阅读说明：本技术 基于热管散热的航空电机定子 (Aviation motor stator based on heat pipe heat dissipation ) 是由 张博 高跃 李彦祥 刘立军 邓春志 于 2021-02-23 设计创作，主要内容包括：本申请公开了基于热管散热的航空电机定子,包括绕组、定子铁芯以及本体,所述绕组设置在定子铁芯外环面处,所述本体设置在定子铁心内侧环面处,还包括热管组件,所述热管组件嵌入所述基座,所述热管组件上设置有散热翅片。本发明具有如下有益效果：通过采用在本体上插接热管组件,利用热管组件上的散热翅片增加了散热面积与散热速度,从而提高了散热速度,避免了热管组件温度升高。(The application discloses aeroengine stator based on heat pipe cooling, including winding, stator core and body, the winding sets up in stator core outer anchor ring department, the body sets up in stator core inboard anchor ring department, still includes the heat pipe subassembly, the embedding of heat pipe subassembly the base, be provided with radiating fin on the heat pipe subassembly. The invention has the following beneficial effects: through adopting the heat pipe subassembly of pegging graft on the body, utilize fin on the heat pipe subassembly to increase heat radiating area and radiating rate to improve radiating rate, avoided the heat pipe subassembly temperature rise.)

1. The aviation motor stator based on heat pipe radiation comprises a winding, a stator core and a body, wherein the winding is arranged on the outer annular surface of the stator core, the body is arranged on the inner annular surface of the stator core, and the aviation motor stator is characterized by further comprising a heat pipe assembly, the heat pipe assembly is embedded into the base, and the heat pipe assembly is provided with radiating fins.

2. A heat pipe heat dissipation based aero-motor stator as claimed in claim 1 wherein said stator core is ring shaped, said windings abut an outer wall of said stator core, and said body abuts an inner wall of said stator core.

3. A heat pipe heat dissipation based aero-motor stator as claimed in claim 1 wherein said heat pipe assembly comprises a plurality of heat pipes, a heat dissipation base and heat dissipation fins, said heat pipes being secured to said heat dissipation base, said heat dissipation fins being disposed on said heat pipes.

4. A heat pipe heat dissipation-based aero-motor stator as claimed in claim 3, wherein said heat dissipating fins are vertically fixed on a wall of said heat pipe.

5. A heat pipe heat dissipation based aero-motor stator as claimed in claim 3 wherein said heat pipe is a hollow heat pipe.

6. A heat pipe heat dissipation based aero-motor stator as claimed in claim 3 wherein said heat pipe ferrule is secured to said base.

7. A heat pipe heat dissipation based aero-motor stator as claimed in claim 3 wherein said heat pipe is U-shaped.

8. A heat pipe heat dissipation-based aero-motor stator as claimed in claim 3, wherein a first heat pipe, a second heat pipe, a third heat pipe and a fourth heat pipe are fixed on said base, and said first heat pipe, said second heat pipe, said third heat pipe and said fourth heat pipe are not communicated with each other.

9. A heat pipe heat dissipation based aero-motor stator as claimed in claim 1 wherein said stator core is interference coupled with said body.

10. A heat pipe heat dissipation based aero-motor stator as claimed in claim 1 wherein a substance capable of absorbing heat based on phase change is disposed within said heat pipe assembly.

Technical Field

The invention relates to the field of permanent magnet synchronous motors, in particular to an aviation motor stator based on heat pipe heat dissipation.

Background

Aviation motors are generally required to have high power, small volume, light weight, i.e., high power density. However, the design with high power density can cause the heat load of the motor to be high, and the motor winding can generate a large amount of heat energy when the motor runs. The heat of the motor winding cannot be effectively transferred, and the serious problems of motor insulation reduction, insulation breakdown, demagnetization of the permanent magnet and the like can be directly caused by the fact that excessive heat is accumulated in the motor winding or the iron core.

Disclosure of Invention

Aiming at the problems, the invention provides an aviation motor stator based on heat pipe heat dissipation.

