An aero-engine oil leakage sealing structure

Abstract

This utility model discloses an oil leakage sealing structure for an aero-engine, belonging to the field of oil leakage sealing technology, for connecting a first pipe and a second pipe. The first pipe has a first mounting groove coaxial with it, a drainage groove located on the outer ring of the first mounting groove, and at least one transition groove connecting the first mounting groove and the drainage groove. The sealing structure also includes: a sealing ring, coaxially mounted in the first mounting groove; a sub-connector, mounted on the first pipe; a female connector, mounted on the second pipe, the female connector being detachably connected to the sub-connector to fix the first pipe and the second pipe and to keep the mounting end of the first pipe coaxially abutting against the mounting end of the second pipe; and an oil leakage detection sensor having a detection probe, the detection end of which penetrates the sub-connector or the first pipe to communicate with the drainage groove. By setting the drainage groove and the oil leakage detection sensor, oil leakage can be detected at the first moment of sealing ring failure.

Description

Technical Field

[0001] This utility model relates to the field of oil leakage sealing technology, and in particular to an oil leakage sealing structure for aero-engines. Background Technology

[0002] As a core component of an aircraft, the safety and reliability of an aircraft engine directly impact flight safety. During the operation of an aircraft engine, the oil system plays a crucial role, primarily comprising the fuel line system and the lubricating oil line system. The former provides high-calorific-value fuel for engine operation, while the latter provides necessary lubrication for the high-speed rotation of the engine rotor. However, the operating environment of an aircraft engine is complex. The oil system, fixed to the engine's outer surface, operates under conditions of large temperature differences, high oil pressure, and strong vibration for extended periods. This makes its sealing components prone to wear and aging, leading to oil leaks.

[0003] In existing aero-engine oil circuit connection technologies, for the rigid connections of oil circuits in small and medium-sized aero-engines and the connections of oil sensor measurement branches (returns) in medium and large aero-engines, traditional sealing structures mainly rely on a single sealing ring for sealing. While this sealing method can ensure the sealing of the oil circuit to a certain extent, it is difficult to detect oil leaks in a timely manner when the sealing ring ages or is damaged due to long-term use. This is because traditional detection methods usually require regular manual inspections, which are not only inefficient but also difficult to monitor in real time. Once an oil leak is not detected in time, it may lead to serious problems such as fuel supply fluctuations and lubricating oil leakage, causing a chain reaction that affects the normal operation of the aero-engine and may even cause serious safety accidents.

[0004] Therefore, it is necessary to develop an oil leak sealing structure for aero engines that can detect oil leaks in a timely manner and is easy to maintain. Utility Model Content

[0005] This utility model provides an oil leakage sealing structure for an aircraft engine to solve the problems in the prior art.

[0006] The present invention adopts the following technical solution: an oil leakage sealing structure for an aircraft engine, used for connecting a first pipe and a second pipe; the first pipe has a first mounting groove coaxial with it, a drainage groove located on the outer ring of the first mounting groove, and at least one transition groove connecting the first mounting groove and the drainage groove; the sealing structure further includes: a sealing ring, coaxially installed in the first mounting groove; a sub-connector, installed on the first pipe; a female connector, installed on the second pipe, the female connector being detachably connected to the sub-connector to fix the first pipe and the second pipe, and to keep the mounting end of the first pipe coaxially abutting against the mounting end of the second pipe; an oil leakage detection sensor having a detection probe, the detection end of the detection probe penetrating the sub-connector or the first pipe to communicate with the drainage groove.

[0007] Preferably, the drainage channel includes a circular groove coaxial with it, and the transition slot is configured with a plurality of evenly distributed drainage channels between the first mounting slot and the first mounting slot.

[0008] Preferably, the drainage channel further includes a liquid-gathering channel extending radially outward from any point of the circular channel.

[0009] Preferably, the detection end of the detection probe extends into the polymer pool.

[0010] Preferably, the first pipe has a first annular protrusion coaxial with it at its mounting end, and the second pipe has a second annular protrusion coaxial with it at its mounting end; the sub-connector is sleeved on the first pipe, and the sub-connector has at least two first limiting blocks; the female connector is sleeved on the second pipe, and the female connector has at least two second limiting blocks; when the sub-connector and the female connector are connected and fixed, the first limiting block abuts against the outside of the first annular protrusion, and the second limiting block abuts against the outside of the second annular protrusion.

