Leakage detection device for liquid cooling system on airplane

Abstract

The utility model belongs to the technical field of airplane liquid cooling system leakage detection device design, and particularly relates to an airplane liquid cooling system leakage detection device which comprises a gas-liquid separator, a liquid storage tank and an expansion tank. The gas-liquid separator is arranged on a pipeline of the liquid cooling system and is positioned at an inlet part of a liquid pump of the liquid cooling system; the liquid storage tank is arranged at the highest point of the liquid cooling system and is connected to the upper part of the gas-liquid separator through a pipeline; a safety valve is arranged at the top of the liquid storage tank; a liquid level sensor is arranged in the liquid storage tank and is used for detecting the liquid level in the liquid storage tank; a piston is arranged in the expansion box and divides the expansion box into a pressure preset cavity and a volume detection cavity; micro-pressure is applied to the piston in the pressure preset cavity; the volume detection cavity is communicated with a pipeline between the gas-liquid separator and the liquid storage tank through a pipeline; a volume sensor is arranged in the volume detection cavity and used for detecting the volume of the volume detection cavity.

Description

Technical Field

[0001] The present application belongs to the technical field of design of leakage detection devices for liquid cooling systems on aircraft, and specifically relates to a leakage detection device for liquid cooling systems on aircraft. Background Art

[0002] Despite the sealing design of the connections between pipes and equipment in aircraft liquid cooling systems, fluid leaks are still unavoidable. Promptly detecting and identifying leaks in aircraft liquid cooling systems and taking appropriate measures can prevent larger leaks and potentially dangerous accidents.

[0003] Currently, a large liquid storage tank is usually installed at the highest point of the liquid cooling system on an aircraft. While meeting the thermal expansion and contraction requirements of the liquid cooling system's coolant, a liquid level sensor is used to measure the liquid level in the tank. The changes in the liquid level are used to determine whether the liquid cooling system has leaked. This method can usually detect liquid leaks in the liquid cooling system in a timely manner, but it requires that the highest point of the liquid cooling system must have sufficient installation space to install a large liquid storage tank. Especially large liquid cooling systems have a large coolant capacity, so the larger the volume of the liquid storage tank, the larger the installation space required, and the installation space must be of sufficient height. If there is not enough height space, the range of the liquid level sensor will be limited. The small range of the liquid level sensor will cause false alarms when the liquid level in the tank fluctuates due to changes in the aircraft's attitude, which will bring unnecessary psychological burden to the pilot.

[0004] This application is proposed in view of the above-mentioned technical defects. Utility Model Content

[0005] The purpose of the present application is to provide a device for detecting leakage of a liquid cooling system on an aircraft, so as to overcome or alleviate at least one of the technical deficiencies of the prior art.

[0006] The technical solution of this application is:

[0007] A leakage detection device for a liquid cooling system on an aircraft, comprising a gas-liquid separator, a liquid storage tank, and an expansion tank;

[0008] The gas-liquid separator is arranged on the pipeline of the liquid cooling system, and is located at the inlet of the liquid pump of the liquid cooling system;

[0009] The liquid storage tank is set at the highest point of the liquid cooling system and is connected to the top of the gas-liquid separator through a pipeline;

[0010] A safety valve is provided on the top of the liquid storage tank;

[0011] A liquid level sensor is provided in the liquid storage tank, and the liquid level sensor is used to detect the liquid level in the liquid storage tank;

[0012] A piston is provided in the expansion box, which divides the expansion box into a pressure preset chamber and a volume detection chamber;

[0013] A micro-pressure is applied to the piston in the pressure preset chamber;

[0014] The volume detection chamber is connected to the pipeline between the gas-liquid separator and the liquid storage tank through a pipeline;

[0015] A volume sensor is arranged in the volume detection cavity, and the volume sensor is used to detect the volume of the volume detection cavity.

[0016] According to at least one embodiment of the present application, in the aforementioned aircraft liquid cooling system leakage detection device, the liquid level sensor is connected to the aircraft electromechanical control system for data collection and display.

[0017] According to at least one embodiment of the present application, in the aforementioned aircraft liquid cooling system leakage detection device, the expansion tank is placed horizontally.

