Integrated electric centrifugal pump of airplane liquid cooling system

Abstract

The utility model belongs to the field of airborne equipment, and particularly relates to an integrated electric centrifugal pump of an airplane liquid cooling system. According to the integrated electric centrifugal pump of the airplane liquid cooling system, the pump body, the motor, the controller and the controller are rearranged, parameters of an impeller and a volute of the centrifugal pump are optimized, and the purpose of in-situ replacement of the electric centrifugal pump is achieved. Comprising a pump body, a motor and a controller which are integrated, the pump body is connected with an output shaft of the motor through a spline on a transmission shaft, and the controller is installed at the upper end of the motor. The installation problem of the electric centrifugal pump in the limited space of an airplane is solved, and meanwhile the heat dissipation problem of the motor and the controller and the electromagnetic compatibility protection problem are solved.

Description

Technical Field

[0001] This utility model belongs to the field of airborne equipment, specifically relating to an integrated electric centrifugal pump for an aircraft liquid cooling system. Background Technology

[0002] Currently, the electric centrifugal pumps used in aircraft liquid cooling systems have several drawbacks. They have a high starting current, which puts a significant strain on the aircraft's electrical system; a high normal operating current, which leads to high power consumption; and the use of brushed motors, which require regular brush replacements, resulting in poor maintainability.

[0003] To address the issues with existing electric centrifugal pumps, the impeller and volute need to be redesigned, the brushless motor replaced, and a controller added. To resolve electromagnetic compatibility issues, an additional controller is required. Due to space constraints on the aircraft, the controller cannot be installed separately; therefore, an integrated electric centrifugal pump structure is needed to ensure the new electric centrifugal pump can replace the existing one in situ. Summary of the Invention

[0004] The purpose of this invention is to provide an integrated electric centrifugal pump for an aircraft liquid cooling system. By rearranging the pump body, motor, controller, and controller, and optimizing the parameters of the centrifugal pump impeller and volute, the electric centrifugal pump can be replaced in situ.

[0005] The present invention provides an integrated electric centrifugal pump for an aircraft liquid cooling system, comprising a pump body, a motor and a controller integrated into one unit. The pump body is connected to the output shaft of the motor via a spline on a drive shaft, and the controller is mounted on the upper end of the motor.

[0006] Advantageously or alternatively, the motor has an upper platform, and the controller is connected to the upper platform via studs.

[0007] Advantageously or alternatively, the controller has a vertically oriented metal mounting plate and a horizontally arranged drive board and power module inside, with a control board mounted on the metal mounting plate.

[0008] Advantageously or alternatively, the drive plate is mounted on the upper platform of the motor housing via support columns.

[0009] Advantageously or alternatively, the power module of the controller is encapsulated in a metal housing and mounted on an upper platform with fins below the upper platform.

[0010] Advantageously or optionally, the control panel has a display panel for displaying the operating time of the electric centrifugal pump and fault codes.

[0011] Advantageously or alternatively, the housing of the controller has a glass plate through which the display panel can be viewed.

[0012] Advantageously or optionally, the controller housing also has an electrical connector for connection to the aircraft power cable.

[0013] Advantageously or alternatively, the motor housing has a closed air duct for forced air cooling through a fan at the rear of the motor.

[0014] Beneficial effects: This utility model integrates electric centrifugal pumps, solving the installation problem of electric centrifugal pumps in the limited space of aircraft, as well as the heat dissipation problem of motor and controller, and the electromagnetic compatibility protection problem.

[0015] The features, functionalities, and advantages already discussed can be implemented independently in various examples, or combined in other examples. Further details of the examples can be seen in the following description and accompanying figures. Attached Figure Description

[0016] When read in conjunction with the accompanying drawings, the embodiments, preferred modes of use, other objects, and descriptions thereof will be best understood by referring to the following detailed description of embodiments of the invention, wherein:

[0017] Figure 1 Structural composition diagram of an electric centrifugal pump;

[0018] Figure 2 Controller installation diagram;

[0019] Figure 3 A schematic diagram of the controller display window.

[0020] 1-Pump body, 2-Motor, 3-Controller, 4-Glass plate, 5-Drive board, 6-Power module, 7-Metal mounting plate, 8-Control board, 9-Electrical connector Detailed Implementation

[0021] The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. In fact, many different examples may be described, and these examples should not be construed as limited to those set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of this disclosure to those skilled in the art.

