Water channel cooling system for aerospace starter generator controller, starter generator controller system and starter generator

Abstract

The utility model discloses a water cooling system for an aerospace generator controller, a generator controller system and a generator, the water cooling system comprises a liquid inlet, a liquid outlet and a partial pressure area, the partial pressure area is communicated with the liquid inlet and the liquid outlet, the partial pressure area comprises a plurality of serially connected water channels, and the plurality of serially connected water channels are communicated with the liquid inlet and the liquid outlet. When cooling liquid enters from the liquid inlet, the cooling liquid firstly enters the partial pressure area and then is discharged from the liquid outlet. According to the utility model, the differential pressure in the controller is realized, and a good heat dissipation effect is achieved. The utility model can be used for the generator controller system. The invention further provides a starting machine.

Description

Technical Field

[0001] The present application relates to the technical field of starter generator controllers, and in particular to a water channel cooling system for aerospace starter generator controllers, a starter generator controller system, and a starter generator. Background Art

[0002] The starter generator controller serves as the control module of the starter generator.

[0003] In the related art, in order to prevent excessive water pressure in the motor controller and reduce the possibility of water entering the controller and damaging the internal structure, it is necessary to design a pressure dividing structure at the coolant inlet and inside the motor controller. The pressure dividing schemes in the related art propose two pressure dividing schemes: series pressure dividing and installing a pressure reducing valve. Specifically:

[0004] (1) In the series pressure division scheme, although the flow rate is uniform and the heat dissipation is uniform, the pressure loss is limited to 30%, and it is difficult to achieve a higher pressure loss. For the cooling system of new energy vehicles, it is difficult to achieve a pressure loss of about 90%.

[0005] (2) In the installation plan of the pressure reducing valve, due to installation requirements, it is installed at the inlet, at least 4 meters away from the outlet, and the volume of the pressure range will be limited.

[0006] That is to say, the related art has the problem that the pressure loss of direct series pressure division is insufficient, and the pressure reducing valve is complicated to install and has a large size. Utility Model Content

[0007] The embodiments of the present application provide a water channel cooling system for an aerospace starter generator controller, a starter generator controller system, and a starter generator, so as to achieve voltage division while ensuring cooling and heat dissipation.

[0008] The embodiments of this application adopt the following technical solutions:

[0009] In a first aspect, an embodiment of the present application provides a water cooling system, wherein the system comprises: a liquid inlet, a liquid outlet, and a pressure-dividing region, wherein the pressure-dividing region is respectively connected to the liquid inlet and the liquid outlet, and the pressure-dividing region comprises a plurality of series water channels,

[0010] When the coolant enters from the liquid inlet, it first enters the partial pressure area and then is discharged from the liquid outlet.

[0011] In some embodiments, the plurality of series-connected water channels form an L-shaped structure.

[0012] In some embodiments, the pressure-dividing region includes a heat dissipation fin structure, and the heat dissipation fin structure is disposed in the center of the plurality of series-connected water channels.

[0013] In some embodiments, a plurality of heat dissipation tooth structures are further included, and the plurality of heat dissipation tooth structures are distributed on one side or multiple sides of the heat dissipation fin structure.

[0014] In some embodiments, the liquid inlet is connected to an aircraft cooling system.

[0015] In some embodiments, the pressure of the aviation cooling system at the liquid inlet is N, and after passing through the partial pressure region, the pressure at the liquid outlet becomes N / 10.

[0016] In some embodiments, the plurality of series water channels in the pressure-dividing region are integrally formed.

[0017] In some embodiments, the voltage division area is located inside a housing of the controller.

[0018] In a second aspect, an embodiment of the present application further provides a starter generator controller system, which includes: the water channel cooling system for aerospace starter generator controller described in the first aspect.

[0019] In a third aspect, an embodiment of the present application further provides a starter generator, which includes the starter generator controller system described in the second aspect.

