Axial magnetic flux aviation special motor air cooling structure

Abstract

The utility model discloses an air cooling structure of a special axial flux aviation motor. The air cooling structure comprises a stator bracket in rolling connection with a rotating shaft, the rear rotor disc and the rotating shaft are fixedly connected to one side of the stator support, and the other side of the front rotor disc is fixedly connected with the rear rotor disc through the outer cover net. A plurality of radial claws are arranged on the periphery of the middle disc-type structure of the stator support, the first air ducts are arranged in the radial claws in the radial direction, the first air inlets are formed in the side face of the disc-type structure, and the first air outlets are formed in the annular faces of the radial claws; the rear rotor disc or the front rotor disc is provided with a second air inlet or a third air inlet corresponding to the first air inlet; the outer cover net is provided with a plurality of fourth air outlets. Cooling the stator bracket from the inside through the first air duct; cooling the stator bracket from the outside through a fourth air duct and a fifth air duct; the second air duct and the third air duct accelerate the cooling rate of the stator bracket through heat transfer. And a multi-air-duct cooling mode is adopted, so that the cooling effect of the stator bracket is effectively improved, the performance of the motor is improved, and high practicability and wide applicability are achieved.

Description

Technical Field

[0001] The invention relates to an air-cooling structure of a motor, in particular to an air-cooling structure of an axial flux aviation-specific motor, and belongs to the technical field of axial flux motors. Background Art

[0002] Axial magnetic field motor, also known as axial flux motor or disc motor, has a disc-type stator assembly and rotor assembly. The motor is composed of multiple stators, which are installed on the stator bracket; most of the heat of the motor is generated by the stator winding, so the heat dissipation efficiency of the stator bracket greatly affects the performance of the motor.

[0003] Therefore, it is necessary to provide a structure to solve the heat dissipation problem and improve the heat dissipation efficiency. Summary of the invention

[0004] In order to solve the deficiencies of the prior art, the purpose of the present invention is to provide an air-cooling structure for an axial flux aviation-specific motor.

[0005] In order to achieve the above object, the present invention adopts the following technical solution:

[0006] An axial flux aviation-specific motor air-cooling structure includes a stator bracket 2 rollingly connected to a rotating shaft 1;

[0007] On one side of the stator bracket 2, the rear rotor disc 5 is fixedly connected to the rotating shaft 1;

[0008] On the other side of the stator support 2, the front rotor disc 3 is fixedly connected to the rear rotor disc 5 through the outer cover net 4 surrounding the stator support 2;

[0009] The middle part of the stator support is a disc structure, and a plurality of radial claws 22 are arranged on the outer periphery of the disc structure. The first air duct is arranged radially inside the radial claws 22, the first air inlet is arranged on the side of the disc structure, and the first air outlet 25 is arranged on the annular surface of the radial claws.

[0010] The rear rotor disc 5 is provided with a second air inlet 51 corresponding to the first air inlet, or the front rotor disc 3 is provided with a third air inlet 31 corresponding to the first air inlet;

[0011] The outer cover net 4 is provided with a plurality of fourth air outlets 41 along the circumferential direction.

[0012] The above-mentioned first air ducts are arranged in pairs, and the first air inlets are respectively arranged on opposite sides of the disc structure.

[0013] In the radial direction, a second air duct leading to a second air inlet 51 is disposed in the rear rotor disk 5 , and a second air outlet 52 is disposed on the annular surface of the rear rotor disk.

[0014] Furthermore, the gap between the rear rotor disk 5 and the stator bracket 2 forms a fourth air duct, and the fourth air duct is connected to the fourth air outlet 41 .

[0015] A third air duct leading to a third air inlet 31 is disposed in the front rotor disk 3 , and a third air outlet 32 ​​is disposed on the annular surface of the rear rotor disk.

[0016] Furthermore, the gap between the front rotor disk 3 and the stator bracket 2 forms a fifth air duct, and the fifth air duct is connected to the fourth air outlet 41 .

[0017] The present invention is beneficial in that:

[0018] An axial flux aviation-specific motor air-cooling structure of the present invention realizes cooling of the stator bracket from the inside by respectively arranging first air inlets on two side surfaces of the stator bracket along the circumferential direction and arranging a first air duct in the stator bracket; arranging corresponding second and third air inlets on the front and rear rotor disks to facilitate entry of cooling air; forming a fourth and fifth air ducts through the gap between the front and rear rotor disks and the stator bracket to realize cooling of the two side surfaces of the stator bracket; and arranging the second and third air ducts in the front and rear rotor disks to accelerate the cooling rate of the stator bracket through heat transfer.

[0019] The air-cooling structure of an axial flux aviation-specific motor of the present invention has a simple structure, is easy to use, and has a multi-duct cooling mode, which effectively improves the cooling effect of the stator bracket and improves the performance of the motor, and has strong practicality and wide applicability. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A cross-sectional view of the schematic structural diagram of the air-cooled structure of an axial flux aviation-specific motor.

[0021] Figure 2 Schematic diagram of the structure of the front rotor disc.

[0022] Figure 3 It is a schematic diagram of the structure of the rear rotor disc.

[0023] Figure 4 A cross-sectional view of a schematic structural diagram of a stator bracket.

[0024] Figure 5 This is a schematic diagram of the structure of the stator bracket.

[0025] The meanings of the symbols in the accompanying drawings are as follows:

[0026] 1. Rotating shaft, 2. Stator bracket, 3. Front rotor disc, 4. Outer cover net, 5. Rear rotor disc;

[0027] 21. front air inlet, 22. radial claw, 23. right air inlet, 24. left air inlet, 25. first air outlet;

[0028] 31. The third air inlet, 32. The third air outlet;

[0029] 41. Fourth air outlet;

[0030] 51. Second air inlet, 52. Second air outlet. DETAILED DESCRIPTION

[0031] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0032] An axial flux aviation-specific motor air-cooling structure is composed of a stator bracket 2, a rear rotor disk 5, a front rotor disk 3 and an outer cover net 4.

