CN221263520U - Cooling structure of permanent magnet synchronous motor of high-power high-speed aviation compressor - Google Patents
Cooling structure of permanent magnet synchronous motor of high-power high-speed aviation compressor Download PDFInfo
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- CN221263520U CN221263520U CN202322790599.0U CN202322790599U CN221263520U CN 221263520 U CN221263520 U CN 221263520U CN 202322790599 U CN202322790599 U CN 202322790599U CN 221263520 U CN221263520 U CN 221263520U
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- 238000001816 cooling Methods 0.000 title claims abstract description 73
- 230000001360 synchronised effect Effects 0.000 title claims abstract description 16
- 230000017525 heat dissipation Effects 0.000 claims abstract description 45
- 230000000694 effects Effects 0.000 abstract description 4
- 239000007788 liquid Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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- Motor Or Generator Cooling System (AREA)
Abstract
The utility model relates to the technical field of aviation motors, in particular to a cooling structure of a permanent magnet synchronous motor of a high-power high-speed aviation compressor. The structure described by the utility model utilizes a double-channel heat dissipation system formed by the motor stator component and the rotor component, increases the contact area of cooling air, and simultaneously utilizes the suction effect formed by the heat dissipation spline to improve the heat dissipation efficiency of the motor, has no additional heat dissipation device, and has compact structure, light weight and few parts, thereby meeting the characteristic requirements of high power density of the aviation high-power motor.
Description
Technical Field
The utility model relates to the technical field of aviation motors, in particular to a cooling structure of a permanent magnet synchronous motor of a high-power high-speed aviation compressor.
Background
The aviation high-power high-speed permanent magnet synchronous motor mainly comprises a motor stator assembly, a rotor assembly and the like, and has compact structure and light weight in product design due to the light weight requirement of the prior aviation aircraft, so that the problem of heat dissipation is always a difficult problem of the aviation high-power high-speed permanent magnet synchronous motor.
The traditional high-power aviation motor adopts liquid cooling or external forced air cooling and other forms. If the liquid cooling structure is complex, a liquid cooling system is needed to be equipped, a special liquid inlet cooling channel is arranged for the motor, and the problems of liquid inlet and sealing of the motor are faced; if external forced air cooling is adopted, an additional fan needs to be designed, and meanwhile, an air duct is designed for air circulation, but the cooling design cannot effectively cool the motor. The cooling forms have the problems of complex structure and heavy weight. .
Disclosure of utility model
The purpose of the utility model is that: the cooling structure of the permanent magnet synchronous motor for the high-power high-speed aviation compressor is provided, and the heat dissipation requirement of the motor is met on the premise of ensuring small size and light weight of the structure.
The technical scheme of the utility model is as follows: in order to solve the technical problem, a cooling structure of a permanent magnet synchronous motor of an aviation high-power high-speed aviation compressor is provided, comprising: the motor comprises a motor shell 1, a stator 2, a left half shaft 4-1, a right half shaft 4-2, a heat dissipation spline 5 and a rotor assembly 6;
The stator 2 is coaxially arranged in the motor shell 1 and is in interference connection with the motor shell 1; the rotor assembly 6 is coaxially arranged in the stator 2; the two ends of the motor shell 1 are symmetrically provided with a cooling air inlet 3 and a cooling air outlet 7;
The heat dissipation spline 5 is coaxially arranged in the rotor assembly 6 and is in interference fit connection with the rotor assembly 6; the left half shaft 4-1 and the right half shaft 4-2 are hollow shafts, the left half shaft 4-1 and the right half shaft 4-2 are respectively sleeved at two ends of the rotor component 6, and the right half shaft 4-2 is provided with an air inlet hole along the radial direction and corresponds to the position of the cooling air inlet 3 on the motor shell 1; the left half shaft 4-1 is provided with air outlet holes along the radial direction, which correspond to the positions of the cooling air outlets 7 on the motor shell 1.
In one possible embodiment, the heat dissipating spline 5 has a spiral groove; the spiral groove and the rotor assembly 6 form a rotor heat dissipation channel through interference fit; the heat dissipation spline rotates synchronously with the rotor assembly 6; drawing cooling air from the cooling air inlet 3 of the motor housing 1 through the spiral groove; cooling air enters the rotor cooling channel through the air inlet hole of the right half shaft 4-2 to directly cool the rotor assembly 6; finally, the air is discharged through a cooling air outlet 7 of the motor housing 1.
In one possible embodiment, the outer circumference of the connection part of the stator 2 and the motor housing 1 is provided with a heat dissipation groove in the circumferential direction; the heat dissipation groove on the outer circumference of the stator 2 and the motor shell 1 form a stator heat dissipation channel, so that cooling air enters the motor to directly dissipate heat of the stator 2; the air passes through the heat dissipation grooves of the stator 2 and is discharged through the cooling air outlet 7 of the motor housing 1.
In one possible embodiment, the heat dissipation groove on the outer circumference of the stator 2 is a U-shaped groove.