[0020] At least one of the above technical solutions adopted in the embodiments of the present application can achieve the following beneficial effects: the water cooling system includes: a liquid inlet, a liquid outlet, and a pressure-dividing region. The pressure-dividing region is respectively connected to the liquid inlet and the liquid outlet, and the pressure-dividing region includes multiple series water channels. When the coolant enters the liquid inlet, it first enters the pressure-dividing region and then is discharged from the liquid outlet. The above cooling system realizes the differential pressure inside the controller, the pressure loss range can be designed, and an excellent heat dissipation effect is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0022] Figure 1 This is a schematic diagram of the internal structure of a water channel cooling system for an aerospace generator controller in an embodiment of the present application;

[0023] Figure 2 This is a schematic diagram of the water flow direction of the water channel cooling system for the aerospace generator controller in an embodiment of the present application;

[0024] Figure 3 This is a schematic diagram of the internal structure of a water channel cooling system for an aerospace generator controller in another embodiment of the present application. DETAILED DESCRIPTION

[0025] To make the purpose, technical solutions, and advantages of this application more clear, the technical solutions of this application will be clearly and completely described below in conjunction with the specific embodiments of this application and the corresponding drawings. Obviously, the embodiments described are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0026] The following describes in detail the technical solutions provided by various embodiments of the present application in conjunction with the accompanying drawings.

[0027] The embodiment of the present application provides a water channel cooling system for aerospace generator controller, such as Figures 1 to 3 As shown, a schematic diagram of the internal structure of the water cooling system in an embodiment of the present application is provided, wherein the system comprises: a liquid inlet 1, a liquid outlet 2, and a pressure-dividing area 3, wherein the pressure-dividing area 3 is connected to the liquid inlet 1 and the liquid outlet 2 respectively, and the pressure-dividing area 3 comprises a plurality of series water channels. When the coolant enters from the liquid inlet 1, it first enters the pressure-dividing area 3 and then is discharged from the liquid outlet 2. The liquid inlet 1 and the liquid outlet 2 are independently arranged and the direction of the liquid inlet 1 is arranged in the same direction as the direction of the liquid outlet 2. The pressure-dividing area 3 is connected with the liquid inlet 1 and the liquid outlet 2. When the coolant enters the pressure-dividing area 3 through the liquid inlet 1, pressure-dividing and heat-dissipating treatment can be performed through a plurality of series water channels. When the coolant enters from the liquid inlet 1, it first enters the pressure-dividing area 3 and then is discharged from the liquid outlet 2. In this way, the plurality of series water channels (pressure-dividing) in the pressure-dividing area 3 control the pressure loss to 90%, and the coolant is pressure-divided from PN20 to PN2. The controller internal pressure is divided, the pressure loss range is designed, and a good heat dissipation effect is achieved. The function of the pressure dividing area 3 is to divide the pressure through multiple series water channels so that the coolant is reduced in pressure after entering the pressure dividing area 3 at the liquid inlet 1, and the heat is dissipated through the heat dissipation structure in the multiple series water channels.

[0028] As a preference in this embodiment, the multiple series water channels form an L-shaped structure.

[0029] The multiple series waterways can form an "L"-shaped structure, such as Figure 2 As shown, the direction of liquid flow in the "L"-shaped structure is shown by the arrow. The elbow pressure-dividing area can divide the pipeline pressure PN20 of the aviation cooling system into PN2, and control its pressure loss to 90%.

[0030] As a preference in this embodiment, the pressure dividing area 3 includes a heat dissipation fin structure 5, and the heat dissipation fin structure 5 is arranged in the center of the plurality of series-connected water channels.

[0031] like Figure 1 and Figure 3As shown, the heat dissipation fin structure 5 is arranged in the center of the multiple series water channels, and the multiple series water channels are connected in series to serve as the pressure dividing area 3.

[0032] As a preference in this embodiment, a plurality of heat dissipation tooth structures 4 are further included, and the plurality of heat dissipation tooth structures 4 are distributed on one side or multiple sides of the heat dissipation fin structure.

[0033] like Figure 1 and Figure 3 As shown, multiple heat dissipation tooth structures 4 are respectively deployed on one side or multiple sides of the heat dissipation fin structure, which can improve the heat dissipation effect.

[0034] As a preference in this embodiment, the liquid inlet 1 is connected to an aviation cooling system (not shown).

[0035] The coolant of the aviation cooling system is connected to the liquid inlet 1 , and the coolant enters the pressure division area 3 through the liquid inlet 1 for pressure division and heat dissipation.

[0036] As a preference in this embodiment, the pressure of the aviation cooling system at the liquid inlet 1 is N, and the pressure at the liquid outlet becomes N / 10 after passing through the pressure-dividing region 3 .