[0022] Now refer to the attached diagram, Figure 1 An example of an integrated electric centrifugal pump for an aircraft liquid cooling system is provided, comprising: a pump body 1, a motor 2, and a controller 3. The pump body 1 is a separate structure, connected to the output shaft of the motor 2 via a spline on a drive shaft. The controller 3 and the housing of the motor 2 are connected by studs, and their internal circuitry is connected by wires.

[0023] See Figure 2The controller 3 also includes a vertically oriented metal mounting plate 7 and a horizontally arranged drive plate 5 and power module 6. A control plate 8 is mounted on the metal mounting plate 7. The drive plate 5 is mounted on the upper platform of the motor housing via support columns. The power module 6 of the controller 3 is encapsulated in a metal shell and mounted on the upper platform of the motor housing. Heat is conducted to the fins of the motor 2 via the upper platform of the motor housing. Fins are located below the upper platform of the motor to increase the heat dissipation area.

[0024] A conductive rubber gasket is installed between motor 2 and controller 3 to seal the area and prevent electromagnetic radiation and interference. A closed air duct is installed inside the housing of motor 2, and forced air cooling is achieved through a fan at the rear of motor 2.

[0025] See Figure 3 The controller 3 has an electrical connector 9 and an electromagnetically shielded glass plate 4 on its outer casing. The electrical connector 9 is connected to the aircraft's power cable to supply power to the electric centrifugal pump. The glass plate 4 is used to observe the cumulative operating time of the booster pump and maintenance reminder indicators displayed internally. The controller 3 has an opening on its side wall with an electromagnetically shielded glass plate installed for observing the digital display of operating time and maintenance reminder indicator lights on the control board 8.

[0026] The connection cable between controller 3 and motor 2 is led out from the upper platform of motor 2 housing to reduce external leads and electromagnetic radiation interference. The surfaces of motor housing and controller are treated with conductive oxidation, and conductive rubber strips are installed at the connection point to ensure complete contact between housing and controller, achieving end-face sealing and electromagnetic shielding.

[0027] Descriptions of various advantageous arrangements have been shown for illustrative and descriptive purposes, but such descriptions are not intended to be exclusive or limited to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different advantageous examples may be described as having different advantages compared to other advantageous examples. One or more examples have been selected and described in order to best illustrate the principles and practical applications of the examples, and to enable those skilled in the art to understand that this disclosure contains various examples with various modifications suitable for the particular intended use.

Claims

1. An integrated electric centrifugal pump for an aircraft liquid cooling system, characterized by: The integrated pump body (1), motor (2) and controller (3) are connected by the spline on the transmission shaft and the output shaft of the motor (2), and the controller (3) is installed on the upper end of the motor (2).

2. The integrated electric centrifugal pump of claim 1, wherein: The motor (2) has an upper platform, and the controller (3) is connected with the upper platform through studs.

3. The integrated electric centrifugal pump of claim 2, wherein: The controller (3) has a vertical metal mounting plate (7) and a horizontally arranged drive plate (5) and power module (6) inside, and a control plate (8) is installed on the metal mounting plate (7).

4. The integrated electric centrifugal pump of claim 3, wherein: The drive plate (5) is installed on the upper platform of the motor housing through support columns.

5. The integrated electric centrifugal pump of claim 4, wherein: The power module (6) of the controller (3) is selected to be packaged with a metal shell and installed on the upper platform, and the lower part of the upper platform has fins.

6. The integrated electric centrifugal pump of claim 5, wherein: The control plate (8) has a display panel for displaying the working time and fault code of the electric centrifugal pump.

7. The integrated electric centrifugal pump of claim 6, wherein: The controller (3) has a glass sheet (4) on the shell, and the display panel can be observed through the glass sheet (4).

8. The integrated electric centrifugal pump of claim 7, wherein: The controller (3) also has an electrical connector (9) on the shell, which is connected to the power cable of the aircraft.

9. The integrated electric centrifugal pump of claim 8, wherein: The motor housing has a closed air duct, and the motor tail fan forces air cooling and heat dissipation.

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