Aircraft hydraulic system air removal device

Abstract

The invention belongs to the technical field of airplane hydraulic system design, and particularly relates to an air removal device of an airplane hydraulic system. The device comprises a lower shell, an oil inlet and an oil outlet are formed in the lower shell, the lower shell is connected with a hydraulic system pipeline through the oil inlet and the oil outlet, an oil-gas separation installation part is arranged on the lower shell, an oil-gas separation cavity is formed in the oil-gas separation installation part, and the oil-gas separation cavity is communicated with the oil-gas separation installation part. The oil-gas separation cavity is communicated with the oil inlet; the upper shell is installed on the lower shell, an oil outlet channel is formed between the shell and the oil-gas separation installation part, the oil-gas separation cavity is communicated with the oil outlet through the oil outlet channel, and a through hole is formed in the upper shell; the oil-gas separation membrane element is mounted in the oil-gas separation cavity; the exhaust pipe is mounted on the oil-gas separation membrane element, and one end of the exhaust pipe extends out of the through hole of the upper shell.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft hydraulic system design, and in particular relates to an aircraft hydraulic system air removal device. Background Art

[0002] Aircraft hydraulic systems rely on hydraulic oil as a medium to do work. If there is gas in the hydraulic oil, it will affect the efficiency of the work, increase the heating of the system, and cause cavitation in the parts and accessories, which will affect the life and reliability of the system and accessories, and may even lead to catastrophic events. Therefore, when the hydraulic system is working, it is necessary to remove the gas in the system as much as possible. There are two types of gas in the hydraulic system: free state and dissolved state. Free air can be discharged through the exhaust valve set in the system during ground maintenance, but dissolved air cannot be discharged and is dissolved in the oil. However, when the system oil temperature drops or there is a sudden change in local pressure, air will leak out.

[0003] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0004] The purpose of the present application is to provide an air removal device for an aircraft hydraulic system to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] An air removal device for an aircraft hydraulic system, comprising:

[0007] A lower housing, wherein an oil inlet and an oil outlet are provided on the lower housing, wherein the lower housing is connected to a hydraulic system pipeline via the oil inlet and the oil outlet, wherein an oil-gas separation mounting portion is provided on the lower housing, wherein an oil-gas separation cavity is formed inside the oil-gas separation mounting portion, and wherein the oil-gas separation cavity is communicated with the oil inlet;

[0008] An upper shell, the upper shell is mounted on the lower shell, an oil outlet passage is formed between the shell and the oil-gas separation mounting portion, the oil outlet passage connects the oil-gas separation cavity with the oil outlet, and a through hole is opened on the upper shell;

[0009] An oil-gas separation membrane element, wherein the oil-gas separation membrane element is installed in the oil-gas separation cavity;

[0010] An exhaust pipe is installed on the oil-gas separation membrane element, and one end of the exhaust pipe extends out from the through hole of the upper shell.

[0011] In at least one embodiment of the present application, the lower shell has a lower shell connecting portion, and the lower shell connecting portion is coaxially sleeved on the outer side of the oil-gas separation mounting portion.

[0012] In at least one embodiment of the present application, the upper shell is cylindrical and is installed on the lower shell connection portion in a detachable manner.

[0013] In at least one embodiment of the present application, the upper shell and the lower shell connecting portion are connected by threads.

[0014] In at least one embodiment of the present application, a sealing ring is provided at the connection between the upper shell and the lower shell.

[0015] In at least one embodiment of the present application, the cross-section of the oil-gas separation membrane element is in the shape of a U-shaped pipe, including a first U-shaped pipe and a second U-shaped pipe separated by the oil-gas separation membrane, and the first U-shaped pipe is respectively connected to the oil-gas separation cavity and the oil outlet channel.

[0016] In at least one embodiment of the present application, the oil-gas separation membrane element is replaced regularly according to a maintenance cycle.

[0017] In at least one embodiment of the present application, the exhaust pipe is installed at the center of the oil-gas separation membrane element, and the exhaust passage inside the exhaust pipe is connected to the second U-shaped pipe.

[0018] In at least one embodiment of the present application, a portion of the exhaust pipe connected to the oil-gas separation membrane element is provided with an exhaust hole.

[0019] In at least one embodiment of the present application, a plurality of exhaust holes are evenly arranged on the exhaust pipe.

