Aircraft electric propulsion motor oil-gas double-cooling radiator based on propeller airflow heat dissipation

Abstract

The invention discloses an aircraft electric propulsion motor oil-gas double-cooling radiator based on propeller airflow heat dissipation. The radiator comprises heat dissipation fins, an oil pipe, cooling oil, an oil storage, an oil pump and a propeller. The top of the aircraft electric propulsion motor is provided with a propeller, the end of the aircraft electric propulsion motor is provided with the cooling fins, oil pipes are arranged in the cooling fins and connected with an oil storage, the oil storage is filled with cooling oil, an oil pump is arranged, the cooling oil is pumped into the motor, and the motor is cooled; and then high-temperature cooling oil output by the motor is fed into the oil pipes in the heat dissipation fins, the cooling oil in the oil pipes in the heat dissipation fins is cooled through airflow generated by the propeller at the top of the electric propulsion motor, the cooled cooling oil is input into the oil storage, circulation of the cooling oil is completed, and therefore heat dissipation and cooling of the electric propulsion motor are achieved. The structure is simple, the utilization rate of system energy is improved, the heat dissipation capability of the motor is improved, and the safety and reliability of the motor are ensured.

Description

Technical Field

[0001] The invention relates to the technical field of motor cooling, and in particular to an oil-gas dual-cooling radiator for an aircraft electric propulsion motor based on propeller airflow heat dissipation. Background Art

[0002] With the development of the aviation industry and the increasing prominence of environmental issues, the global demand for electrification of aircraft is increasing day by day. Compared with traditional fuel aircraft engines, electric propulsion motors have significant advantages such as high energy conversion efficiency, no pollution, and low noise, and have received widespread attention from researchers. As the core power component of electric aircraft, the comprehensive ability of electric propulsion motors directly affects the performance of aircraft.

[0003] With the continuous updating and upgrading of electric propulsion motor technology, the issue of efficient heat dissipation of electric propulsion motors has attracted more and more attention from researchers. The heat dissipation and cooling performance of the motor has an important impact on the power density. The heat dissipation and cooling performance determines the heat dissipation ability of the motor when it is running at high power, which in turn affects the improvement of its power density. High power density motors are small in size, have high power per unit volume, and have a small surface area, so efficient heat dissipation technology is required to prevent excessive temperature rise.

[0004] Motor cooling technologies mainly include air cooling, oil cooling and water cooling. Direct oil cooling is a more efficient cooling method. However, the cooling oil after heating up in motor oil cooling needs to be cooled by a cooling device before it can be recycled. Additional cooling devices often increase energy consumption. How to re-cool the heated cooling oil without adding additional cooling devices to reduce system energy consumption and improve system energy utilization has gradually attracted the attention of researchers. It is urgent to study a cooling device suitable for re-cooling the cooling oil of electric propulsion motors. Summary of the invention

[0005] The present invention aims to provide an aircraft electric propulsion motor oil-gas dual-cooling radiator based on propeller airflow heat dissipation with high heat dissipation efficiency and low energy consumption.

[0006] The technical solution to achieve the purpose of the present invention is: an oil-gas dual-cooling radiator for an aircraft electric propulsion motor based on propeller airflow heat dissipation, comprising a heat dissipation fin, an oil pipe, cooling oil, an oil reservoir, an oil pump and a propeller;

[0007] A propeller is arranged on the top of the electric propulsion motor of the aircraft, and a cooling fin is arranged on the end; an oil pipe is arranged in the cooling fin, the oil pipe is connected to an oil reservoir, the oil reservoir is filled with cooling oil, and an oil pump is arranged, the oil pump is used to pump the cooling oil into the motor to cool the motor; the high-temperature cooling oil output by the motor is input into the oil pipe in the cooling fin, the airflow generated by the propeller on the top of the electric propulsion motor cools the cooling oil in the oil pipe inside the cooling fin, and the cooled cooling oil is input into the oil reservoir, completing the circulation of the cooling oil, thereby realizing heat dissipation cooling of the electric propulsion motor.

