforementioned components, the cooling oil carries the heat from the motor and enters the left collector pipe 21 through the left pressure plate 24. It then flows through the flat pipe 22 and collects in the right collector pipe 25. Finally, it flows back to the external cooling circuit through the right pressure plate 26, completing the cooling oil circulation and heat exchange. On the air side, when the cooling airflow passes through the heat dissipation core, because the core has a circular structure, it can completely fit the inner wall of the motor shroud, eliminating the dead zones and vortex phenomena at the corners caused by traditional square radiators. This allows the airflow to pass through the core evenly and smoothly, and stably absorb the heat from the flat pipe 22, the left collector pipe 21, and the right collector pipe 25, effectively reducing the local overheating of the heat dissipation core and ensuring the stable use of the radiator.

[0036] The flat tube 22 is equipped with a flow disturbance mechanism to guide the cross-flow of cooling oil. The flow disturbance mechanism includes flow channels 50 and baffles 51 inside the flat tube 22. The cross-section of the baffles 51 is W-shaped and there are several baffles 51. If the baffles 51 are arranged at equal intervals inside the flat tube 22, the flow channels 50 are separated, and the cooling oil that absorbs heat in multiple flow channels 50 independently guides the heat to the surface of the flat tube 22.

[0037] The baffle 51 has staggered guide ports 52 on its inclined surface along the direction of cool oil flow. Cooling oil is transported through the guide ports 52 to the adjacent partitioned flow channels 50, so that the cool oil flows alternately in the adjacent flow channels 50, ensuring the consistency of cooling oil heat dissipation inside the flat tube 22, and making the temperature of the windward side of the flat tube 22 approach the temperature of the rear surface, thus ensuring efficient heat dissipation of the flat tube 22.

[0038] The guide port 52 is a hollow cone shape. The inner diameter of the guide port 52 gradually decreases along the flow direction of the cooling oil. The cooling oil velocity through the guide port 52 increases, which enhances the fluid flushing effect, avoids flow dead zones and local overheating, makes the temperature of the entire flat tube 22 heat exchange surface more uniform, and improves the operating stability and service life of the heat exchanger.

[0039] like Figure 11 As shown, through the above structure, the cooling oil enters the left pressure plate 24 through the external pipeline, and flows into the arc-shaped left liquid collecting pipe 21 with the liquid collecting chamber 40 inside the left pressure plate 24. The left liquid collecting pipe 21 matches the inner wall of the motor rectifier cover, which can smoothly and evenly distribute the cooling oil into multiple sets of parallel flat pipes 22, avoiding uneven flow leading to insufficient local heat exchange. When the cooling oil flows inside the flat pipe 22, the W-shaped baffle 51 divides the flow channel 50 inside the flat pipe 22 into multiple small channels, increasing the contact area between the cooling oil and the pipe wall. At the same time, the hollow conical guide ports 52 staggered on the baffle 51 gradually narrow along the flow direction, forcing the cooling oil to accelerate and flow turbulently between adjacent flow channels 50, effectively destroying the fluid boundary layer and significantly improving the heat transfer efficiency of the cooling oil to the wall of the flat pipe 22.

[0040] The fin 27 is a louvered aluminum fin 27 with a density of 15-25 FPI and a louver opening angle of 30°-45° to adapt to different wind resistance and heat exchange performance requirements. The fin 27 with the tilt angle guides the airflow to fully impact the flat tube 22 to achieve rapid heat conduction.

[0041] like Figure 3 As shown, the louvered aluminum fins 27 between adjacent flat tubes 22 are inclined, which greatly expands the heat exchange area on the air side and cuts the airflow boundary layer, efficiently dissipating the heat transferred by the flat tubes 22 into the external airflow and achieving continuous and stable heat dissipation.

[0042] Both the left liquid collection pipe 21 and the right liquid collection pipe 25 are made of aluminum alloy, which has high thermal conductivity and low density, ensuring stable heat dissipation of the radiator while meeting the requirements of lightweighting of low-altitude aircraft.

[0043] As another embodiment, such as Figure 6 and Figure 7 As shown, the left collection tube 21 and the right collection tube 25 adopt a split molding structure, which includes two types of split molding structures: The first type of split molding structure is formed by stacking and welding two sets of tubes. It has two liquid collection chambers 40 inside. While ensuring the arc shape of the left liquid collection tube 21 and the right liquid collection tube 25, it effectively increases the cross-sectional area of ​​the liquid collection tube, reduces the fluid resistance, and increases the time that the cooling oil that absorbs the heat of the motor stays in the heat dissipation core, thus enhancing the heat dissipation of the cooling oil. The second type of split molding structure includes a cover plate 211 and a main plate 213. Both ends of the main plate 213 extend downward and bend upward to form a buckle 214. The cover plate 211 has an n-shaped cross section, and both ends of the cover plate 211 extend downward to form an insertion part 212. The insertion part 212 is fitted into the buckle 214. The cover plate 211, buckle 214, main plate 213 and insertion part 212 together form a liquid collection cavity 40. The left liquid collection tube 21 and the right liquid collection tube 25 adopt a split molding structure, which is convenient for processing and welding. At the same time, it can be rapidly developed and iterated based on the existing product platform, which greatly reduces the development cycle, cost and risk of new products. The end of the sleeve 214 away from the main board 213 is bent to form a guide arc edge 215. When assembling the cover plate 211, the insertion part 212 contacts the guide arc edge 215 and is guided along its arc surface to move into the sleeve 214, completing the assembly of the cover plate 211, sleeve 214, main board 213 and insertion part 212. The guide arc edge 215 improves the assembly positioning accuracy. Then the guide arc edge 215 and the insertion part 212 are welded and fixed. The weld is contained in the groove between the guide arc edge 215 and the cover plate 211, which does not affect the appearance of the weld and ensures the reliability of the weld.