The technical scheme adopted by the invention is as follows:

the utility model provides an aeroengine stator based on heat pipe cooling, includes winding, stator core and body, the winding sets up in stator core outer annular face department, the body sets up in stator core inboard ring face department, still includes the heat pipe subassembly, the embedding of heat pipe subassembly the base, be provided with radiating fin on the heat pipe subassembly.

When the current density of the motor winding continuously rises, the winding generates a large amount of heat which is firstly transferred to the stator core through the winding, the stator core is in interference connection with the body, the heat is then transferred to the body from the stator core, the body is embedded with a large amount of heat pipe assemblies (particularly the heat pipe assemblies with high heat conductivity coefficients), and the heat is continuously brought to the heat conduction fins due to the high heat conductivity coefficients of the heat pipe assemblies and is brought into the air along with the air flow.

In the motor stator, the heat pipe assembly is inserted into the body, and the heat radiating area and the heat radiating speed are increased by utilizing the heat radiating fins on the heat pipe assembly, so that the heat radiating speed is improved, and the temperature rise of the heat pipe assembly is avoided.

Optionally, the stator core is annular, the winding is attached to the outer wall of the stator core, and the body is attached to the inner wall of the stator core.

Optionally, the heat pipe assembly includes a plurality of heat pipes, a heat dissipation base and heat dissipation fins, the heat pipes are fixed on the heat dissipation base, and the heat dissipation fins are arranged on the heat pipes.

Optionally, the heat dissipation fins are vertically fixed on the tube wall of the heat pipe.

Optionally, the heat pipe is a hollow heat pipe.

The heat pipe of cavity form can guarantee that the heat pipe can have good heat conductivity, and when the heat transfer on the body was for the heat pipe, the temperature of the gas in the heat pipe rose, and high-temperature gas rose to the crest of a pipe department of heat pipe rapidly, and then radiating fin was in the air with heat transfer rapidly on the pipe wall of rethread heat pipe.

Optionally, the heat pipe ferrule is fixed on the base.

Optionally, the heat pipe is U-shaped.

The U-shaped heat pipes are convenient for being clamped and fixed on the base, and the pipe walls of two adjacent heat pipes are tightly attached.

Optionally, the base is fixed with a first heat pipe, a second heat pipe, a third heat pipe and a fourth heat pipe, and the first heat pipe, the second heat pipe, the third heat pipe and the fourth heat pipe are not communicated with each other.

The heat pipes are not communicated with each other, so that mutual interference among the heat pipes can be avoided.

Optionally, the stator core is in interference connection with the body.

The interference connection can guarantee that the joint strength between stator core and the body is high stability good, can guarantee again that the radiating rate is fast.

Optionally, the interference joint of the stator core and the body can be coated with heat-conducting silicone grease or other substances with high heat conductivity coefficient, so that the heat dissipation efficiency is improved.

Optionally, a substance capable of absorbing heat based on phase change is disposed in the heat pipe assembly.

The invention has the beneficial effects that: through adopting the heat pipe subassembly of pegging graft on the body, utilize fin on the heat pipe subassembly to increase heat radiating area and radiating rate to improve radiating rate, avoided the heat pipe subassembly temperature rise.

Description of the drawings:

FIG. 1 is a schematic diagram of an aero-motor stator based on heat pipe heat dissipation;

FIG. 2 is a schematic view of the body and stator core fit;

FIG. 3 is a schematic block diagram of the construction of a heat pipe assembly;

FIG. 4 is a side view of the heat pipe assembly;

fig. 5 is a schematic cross-sectional view taken along the direction T-T in fig. 4.

The figures are numbered: 1. the heat pipe assembly comprises a heat pipe assembly, 2, a body, 3, a stator core, 4, a winding, 101, a first heat pipe, 102, a second heat pipe, 103, a third heat pipe, 104, a fourth heat pipe, 105, radiating fins, 106 and a base.

The specific implementation mode is as follows:

the present invention will be described in detail below with reference to the accompanying drawings.

As shown in fig. 1, fig. 2, fig. 3, fig. 4, and fig. 5, the aviation motor stator based on heat pipe heat dissipation includes a winding 4, a stator core 3, and a body 2, the winding 4 is disposed on an outer annular surface of the stator core 3, the body 2 is disposed on an inner annular surface of the stator core, and further includes a heat pipe assembly 1, the heat pipe assembly 1 is embedded in a base 106, and the heat pipe assembly 1 is provided with heat dissipation fins 105.