[0008] Furthermore, the heat dissipation fins are cross-connected by multiple layers of annular circumferential fins and multiple rectangular radial fins to form an integrated structure with multiple layers of circular rings connected; the radius difference between two adjacent annular circumferential fins is the same; the rectangular radial fins extend from the innermost annular circumferential fin to the outermost annular circumferential fin, and the angle between each two rectangular radial fins is the same.

[0009] Furthermore, a cooling oil flow channel hole is provided at the midpoint between every two rectangular radial fins on the annular circumferential fin, and the centers of the cooling oil flow channel holes at the same position are on the same radius.

[0010] Furthermore, an oil pipe is installed in the cooling oil flow channel hole, and the outer wall of the oil pipe is connected to the cooling oil flow channel hole opened by the annular circumferential fin, and the heat of the cooling oil is transferred to the annular circumferential fin through the oil pipe.

[0011] Furthermore, the oil pipe is a curved pipe in which straight pipes and arc-shaped pipes are alternately connected, and is installed in the heat dissipation fins along the circumferential direction.

[0012] Furthermore, the oil pipe is provided with an oil inlet and an oil outlet on the outside of the heat dissipation fin, and the oil inlet, the oil outlet and two adjacent straight pipes are connected to form an internally connected oil pipe.

[0013] Furthermore, each layer of annular circumferential fins of the heat dissipating fins is provided with a partition between the oil inlet and the oil outlet of the oil pipe, so as to block heat conduction between the high-temperature cooling oil at the oil inlet and the low-temperature cooling oil at the oil outlet.

[0014] Furthermore, the centerline angle of adjacent straight pipes in the oil pipe is 12° to 15°, both ends of the center arc of the arc pipe are tangent to the centerline of the straight pipe, and the straight pipe and the arc pipe are staggered and connected so that the oil pipe is arranged circumferentially along the heat dissipation fin.

[0015] Furthermore, the heat dissipation fins and the oil pipes are both made of copper.

[0016] A working method of an aircraft electric propulsion motor oil-gas dual-cooling radiator based on propeller airflow heat dissipation, the working process of the oil-gas dual-cooling radiator is as follows:

[0017] The cooling oil is pumped out by the oil pump and transported to the motor through the oil pipe for motor cooling. The heated cooling oil flows out of the motor and enters the radiating fins through the oil inlet of the radiating fins. Since the oil pipe is connected to the radiating fins, the cooling oil transfers the heat to the radiating fins through the oil pipe under the action of heat conduction. The airflow formed by the rotation of the propeller on the top of the motor performs convective heat exchange, takes away the heat of the cooling oil, and improves the heat dissipation efficiency through the radiating fins, thereby finally achieving the purpose of cooling the cooling oil. The cooled cooling oil flows back to the oil storage tank to complete the cycle.

[0018] Compared with the prior art, the present invention has the following significant advantages:

[0019] (1) By arranging a radiator at the end of the motor and using the forced air cooling of the propeller to re-cool the heated cooling oil, the energy utilization rate is improved, and no additional cooling device is required, which simplifies the manufacturing process and improves the heat dissipation capacity;

[0020] (2) The structure of combining heat dissipation fins and oil pipes increases the contact area between the oil pipes and the heat dissipation fins, enhances the convection heat transfer capacity, and improves the heat dissipation efficiency;

[0021] (3) The inner diameter, thickness and number of the circular rings in the heat sink fins can be adjusted according to actual needs. According to the actual situation, the angle between adjacent straight oil pipes can be adjusted to set a cooling structure with multiple layers of heat sink fins and oil pipes stacked on top of each other. The system has strong adjustability and high cooling efficiency, which effectively reduces the cooling oil temperature and ensures the long-term safe and reliable operation of the motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural diagram of the oil-gas dual-cooling radiator of the aircraft electric propulsion motor based on propeller airflow heat dissipation of the present invention.

[0023] Figure 2 It is a side structural schematic diagram of the present invention.

[0024] Figure 3 It is a structural schematic diagram of the heat dissipation fins in the present invention.

[0025] Figure 4 It is a structural schematic diagram of the oil pipe in the present invention.