[0018] According to at least one embodiment of the present application, in the aforementioned aircraft liquid cooling system leakage detection device, a micro-pressure is applied to the piston in the preset pressure chamber, which is achieved by pressurizing the preset pressure chamber.

[0019] According to at least one embodiment of the present application, in the aforementioned aircraft liquid cooling system leakage detection device, the pressurized gas in the preset pressure chamber is nitrogen.

[0020] According to at least one embodiment of the present application, in the aforementioned aircraft liquid cooling system leakage detection device, micro-pressure is applied to the piston in the preset pressure chamber, which is achieved by providing a spring in the preset pressure chamber.

[0021] According to at least one embodiment of the present application, in the aforementioned aircraft liquid cooling system leakage detection device, the volume sensor is connected to the aircraft electromechanical control system for data collection and display.

[0022] This application has at least the following beneficial technical effects:

[0023] Provided is a leakage detection device for a liquid cooling system on an aircraft. The device splits the liquid level measurement function currently implemented by a liquid storage tank to construct a pressure balance body for the liquid storage tank and an expansion tank. The liquid storage tank, which needs to be arranged at the highest point of the liquid cooling system, can be designed to have a smaller volume and height to reduce the requirement for installation space. The expansion tank can be installed at any appropriate position and can be designed to have a larger volume to balance the volume change caused by thermal expansion and contraction of the coolant. By detecting the volume of its volume detection cavity and the liquid level of the liquid storage tank, it is possible to accurately determine whether a liquid leakage in the liquid cooling system has occurred, thereby avoiding false alarms and unnecessary psychological burden on the pilot. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a schematic diagram of a liquid cooling system leakage detection device on an aircraft provided by an embodiment of the present application;

[0025] in:

[0026] 1-gas-liquid separator; 2-pipeline; 3-liquid pump; 4-liquid storage tank; 5-safety valve; 6-liquid level sensor; 7-expansion tank; 8-piston; 9-volume sensor;

[0027] A-Pressure preset chamber; B-Volume detection chamber.

[0028] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0029] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0030] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0031] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0032] The liquid cooling system on an aircraft uses a liquid pump to drive the coolant to circulate in the pipeline. Based on this, an embodiment of the present application provides a leakage detection device for the liquid cooling system on an aircraft, such as Figure 1 As shown, it includes a gas-liquid separator 1, a liquid storage tank 4, and an expansion tank 7.

[0033] The gas-liquid separator 1 is arranged on a pipeline 2 of a liquid cooling system and is located at an inlet portion of a liquid pump 3 of the liquid cooling system.

[0034] The liquid storage tank 4 is set at the highest point of the liquid cooling system and is connected to the top of the gas-liquid separator 1 through a pipeline. The gas-liquid separator 1 can separate the gas in the coolant in the pipeline 2. The separated gas can be discharged to the liquid storage tank 4 through the pipeline in time to avoid the presence of gas in the coolant affecting the stability of the liquid pump 4.

[0035] A safety valve 5 is provided on the top of the liquid storage tank 4. When there is too much gas on the top of the liquid storage tank 4 and the pressure exceeds the safety limit value, the safety valve 5 will automatically open to relieve the pressure.

[0036] A liquid level sensor 6 is provided in the liquid storage tank 4. The liquid level sensor 6 is used to detect the liquid level in the liquid storage tank 4 and can be connected to the aircraft electromechanical control system for data acquisition and display. When adding coolant to the liquid cooling system, the liquid level in the liquid storage tank 4 can be used to determine whether the coolant in the liquid cooling system is full.

[0037] A piston 8 is provided in the expansion box 7, and the piston 8 divides the expansion box 7 into a pressure preset chamber A and a volume detection chamber B. The expansion box 7 can be placed horizontally.

[0038] A micro-pressure is applied to the piston 8 in the preset pressure chamber A. The specific magnitude of the micro-pressure can be selected by relevant technical personnel based on actual conditions when applying the technical solution of this application, and no further explanation is provided here. The micro-pressure applied to the piston 8 in the preset pressure chamber A can be achieved by pressurizing the preset pressure chamber A or providing a spring. Nitrogen can be selected as the pressurizing gas.

