Oil-gas separation device for lubricating oil tank of aero-engine

Abstract

The oil-gas separation device of the aircraft engine lubricating oil tank comprises a shell and multiple stages of baffles, the shell is hollow, an air inlet is formed in one end of the shell, an exhaust port is formed in the other end of the shell, the air inlet is located in the bottom of the shell, and a certain included angle exists between the air inlet and the exhaust port; the baffles are arranged in the shell, communicating grooves are formed in the baffles, the communicating grooves of the other baffles and the air inlet are located on the same side except the last-stage baffle close to the exhaust port, and the communicating groove of the last-stage baffle is opposite to the communicating grooves of the other baffles in position. According to the oil-gas separation device for the lubricating oil tank of the aero-engine, the oil-gas separation device for the lubricating oil tank of the aero-engine is compact in structure, high in oil-gas separation efficiency and high in reliability.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engines, in particular to an oil-gas separation device of an aviation engine lubricating oil tank. Background Art

[0002] The aircraft engine oil tank is an important component of the aircraft engine oil system. It is responsible for storing and providing the oil required for cooling and lubricating the engine's rotating parts, and determines whether the engine can work safely and reliably. The oil-gas separation device is installed on the oil tank and is mainly used to separate the oil from the oil gas so that the oil can flow smoothly back to the oil tank for reuse, thereby reducing oil consumption.

[0003] At present, the oil-gas separation devices used in aero-engines are mainly centrifugal, dynamic pressure and flat plate types. The centrifugal oil-gas separator mainly uses the centrifugal force generated by the rotation of the rotor to separate the gas from the oil-gas mixture. It needs to consume a certain amount of power to drive the rotor. The working principle of the dynamic pressure oil-gas separator is similar to that of the centrifugal oil-gas separator. It also uses centrifugal force to separate the lubricating oil and air with a large density difference, but the specific implementation method is different. The dynamic pressure oil-gas separator is generally a cylindrical structure. The oil-gas mixture flows into the cylinder at a high speed in a tangential direction and flows downward in the cylinder in a spiral shape. The lubricating oil and air are separated due to the centrifugal force. The flat plate oil-gas separator has the simplest structure. Its structure is a flat plate with many holes or a metal mesh partition. When the oil-gas mixture passes through the slit or mesh, the bubbles burst, thereby separating the oil and gas. Among them, the centrifugal oil-gas separator has the best separation effect, but it needs to be equipped with a corresponding transmission device. The structure is complex. The flat-plate oil-gas separator has the simplest structure, but the separation effect is the worst. The dynamic pressure oil-gas separator is more common in practical applications, but the oil-gas separation effect has certain limitations and cannot efficiently separate the gas from the oil-gas mixture, resulting in increased lubricating oil consumption. Utility Model Content

[0004] The purpose of this utility model is to provide an efficient, compact, reliable and adaptable oil-gas separation solution to meet the stringent requirements of modern aircraft engines for lubricating oil management.

[0005] To achieve the above-mentioned purpose, the technical solution adopted by the present invention is to provide an oil-gas separation device for an aircraft engine oil tank, the oil-gas separation device for the aircraft engine oil tank comprising:

[0006] A housing, wherein the housing is hollow, an air inlet is provided at one end of the housing, and an exhaust port is provided at the other end of the housing, the air inlet is located at the bottom of the housing, and a certain angle is formed between the air inlet and the exhaust port;

[0007] A multi-stage baffle is arranged inside the shell, and a connecting groove is opened on the baffle. Except for the last stage baffle close to the exhaust port, the connecting grooves of the other baffles are on the same side as the air inlet, and the connecting groove of the last stage baffle is opposite to the connecting grooves of the other baffles.

[0008] In one embodiment, the shell, the baffle, the air inlet, and the exhaust port are connected as a whole by welding.

[0009] In one embodiment, the angle between the air inlet and the air outlet is 65°.

[0010] In one embodiment, the housing, the baffle, the air inlet, and the air outlet are all made of aluminum alloy.

[0011] In one embodiment, it includes a first-stage baffle and a second-stage baffle, the first-stage baffle is close to the air inlet, the second-stage baffle is close to the exhaust port, the connecting groove of the first-stage baffle is on the same side as the air inlet, and the connecting groove of the second-stage baffle is opposite to the connecting groove of the first-stage baffle.

[0012] In one embodiment, the communicating groove formed on the baffle is arc-shaped, and the center of the arc is located on the central axis of the shell.

[0013] One or more of the above technical solutions in the embodiments of the present invention have at least the following technical effects or advantages:

[0014] The oil-gas separation device for an aircraft engine oil tank provided by the embodiment of the utility model effectively extends the flow path of the oil-gas mixture through a multi-stage baffle structure provided inside the device, and utilizes centrifugal force and gravity to more fully separate the oil and gas. This design improves the efficiency of oil-gas separation, reduces lubricating oil loss and environmental pollution. In addition, compared with traditional oil-gas separation devices, the multi-stage baffle structure used in this application is more compact, occupies a smaller area, and is easier to install and arrange above the aircraft engine oil tank. This not only saves space, but also reduces the weight and cost of the device. At the same time, it can also meet the requirements of high and low temperature operating environments, has a simple structure, is easy to manufacture, and has high reliability.

[0015] In summary, the oil-gas separation device of the aircraft engine lubricating oil tank of the present application has a compact structure, high oil-gas separation efficiency and high reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 A front view of the oil-gas separation device of the aircraft engine oil tank provided by an embodiment of the utility model;

[0018] Figure 2 for Figure 1 Cross-section at AA;

[0019] Figure 3 for Figure 1 Cross-section at the middle BB;

[0020] Figure 4 A side view of the oil-gas separation device of an aircraft engine oil tank provided by an embodiment of the utility model.

