Air-cooling heat dissipation framework for eVTOL propulsion motor

Abstract

The invention discloses an air-cooling heat dissipation framework for an eVTOL propulsion motor, and belongs to the technical field of aircraft heat management. The structure comprises a nacelle, a controller water cooling plate, an axial flow cooling fan, a fan cover and a radiator. Cooling air enters from an annular inlet between a nacelle and a motor, flows through the surface of a controller water cooling plate, is pressurized by an axial flow cooling fan, is rectified by a fan cover and then is guided to a radiator. The fan cover is directly fixed on the radiator, the structure is compact, and the wind resistance is reduced; the contact surface of the controller water-cooling plate and cooling air is provided with radiating fins so as to increase the heat exchange area. According to the invention, through optimization of the air duct layout and component integration, the air flow pressure loss is effectively reduced, the heat dissipation efficiency and the system reliability are improved, and the structure is especially suitable for a high-power-density eVTOL propulsion motor.

Description

Technical Field

[0001] This invention belongs to the field of aircraft technology and relates to an air-cooled heat dissipation architecture for an eVTOL propulsion motor. Background Technology

[0002] Low-altitude economy is a major future development direction, and the propulsion motor is a key component of Electric Vertical Take-off and Landing (eVTOL) aircraft, providing power for low-altitude flight. Currently, eVTOL propulsion motors pursue high power and high power density, which leads to heat dissipation issues. eVTOL propulsion motors generate heat due to losses during operation. The rotor can be cooled by airflow through external rotor supports, while the stator windings and the controller integrated within the stator require coolant to remove heat. After the coolant removes the heat, it needs to be exchanged to the external environment through a heat exchanger.

[0003] Currently, heat exchangers typically use electric or mechanically driven fans to enhance heat dissipation. However, due to the limited space within the nacelle where the eVTOL propulsion motor is installed, a cooling duct structure needs to be designed to reduce air resistance, meet the flow requirements of large volumes of cooling air, and minimize energy loss from the propulsion motor system driving the cooling fan. Simultaneously, the heat dissipation area can be increased by designing the cooling duct structure, thereby improving the eVTOL propulsion motor's heat dissipation capacity. Summary of the Invention

[0004] To address the aforementioned problems, this invention provides an air-cooled heat dissipation architecture for eVTOL propulsion motors. This cooling air duct structure can effectively reduce wind resistance and improve heat dissipation capacity.

[0005] According to the technical solution of the present invention: a wind-cooled heat dissipation architecture for an eVTOL propulsion motor, characterized in that it comprises: The nacelle surrounds the eVTOL propulsion motor, and cooling air enters from an annular inlet between the nacelle and the propulsion motor. The controller water-cooling plate is through which cooling air flows; An axial cooling fan is located downstream of the controller water-cooling plate and is used to pressurize the cooling air flowing through the controller water-cooling plate. A fan shroud, located downstream of the axial cooling fan, is used to rectify the pressurized cooling air. A radiator, located downstream of the fan shroud, receives rectified cooling air. The fan cover is directly fixed to the heat sink; The controller water-cooled plate is located upstream of the axial fan, and the contact surface between it and the axial cooling fan is provided with heat dissipation fins to increase the heat exchange area.

[0006] As a further improvement of the present invention, the power of the axial cooling fan is 1.5 kW.

[0007] As a further improvement of the present invention, the fan cover is fixedly connected to the heat sink by screws.

[0008] As a further improvement of the present invention, it also includes a radiator outlet pipe, a radiator inlet pipe A, a radiator inlet pipe B, and a pressure relief pipe, wherein the radiator outlet pipe, radiator inlet pipe A, radiator inlet pipe B, and pressure relief pipe are all connected to the radiator and are provided with a sealing structure.

[0009] As a further improvement of the present invention, the sealing structure includes an end face seal and a fixed seal.

[0010] As a further improvement of the present invention, the radiator outlet pipe is provided with a connector port, and a seal is achieved by connecting the connector port to the radiator.

[0011] As a further improvement of the present invention, the heat dissipation fins are integrated into the contact surface between the water cooling channel and the cooling air of the controller water cooling plate.

[0012] The technical advantages of this invention are as follows: Significantly improved heat dissipation efficiency: Adding heat dissipation fins to the contact surface between the controller's water-cooled plate and the cooling air directly increases the heat exchange area, enhancing heat dissipation capacity and effectively addressing the concentrated heat generated by high-power-density motors. Optimized airflow organization and efficiency: Combining axial cooling fan pressurization with fan shroud rectification effectively reduces airflow pressure loss in the duct, ensuring uniform and efficient cooling airflow through the radiator and improving overall heat exchange efficiency.