In one possible embodiment, the depth of the U-shaped groove is 4mm.
In one possible embodiment, the left axle shaft 4-1 and the right axle shaft 4-2 are respectively connected with the rotor assembly 6 through interference fit, and the rotor assembly 6 drives the left axle shaft 4-1 and the right axle shaft 4-2 to rotate through interference fit.
The beneficial technical effects of the utility model are as follows:
The utility model increases the contact area of cooling air by using a double-channel heat dissipation system formed by the motor stator component and the rotor component, improves the heat dissipation efficiency of the motor by using the suction effect formed by the heat dissipation spline, has no additional heat dissipation device, has compact structure, light weight and few parts, and meets the characteristic requirement of high power density of the aviation high-power motor.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following description will briefly explain the drawings required to be used in the embodiments of the present utility model, and it is obvious that the drawings described below are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a stator, rotor and cooling structure of a permanent magnet synchronous motor of an aviation high-power high-speed aviation compressor according to an embodiment of the utility model;
The motor comprises a 1-motor shell, a 2-stator, a 3-cooling air inlet, a 4-1-left half shaft, a 4-2-right half shaft, a 5-heat dissipation spline, a 6-rotor assembly and a 7-cooling air outlet, wherein the motor shell is provided with a plurality of cooling air inlets;
FIG. 2 is a schematic diagram of a heat dissipating spline structure;
Fig. 3 is a schematic view of a stator structure.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features and exemplary embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by showing examples of the invention. The present invention is in no way limited to any particular arrangement and method set forth below, but rather covers any adaptations, alternatives, and modifications of structure, method, and device without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques have not been shown in detail in order not to unnecessarily obscure the present invention.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other, and the embodiments may be referred to and cited with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
Fig. 1 is a schematic diagram of an implementation of a stator assembly, a rotor assembly and a cooling structure of a permanent magnet synchronous motor of an aviation high-power high-speed aviation compressor according to an embodiment of the invention.
Referring to fig. 1, a cooling structure of a permanent magnet synchronous motor of an aviation high-power high-speed aviation compressor includes: the motor comprises a motor shell 1, a stator 2, a left half shaft 4-1, a right half shaft 4-2, a heat dissipation spline 5 and a rotor assembly 6;
The stator 2 is coaxially arranged in the motor shell 1 and is in interference connection with the motor shell 1; the rotor assembly 6 is coaxially arranged in the stator 2; the two ends of the motor shell 1 are symmetrically provided with a cooling air inlet 3 and a cooling air outlet 7;
The heat dissipation spline 5 is coaxially arranged in the rotor assembly 6 and is in interference fit connection with the rotor assembly 6; the left half shaft 4-1 and the right half shaft 4-2 are hollow shafts, the left half shaft 4-1 and the right half shaft 4-2 are respectively sleeved at two ends of the rotor component 6, and the right half shaft 4-2 is provided with an air inlet hole along the radial direction and corresponds to the position of the cooling air inlet 3 on the motor shell 1; the left half shaft 4-1 is provided with air outlet holes along the radial direction, which correspond to the positions of the cooling air outlets 7 on the motor shell 1.
In one possible embodiment, the heat dissipating spline 5 has a spiral groove; the spiral groove and the rotor assembly 6 form a rotor heat dissipation channel through interference fit; the heat dissipation spline and the rotor 6 rotate synchronously; drawing cooling air from the cooling air inlet 3 of the motor housing 1 through the spiral groove; cooling air enters the rotor cooling channel through the air inlet hole of the right half shaft 4-2 to directly cool the rotor assembly 6; finally, the air is discharged through a cooling air outlet 7 of the motor housing 1.
In one possible embodiment, the outer circumference of the connection part of the stator 2 and the motor housing 1 is provided with a heat dissipation groove in the circumferential direction; the heat dissipation groove on the outer circumference of the stator 2 and the motor shell 1 form a stator heat dissipation channel, so that cooling air enters the motor to directly dissipate heat of the stator 2; the air passes through the heat dissipation grooves of the stator 2 and is discharged through the cooling air outlet 7 of the motor housing 1.
In one possible embodiment, the heat dissipation groove on the outer circumference of the stator 2 is a U-shaped groove.
In one possible embodiment, the depth of the U-shaped groove is 4mm.
In one possible embodiment, the left axle shaft 4-1 and the right axle shaft 4-2 are each connected to the rotor assembly 6 by an interference fit, and the rotor assembly 6 is rotated by the interference fit with the axle shaft 4.
Working principle:
The cooling air enters the motor through the cooling air inlet 3 and is divided into two paths to respectively dissipate heat of the stator 2 and the rotor assembly 6. As shown in fig. 3, the outer circumference of the stator 2 adopts a heat dissipation groove with a diversion function, and forms a stator heat dissipation channel with the motor shell 1, so that cooling air enters the motor to directly dissipate heat of the stator 2. The air passes through the heat dissipation grooves of the stator 2 and is discharged through the cooling air outlet 7 of the motor housing 1. Wherein the outer circle heat dissipation channel of the stator 2 is formed by 60U-shaped grooves with the width of 3mm and the depth of 4 mm.
