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

Abstract

The utility model 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. According to the utility model, 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 utility model relates to the technical field of motor cooling, 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, global demand for electrified aircraft is growing. Compared to traditional fuel-powered aircraft engines, electric propulsion motors offer significant advantages such as high energy conversion efficiency, zero pollution, and low noise, attracting widespread attention from researchers. As the core power component of electric aircraft, the overall performance of electric propulsion motors directly affects aircraft performance.

[0003] With the continuous advancement and upgrading of electric propulsion motor technology, researchers are increasingly focusing on the issue of efficient heat dissipation in electric propulsion motors. Motor cooling performance has a significant impact on power density. This performance determines the motor's ability to dissipate heat during high-power operation, which in turn affects its power density. High-power-density motors, due to their compact size, high power per unit volume, and small surface area, require efficient heat dissipation technology to prevent excessive temperature rise.

[0004] Motor cooling technologies primarily include air cooling, oil cooling, and water cooling. Direct oil cooling is a more efficient method, but the heated oil requires a cooling device for recycling, and additional cooling devices often increase energy consumption. Researchers are increasingly interested in recooling the heated oil without adding additional cooling devices to reduce system energy consumption and improve energy utilization. There is an urgent need to develop a cooling device suitable for recooling the cooling oil in electric propulsion motors. Utility Model Content

[0005] The utility model 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 for achieving the purpose of the utility model 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 provided on the top of the electric propulsion motor of the aircraft, and a heat dissipation fin is provided at the end; an oil pipe is provided in the heat dissipation fin, the oil pipe is connected to an oil reservoir, the oil reservoir is filled with cooling oil, and an oil pump is provided, 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 heat dissipation 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 heat dissipation fin, and the cooled cooling oil is input into the oil reservoir, completing the circulation of the cooling oil, thereby realizing heat dissipation and 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 connected by multiple layers of circular rings; 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 fin 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 the 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, thereby blocking 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 between adjacent straight pipes in the oil pipe is 12° to 15°, the two 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 along the circumference of the heat dissipation fin.

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

[0016] Compared with the prior art, the present invention has the following significant advantages:

[0017] (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;

[0018] (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;

[0019] (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, effectively reduces the cooling oil temperature, and ensures the long-term safe and reliable operation of the motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a structural diagram of an aircraft electric propulsion motor oil-gas dual-cooling radiator based on propeller airflow heat dissipation according to the utility model.

[0021] Figure 2 It is a side structural diagram of the utility model.

[0022] Figure 3 It is a structural schematic diagram of the heat dissipation fins in the utility model.

[0023] Figure 4 It is a structural schematic diagram of the oil pipe in the utility model.

[0024] In the figure: 1-heat sink fin, 2-oil pipe, 3-cooling oil, 4-oil reservoir, 5-oil pump, 6-propeller, 1-1-annular circumferential fin, 1-2-rectangular radial fin, 1-3-cooling oil flow hole, 1-4-partition, 2-1-arc pipe, 2-2-straight pipe, 2-3-oil inlet, 2-4-oil outlet. DETAILED DESCRIPTION

[0025] 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 embodiments described 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 making creative efforts are within the scope of protection of the present invention.

[0026] The utility model 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 reservoir 4, an oil pump 5 and a propeller 6;

[0027] A propeller 6 is provided on the top of the electric propulsion motor of the aircraft, and a heat dissipation fin 1 is provided at the end; an oil pipe 2 is provided 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 provided, 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, and 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 to complete the circulation of the cooling oil 3, thereby realizing heat dissipation and cooling of the electric propulsion motor.

[0028] Furthermore, the heat dissipation fins 1 are cross-connected by multiple layers of annular circumferential fins 1-1 and multiple rectangular radial fins 1-2, forming an integrated structure with multiple layers of circular rings 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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 the two adjacent straight pipes 2-2 are connected to form an internally connected oil pipe 2.

[0033] 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, blocking 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.

[0034] Furthermore, the centerline angle between adjacent straight pipes 2-2 in the oil pipe 2 is 12° to 15°, the two ends of the center arc of the arc pipe 2-1 are tangent to the centerline 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 sink 1.

[0035] Furthermore, the heat dissipation fins 1 and the oil pipe 2 are both made of copper.