[0021] The reference numerals are as follows:

[0022] 1. Shell; 2. Baffle; 11. Air inlet; 12. Exhaust port; 21. First-stage baffle; 22. Second-stage baffle; 23. Connecting groove. DETAILED DESCRIPTION

[0023] The following describes in detail embodiments of the present invention, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0024] In the description of the present invention, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention 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 cannot be understood as a limitation on the present invention.

[0025] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of this utility model, "plurality" means two or more, unless otherwise specifically defined.

[0026] In this utility model, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection; direct connection, indirect connection through an intermediate medium, internal communication between two components, or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0027] See also Figures 1 to 4 The embodiment of the present application provides an oil-gas separation device for an aircraft engine oil tank, comprising a housing 1 and a multi-stage baffle 2. The housing 1 is hollow, an air inlet 11 is provided at one end of the housing 1, and an exhaust port 12 is provided at the other end of the housing 1. The air inlet 11 is located at the bottom of the housing 1, and there is a certain angle between the air inlet 11 and the exhaust port 12 (specifically, it can be as follows: Figure 4 65° as shown); the baffle 2 is arranged inside the shell 1, and a connecting groove 23 is opened on the baffle 2 (for connecting the chambers on both sides of the baffle 2), and except for the last-stage baffle 2 close to the exhaust port 12, the connecting grooves 23 of the remaining baffles 2 are on the same side as the air inlet 11, and the connecting groove 23 of the last-stage baffle 2 is opposite to the connecting grooves 23 of the remaining baffles 2.

[0028] Specifically, the oil-gas separation device of the aircraft engine oil tank provided in the embodiment of the present application includes a first-stage baffle 21 and a second-stage baffle 22. The first-stage baffle 21 is close to the air inlet 11, and the second-stage baffle 22 is close to the exhaust port 12. The connecting groove 23 of the first-stage baffle 21 is on the same side as the air inlet 11, and the connecting groove 23 of the second-stage baffle 22 is opposite to the connecting groove 23 of the first-stage baffle 21.

[0029] During use, the oil-gas separator is installed above the oil tank, and the oil-gas mixture in the oil tank enters the oil-gas separation device through the air inlet 11. Since the connecting groove 23 of the first-stage baffle 21 is on the same side as the air inlet 11, the oil-gas mixture will undergo sufficient centrifugal movement and then pass through the connecting groove 23. Since the connecting groove 23 on the first-stage baffle 21 is opposite to the connecting groove 23 of the second-stage baffle 22, the oil-gas mixture will also fully move in the oil-gas separator housing 1, so that the lubricating oil in the oil-gas mixture adheres to the inner wall of the oil-gas separator housing 1, and then flows back to the oil tank through the connecting groove 23 on the first-stage baffle 21 and the air inlet 11, and the remaining gas flows out from the connecting groove 23 of the second-stage baffle 22 and the exhaust port 12 (the connecting groove 23 on the first-stage baffle 21 is located at the bottom, and the connecting groove 23 on the second-stage baffle 22 is located at the top).

[0030] In one embodiment, the housing 1, baffle 2, air inlet 11, and exhaust port 12 are connected integrally by welding. The welding connection enhances the overall strength and rigidity of the device, improves the reliability and durability of the device, and ensures long-term stable operation of the device in harsh environments.

[0031] In one embodiment, the housing 1, baffle 2, air inlet 11, and exhaust port 12 are all made of aluminum alloy. Aluminum alloy has the advantages of being lightweight, high-strength, and corrosion-resistant, which reduces the weight and cost of the device and improves its durability and reliability.

[0032] In one embodiment, the connecting groove 23 formed on the baffle 2 is arc-shaped, with the center of the arc located on the central axis of the housing 1. The arc-shaped groove design allows the oil-gas mixture to flow more smoothly, reduces flow resistance, and enhances the centrifugal motion of the oil-gas mixture, thereby improving oil-gas separation efficiency.

[0033] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An oil-gas separation device for an aircraft engine oil tank, characterized in that: The oil-gas separation device of the aircraft engine oil tank comprises: A housing, wherein the housing is hollow, an air inlet is provided at one end of the housing, and an exhaust port is provided at the other end of the housing, the air inlet is located at the bottom of the housing, and a certain angle is formed between the air inlet and the exhaust port; A multi-stage baffle is arranged inside the shell, and a connecting groove is opened on the baffle. Except for the last stage baffle close to the exhaust port, the connecting grooves of the other baffles are on the same side as the air inlet, and the connecting groove of the last stage baffle is opposite to the connecting grooves of the other baffles.

2. The oil-gas separation device for an aircraft engine oil tank according to claim 1, characterized in that: The shell, the baffle, the air inlet and the air outlet are connected as a whole by welding.

3. The oil-gas separation device for an aircraft engine oil tank according to claim 1, characterized in that: The included angle between the air inlet and the air outlet is 65°.

4. The oil-gas separation device for an aircraft engine oil tank according to claim 1, characterized in that: The shell, the baffle, the air inlet and the air outlet are all made of aluminum alloy.

5. The oil-gas separation device for an aircraft engine oil tank according to claim 1, characterized in that: It includes a first-stage baffle and a second-stage baffle, the first-stage baffle is close to the air inlet, the second-stage baffle is close to the exhaust port, the connecting groove of the first-stage baffle is on the same side as the air inlet, and the connecting groove of the second-stage baffle is opposite to the connecting groove of the first-stage baffle.

6. The oil-gas separation device for an aircraft engine oil tank according to claim 1, characterized in that: The connecting groove provided on the baffle is arc-shaped, and the center of the arc is located on the central axis of the shell.

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