Oil collecting device of aero-engine

Abstract

The utility model relates to an aero-engine oil collecting device. Comprising an oil collecting box arranged below the aero-engine, the top end of the oil collecting box is connected with a connecting oil pipe and a first oil pipe, the connecting oil pipe is connected with a flow collecting valve, the flow collecting valve is further connected with a second oil pipe and a third oil pipe, and an oil discharge outlet is formed in one side of the oil collecting box. The oil collecting box is connected with the oil pipes, so that the residual oil ports in all positions are integrated with the engine, unified discharging is achieved through the oil discharging port of the oil collecting box, the matching efficiency of the oil collecting box and a square interface of an airplane is improved, and an oil discharging device or an oil discharging structure only needs to be connected with the oil discharging port of the oil collecting box.

Description

Technical Field

[0001] This application relates to the field of engine oil collection device technology, and in particular to an oil collection device for an aircraft engine. Background Technology

[0002] Fuel drain ports are an important component of aero engines. They are designed at the locations of critical components such as the fuel pump, motor, and combustion chamber. Their main function is to drain lubricating oil, fuel, and other fluids from the engine, preventing these fluids from contaminating engine parts or coming into contact with hot components and causing a fire. Fuel drain ports also allow for the inspection of fluid leaks in engine components, helping to identify failed parts. Therefore, fuel drain ports play a crucial role in engines.

[0003] Turboshaft and turboprop engines in aero-engines have relatively complex structures and numerous locations where excess oil may accumulate. Current methods typically involve installing individual pipelines in the aircraft nacelle to connect to each excess oil port and eject it through these pipelines. However, this existing method has the following drawbacks:

[0004] 1. There are too many pipeline interfaces, requiring matching between the engine and aircraft manufacturers, making the docking process cumbersome.

[0005] 2. The separate connection lines for each excess oil port in the engine room occupy space and require separate design and layout. Utility Model Content

[0006] To address the problems mentioned in the background art, the purpose of this application is to provide an oil collection device for an aircraft engine. It includes an oil collection box disposed below the aircraft engine, with a connecting oil pipe and a first oil pipe connected to the top of the oil collection box. The connecting oil pipe is connected to a confluence valve, which is also connected to a second oil pipe and a third oil pipe. An oil drain port is provided on one side of the oil collection box.

[0007] Preferably, the oil collection box is a square steel plate box.

[0008] Preferably, a fixing plate is fixedly connected to the side of the oil collection box away from the oil drain port, and the fixing plate is connected to the aircraft engine.

[0009] Preferably, a fourth oil pipe is connected to one side of the oil drain port of the oil collection box, and the fourth oil pipe is located above the oil drain port.

[0010] Preferably, the oil drain port is located above the bottom of the oil collection box.

[0011] Preferably, the first oil pipe is the residual oil pipe for the cleaning road, the second oil pipe is the residual oil pipe for the fuel pump, the third oil pipe is the residual oil pipe for the starter generator, and the confluence valve is a three-way valve.

[0012] Preferably, the fourth oil pipe is the residual oil pipe of the unloading valve.

[0013] Preferably, the oil collection box is connected to the connecting oil pipe and the first oil pipe respectively through a 74° tapered pipe joint, and the three-way valve is connected to the connecting oil pipe, the fuel pump residual oil pipe and the starter generator residual oil pipe respectively through a 74° tapered pipe joint.

[0014] Preferably, the oil collection box is connected to the fourth oil pipe via a 74° tapered pipe joint.

[0015] In summary, this application includes the following beneficial technical effects:

[0016] 1. By connecting the oil collection box to each oil pipe, the excess oil ports at each location are integrated with the engine, and the oil is discharged uniformly through the drain port of the oil collection box, which improves the matching efficiency with the aircraft interface and makes the oil draining device or structure only need to be connected to the drain port of the oil collection box.

[0017] 2. The spatial structure design of the connection points between each oil pipe and the oil collection box saves on the piping layout work in the engine room, while freeing up engine room piping space and optimizing the spatial structure. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of this utility model;

[0019] Figure 2 This is an enlarged view of the confluence valve part of this utility model;

[0020] Figure 3 This is an enlarged view of the oil collection box part of this utility model.