[0020] The invention has at least the following beneficial technical effects:

[0021] The aircraft hydraulic system air removal device of the present application can discharge the air dissolved in the hydraulic system oil, so that the air solution in the hydraulic system oil is reduced to an unsaturated state, thereby avoiding the damage to the hydraulic system caused by the release of air due to temperature and pressure changes during the operation of the hydraulic system. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic diagram of an aircraft hydraulic system air removal device according to an embodiment of the present application;

[0023] Figure 2 It is a partial schematic diagram of an oil-gas separation membrane element according to one embodiment of the present application;

[0024] Figure 3 It is a cross-sectional view of an oil-gas separation membrane element according to one embodiment of the present application.

[0025] in:

[0026] 1- oil inlet; 2- lower shell; 3- oil outlet; 4- exhaust pipe; 5- oil-gas separation membrane element; 6- upper shell; 7- air; 8- hydraulic oil; 9- oil-gas separation membrane. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0028] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0029] The following is combined with Figures 1 to 3 This application is described in further detail.

[0030] The present application provides an aircraft hydraulic system air removal device, comprising: a lower shell 2, an upper shell 6, an oil-gas separation membrane element 5 and an exhaust pipe 4.

[0031] Specifically, Figure 1 As shown, an oil inlet 1 and an oil outlet 3 are provided on the lower shell 2, and the lower shell 2 is connected to the hydraulic system pipeline through the oil inlet 1 and the oil outlet 3. An oil-gas separation mounting part is provided on the lower shell 2, and an oil-gas separation cavity is formed inside the oil-gas separation mounting part, and the oil-gas separation cavity is connected with the oil inlet 1; the upper shell 6 is installed on the lower shell 2, and an oil outlet channel is formed between the shell 6 and the oil-gas separation mounting part, and the oil outlet channel connects the oil-gas separation cavity with the oil outlet 3, and a through hole is opened on the upper shell 6; the oil-gas separation membrane element 5 is installed in the oil-gas separation cavity; the exhaust pipe 4 is installed on the oil-gas separation membrane element 5, and one end of the exhaust pipe 4 extends out from the through hole of the upper shell 6.

[0032] In a preferred embodiment of the present application, the lower housing 2 has a lower housing connection portion, which is coaxially sleeved on the outer side of the oil-gas separation mounting portion. The upper housing 6 is cylindrical and is mounted on the lower housing connection portion in a detachable mounting manner. The upper housing 6 is connected to the lower housing connection portion by threads. Advantageously, in this embodiment, a sealing ring is provided at the connection between the upper housing 6 and the lower housing connection portion.

[0033] In a preferred embodiment of the present application, Figure 2-3 As shown, the cross section of the oil-gas separation membrane element 5 is in the shape of a Chinese character "U", and includes a first Chinese character "U"-shaped pipe and a second Chinese character "U"-shaped pipe separated by the oil-gas separation membrane 9, and the first Chinese character "U"-shaped pipe is connected to the oil-gas separation cavity and the oil outlet channel respectively. The exhaust pipe 4 is installed at the center of the oil-gas separation membrane element 5, and the exhaust channel inside the exhaust pipe 4 is connected to the second Chinese character "U"-shaped pipe. The part where the exhaust pipe 4 is connected to the oil-gas separation membrane element 5 is provided with an exhaust hole. Preferably, a plurality of exhaust holes are evenly provided on the exhaust pipe 4. The hydraulic oil 8 entering from the oil inlet 1 passes through the oil-gas separation cavity and enters the first U-shaped channel of the oil-gas separation membrane element 5. The oil-gas separation membrane 9 is a polymer membrane. The function is that when the hydraulic oil 8 containing dissolved air 7 passes through the oil-gas separation membrane 9, the air 7 is separated from the hydraulic oil 8 through the leakage of the oil-gas separation membrane 9. The air 7 passes through the second U-shaped pipe, enters the exhaust pipe 4 through the exhaust hole, and is discharged into the atmosphere through the exhaust pipe 4. The hydraulic oil 8 in the first U-shaped channel that excludes the air 7 passes through the oil outlet channel and flows into the pressure system pipeline from the oil outlet 3.

[0034] In a preferred embodiment of the present application, the oil-gas separation membrane element 5 can be replaced regularly according to a maintenance cycle. During replacement, the upper shell 6 is removed, the oil-gas separation membrane element 5 is replaced, and then the upper shell 6 is installed.