[0013] Compact design and low air resistance: The fan shroud is directly mounted to the radiator, eliminating the need for additional connectors. This integrated design not only simplifies the structure and achieves lightweight construction, but also reduces internal airflow resistance, making it ideal for the compact space of eVTOL nacelles.

[0014] Reduced system energy consumption: To address the flow resistance of the heat dissipation channel and the matching requirements of heat dissipation and airflow, a high-speed axial fan is designed based on high-load blade profile optimization technology. This enables efficient and stable operation under high air pressure and large airflow conditions, significantly reducing the power consumption of the cooling system itself and helping to improve the aircraft's endurance.

[0015] Highly reliable sealing and integration: The system employs a multi-layer sealing structure that combines end faces and fixing at each pipe interface, and utilizes sealed pipe nozzles to ensure no leakage at critical connection points, thus guaranteeing the long-term reliability of the entire cooling system under complex operating conditions. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the cooling architecture of the present invention.

[0017] Figure 2 This is a schematic diagram of the structure of the present invention.

[0018] Figure 3 This is a schematic diagram of a cold-cut air duct structure.

[0019] Figure 4 This is an exploded view of the present invention.

[0020] Figure 5 This is a schematic diagram of the fan cover connection structure.

[0021] Figure 6a This is a schematic diagram of the sealing structure of the radiator outlet pipe.

[0022] Figure 6b This is a schematic diagram of the sealing structure of the radiator inlet pipe A.

[0023] Figure 6c This is a schematic diagram of the sealing structure of the pressure relief pipe.

[0024] Figure 6d This is a schematic diagram of the sealing structure of the radiator inlet pipe B.

[0025] Figure 7 This is a schematic diagram of the heat dissipation fin structure of a water-cooled plate. Detailed Implementation

[0026] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings.

[0027] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. The described embodiments are merely some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0028] Figure 1-7 The components include a controller water-cooled plate 1, an axial flow cooling fan 2, a radiator outlet pipe 3, a first end face seal 31, a pipe nozzle interface 32, a sealing pipe nozzle 4, a fan cover 5, a radiator 6, a radiator inlet pipe A 7, a second fixed seal 71, a second end face seal 72, a pressure relief pipe 8, a third fixed seal 81, a third end face seal 82, a radiator inlet pipe B 9, a fourth fixed seal 91, a fourth end face seal 92, a nacelle 10, an annular inlet 11, and heat dissipation fins 12.

[0029] like Figure 1-7 As shown, this embodiment provides an air-cooled heat dissipation architecture for an eVTOL propulsion motor, primarily applied inside the nacelle surrounding the eVTOL propulsion motor. Its core function is to guide cooling air to flow efficiently through the heat dissipation components, carrying away the heat generated during motor operation.

[0030] like Figure 1 The cooling architecture schematic diagram shows the following workflow of the entire system: The eVTOL propulsion motor and its controller generate heat during operation. High-temperature coolant circulates in the liquid cooling circuit, carrying the heat to the radiator 6. Simultaneously, the cooling air guided by this cooling duct structure provides forced air cooling to the radiator 6, completing heat exchange and ultimately dissipating the heat to the external environment.

[0031] like Figure 3 and Figure 4 The specific structure of the cooling air duct is as follows: Cooling air enters the air duct through the annular inlet 11 between the nacelle 10 and the propulsion motor. The airflow first flows over the surface of the controller water-cooled plate 1 for initial cooling. Subsequently, the airflow enters the working area of ​​the axial cooling fan 2, which pressurizes the airflow to overcome the subsequent flow resistance.

[0032] The axial cooling fan 2 has undergone aerodynamic optimization design. In this embodiment, its power rating is 1.5kW, and it can achieve a high operating efficiency of not less than 68% under the conditions of air volume not less than 2500m³ / h and air pressure not less than 800Pa.

[0033] The pressurized airflow then enters the fan shroud 5. For example... Figure 5 As shown, the fan shroud 5 is directly fixed to the inlet surface of the radiator 6 with screws, eliminating the need for a separate mounting bracket. This direct connection method makes the structure extremely compact, reduces weight, and the fan shroud 5 can effectively rectify the turbulent rotating airflow from the axial cooling fan 2, turning it into a more uniform and directional airflow, thereby reducing air pressure loss and ensuring that the airflow can evenly cover the entire heat exchange surface of the radiator 6, enhancing the heat exchange effect.