[0021] Explanation of reference numerals in the attached figures:

[0022] 1. Oil collection box; 2. Connecting oil pipe; 3. First oil pipe; 4. Combination valve; 5. Second oil pipe; 6. Third oil pipe; 7. Oil drain port; 8. Fixing plate; 9. Fourth oil pipe. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of this application. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0024] The following is in conjunction with the appendix Figure 1-3This application provides a more detailed description. An embodiment of this application discloses an oil collection device for an aircraft engine, including an oil collection box 1 disposed below the aircraft engine. The top of the oil collection box 1 is connected to a connecting oil pipe 2 and a first oil pipe 3. The connecting oil pipe 2 is connected to a confluence valve 4, which is also connected to a second oil pipe 5 and a third oil pipe 6. Through the confluence valve 4, oil pipes that can be integrated are connected together, and excess oil flows from the confluence valve 4 into the connecting oil pipe 2 and finally into the oil collection box 1. The first oil pipe 3, which cannot be connected to the confluence valve 4, is separately disposed at the top of the oil collection box 1, parallel to the connecting oil pipe 2. An oil drain port 7 is provided on one side of the oil collection box 1 for draining the excess oil collected in the oil collection box 1.

[0025] Specifically, the second oil pipe 5 is the fuel pump residual oil pipe, and the third oil pipe 6 is the starter / generator residual oil pipe. The merging valve 4 is a three-way valve used to merge and collect residual oil from the fuel pump residual oil pipe and the starter / generator residual oil pipe and send it to the connecting oil pipe 2. The first oil pipe 3 is a separate oil pipe set up for other oil pipes that cannot be connected to the merging valve 4. Therefore, the first oil pipe 3 can be an oil pipe that is directly connected to a specific part of the engine for direct collection of residual oil, or it can be an oil pipe that is connected to other merging valves 4 to collect other residual oil in a unified manner. In this embodiment, the first oil pipe 3 is the flushing road residual oil pipe. Based on this setting, only two oil pipe interfaces need to be set at the top of the oil collection box 1. In this embodiment, the oil collection box 1 is connected to the connecting oil pipe 2 and the first oil pipe 3 respectively through two 74° tapered pipe joints. To facilitate future replacement of oil pipes and maintain the consistency of all oil pipe connections, the interface of the confluence valve 4 is also a 74° tapered pipe connector. Specifically, the three-way valve, which serves as the confluence valve 4, is connected to the connecting oil pipe 2, the fuel pump excess oil pipe, and the starter / generator excess oil pipe respectively through the 74° tapered pipe connector.

[0026] Furthermore, the oil collection box 1 is a square steel box, specifically a square iron box welded from steel plates.

[0027] Furthermore, a fixing plate 8 is fixedly connected to the side of the oil collection box 1 away from the oil outlet 7. The fixing plate 8 is connected to the aircraft engine and is used to fix the position of the oil collection box 1 relative to the aircraft engine.

[0028] Furthermore, in practice, when the first oil pipe 3 still cannot meet the number of residual oil interfaces of the aircraft engine, a fourth oil pipe 9 is also connected to the side of the oil collection box 1 where the drain port 7 is located. The fourth oil pipe 9 is set up when the first oil pipe 3 still cannot meet the actual required number of oil pipes. Therefore, the fourth oil pipe 9 can be connected to other confluence valves 4 to further collect residual oil in other oil pipes, or it can be connected independently to the residual oil interface of the aircraft engine to directly collect residual oil. In this embodiment, the fourth oil pipe 9 is the residual oil pipe of the unloading valve. The fourth oil pipe 9 is located on the side of the oil collection box 1 where the drain port 7 is located, which is beneficial to improving space utilization. Moreover, the fourth oil pipe 9 is located above the drain port 7, which is used to determine the spatial relationship between the fourth oil pipe 9 and the drain port 7, so that the residual oil in the fourth oil pipe 9 can flow out from the drain port 7. When the side of the oil collection box 1 with the oil drain port 7 is designated as the front side, the rear side is connected to the fixing plate 8, and the top is connected to the connecting oil pipe 2 and the first oil pipe 3. At this time, there are no additional devices at the bottom and sides of the oil collection box 1, which greatly reduces the space occupied by the oil collection box 1 itself. The oil collection box 1 is also connected to the fourth oil pipe 9 through a 74° tapered pipe joint to ensure the uniformity of the joints.