When the current density of the motor winding 4 continuously rises, the winding 4 generates a large amount of heat, the heat is firstly transferred to the stator core 3 through the winding 4, the stator core 3 is in interference connection with the body 2, the heat is then transferred to the body 2 from the stator core 3, the body 2 is embedded with a large amount of heat pipe assemblies 1 (particularly, the heat pipe assemblies 1 are the heat pipe assemblies 1 with high heat conductivity coefficients), and the heat is continuously brought to the heat conduction fins due to the high heat conductivity coefficients of the heat pipe assemblies 1 and is brought into the air along with the air flow.

In the motor stator, the heat pipe assembly 1 is inserted into the body 2, and the heat radiating area and the heat radiating speed are increased by using the heat radiating fins 105 on the heat pipe assembly 1, so that the heat radiating speed is increased, and the temperature rise of the heat pipe assembly 1 is avoided.

As shown in fig. 1, 2, 3, 4 and 5, the stator core 3 is annular, the winding 4 is attached to the outer wall of the stator core 3, and the body 2 is attached to the inner wall of the stator core 3.

As shown in fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5, the heat pipe assembly 1 includes a plurality of heat pipes, a heat dissipation base 106 and heat dissipation fins 105, the heat pipes are fixed on the heat dissipation base 106, and the heat dissipation fins 105 are disposed on the heat pipes.

As shown in fig. 1, fig. 2, fig. 3, fig. 4, and fig. 5, the heat dissipating fins 105 are vertically fixed to the wall of the heat pipe.

As shown in fig. 1, fig. 2, fig. 3, fig. 4, and fig. 5, the heat pipe is a hollow heat pipe.

The heat pipe of cavity form can guarantee that the heat pipe can have good heat conductivity, and when the heat transfer on body 2 was for the heat pipe, the gaseous temperature of heat pipe rose, and high-temperature gas rose to the crest of a pipe department of heat pipe rapidly, and then radiating fin 105 on the pipe wall of rethread heat pipe was in the air with heat transfer rapidly.

As shown in fig. 1, 2, 3, 4 and 5, the heat pipe ferrule is secured to the base 106.

As shown in fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5, the heat pipe is U-shaped.

The U-shaped heat pipes facilitate the fixing of the ferrule on the base 106, and the pipe walls of two adjacent heat pipes are tightly attached.

As shown in fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5, a first heat pipe 101, a second heat pipe 102, a third heat pipe 103 and a fourth heat pipe 104 are fixed on a base 106, and the first heat pipe 101, the second heat pipe 102, the third heat pipe 103 and the fourth heat pipe 104 are not communicated with each other.

The heat pipes are not communicated with each other, so that mutual interference among the heat pipes can be avoided.

As shown in fig. 1, 2, 3, 4, and 5, the stator core 3 is interference-connected to the body 2.

Interference connection can guarantee that the joint strength high stability between stator core 3 and the body 2 is high, can guarantee again that the radiating rate is fast.

It should be noted that the arrows in fig. 4 and 5 indicate the direction of heat transfer, the body 2 transfers heat to the heat pipe, the heat pipe transfers heat to the heat dissipating fins 105, and the heat dissipating fins then transfer heat to the air.

A substance that can absorb heat based on phase change is also placed inside the heat pipe assembly 1.

The substances capable of absorbing heat based on phase change can be liquid or solid, the liquid is heated to vaporize and then be liquefied when being cooled, and the solid is heated to vaporize and then be desublimated when being cooled, so that the heat can be transferred from bottom to top in the two processes. The substance that can absorb heat based on phase change is particularly arranged within the first heat pipe 101, or the second heat pipe 102, or the third heat pipe 103, or the fourth heat pipe 104. Of course, the substance that can absorb heat based on the phase change is not limited to a liquid or a solid, and may be a gas.

The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, which is defined by the claims and their equivalents, and can be directly or indirectly applied to other related fields of technology.