[0011] Preferably, the outer ring of the sub-connector has an external thread, and one end of the female connector has an internal thread groove, wherein the sub-connector is threaded into the internal thread groove via the external thread.

[0012] Preferably, the first annular protrusion has a first clearance groove corresponding to the first limiting block, and the first limiting block can pass through the first annular protrusion through the corresponding first clearance groove; the second annular protrusion has a second clearance groove corresponding to the second limiting block, and the second limiting block can pass through the second annular protrusion through the corresponding second clearance groove.

[0013] Preferably, both the sub-connector and the female connector are provided with an annular inner ring. The diameter of the annular inner ring of the sub-connector is adapted to the outer diameter of the first annular protrusion, and the diameter of the annular inner ring of the female connector is adapted to the outer diameter of the second annular protrusion.

[0014] Preferably, the liquid pool extends to the outer wall of the first annular protrusion, and a perforation is provided on the inner wall of the sub-connector. The detection end of the detection probe passes through the perforation and is placed at the outer opening of the liquid pool.

[0015] Preferably, the second pipe has a second mounting groove coaxial with it on the mounting end side, and the sealing ring is located in the first mounting groove and the second mounting groove.

[0016] The above-mentioned technical solutions adopted in the embodiments of this utility model can achieve the following beneficial effects:

[0017] Firstly, by incorporating drainage channels and oil leak detection sensors, oil leaks can be detected immediately upon seal failure. This prevents more serious problems caused by prolonged undetected leaks. Secondly, in equipment like aircraft engines, where safety and reliability are paramount, this sealing structure effectively controls the extent of leaks, preventing uncontrolled oil leakage from contaminating and damaging other engine components.

[0018] Secondly, the detachable male and female connectors make connecting and disconnecting the first and second pipes much easier. After detecting an oil leak and determining that the problem lies with the sealing ring, the pipe connection can be quickly disassembled, and the sealing ring replaced promptly. Attached Figure Description

[0019] The accompanying drawings, which are included to provide a further understanding of the present invention and constitute a part of this invention, illustrate exemplary embodiments of the present invention and, together with the description thereof, serve to explain the present invention and do not constitute an undue limitation thereof. In the drawings:

[0020] Figure 1 This is a plan view of the present invention;

[0021] Figure 2 This is a three-dimensional structural cross-sectional view of the present invention;

[0022] Figure 3 This is an exploded view of the present invention;

[0023] Figure 4 This is an exploded view of the first pipe and sealing ring of this utility model;

[0024] Figure 5 This is an exploded view of the first pipe and sub-connector of this utility model;

[0025] Figure 6 This is an exploded view of the second pipe and the female connector of this utility model.

[0026] Figure Labels

[0027] 1-First pipe; 11-First mounting groove; 12-Drainage groove; 121-Circular groove; 122-Accumulation tank; 13-Transition groove; 14-First annular protrusion; 15-First clearance groove;

[0028] 2-Second pipe; 21-Second annular protrusion; 22-Second clearance groove; 23-Second mounting groove;

[0029] 3-Sealing ring;

[0030] 4-Sub-connector; 41-First limiting block; 42-External thread; 43-Through hole;

[0031] 5-Female connector; 51-Second limit block; 52-Internal thread groove;

[0032] 61 - Detection probe. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0034] The technical solutions provided by the various embodiments of this utility model are described in detail below with reference to the accompanying drawings.

[0035] Reference Figures 1 to 6 As shown in the figure, this utility model embodiment provides an oil leakage sealing structure for an aircraft engine, used for connecting the first pipe 1 and the second pipe 2. This sealing structure can be used for hard connections in the oil circuits of small and medium-sized aircraft engines and is suitable for small and medium diameter oil pipes. For medium and large aircraft engines, it can be applied to the measurement branches (loops) of oil sensors (temperature, pressure, etc.).

[0036] The first pipe 1 has a first mounting groove 11 coaxial with it, a flow channel 12 located on the outer ring of the first mounting groove 11, and at least one transition groove 13 connecting the first mounting groove 11 and the flow channel 12.