[0034] The rectified high-pressure cooling air eventually enters the radiator 6, where it undergoes efficient heat exchange with the high-temperature coolant flowing inside, completing the final heat dissipation process.

[0035] To ensure the reliability of the coolant circuit connection, such as Figure 4 and Figures 6a-6dAs shown, the system also includes a radiator outlet pipe 3, a radiator inlet pipe A 7, a pressure relief pipe 8, and a radiator inlet pipe B 9. Each of these pipes has a sealing structure at its connection to the radiator 6. Specifically, the radiator outlet pipe 3 has a first end face seal 31 and a connector port 32; the radiator inlet pipe A 7 has a second fixed seal 71 and a second end face seal 72; the pressure relief pipe 8 has a third fixed seal 81 and a third end face seal 82; and the radiator inlet pipe B 9 has a fourth fixed seal 91 and a fourth end face seal 92. A sealing connector port 4 is installed between the connector port 32 of the radiator outlet pipe 3 and the corresponding port on the radiator 6, ensuring a reliable seal at this connection point. This multi-seal design effectively eliminates the risk of coolant leakage.

[0036] To further improve heat dissipation capabilities, such as Figure 7 As shown, heat dissipation fins 12 are added to the contact surface between the water-cooling channel and the cooling air of the controller water-cooling plate 1. The heat dissipation fins 12 significantly increase the contact area between the controller water-cooling plate 1 and the cooling air. When the cooling air flows through the area between the controller water-cooling plate 1 and the axial cooling fan 2, it can carry away heat more efficiently.

[0037] In summary, this embodiment has successfully constructed an efficient, compact, and reliable eVTOL propulsion motor cooling duct structure by optimizing the air duct layout, key component structure, and connection method. It is particularly suitable for high-power eVTOL propulsion motors with a power density of not less than 5kW / kg.

[0038] Finally, it should be noted that the above specific embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to examples, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A wind-cooled heat dissipation architecture for an eVTOL propulsion motor, characterized in that, include: The nacelle (10) surrounds the eVTOL propulsion motor, and cooling air enters from the annular inlet (11) between the nacelle (10) and the propulsion motor; The controller water-cooled plate (1) is through which cooling air flows; An axial cooling fan (2) is located downstream of the controller water-cooled plate (1) and is used to pressurize the cooling air flowing through the controller water-cooled plate (1); A fan shroud (5) is located downstream of the axial cooling fan (2) and is used to rectify the pressurized cooling air. A radiator (6) is located downstream of the fan shroud (5) and receives rectified cooling air; The fan cover (5) is directly fixed to the radiator (6); The contact surface between the controller water-cooled plate (1) and the axial flow cooling fan (2) is provided with heat dissipation fins (12) to increase the heat exchange area.

2. The air-cooled heat dissipation architecture for an eVTOL propulsion motor as described in claim 1, characterized in that: The power of the axial cooling fan (2) is 1.5kw.

3. The air-cooled heat dissipation architecture for an eVTOL propulsion motor as described in claim 1, characterized in that: The fan cover (5) is fixedly connected to the heat sink (6) by screws.

4. The air-cooled heat dissipation architecture for an eVTOL propulsion motor as described in claim 1, characterized in that: It also includes a radiator outlet pipe (3), a radiator inlet pipe A (7), a radiator inlet pipe B (9), and a pressure relief pipe (8). The radiator outlet pipe (3), the radiator inlet pipe A (7), the radiator inlet pipe B (9), and the pressure relief pipe (8) are all connected to the radiator (6) and are provided with a sealing structure.

5. The air-cooled heat dissipation architecture for an eVTOL propulsion motor as described in claim 4, characterized in that: The sealing structure includes an end face seal and a fixed seal.

6. The air-cooled heat dissipation architecture for an eVTOL propulsion motor as described in claim 5, characterized in that: The radiator outlet pipe (3) is provided with a pipe fitting interface and is connected to the radiator (6) through a sealing pipe fitting (4) to achieve sealing.

7. The air-cooled heat dissipation architecture for an eVTOL propulsion motor as described in claim 1, characterized in that: The heat dissipation fins (12) are integrated into the water cooling channel and the cooling air contact surface of the controller water cooling plate (1).

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