[0036] The present invention also provides a method for operating the aircraft electric propulsion motor oil-air dual-cooling radiator based on propeller airflow heat dissipation, the process of which is as follows:

[0037] 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 radiating fin 1 through the oil inlet 2-3 of the radiating fin 1. Since the oil pipe 2 is connected to the radiating fin 1, the cooling oil 3 transfers heat to the radiating 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 convective heat exchange, takes away the heat of the cooling oil 3, and improves the heat dissipation efficiency through the radiating fin 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.

[0038] The utility model provides an axial flux permanent magnet motor cooling oil cooling system and a cooling method thereof. By setting 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. The manufacturing process is simplified and the heat dissipation stability is also improved. The unique heat dissipation fin structure and oil pipe design 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 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.

[0039] The technical solutions in the embodiments of the present invention will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present invention.

[0040] Example

[0041] Combine Figure 1 、 Figure 2 The utility model 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;

[0042] A propeller 6 is provided on the top of the electric propulsion motor of the aircraft, and the heat dissipation fin 1 is provided at the end. An oil pipe 2 is provided in the heat dissipation fin 1, and the oil pipe 2 is connected to the oil reservoir 4. The oil reservoir 4 is filled with cooling oil 3, and an oil pump 5 is provided. 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 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. The cooled cooling oil 3 is input into the oil reservoir 4 to complete the circulation of the cooling oil 3, thereby realizing heat dissipation and cooling of the electric propulsion motor.

[0043] As a specific example, combining Figure 3 The heat dissipation fins 1 are cross-connected by several layers of annular circumferential fins 1-1 and several rectangular radial fins 1-2, forming an integrated structure with 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.

[0044] 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.

[0045] Furthermore, the rectangular radial fins 1-2 are arranged in the middle position between two adjacent cooling oil flow 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.

[0046] 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 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.

[0047] 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.

[0048] 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 .

[0049] As a specific example, 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. 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, which affects the cooling effect.

[0050] Furthermore, the rectangular radial fins 1-2 provided on the outer wall of the outermost circular ring and the inner wall of the innermost circular ring of the heat sink 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 centerline angle of adjacent straight pipes 2-2 in the oil pipe 2 is 12° to 15°. The ends of the center arc of the curved pipe 2-1 of the oil pipe 2 are tangent to the centerline of the straight pipe 2-2. The combination of the straight pipe 2-2 and the curved pipe 2-1 allows the oil pipe 2 to be arranged along the circumference of the heat sink 1, increasing the thermal contact area between the oil pipe 2 and the heat sink 1.

[0051] As a specific example, the heat dissipation 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.

[0052] As a specific example, the working principle of the oil-gas dual-cooling radiator is as follows:

[0053] 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 radiating fin 1 through the oil inlet 2-3 of the radiating fin 1. Since the oil pipe 2 is connected to the radiating fin 1, the cooling oil 3 transfers heat to the radiating 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 convective heat exchange, takes away the heat of the cooling oil 3, and improves the heat dissipation efficiency through the radiating fin 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.

[0054] 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.

[0055] This utility model uses specific examples to illustrate the principles and implementation methods of this utility model. The above examples are only used to help understand the method and core concept of this utility model. At the same time, for those skilled in the art, according to the concept of this utility model, there may be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the utility model.

Claims

1. An aircraft electric propulsion motor oil-air 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 provided on the top of the electric propulsion motor of the aircraft, and a heat dissipation fin (1) is provided at the end; an oil pipe (2) is provided in the heat dissipation fin (1), the oil pipe (2) is connected to an oil reservoir (4), cooling oil (3) is poured into the oil reservoir (4), and an oil pump (5) is provided, 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) that are cross-connected to form an integrated structure in which multiple 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 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).

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 interlacing a straight pipe (2-2) and an arc-shaped pipe (2-1), and is circumferentially installed inside the heat dissipation fin (1).

6. The aircraft electric propulsion motor oil-air dual-cooling radiator based on propeller airflow heat dissipation according to claim 5, characterized in that: The oil pipe (2) is provided with an oil inlet (2-3) and an oil outlet (2-4) outside 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, 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 centerline angles of adjacent straight pipes (2-2) in the oil pipe (2) are 12° to 15°, the two ends of the center arc of the arc-shaped pipe (2-1) are tangent to the centerline of the straight pipe (2-2), and the straight pipe (2-2) and the arc-shaped pipe (2-1) are staggeredly connected 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 pipes (2) are both made of copper.

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