[0037] The sealing structure also includes a sealing ring 3, a sub-connector 4, a female connector 5, and an oil leak detection sensor: the sealing ring 3 is coaxially installed in the first mounting groove 11; the sub-connector 4 is installed on the first pipe 1; the female connector 5 is installed on the second pipe 2, and the female connector 5 is detachably connected to the sub-connector 4 to fix the first pipe 1 and the second pipe 2, and to keep the mounting end of the first pipe 1 coaxially abutting against the mounting end of the second pipe 2; the oil leak detection sensor (which can be a contact leak sensor; or a sensor of model Chang'an Wenying A-FLC1000, which absorbs and restructures carbon atoms in the oil, causing a change in the resistance of the leak rope, and transmitting the detection signal to the oil leak controller. This sensor has a fast detection speed and a wide range, alarming in about 1 minute for kerosene, about 2 minutes for gasoline, and about 3 minutes for diesel) has a detection probe 61, the detection end of which passes through the sub-connector 4 or the first pipe 1 to communicate with the drainage groove 12.

[0038] In this embodiment, the aircraft engine oil leakage sealing structure is mainly used to connect the first pipe 1 and the second pipe 2. Under normal circumstances, the sealing ring 3 installed in the first mounting groove 11 of the first pipe 1 plays a sealing role, preventing oil leakage, ensuring the sealing of the connection between the first pipe 1 and the second pipe 2, and allowing the oil to flow normally in the pipe.

[0039] When the sealing ring 3 ages due to long-term use or fails for other reasons, the oil that was originally blocked by the sealing ring 3 will be released and overflow from the first mounting groove 11. Because of the transition groove 13 connecting the first mounting groove 11 and the drainage groove 12, the overflowing oil will flow into the drainage groove 12 along the transition groove 13. The detection probe 61 of the oil leakage detection sensor has its detection end connected to the drainage groove 12. Once the oil flows into the drainage groove 12, the detection probe 61 can detect the presence of the oil, thus detecting the oil leakage at the first moment and allowing for timely measures such as replacing the sealing ring 3.

[0040] In summary, by incorporating the drainage groove 12 and the oil leakage detection sensor, oil leakage can be detected immediately upon failure of the sealing ring 3. This avoids more serious problems caused by prolonged undetected oil leakage. Furthermore, in equipment like aero engines, where safety and reliability requirements are extremely high, this sealing structure effectively controls the extent of oil leakage, preventing uncontrolled oil leakage from contaminating and damaging other engine components.

[0041] The detachable male connector 4 and female connector 5 make connecting and disconnecting the first pipe 1 and the second pipe 2 more convenient. After detecting an oil leak and determining that the problem lies with the sealing ring 3, the pipe connection can be quickly disassembled, and the sealing ring 3 can be replaced promptly.

[0042] It should be noted that the second pipe 2 has a second mounting groove 23 coaxial with it on the mounting end side, and the sealing ring 3 is located in the first mounting groove 11 and the second mounting groove 23.

[0043] In some practical applications, refer to Figure 2 and Figure 4 As shown, the drainage channel 12 includes a circular groove 121 coaxial with it, and the transition slot 13 is configured between a plurality of evenly distributed drainage channels 12 and the first mounting slot 11. Furthermore, the drainage channel 12 also includes a liquid-gathering channel 122 extending radially outward from any point of the circular groove 121. The detection end of the detection probe 61 penetrates into the liquid-gathering channel 122.

[0044] Multiple evenly distributed transition slots 13 allow oil to flow more uniformly from the first mounting slot 11 into the circular slot 121, and then from the circular slot 121 into the liquid collection tank 122 (it should be noted that the liquid collection tank 122 should be located at the lowest point of the connection between the first and second pipelines), reducing the uncertainty of the oil leakage location and ensuring the accuracy of the detection results. The design of the liquid collection tank 122 allows the oil to be concentrated, making it easier to detect small amounts of oil leakage than to detect directly in the circular slot 121, thus improving the sensitivity and timeliness of oil leakage detection and preventing the oil leakage situation from worsening.