[0029] Furthermore, the oil drain port 7 is located above the bottom of the oil collection box 1, so that there is a certain space between the bottom of the oil collection box 1 and the oil drain port 7, ensuring that the oil collection box 1 can pre-store some oil.

[0030] Working principle: Connect one end of the fuel pump residual fuel line and the starter / generator residual fuel line to the aircraft engine, and the other end to a three-way valve. The three-way valve connects to connecting oil line 2, and connecting oil line 2 connects to the oil collection box 1. Connect one end of the cleaning path residual fuel line to the aircraft engine and the other end to the oil collection box 1. Connect one end of the unloading valve residual fuel line to the engine and the other end to the oil collection box 1. First, connect the mounting plate 8 to the aircraft engine using conventional connection techniques, and then connect the oil collection box 1 to the mounting plate 8 using conventional techniques such as welding. Connect the drain port 7 to the external drain pipe. When the aircraft engine starts, the residual fuel flows along the set oil pipe structure to the oil collection box 1 and is finally discharged from the drain port 7.

[0031] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units; they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs.

[0032] In this application, unless otherwise expressly specified and limited, the terms "installation", "setting", "connection", "fixing", "screw connection", etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components or the interaction between two components. Unless otherwise expressly limited, those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0033] It is understood that those skilled in the art can make equivalent substitutions or changes based on the technical solution and concept of this application, and all such substitutions or changes should fall within the protection scope of the appended claims.

Claims

1. An oil collection device for an aircraft engine, characterized in that, It includes an oil collection box (1) located below the aircraft engine. The top of the oil collection box (1) is connected to a connecting oil pipe (2) and a first oil pipe (3). The connecting oil pipe (2) is connected to a confluence valve (4). The confluence valve (4) is also connected to a second oil pipe (5) and a third oil pipe (6). An oil drain port (7) is provided on one side of the oil collection box (1).

2. The aircraft engine oil collection device according to claim 1, characterized in that, The oil collection box (1) is a square steel plate box.

3. The aircraft engine oil collection device according to claim 2, characterized in that, A fixing plate (8) is fixedly connected to the side of the oil collection box (1) away from the oil outlet (7), and the fixing plate (8) is connected to the aircraft engine.

4. The aircraft engine oil collection device according to claim 3, characterized in that, The oil collection box (1) is provided with a fourth oil pipe (9) connected to one side of the oil outlet (7), and the fourth oil pipe (9) is located above the oil outlet (7).

5. The aircraft engine oil collection device according to claim 1, characterized in that, The oil drain port (7) is located above the bottom of the oil collection box (1).

6. The aircraft engine oil collection device according to claim 1, characterized in that, The first oil pipe (3) is the residual oil pipe for cleaning the road, the second oil pipe (5) is the residual oil pipe for the fuel pump, the third oil pipe (6) is the residual oil pipe for the starter generator, and the confluence valve (4) is a three-way valve.

7. The aircraft engine oil collection device according to claim 4, characterized in that, The fourth oil pipe (9) is the residual oil pipe of the unloading valve.

8. The aircraft engine oil collection device according to claim 6, characterized in that, The oil collection box (1) is connected to the connecting oil pipe (2) and the first oil pipe (3) respectively through a 74° tapered pipe joint. The three-way valve is connected to the connecting oil pipe (2), the fuel pump residual oil pipe and the starter generator residual oil pipe respectively through a 74° tapered pipe joint.

9. The aircraft engine oil collection device according to claim 4, characterized in that, The oil collection box (1) is connected to the fourth oil pipe (9) via a 74° tapered pipe joint.

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