[0026] In the figure: 1-heat dissipation fin, 2-oil pipe, 3-cooling oil, 4-oil storage tank, 5-oil pump, 6-propeller, 1-1-annular circumferential fin, 1-2-rectangular radial fin, 1-3-cooling oil flow channel hole, 1-4-partition, 2-1-arc pipe, 2-2-straight pipe, 2-3-oil inlet, 2-4-oil outlet. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] The present invention provides an aircraft electric propulsion motor oil-gas dual-cooling radiator based on propeller airflow heat dissipation, comprising a heat dissipation fin 1, an oil pipe 2, cooling oil 3, an oil storage tank 4, an oil pump 5 and a propeller 6;

[0029] A propeller 6 is arranged on the top of the electric propulsion motor of the aircraft, and a cooling fin 1 is arranged on the end; an oil pipe 2 is arranged in the cooling fin 1, the oil pipe 2 is connected to an oil reservoir 4, the oil reservoir 4 is filled with cooling oil 3, and an oil pump 5 is arranged, the oil pump 5 is used to pump the cooling oil 3 into the motor to cool the motor; the high-temperature cooling oil 3 output by the motor is input into the oil pipe 2 in the cooling fin 1, the airflow generated by the propeller 6 on the top of the electric propulsion motor cools the cooling oil 3 in the oil pipe 2 inside the cooling fin 1, and the cooled cooling oil 3 is input into the oil reservoir 4 to complete the circulation of the cooling oil 3, thereby realizing the heat dissipation cooling of the electric propulsion motor.

[0030] Furthermore, the heat dissipation fin 1 is cross-connected by multiple layers of annular circumferential fins 1-1 and multiple rectangular radial fins 1-2, forming an integrated structure of multiple layers of circular rings; the radius difference between two adjacent annular circumferential fins 1-1 is the same; the rectangular radial fins 1-2 extend from the innermost annular circumferential fin 1-1 to the outermost annular circumferential fin 1-1, and the angle between each two rectangular radial fins 1-2 is the same.

[0031] Furthermore, a cooling oil flow channel hole 1-3 is provided at the midpoint between every two rectangular radial fins 1-2 on the annular circumferential fin 1-1, and the centers of the cooling oil flow channel holes 1-3 at the same position are on the same radius.

[0032] Furthermore, an oil pipe 2 is installed in the cooling oil flow channel hole 1-3, and the outer wall of the oil pipe 2 is connected to the cooling oil flow channel hole 1-3 opened by the annular circumferential fin 1-1, and the heat of the cooling oil 3 is transferred to the annular circumferential fin 1-1 through the oil pipe 2.

[0033] Furthermore, the oil pipe 2 is a curved pipe in which straight pipes 2 - 2 and arc-shaped pipes 2 - 1 are alternately connected, and is installed in the heat dissipation fins 1 along the circumferential direction.

[0034] Furthermore, the oil pipe 2 is provided with an oil inlet 2-3 and an oil outlet 2-4 on the outside of the heat dissipation fin 1, and the oil inlet 2-3, the oil outlet 2-4 and two adjacent straight pipes 2-2 are connected to form an internally connected oil pipe 2.

[0035] Furthermore, each layer of annular circumferential fins 1-1 of the heat dissipating fins 1 is provided with a partition 1-4 between the oil inlet 2-3 and the oil outlet 2-4 of the oil pipe 2 to block heat conduction between the high-temperature cooling oil 3 at the oil inlet 2-3 and the low-temperature cooling oil 3 at the oil outlet 2-4.

[0036] Furthermore, the center line angle of adjacent straight pipes 2-2 in the oil pipe 2 is 12° to 15°, both ends of the center arc of the arc pipe 2-1 are tangent to the center line of the straight pipe 2-2, and the straight pipe 2-2 and the arc pipe 2-1 are staggered and connected so that the oil pipe 2 is arranged circumferentially along the heat dissipation fin 1.

[0037] Furthermore, the heat dissipation fins 1 and the oil pipes 2 are both made of copper.