[0045] In some practical applications, refer to Figure 2 , Figure 5 and Figure 6 As shown, the first pipe 1 has a first annular protrusion 14 coaxial with it at its mounting end, and the second pipe 2 has a second annular protrusion 21 coaxial with it at its mounting end; the sub-connector 4 is sleeved on the first pipe 1, and the sub-connector 4 has at least two first limiting blocks 41; the female connector 5 is sleeved on the second pipe 2, and the female connector 5 has at least two second limiting blocks 51; when the sub-connector 4 and the female connector 5 are connected and fixed, the first limiting block 41 abuts against the outside of the first annular protrusion 14, and the second limiting block 51 abuts against the outside of the second annular protrusion 21.

[0046] Specifically, the outer ring of the sub-connector 4 has an external thread 42, and one end of the female connector 5 has an internal thread groove 52. The sub-connector 4 is threaded into the internal thread groove 52 through the external thread 42.

[0047] In this embodiment, the aircraft engine oil leakage sealing structure is used to connect the first pipe 1 and the second pipe 2. During initial installation, the sealing ring 3 is coaxially installed in the first mounting groove 11 of the first pipe 1, the sub-connector 4 is sleeved on the first pipe 1, and the female connector 5 is sleeved on the second pipe 2. The sub-connector 4 and the female connector 5 are connected and fixed by threads, that is, the external thread 42 of the outer ring of the sub-connector 4 is screwed into the internal thread groove 52 at one end of the female connector 5.

[0048] As the male connector 4 and female connector 5 are gradually tightened, the first limiting block 41 on the male connector 4 will abut against the outside of the first annular protrusion 14 at the mounting end of the first pipe 1, and the second limiting block 51 on the female connector 5 will abut against the outside of the second annular protrusion 21 at the mounting end of the second pipe 2. This limiting method allows the mounting ends of the first pipe 1 and the second pipe 2 to abut together, ensuring the stability of the pipe connection. Threaded connections have a certain self-locking characteristic, making them less prone to loosening under certain external forces. Moreover, the sleeve and threaded connection method of the male connector 4 and female connector 5 makes the installation process relatively simple.

[0049] In some practical applications, refer to Figures 5 to 6 As shown, the first annular protrusion 14 has a first clearance groove 15 corresponding to the first limiting block 41, and the first limiting block 41 can pass through the first annular protrusion 14 through the corresponding first clearance groove 15; the second annular protrusion 21 has a second clearance groove 22 corresponding to the second limiting block 51, and the second limiting block 51 can pass through the second annular protrusion 21 through the corresponding second clearance groove 22.

[0050] When installing the first pipe 1 and the second pipe 2, first, the sub-connector 4 is fitted onto the first pipe 1, so that the first limiting block 41 on the sub-connector 4 is aligned with the first clearance groove 15 on the first annular protrusion 14. Then, the first limiting block 41 can be easily passed through the first annular protrusion 14 through the corresponding first clearance groove 15. Similarly, the female connector 5 is fitted onto the second pipe 2, so that the second limiting block 51 on the female connector 5 is aligned with the second clearance groove 22 on the second annular protrusion 21, and passes through the second annular protrusion 21.

[0051] Next, by rotating the sub-connector 4, its outer thread 42 is threadedly connected to the inner thread groove 52 at one end of the female connector 5. Simultaneously, rotating the sub-connector 4 and the female connector 5 causes the first limiting block 41 and the second limiting block 51 to respectively avoid the first clearance groove 15 and the second groove. The design of the first clearance groove 15 and the second clearance groove 22 avoids direct interference between the first limiting block 41 and the second limiting block 51 and the first annular protrusion 14 and the second annular protrusion 21 during installation, allowing the sub-connector 4 and the female connector 5 to be quickly and initially installed onto the first pipe 1 and the second pipe 2, greatly improving the speed and efficiency of installation.

[0052] In some practical applications, both the sub-connector 4 and the female connector 5 are provided with an annular inner ring. The diameter of the annular inner ring of the sub-connector 4 is adapted to the outer diameter of the first annular protrusion 14, and the diameter of the annular inner ring of the female connector 5 is adapted to the outer diameter of the second annular protrusion 21. Therefore, after the sub-connector 4 and the female connector 5 are connected, the coaxiality of the first pipe 1 and the second pipe 2 can be ensured.

[0053] In some practical applications, the liquid collection tank 122 extends to the outer wall of the first annular protrusion 14, and a perforation 43 is provided on the inner wall of the sub-connector 4 (e.g., Figure 2 and Figure 5 The detection probe's detection end passes through the perforation 43 and is placed at the outer opening of the liquid collection tank 122. This method only requires fixing the oil leak detection sensor to the first annular protrusion 14 or the first pipe 1 and extending its detection probe into the perforation 43.