As shown in fig. 2, the heat dissipation spline 5 is designed as a spiral groove with a suction effect, wherein the number of the spiral grooves is 14, and the spiral grooves are uniformly distributed on the outer circumference. The spiral groove and the rotor 6 form a rotor heat dissipation channel through interference fit. The heat radiation spline rotates in synchronization with the rotor 6. Cooling air from the cooling air inlet 3 of the motor housing 1 is sucked through the spiral groove. The cooling air passes through the holes of the shaft 4 and enters the rotor cooling channels to directly cool the rotor 6. Finally, the air is discharged through the cooling air outlet 7 of the motor housing 2.
The cooling air inlet 3 and the cooling air outlet 7 are arranged in a central symmetry manner in the motor housing, so that cooling air is ensured to have heat dissipation channels entering the stator 2 and the rotor 6.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered in the scope of the present invention.
Claims (6)
1. The utility model provides an aviation high-power high-speed aviation compressor PMSM cooling structure which characterized in that includes: the motor comprises a motor shell (1), a stator (2), a left half shaft (4-1), a right half shaft (4-2), a heat dissipation spline (5) and a rotor assembly (6);
The stator (2) is coaxially arranged in the motor shell (1) and is in interference connection with the motor shell (1); the rotor assembly (6) is coaxially arranged in the stator (2); the two ends of the motor shell (1) are symmetrically provided with a cooling air inlet (3) and a cooling air outlet (7);
The heat dissipation spline (5) is coaxially arranged in the rotor assembly (6) and is in interference fit connection with the rotor assembly (6); the left half shaft (4-1) and the right half shaft (4-2) are hollow shafts, the left half shaft (4-1) and the right half shaft (4-2) are respectively sleeved at two ends of the rotor assembly (6), and the right half shaft (4-2) is provided with an air inlet hole along the radial direction and corresponds to the position of a cooling air inlet (3) on the motor shell (1); the left half shaft (4-1) is provided with air outlet holes along the radial direction, which correspond to the positions of cooling air outlets (7) on the motor shell (1).
2. The cooling structure of the permanent magnet synchronous motor of the aviation high-power high-speed aviation compressor according to claim 1, wherein the heat dissipation spline (5) is provided with a spiral groove; the spiral groove and the rotor assembly (6) form a rotor heat dissipation channel through interference fit; the heat dissipation spline and the rotor assembly (6) synchronously rotate; sucking cooling air from a cooling air inlet (3) of the motor housing (1) through the spiral groove; cooling air enters the rotor cooling channel through the air inlet hole of the right half shaft (4-2) to directly cool the rotor assembly (6); finally, the air is discharged through a cooling air outlet (7) of the motor housing (1).
3. The cooling structure of the permanent magnet synchronous motor of the aviation high-power high-speed aviation compressor according to claim 1, wherein a heat dissipation groove is formed in the circumferential direction of the outer periphery of the joint of the stator (2) and the motor shell (1); the heat dissipation groove on the outer circumference of the stator (2) and the motor shell (1) form a stator heat dissipation channel, so that cooling air enters the motor to directly dissipate heat of the stator (2); air passes through the heat dissipation grooves of the stator (2) and is discharged through the cooling air outlet (7) of the motor shell (1).
4. The cooling structure of the permanent magnet synchronous motor of the aviation high-power high-speed aviation compressor according to claim 3, wherein the heat dissipation groove on the outer circumference of the stator (2) is a U-shaped groove.
5. The cooling structure of the permanent magnet synchronous motor of the aviation high-power high-speed aviation compressor, according to claim 4, is characterized in that the depth of the U-shaped groove is 4mm.
6. The cooling structure of the permanent magnet synchronous motor of the aviation high-power high-speed aviation compressor according to claim 1 is characterized in that a left half shaft (4-1) and a right half shaft (4-2) are respectively connected with a rotor assembly (6) through interference fit, and the rotor assembly (6) drives the left half shaft (4-1) and the right half shaft (4-2) to rotate through interference fit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322790599.0U CN221263520U (en) | 2023-10-17 | 2023-10-17 | Cooling structure of permanent magnet synchronous motor of high-power high-speed aviation compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322790599.0U CN221263520U (en) | 2023-10-17 | 2023-10-17 | Cooling structure of permanent magnet synchronous motor of high-power high-speed aviation compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221263520U true CN221263520U (en) | 2024-07-02 |
Family
ID=91655499
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322790599.0U Active CN221263520U (en) | 2023-10-17 | 2023-10-17 | Cooling structure of permanent magnet synchronous motor of high-power high-speed aviation compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221263520U (en) |
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2023
- 2023-10-17 CN CN202322790599.0U patent/CN221263520U/en active Active
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