[0038] The present invention also provides a working method of the aircraft electric propulsion motor oil-gas dual-cooling radiator based on propeller airflow heat dissipation as described above, the process is as follows:

[0039] The cooling oil 3 is pumped out by the oil pump 5 and transported to the motor through the oil pipe 2 for motor cooling. The heated cooling oil 3 flows out of the motor and enters the heat sink 1 through the oil inlet 2-3 of the heat sink 1. Since the oil pipe 2 is connected to the heat sink 1, the cooling oil 3 transfers the heat to the heat sink 1 through the oil pipe 2 under the action of heat conduction. The airflow formed by the rotation of the propeller 6 on the top of the motor performs convection heat exchange, takes away the heat of the cooling oil 3, and improves the heat dissipation efficiency through the heat sink 1, finally achieving the purpose of cooling the cooling oil 3. The cooled cooling oil 3 flows back to the oil storage tank 4 to complete the cycle.

[0040] The axial flux permanent magnet motor cooling oil cooling system and cooling method provided by the present invention, by setting a radiator at the end of the motor to re-cool the heated cooling oil using the forced air cooling of the propeller, improves the energy utilization rate and no longer needs to provide an additional cooling device, simplifies the manufacturing process, and improves the heat dissipation stability. The unique heat dissipation fin structure and the design of the oil pipe increase the contact area between the oil pipe and the heat dissipation fin, enhance the convection heat transfer capacity, and improve the heat dissipation efficiency. The inner diameter, thickness and number of the circular rings in the heat dissipation fins can be adjusted according to actual needs, and the angle between adjacent straight pipes of the oil pipe can also be adjusted according to actual conditions. A cooling structure with multiple layers of heat dissipation fins and oil pipes superimposed can also be set. The system has strong adjustability and high cooling efficiency, effectively reduces the cooling oil temperature, and ensures the long-term safe and reliable operation of the motor.

[0041] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present invention.

[0042] Example

[0043] Combination Figure 1 , Figure 2 The present invention discloses an aircraft electric propulsion motor oil-gas dual-cooling radiator based on propeller airflow heat dissipation, comprising a heat dissipation fin 1, an oil pipe 2, cooling oil 3, an oil reservoir 4, an oil pump 5 and a propeller 6;

[0044] A propeller 6 is arranged on the top of the electric propulsion motor of the aircraft, and the heat sink 1 is arranged on the end. An oil pipe 2 is arranged in the heat sink 1, and the oil pipe 2 is connected to an oil reservoir 4. The oil reservoir 4 is filled with cooling oil 3, and an oil pump 5 is arranged. First, the cooling oil 3 is pumped into the motor to cool the motor. The high-temperature cooling oil 3 output by the motor is sent to the oil pipe 2 in the heat sink 1. The cooling oil 3 in the oil pipe 2 inside the heat sink 1 is cooled by the airflow generated by the propeller 6 on the top of the electric propulsion motor. The cooled cooling oil 3 is input into the oil reservoir 4 to complete the circulation of the cooling oil 3, thereby realizing the heat dissipation and cooling of the electric propulsion motor.

[0045] As a specific example, combining Figure 3 The heat dissipation fin 1 is composed of a plurality of layers of annular circumferential fins 1-1 and a plurality of rectangular radial fins 1-2 which are cross-connected to form an integrated structure of multiple layers of circular rings; the radius difference between two adjacent annular circumferential fins 1-1 is the same; the rectangular radial fins 1-2 extend from the innermost annular circumferential fin 1-1 to the outermost annular circumferential fin 1-1, and the angle between each two rectangular radial fins 1-2 is the same.

[0046] As a specific example, a cooling oil flow channel hole 1-3 is opened at the midpoint between every two rectangular radial fins 1-2 on the annular circumferential fin 1-1, and the centers of the cooling oil flow channel holes 1-3 at the same position are on the same radius.

[0047] Furthermore, the rectangular radial fins 1-2 are arranged in the middle position between two adjacent cooling oil flow channel holes 1-3 of each layer of circular rings, and the two adjacent layers of circular rings are connected by the rectangular radial fins 1-2. The integrated heat dissipation fins 1 not only increase the stability of the heat dissipation fin structure, but also increase the heat transfer path and heat exchange area, thereby improving the heat dissipation efficiency.