[0037] The pressure-dividing area 3 is a water channel pressure-dividing design. The multiple series-connected water channels in the pressure-dividing area 3 form a bend pressure-dividing area. The bend pressure-dividing area can divide the pipeline pressure PN20 of the aviation cooling system into PN2 and control its pressure loss to about 90%.

[0038] It can be understood that the pressure-dividing area 3 serves as the main heat exchange area in the controller, and the pressure-dividing area is L-shaped from top to bottom, with heat dissipation fins distributed in the center of the pipe to enhance the heat dissipation effect. Finally, the coolant flows out through the outlet through the pressure-dividing area.

[0039] As a preference in this embodiment, the multiple series water channels in the pressure dividing area 3 are integrally formed.

[0040] like Figure 1 and Figure 3 As shown, the multiple series water channels in the pressure dividing area 3 can be designed as an integral part, so as to facilitate production and installation.

[0041] As a preference in this embodiment, the voltage dividing area 3 is located inside the housing of the controller.

[0042] like Figure 1 and Figure 3 As shown, the pressure-dividing area 3 inside the housing of the controller can receive the coolant from the liquid inlet 1 and discharge it from the liquid outlet 2 after pressure reduction and heat dissipation.

[0043] The embodiment of the present application further provides a starter generator controller system, which includes: the water channel cooling system for aerospace starter generator controller, the system includes: a liquid inlet, a liquid outlet, and a pressure dividing area, the pressure dividing area is respectively connected to the liquid inlet and the liquid outlet, the pressure dividing area includes a plurality of series water channels,

[0044] When the coolant enters from the liquid inlet, it first enters the partial pressure area and then is discharged from the liquid outlet.

[0045] In some embodiments, the plurality of series-connected water channels form an L-shaped structure.

[0046] In some embodiments, the pressure dividing area includes a heat dissipation fin structure, and the heat dissipation fin structure is disposed in the center of the water channel.

[0047] In some embodiments, a plurality of heat dissipation tooth structures are further included, and the plurality of heat dissipation tooth structures are distributed on one side or multiple volumes of the heat dissipation fin structure.

[0048] In some embodiments, the liquid inlet is connected to an aircraft cooling system.

[0049] In some embodiments, the pressure of the aviation cooling system at the liquid inlet is N, and after passing through the partial pressure region, the pressure at the liquid outlet becomes N / 10.

[0050] In some embodiments, the plurality of series water channels in the pressure-dividing region are integrally formed.

[0051] In some embodiments, the voltage division area is located inside a housing of the controller.

[0052] An embodiment of the present application further provides a starter generator, which includes the starter generator controller system.

[0053] The starter controller system divides the aviation cooling system's pipe pressure (PN20) into PN2, controlling the pressure drop to approximately 90% while dissipating heat, making it more suitable for starters.

[0054] The foregoing is merely an embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various changes and variations. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present application should all be included within the scope of the claims of the present application.

Claims

1. A water channel cooling system for aerospace generator controller, wherein: The system includes: a liquid inlet, a liquid outlet, and a pressure-dividing area, wherein the pressure-dividing area is connected to the liquid inlet and the liquid outlet respectively, and the pressure-dividing area includes a plurality of series-connected water channels. When the coolant enters from the liquid inlet, it first enters the partial pressure area and then is discharged from the liquid outlet.

2. The system of claim 1, wherein: The multiple series-connected water channels form an L-shaped structure.

3. The system of claim 1, wherein: The pressure dividing area includes a heat dissipation fin structure, and the heat dissipation fin structure is arranged in the center of the plurality of series water channels.

4. The system of claim 3, wherein: It also includes a plurality of heat dissipation tooth structures, which are distributed on one side or multiple sides of the heat dissipation fin structure.

5. The system of claim 1, wherein: The liquid inlet is connected to an aviation cooling system.

6. The system of claim 5, wherein: The pressure of the aviation cooling system at the liquid inlet is N, and after passing through the partial pressure region, the pressure at the liquid outlet becomes N / 10.

7. The system of claim 1, wherein: The plurality of series-connected water channels in the pressure-dividing area are integrally formed.

8. The system of claim 1, wherein: The voltage division area is located inside the housing of the controller.

9. A generator controller system, wherein: include: A water channel cooling system for an aerospace generator controller according to any one of claims 1 to 8.

10. A generator, wherein: Comprising the generator controller system as described in claim 9.

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