A leakage storage device

Abstract

The application provides a liquid leakage storage device, belonging to the technical field of airborne fuel tank inerting, which comprises a cavity 1, a locking screw and nut assembly 3, a liquid discharge nozzle 4 and a cap assembly 5. The cavity 1 is a cylindrical structure, the upper end surface is provided with a flange plate interface for connecting with a reserved mounting surface of a pipeline shell, and a thin tube is arranged on the upper end surface and extends into the cavity. The lower end surface is provided with a flange plate interface for connecting with the liquid discharge nozzle 4. The locking screw and nut assembly 3 fastens the liquid discharge nozzle 4 and the cavity 1. The cap assembly 5 is threadedly connected with the liquid discharge nozzle 4. The device can prevent fuel slow seepage through a one-way valve and further pollute the airborne inerting system, and can realize that the stored liquid leakage cannot flow back under different flight postures, and can be widely applied to the structure design with liquid leakage storage requirements.

Description

Technical Field

[0001] This application belongs to the field of airborne fuel tank inerting technology, and particularly relates to a leakage storage device. Background Technology

[0002] The connecting lines between the aircraft fuel tank and the inerting system are designed with one-way valves to prevent fuel from flowing back into the inerting system.

[0003] However, currently, the sealing performance of one-way valves can only be 100% sealed under certain pressure conditions, and one-way valves are prone to failure. Fuel still has the risk of slow reverse leakage. Once the inerting system is contaminated by fuel, its performance will degrade or even fail and become unusable. Summary of the Invention

[0004] To address the problem in related technologies where slowly leaking fuel diffuses into the front-end inerting system, leading to performance degradation or even failure of the inerting system, this invention provides a leakage storage device, the technical solution of which is as follows:

[0005] A leakage storage device includes: a cavity 1, a locking screw and nut assembly 3, a drain nozzle 4, and a plug assembly 5;

[0006] The cavity 1 is a cylindrical structure with a flange interface reserved on the upper end for connecting to the reserved mounting surface of the pipeline shell. A thin tube is provided on the upper end and extends into the cavity. A flange interface is reserved on the lower end for connecting the drain nozzle 4.

[0007] The locking screw and nut assembly 3 secures the drain nozzle 4 to the cavity 1; the plug assembly 5 is threadedly connected to the drain nozzle 4.

[0008] Optionally, a sealing groove is provided on the lower end face of the cavity 1, and a sealing ring 2 is provided in the sealing groove. The sealing ring 2 is located between the drain nozzle 4 and the cavity 1. The sealing ring 2 is in a compressed state under the fastening action of the locking screw and nut assembly 3.

[0009] Optionally, the lower drain port of the drain nozzle 4 has an M12 external thread and a 74° bevel at the lower end.

[0010] Optionally, the plug assembly 5 is composed of an M12 outer nut, a movable plug with a 74° beveled end face, and a chain link.

[0011] Optionally, the drain nozzle 4 and the plug assembly 5 are screwed together to form a beveled seal.

[0012] Optionally, the upper surface of the cavity 1 is provided with multiple connection holes, and the cavity 1 is connected to the reserved mounting surface of the pipeline shell through the connection holes.

[0013] Optionally, a plurality of fastening holes are provided at the corresponding positions of the lower end face of the cavity 1 and the edge of the drain nozzle 4. The locking screw and nut assembly 3 passes through the fastening holes to fasten the drain nozzle 4 to the cavity 1.

[0014] Optionally, the length of the capillary extension is 2 / 3 of the cavity depth.

[0015] Optionally, the diameter of the capillary tube ranges from Φ1 to Φ3.

[0016] This invention adds a leakage storage device to the connecting pipeline between the airborne inerting system and the aircraft fuel tank, which can prevent fuel from slowly seeping through the one-way valve and contaminating the airborne inerting system. It also ensures that stored leakage will not flow back under different flight attitudes, and can be widely applied in structural designs requiring leakage storage. Attached Figure Description

[0017] Figure 1 This is a schematic cross-sectional view of a leakage storage device provided in an embodiment of the present invention;

[0018] Figure 2 This is a top view schematic diagram of a leakage storage device provided in an embodiment of the present invention;

[0019] Figure 3 This is a schematic diagram illustrating the use of a leakage storage device provided in an embodiment of the present invention. Detailed Implementation

[0020] The present application will now be described in further detail with reference to specific embodiments and accompanying drawings.

[0021] This invention provides a leakage storage device; please refer to [link / reference]. Figure 1 It includes: cavity 1, sealing ring 2, locking screw and nut assembly 3, drain nozzle 4, and plug assembly 5;

[0022] The cavity 1 is a cylindrical structure with a flange interface pre-installed on its upper end for connection to the pre-installed mounting surface of the pipeline shell. The upper end may have multiple connection holes a, such as... Figure 2 As shown, four connection holes a can be provided, and screws and nuts can be used to connect to the reserved mounting surface of the pipeline shell through these four connection holes a; the lower end face is also a flange interface and is provided with a sealing groove, and the sealing ring 2 is located in the sealing groove;

[0023] The drain nozzle 4 and the cavity 1 are connected by a flange, and the sealing ring 2 is located between the drain nozzle 4 and the cavity 1.

[0024] The locking screw and nut assembly 3 is used to fasten the drain nozzle 4 to the cavity 1, so that the sealing ring 2 is in a compressed state.