[0033] like Figure 1 As shown, the stator bracket 2 is rollingly connected to the rotating shaft 1 through a bearing, the rear rotor disk 5 is fixedly connected to the rotating shaft 1 through bolts on one side of the stator bracket 2, the outer cover net 4 is fixedly connected to the rear rotor disk 5 through bolts, and the front rotor disk 3 is fixedly connected to the outer cover net 4 through bolts on the other side of the stator bracket 2.

[0034] like Figure 2 As shown, the outer cover net 4 is provided with a plurality of fourth air outlets 41 along the circumferential direction.

[0035] like Figure 4 and 5 As shown, the middle part of the stator support is a disc structure, and a plurality of radial claws 22 are provided on the outer periphery of the disc structure. In the radial direction, a pair of first air ducts are provided in the radial claws 22, the first air inlets (right air inlet 23, left air inlet 24) are respectively provided on the opposite sides of the disc structure, and the first air outlets 25 are respectively provided on the annular surfaces of the radial claws. The stator support is also provided with a corresponding front air inlet 21.

[0036] like Figure 3 As shown, the rear rotor disc 5 is provided with a second air inlet 51 corresponding to the first air inlet (left air inlet 24) in the axial direction. In addition, a second air duct leading to the second air inlet 51 is provided in the rear rotor disc 5 in the radial direction, and a second air outlet 52 is provided on the annular surface of the rear rotor disc.

[0037] The gap between the rear rotor disk 5 and the stator bracket 2 also forms a fourth air duct, which is connected to the fourth air outlet 41 .

[0038] like Figure 2 As shown, along the axial direction, the front rotor disk 3 is provided with a third air inlet 31 corresponding to the first air inlet (right air inlet 23); and along the radial direction, a third air duct leading to the third air inlet 31 is provided in the front rotor disk 3, and the third air outlet 32 ​​is provided on the annular surface of the rear rotor disk.

[0039] The gap between the front rotor disk 3 and the stator bracket 2 also forms a fifth air duct, which is connected to the fourth air outlet 41 .

[0040] When using,

[0041] The shaft rotates at high speed with the motor.

[0042] A. External cold air enters the inside of the turntable housing (the front rotor disc 3 and the rear rotor disc 5) through the third air inlet 31 and the second air inlet 51 respectively, passes through the third air duct and the second air duct, and is thrown out from the third air outlet 32 ​​and the second air outlet 52 to cool the rotor disc housing;

[0043] B. External cold air enters the motor through the third air inlet 31 and the second air inlet 51, and enters the stator bracket 2 through the right air inlet 23 and the left air inlet 24 respectively, carrying the heat generated by the stator bracket to become hot air and be discharged through the first air outlet 25, and then thrown out of the motor through the fourth air outlet 41, dissipating the heat of the stator bracket from the inside;

[0044] C. External cold air enters the motor through the third air inlet 31 and the second air inlet 51. The gap between the rear rotor disk 5 and the stator bracket 2 and the gap between the front rotor disk 3 and the stator bracket 2, i.e., the fourth air duct and the fifth air duct, dissipate heat on both sides of the stator bracket.

[0045] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the above embodiments do not limit the present invention in any form, and any technical solution obtained by equivalent replacement or equivalent transformation falls within the protection scope of the present invention.

Claims

1. An air-cooling structure for an axial flux aviation-specific motor. It is characterized in that It comprises a stator support (2) which is rollingly connected to the rotating shaft (1); On one side of the stator bracket (2), the rear rotor disc (5) is fixedly connected to the rotating shaft (1); On the other side of the stator support (2), the front rotor disk (3) is fixedly connected to the rear rotor disk (5) via an outer cover net (4) surrounding the stator support (2); The middle part of the stator support is a disc-shaped structure, a plurality of radial claws (22) are provided on the outer periphery of the disc-shaped structure, a first air duct is radially arranged inside the radial claws (22), a first air inlet is arranged on the side of the disc-shaped structure, and a first air outlet (25) is arranged on the annular surface of the radial claws; The rear rotor disk (5) is provided with a second air inlet (51) corresponding to the first air inlet, or the front rotor disk (3) is provided with a third air inlet (31) corresponding to the first air inlet; The outer cover net (4) is provided with a plurality of fourth air outlets (41) along the circumferential direction.

2. The air cooling structure according to claim 1, It is characterized in that The first air ducts are arranged in pairs, and the first air inlets are respectively arranged on opposite sides of the disc structure.

3. The air cooling structure according to claim 1, It is characterized in that In the radial direction, a second air duct leading to a second air inlet (51) is provided in the rear rotor disk (5), and a second air outlet (52) is provided on the annular surface of the rear rotor disk.

4. The air cooling structure according to claim 3, It is characterized in that In the radial direction, the gap between the rear rotor disk (5) and the stator support (2) forms a fourth air duct, and the fourth air duct is connected to the fourth air outlet (41).

5. The air cooling structure according to claim 1, It is characterized in that In the radial direction, a third air duct leading to a third air inlet (31) is provided in the front rotor disk (3), and the third air outlet (32) is provided on the annular surface of the rear rotor disk.

6. The air cooling structure according to claim 5, It is characterized in that In the radial direction, the gap between the front rotor disk (3) and the stator support (2) forms a fifth air duct, and the fifth air duct is connected to the fourth air outlet (41).

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