[0039] The volume detection chamber B is connected to the pipeline between the gas-liquid separator 1 and the liquid storage tank 4 through a pipeline. Part of the coolant will enter the volume detection chamber B, so that the pressure in the volume detection chamber B is balanced with the pressure in the pressure preset chamber A.

[0040] A volume sensor 9 is provided in the volume detection cavity B. The volume sensor 9 is used to detect the volume of the volume detection cavity B and can be connected to the aircraft electromechanical control system for data collection and display.

[0041] In the aircraft liquid cooling system leak detection device disclosed in the above embodiment, the liquid storage tank 4 and the expansion tank 7 form a pressure balance body. Under the action of the preset micro-pressure in the preset pressure chamber A, when liquid leaks from the liquid cooling system, the liquid level of the liquid storage tank 4 and the volume of the volume detection chamber B in the expansion tank 7 can be detected to continuously decrease and continuously reach a new equilibrium, thereby enabling timely judgment of liquid leakage in the liquid cooling system.

[0042] The aircraft liquid cooling system leakage detection device disclosed in the above embodiment splits the liquid level measurement function currently implemented by the liquid storage tank to construct a pressure balance body of the liquid storage tank 4 and the expansion tank 7. The liquid storage tank 4, which needs to be set at the highest point of the liquid cooling system, can be designed to have a smaller volume and height to reduce the requirements for installation space. The expansion tank 7 can be installed at any appropriate position and can be designed to have a larger volume to balance the volume change caused by thermal expansion and contraction of the coolant. By detecting the volume of its volume detection chamber B and the liquid level of the liquid storage tank 4, it is accurately determined that a liquid leakage has occurred in the liquid cooling system, thereby avoiding false alarms and unnecessary psychological burdens on the pilot.

[0043] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A device for detecting leakage of liquid cooling system on an aircraft, characterized in that: It comprises a gas-liquid separator (1), a liquid storage tank (4), and an expansion tank (7); The gas-liquid separator (1) is arranged on a pipeline (2) of a liquid cooling system and is located at an inlet portion of a liquid pump (3) of the liquid cooling system; The liquid storage tank (4) is arranged at the highest point of the liquid cooling system and is connected to the upper part of the gas-liquid separator (1) through a pipeline; A safety valve (5) is provided on the top of the liquid storage tank (4); A liquid level sensor (6) is provided in the liquid storage tank (4), and the liquid level sensor (6) is used to detect the liquid level in the liquid storage tank (4); A piston (8) is provided in the expansion box (7), and the piston (8) divides the expansion box (7) into a pressure preset chamber (A) and a volume detection chamber (B); A micro-pressure is applied to the piston (8) in the pressure preset chamber (A); The volume detection chamber (B) is connected to the pipeline between the gas-liquid separator (1) and the liquid storage tank (4) through a pipeline; A volume sensor (9) is arranged in the volume detection cavity (B), and the volume sensor (9) is used to detect the volume of the volume detection cavity (B).

2. The device for detecting leakage of liquid cooling system on an aircraft according to claim 1, characterized in that: The liquid level sensor (6) is connected to the aircraft electromechanical control system for data collection and display.

3. The device for detecting leakage of liquid cooling system on an aircraft according to claim 1, characterized in that: The expansion tank (7) is placed horizontally.

4. The device for detecting leakage of liquid cooling system on an aircraft according to claim 1, characterized in that: A micro-pressure is applied to the piston (8) in the pressure preset chamber (A), which is achieved by charging the pressure preset chamber (A).

5. The device for detecting leakage of liquid cooling system on an aircraft according to claim 4, characterized in that: The pressurized gas in the pressure preset chamber (A) is nitrogen.

6. The device for detecting leakage of liquid cooling system on an aircraft according to claim 4, characterized in that: A micro-pressure is applied to the piston (8) in the pressure preset chamber (A), which is achieved by arranging a spring in the pressure preset chamber (A).

7. The device for detecting leakage of liquid cooling system on an aircraft according to claim 1, characterized in that: The volume sensor (9) is connected to the aircraft electromechanical control system for data collection and display.

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