[0054] The above description is merely an embodiment of this utility model and is not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this utility model should be included within the scope of the claims of this utility model.

Claims

1. An oil leakage sealing structure for an aircraft engine, used for connecting a first pipe (1) and a second pipe (2); characterized in that, The first pipe (1) has a first mounting groove (11) coaxial with it, a drainage groove (12) located on the outer ring of the first mounting groove (11), and at least one transition groove (13) connecting the first mounting groove (11) and the drainage groove (12). The sealing structure also includes: The sealing ring (3) is coaxially installed in the first mounting groove (11); Sub-connector (4) is installed on the first pipe (1); The female connector (5) is installed on the second pipe (2). The female connector (5) is detachably connected to the sub-connector (4) to fix the first pipe (1) and the second pipe (2) and to keep the mounting end of the first pipe (1) coaxial with the mounting end of the second pipe (2). The oil leak detection sensor has a detection probe (61) whose detection end is inserted into a sub-connector (4) or a first pipe (1) to communicate with a drainage channel (12).

2. The oil leakage sealing structure for an aircraft engine according to claim 1, characterized in that, The drainage groove (12) includes a circular groove (121) coaxial with it, and the transition groove (13) is configured in a plurality of evenly distributed between the drainage groove (12) and the first mounting groove (11).

3. The oil leakage sealing structure for an aircraft engine according to claim 2, characterized in that, The drainage channel (12) also includes a liquid collection channel (122) extending radially outward from any point of the circular channel (121).

4. The oil leakage sealing structure for an aircraft engine according to claim 3, characterized in that, The detection end of the detection probe (61) is inserted into the polymer tank (122).

5. The oil leakage sealing structure for an aircraft engine according to claim 3, characterized in that, The first pipe (1) has a first annular protrusion (14) coaxial with it at the installation end, and the second pipe (2) has a second annular protrusion (21) coaxial with it at the installation end; the sub-connector (4) is sleeved on the first pipe (1), and the sub-connector (4) has at least two first limiting blocks (41); the female connector (5) is sleeved on the second pipe (2), and the female connector (5) has at least two second limiting blocks (51); when the sub-connector (4) and the female connector (5) are connected and fixed, the first limiting block (41) abuts against the outside of the first annular protrusion (14), and the second limiting block (51) abuts against the outside of the second annular protrusion (21).

6. The oil leakage sealing structure for an aircraft engine according to claim 5, characterized in that, The outer ring of the sub-connector (4) has an external thread (42), and one end of the female connector (5) has an internal thread groove (52). The sub-connector (4) is threaded into the internal thread groove (52) by the external thread (42).

7. The oil leakage sealing structure for an aircraft engine according to claim 5, characterized in that, The first annular protrusion (14) has a first clearance groove (15) corresponding to the first limiting block (41) and the first limiting block (41) can pass through the first annular protrusion (14) through the corresponding first clearance groove (15); the second annular protrusion (21) has a second clearance groove (22) corresponding to the second limiting block (51) and the second limiting block (51) can pass through the second annular protrusion (21) through the corresponding second clearance groove (22).

8. The oil leakage sealing structure for an aircraft engine according to claim 5, characterized in that, Both the sub-connector (4) and the female connector (5) are provided with an annular inner ring. The diameter of the annular inner ring of the sub-connector (4) is adapted to the outer diameter of the first annular protrusion (14), and the diameter of the annular inner ring of the female connector (5) is adapted to the outer diameter of the second annular protrusion (21).

9. The oil leakage sealing structure for an aircraft engine according to claim 8, characterized in that, The liquid pool (122) extends to the outer wall of the first annular protrusion (14), and a perforation (43) is provided on the inner wall of the sub-connector (4). The detection end of the detection probe passes through the perforation (43) and is placed at the outer opening of the liquid pool (122).

10. The oil leakage sealing structure for an aircraft engine according to claim 1, characterized in that, The second pipe (2) has a second mounting groove (23) coaxial with it on the mounting end side, and the sealing ring (3) is located in the first mounting groove (11) and the second mounting groove (23).

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