[0025] Multiple fastening holes may be provided at corresponding positions on the lower end face of the cavity 1 and the upper end face of the discharge nozzle 4. The fastening holes on the lower end face of the cavity 1 and the fastening holes on the upper end face of the discharge nozzle 4 have the same shape and size. Figure 2 As shown, the lower end face of the cavity 1 may be provided with 4 fastening holes b. The locking screw and nut assembly 3 passes through the fastening holes to fasten the drain nozzle 4 to the cavity 1; the plug assembly 5 is threadedly connected to the drain nozzle 4.

[0026] A thin tube is provided on the upper end face of cavity 1 and extends into the cavity. To facilitate the collection of liquid from the upper connected pipeline structure, the thin tube is located at the circular part of the upper end face of cavity 1 (corresponding to the lowest point of the pipeline structure) and extends downward. The volume above and below the tube opening (including the volume of cavity 1 and the drain nozzle 4) is approximately 1 / 2 each. When the flight attitude changes, as long as the amount of stored liquid is less than 1 / 2 of the cavity volume (ensuring this through reasonable periodic drainage), the liquid inside the cavity will never flow back through the thin tube. The diameter of the thin tube should not be too large, taking the range of Φ1 to Φ3, to prevent backflow from occurring easily in a short time even if a small amount of liquid enters the thin tube when the aircraft's attitude changes.

[0027] The lower drain port of the drain nozzle 4 has an M12 external thread and a 74° bevel at the lower end. The plug assembly 5 is composed of an M12 outer nut, a movable plug with a 74° bevel at the end, and a chain link. The drain nozzle 4 and the plug assembly 5 are sealed by tightening the threads.

[0028] The plug assembly 5 and the drain nozzle 4 can be repeatedly tightened and removed to allow for periodic drainage of waste liquid as needed for maintenance.

[0029] Under certain special operating conditions, fuel in the aircraft fuel tank may seep back into the pipeline through a one-way valve. Without protective measures, this could flow to the upstream air separator and cause product failure. Please see [link / reference]. Figure 3 The leakage storage device provided by this invention is installed in the pipeline from which inert gas flows to the aircraft fuel tank. As a protective measure, the leakage storage device will enter the leakage storage device when the fuel that has seeped in flows through the lowest point of the pipeline. The liquid that enters the leakage storage device is not easy to flow back into the pipeline. Even when the aircraft changes attitude, it can ensure that the fuel does not continue to flow upstream. The stored liquid can be drained during the regular inspection of the aircraft.

[0030] This invention is particularly suitable for the front end of a one-way valve in the pipeline connection between the airborne inerting system and the aircraft fuel tank. When a small amount of fuel leaks from the fuel tank to the front end of the one-way valve, it is used to store the oil and prevent the oil from flowing back into the inerting system and causing contamination of the inerting system. This invention can achieve the effect of preventing the stored oil from flowing back under different flight attitudes and can be widely used in waste liquid storage design in various scenarios.

[0031] The leakage storage device provided by this invention can be widely used in many fields, including airborne fuel tank inerting technology and pipeline fluid technology.

[0032] The above description merely illustrates the embodiments of this application, and while the description is quite specific and detailed, it should not be construed as limiting the scope of this patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these modifications and improvements all fall within the scope of protection of this application.

Claims

1. A leakage storage device, characterized in that, The device, located in the pipeline connecting the airborne inerting system and the aircraft fuel tank, includes: a cavity (1), a locking screw and nut assembly (3), a drain nozzle (4), and a plug assembly (5). The cavity (1) is a cylindrical structure with a flange interface reserved on the upper end for connecting to the reserved mounting surface of the pipeline shell. A thin tube is provided on the upper end and extends into the cavity. A flange interface is reserved on the lower end for connecting the drain nozzle (4). The locking screw and nut assembly (3) secures the drain nozzle (4) to the cavity (1); the plug assembly (5) is threadedly connected to the drain nozzle (4); The lower drain port of the drain nozzle (4) is an M12 external thread, and the lower end face is... Angle bevel; plug assembly (5) consists of an M12 outer nut and an end face of The inclined surface is composed of a movable plug and a chain link; the drain nozzle (4) and the plug assembly (5) are tightened by threads to achieve an inclined surface seal; The thin tube is positioned at the circular point on the upper end face of the cavity and extends downwards. The circular point on the upper end face of the cavity corresponds to the lowest point of the pipeline channel structure. The volumes above and below the tube opening are respectively... The volume below the nozzle includes both the cavity and the discharge nozzle; when the flight attitude changes, as long as the stored liquid volume is less than the cavity volume... The liquid inside the cavity will never flow backward through the capillary tube; the diameter of the capillary tube is... .

2. The apparatus according to claim 1, characterized in that, A sealing groove is provided on the lower end face of the cavity (1), and a sealing ring (2) is provided in the sealing groove. The sealing ring (2) is located between the drain nozzle (4) and the cavity (1). The sealing ring (2) is in a compressed state under the fastening action of the locking screw and nut assembly (3).

3. The apparatus according to claim 1, characterized in that, The upper surface of the cavity (1) is provided with multiple connection holes, and the cavity (1) is connected to the reserved mounting surface of the pipeline shell through the connection holes.

4. The apparatus according to claim 1, characterized in that, Multiple fastening holes are provided at corresponding positions on the lower end face of the cavity (1) and the upper end face of the discharge nozzle (4). The locking screw and nut assembly (3) passes through the fastening holes to fasten the discharge nozzle (4) and the cavity (1).

Images