[0035] The aircraft hydraulic system air removal device of the present application, the lower shell 2 is used to fix the oil-gas separation membrane element 5, and has a certain fixing strength. The oil inlet 1 in the lower shell 2 is connected to the hydraulic system pipeline on the aircraft, and the hydraulic oil 8 dissolved with air 7 enters the air removal device through the oil inlet 1. The oil-gas separation membrane element 5 is installed in the oil-gas separation cavity of the lower shell 2. The air 7 dissolved in the hydraulic oil 8 is filtered out through the oil-gas separation membrane element 5 by osmosis, and the filtered air 7 is discharged from the air removal device through the exhaust pipe 4 and discharged into the atmosphere; the oil outlet 3 in the lower shell 2 is connected to the hydraulic system pipeline, and the hydraulic oil 8 that removes the air 7 flows back to the hydraulic system through the oil outlet 3 after passing through the oil outlet channel. The upper shell 6 is connected and fixed to the lower shell 2 to encapsulate the entire device. By removing the upper shell 6, the oil-gas separation membrane element 5 can be replaced regularly.

[0036] The aircraft hydraulic system air removal device of the present application can remove air dissolved in the oil of the aircraft hydraulic system, thereby preventing air from being released due to changes in temperature and pressure during the operation of the hydraulic system, thereby preventing the hydraulic system from being damaged.

[0037] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An air removal device for an aircraft hydraulic system, characterized in that: include: A lower housing (2), wherein the lower housing (2) is provided with an oil inlet (1) and an oil outlet (3), wherein the lower housing (2) is connected to a hydraulic system pipeline via the oil inlet (1) and the oil outlet (3), wherein an oil-gas separation mounting portion is provided on the lower housing (2), wherein an oil-gas separation cavity is formed inside the oil-gas separation mounting portion, and wherein the oil-gas separation cavity is in communication with the oil inlet (1); an upper shell (6), the upper shell (6) being mounted on the lower shell (2), an oil outlet passage being formed between the shell (6) and the oil-gas separation mounting portion, the oil outlet passage connecting the oil-gas separation cavity with the oil outlet (3), and a through hole being formed on the upper shell (6); An oil-gas separation membrane element (5), the oil-gas separation membrane element (5) being installed in the oil-gas separation cavity; An exhaust pipe (4), wherein the exhaust pipe (4) is mounted on the oil-gas separation membrane element (5), and one end of the exhaust pipe (4) extends out from a through hole of the upper shell (6).

2. The aircraft hydraulic system air removal device according to claim 1, characterized in that: The lower shell (2) has a lower shell connecting portion, and the lower shell connecting portion is coaxially sleeved on the outer side of the oil-gas separation mounting portion.

3. The aircraft hydraulic system air removal device according to claim 1, characterized in that: The upper shell (6) is cylindrical and is mounted on the lower shell connecting portion in a detachable manner.

4. The aircraft hydraulic system air removal device according to claim 3, characterized in that: The upper shell (6) is connected to the lower shell connecting portion via threads.

5. The aircraft hydraulic system air removal device according to claim 4, characterized in that: A sealing ring is provided at the connection between the upper shell (6) and the connection part of the lower shell.

6. The aircraft hydraulic system air removal device according to claim 1, characterized in that: The cross section of the oil-gas separation membrane element (5) is in the shape of a U-shaped line, and comprises a first U-shaped pipe and a second U-shaped pipe separated by the oil-gas separation membrane (9); the first U-shaped pipe is respectively connected to the oil-gas separation cavity and the oil outlet channel.

7. The aircraft hydraulic system air removal device according to claim 6, characterized in that: The oil-gas separation membrane element (5) is replaced regularly according to a maintenance cycle.

8. The aircraft hydraulic system air removal device according to claim 7, characterized in that: The exhaust pipe (4) is installed at the center of the oil-gas separation membrane element (5), and the exhaust passage inside the exhaust pipe (4) is connected to the second U-shaped pipeline.

9. The aircraft hydraulic system air removal device according to claim 8, characterized in that: An exhaust hole is provided at the portion where the exhaust pipe (4) is connected to the oil-gas separation membrane element (5).

10. The aircraft hydraulic system air removal device according to claim 9, characterized in that: A plurality of exhaust holes are evenly arranged on the exhaust pipe (4).

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