[0048] As a specific example, an oil pipe 2 is installed in the cooling oil flow channel hole 1-3, and the outer wall of the oil pipe 2 is connected to the cooling oil flow channel hole 1-3 opened in the annular circumferential fin 1-1, and the heat of the cooling oil 3 is transferred to the annular circumferential fin 1-1 through the oil pipe 2.

[0049] As a specific example, combining Figure 4 The oil pipe 2 is a curved pipe connected by a straight pipe 2-2 and an arc-shaped pipe 2-1, and is installed in the heat dissipation fin 1 along the circumferential direction.

[0050] As a specific example, the oil pipe 2 is provided with an oil inlet 2 - 3 and an oil outlet 2 - 4 at the position of the heat dissipation fin 1 .

[0051] As a specific example, each layer of annular circumferential fins 1-1 of the heat dissipating fin 1 is provided with a partition 1-4 between the oil inlet 2-3 and the oil outlet 2-4 of the oil pipe 2. Since the thermal conductivity of air is very low, heat conduction between the high-temperature cooling oil 3 at the oil inlet 2-3 and the low-temperature cooling oil 3 at the oil outlet 2-4 is avoided to affect the cooling effect.

[0052] Furthermore, the rectangular radial fins 1-2 provided on the outermost circular ring outer wall and the innermost circular ring inner wall of the heat dissipation fin 1 should avoid the oil pipe 2. The additional rectangular radial fins 1-2 can further enhance the heat exchange capacity and improve the heat dissipation efficiency. In this embodiment, the center line angle of adjacent straight pipes 2-2 in the oil pipe 2 is 12° to 15°, and the two ends of the center arc line of the arc pipe 2-1 of the oil pipe 2 are tangent to the center line of the straight pipe 2-2. The combination of the straight pipe 2-2 and the arc pipe 2-1 enables the oil pipe 2 to be arranged circumferentially along the heat dissipation fin 1, thereby increasing the thermal contact area between the oil pipe 2 and the heat dissipation fin 1.

[0053] As a specific example, the heat sink fins 1 and the oil pipes 2 are both made of copper to improve thermal conductivity, thereby improving the heat dissipation effect of the radiator.

[0054] As a specific example, the working principle of the oil-gas dual-cooling radiator is as follows:

[0055] The cooling oil 3 is pumped out by the oil pump 5 and transported to the motor through the oil pipe 2 for motor cooling. The heated cooling oil 3 flows out of the motor and enters the heat sink 1 through the oil inlet 2-3 of the heat sink 1. Since the oil pipe 2 is connected to the heat sink 1, the cooling oil 3 transfers the heat to the heat sink 1 through the oil pipe 2 under the action of heat conduction. The airflow formed by the rotation of the propeller 6 on the top of the motor performs convection heat exchange, takes away the heat of the cooling oil 3, and improves the heat dissipation efficiency through the heat sink 1, finally achieving the purpose of cooling the cooling oil 3. The cooled cooling oil 3 flows back to the oil storage tank 4 to complete the cycle.

[0056] As a specific example, the oil-gas dual-cooling radiator of the present invention can be used in combination with other cooling systems, such as a casing water cooling system, rotor oil-swinging or oil-spraying cooling, etc.

[0057] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scopes. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An aircraft electric propulsion motor oil-gas dual-cooling radiator based on propeller airflow heat dissipation, characterized in that: It comprises a heat dissipation fin (1), an oil pipe (2), cooling oil (3), an oil storage tank (4), an oil pump (5) and a propeller (6); A propeller (6) is arranged on the top of the electric propulsion motor of the aircraft, and a heat dissipation fin (1) is arranged at the end; an oil pipe (2) is arranged in the heat dissipation fin (1), the oil pipe (2) is connected to an oil reservoir (4), the oil reservoir (4) is filled with cooling oil (3), and an oil pump (5) is arranged, the oil pump (5) is used to pump the cooling oil (3) into the motor to cool the motor; the high-temperature cooling oil (3) output by the motor is input into the oil pipe (2) in the heat dissipation fin (1), the airflow generated by the propeller (6) on the top of the electric propulsion motor cools the cooling oil (3) in the oil pipe (2) inside the heat dissipation fin (1), and the cooled cooling oil (3) is input into the oil reservoir (4), completing the circulation of the cooling oil (3) and realizing heat dissipation cooling of the electric propulsion motor.

2. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 1 is characterized in that: The heat dissipation fin (1) is composed of a plurality of layers of annular circumferential fins (1-1) and a plurality of rectangular radial fins (1-2) which are cross-connected to form an integrated structure in which a plurality of layers of circular rings are connected; the radius difference between two adjacent annular circumferential fins (1-1) is the same; the rectangular radial fins (1-2) extend from the innermost annular circumferential fin (1-1) to the outermost annular circumferential fin (1-1), and the angle between each two rectangular radial fins (1-2) is the same.

3. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 2 is characterized in that: A cooling oil flow channel hole (1-3) is provided at the midpoint between every two rectangular radial fins (1-2) on the annular circumferential fin (1-1), and the centers of the cooling oil flow channel holes (1-3) at the same position are on the same radius.

4. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 3 is characterized in that: An oil pipe (2) is installed in the cooling oil flow channel hole (1-3), and the outer wall of the oil pipe (2) is connected to the cooling oil flow channel hole (1-3) opened in the annular circumferential fin (1-1), and the heat of the cooling oil (3) is transferred to the annular circumferential fin (1-1) through the oil pipe (2).

5. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 1 is characterized in that: The oil pipe (2) is a curved pipe formed by alternatingly connecting a straight pipe (2-2) and an arc-shaped pipe (2-1), and is installed in the heat dissipation fin (1) along the circumferential direction.

6. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 5 is characterized in that: The oil pipe (2) is provided with an oil inlet (2-3) and an oil outlet (2-4) on the outside of the heat dissipation fin (1); the oil inlet (2-3), the oil outlet (2-4) and two adjacent straight pipes (2-2) are connected to form an internally connected oil pipe (2).

7. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 5 is characterized in that: Each layer of annular circumferential fins (1-1) of the heat dissipation fins (1) is provided with a partition (1-4) between the oil inlet (2-3) and the oil outlet (2-4) of the oil pipe (2), thereby blocking heat conduction between the high-temperature cooling oil (3) of the oil inlet (2-3) and the low-temperature cooling oil (3) of the oil outlet (2-4).

8. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 5, characterized in that: The center line angle of adjacent straight pipes (2-2) in the oil pipe (2) is 12° to 15°, the two ends of the center arc of the arc-shaped pipe (2-1) are tangent to the center line of the straight pipe (2-2), and the straight pipe (2-2) and the arc-shaped pipe (2-1) are connected in an alternating manner so that the oil pipe (2) is arranged along the circumference of the heat dissipation fin (1).

9. The aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation according to claim 1, characterized in that: The heat dissipation fins (1) and the oil pipe (2) are both made of copper.

10. A method for operating an aircraft electric propulsion motor oil-air dual cooling radiator based on propeller airflow heat dissipation as claimed in any one of claims 1 to 9, characterized in that: The process is as follows: The cooling oil (3) is pumped out by the oil pump (5) and transported to the motor through the oil pipe (2) for cooling the motor. The heated cooling oil (3) flows out of the motor and enters the heat dissipation fin (1) through the oil inlet (2-3) of the heat dissipation fin (1). Since the oil pipe (2) is connected to the heat dissipation fin (1), the cooling oil (3) transfers heat to the heat dissipation fin (1) through the oil pipe (2) under the action of heat conduction. The airflow formed by the rotation of the propeller (6) on the top of the motor performs convection heat exchange, takes away the heat of the cooling oil (3), and improves the heat dissipation efficiency through the heat dissipation fin (1), thereby finally achieving the purpose of cooling the cooling oil (3). The cooled cooling oil (3) flows back to the oil storage tank (4) to complete the cycle.

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