[0044] In another alternative embodiment, such as Figure 8 As shown, the flat tube 22 and fins 27 located in the middle of the heat dissipation core are bent outward to form air guide holes 30. The diameter of the air guide holes 30 is set to 50mm-100mm to adapt to different installation requirements. By integrating fan blades inside the motor rectifier, the airflow is actively guided through the air guide holes 30, realizing the switching between blowing and suction modes to adapt to heat exchange equipment with circular, arc-shaped or narrow irregular installation spaces.

[0045] like Figure 12 As shown, in this scheme, the left pressure plate 24 and the right pressure plate 26 can be set in two sets, forming two sets of cooling oil circulation systems in the flat tube 22 to meet the heat dissipation requirements of different motors.

[0046] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention.

Claims

1. A circular heat exchanger structure adapted for a low-altitude aircraft motor, comprising a left liquid collecting pipe (21) and a right liquid collecting pipe (25) as liquid collecting components, characterized in that, The left liquid collecting pipe (21) and the right liquid collecting pipe (25) are both arc-shaped structures with internal liquid collecting chambers (40), and are adapted to the preset inner wall of the motor rectifier cover. Multiple sets of parallel flat pipes (22) are connected between the left liquid collecting pipe (21) and the right liquid collecting pipe (25). The length of the multiple sets of flat pipes (22) gradually decreases from the middle to the outside. Fins (27) are provided between adjacent flat pipes (22), and the two ends of the fins (27) are connected to the left liquid collecting pipe (21) and the right liquid collecting pipe (25) respectively. The end faces of the liquid collecting pipe (21) and the right liquid collecting pipe (25) are respectively equipped with a left pressure plate (24) and a right pressure plate (26) for connecting external pipelines. The left pressure plate (24), the right pressure plate (26), the left liquid collecting pipe (21), the right liquid collecting pipe (25), the flat pipe (22) and the fins (27) together form a heat dissipation core. The opposite sides of the left liquid collecting pipe (21) and the right liquid collecting pipe (25) are connected by brazing with mounting brackets (23). The mounting brackets (23) are used to install the heat dissipation core inside the motor rectifier.

2. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 1, characterized in that, The left liquid collection pipe (21) and the right liquid collection pipe (25) adopt an integrated molding structure, which is formed by bending the extruded pipe into an arc shape.

3. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 1, characterized in that, The left liquid collecting pipe (21) and the right liquid collecting pipe (25) adopt a split molding structure, which is formed by stacking and welding two sets of pipe bodies, and has two liquid collecting cavities (40) inside.

4. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 1, characterized in that, The left collection tube (21) and the right collection tube (25) adopt a split molding structure. The split molding structure includes a cover plate (211) and a main plate (213). Both ends of the main plate (213) extend downward and bend upward to form a buckle (214). The cover plate (211) has an n-shaped cross section, and both ends of the cover plate (211) extend downward to form an insertion part (212). The insertion part (212) is fitted into the buckle (214). The cover plate (211), the buckle (214), the main plate (213) and the insertion part (212) together enclose to form a collection cavity (40).

5. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 4, characterized in that, The end of the buckle (214) away from the main board (213) is bent to form a guide arc edge (215), and the insertion part (212) is positioned and stably inserted into the buckle (214) through the guide arc edge (215).

6. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 1, characterized in that, The flat tube (22) is provided with a flow disturbance mechanism to guide the cross-flow of cooling oil. The flow disturbance mechanism includes a flow channel (50) and a flow disturbance plate (51) inside the flat tube (22). The cross-section of the flow disturbance plate (51) is W-shaped, and there are several flow disturbance plates (51). If the flow disturbance plates (51) are arranged at equal intervals inside the flat tube (22), the flow channel (50) will be separated.

7. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 6, characterized in that, The slope of the spoiler (51) is staggered with guide ports (52), through which cooling oil is transported to the adjacent partition channel (50).

8. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 7, characterized in that, The guide port (52) is a hollow cone-shaped tube, and the inner diameter of the guide port (52) gradually decreases along the direction of cooling oil flow.

9. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 1, characterized in that, The fins (27) are louvered aluminum fins (27), with a density of 15-25 FPI and a louver opening angle of 30°-45° to adapt to different wind resistance and heat exchange performance requirements.

10. The circular heat exchanger structure adapted for low-altitude aircraft motors according to claim 1, characterized in that, Both the left liquid collection tube (21) and the right liquid collection tube (25) are made of aluminum alloy.

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