Sealing structure of lubricating oil tank of aircraft engine
By using multi-layer rubber ring seals and an oil tank cover with an ultra-tolerance fit design on the aircraft engine oil tank, the problems of easy damage to the sealing structure, increased weight and increased airflow resistance in the existing technology are solved, and a sealing effect with high reliability and convenient disassembly and assembly is achieved.
Patent Information
- Application Number
- CN202422794982.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-16
- Publication Date
- 2025-10-03
- Estimated Expiration
- 2034-11-16
AI Technical Summary
The sealing structure of the existing aircraft engine lubricating oil tank has problems such as reduced sealing performance after multiple disassembly and assembly, complex structure, increased weight and increased airflow resistance.
It adopts a multi-layer rubber ring sealing structure and an ultra-tolerance fit design, combined with an aluminum alloy oil tank cover and box body. The sealing effect is achieved through the embedding of the rubber ring and the cooperation of the stress mounting ring. During disassembly, the quick disassembly slot is used for convenient disassembly and assembly.
The sealing structure has high reliability and long service life, is easy to disassemble and assemble, reduces the risk of oil leakage, reduces weight and airflow resistance, and simplifies the maintenance process.
Smart Images
Figure CN223410919U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of oil tank sealing, in particular to a sealing structure of an aircraft engine lubricating oil tank. Background Art
[0002] Gas turbine aircraft engines, the power source for a variety of aircraft, including civil aircraft, are known as the "heart" of aircraft. Lubricating oil is crucial to these engines. Every aircraft engine must be equipped with an oil tank, which is typically located either inside or outside the engine. Internally installing the tank consumes very limited space within the engine, while externally installing it increases the engine's size and volume, increasing flight drag and complicating aircraft-engine integration.
[0003] Existing oil tanks are mostly externally mounted, typically using brackets to attach to specific locations on the engine or fuselage. This takes up space outside the aircraft engine, increasing weight and airflow resistance. Furthermore, the tanks have numerous external piping and a complex structure. The oil caps are often bolted shut, and repeated removal can damage the threaded holes in the tank's sidewalls. This can lead to failure of the cap's fit with the tank wall, leading to oil leakage from the sidewalls. Therefore, there is an urgent need for improved sealing structures for aircraft engine oil tanks to address the shortcomings of existing technologies. Utility Model Content
[0004] In view of the deficiencies in the prior art, the utility model provides a sealing structure for an aircraft engine lubricating oil tank, which can be disassembled and assembled multiple times without affecting the sealing properties of the lubricating oil.
[0005] To achieve the above-mentioned object, the present invention provides the following technical solution: a sealing structure for an aircraft engine oil tank, comprising an oil tank body and an oil tank cover adapted to one side of the oil tank body, wherein one side of the oil tank cover is fixedly connected to a first vent hole, a plurality of sidewall rubber ring mounting grooves are formed on the outer side of the oil tank cover, a second sealing rubber ring is embedded in the sidewall rubber ring mounting groove, a plurality of anti-oil leakage rubber ring mounting grooves are formed on the outer side of the first vent hole, a first sealing rubber ring is embedded in the anti-oil leakage rubber ring mounting groove, a concave quick-release groove is formed on a side of the oil tank cover away from the first vent hole, a stress mounting ring is provided on the inner ring of the oil tank cover, the outer diameter of the oil tank cover and the inner diameter of the oil tank body connection position are out-of-tolerance fit, a mounting positioning ring is provided on the side of the stress mounting ring, a plurality of casing rubber ring mounting grooves are formed on the outer side of the oil tank cover and the inner wall of the oil tank body, a third sealing rubber ring is embedded in the casing rubber ring mounting groove.
[0006] Preferably, a matching groove is provided on the inner bottom of the oil tank cover, and an inclined mounting chamfer is provided on the side surface of the oil tank cover.
[0007] Preferably, an intermediate casing is provided on the outer side of the oil box body, a second vent hole is provided in the intermediate casing, and a plurality of internal supporting ribs are provided on the inner wall of the intermediate casing away from the oil box cover.
[0008] Preferably, the lubricating oil box body is provided with an engine rotor shaft through hole for mounting the engine rotor shaft and an engine inner duct for passing air.
[0009] Preferably, a plurality of internal support members are provided in the oil tank body.
[0010] Preferably, a plurality of inner channel guides are provided in the inner channel of the engine.
[0011] In view of the shortcomings of the prior art, the present invention provides a sealing structure for an aircraft engine lubricating oil tank, which overcomes the shortcomings of the prior art. The beneficial effects of the present invention are:
[0012] In the utility model, the overall structure is simple, disassembly and assembly are convenient, the weight is light, the oil sealing system has high reliability and long service life, and the lubricating oil sealing characteristics are not affected after multiple disassembly and assembly. The opening area of the lubricating oil tank cover is large, which is convenient for maintaining the oil tank system. The side wall of the lubricating oil tank cover can increase the rigidity of the intermediate casing and reduce the deformation of the intermediate casing.
[0013] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or understood by practicing the present invention. The purpose and other advantages of the present invention can be achieved and obtained by the structures indicated in the description, claims and drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention.
[0015] Figure 1 This is a schematic diagram of the overall explosion structure of the utility model;
[0016] Figure 2 This is a structural diagram of the utility model as a whole exploded from another perspective;
[0017] Figure 3 This is a schematic diagram of the structure of a partial lubricating oil tank in the utility model;
[0018] Figure 4 This is a schematic structural diagram of the intermediate casing in the present invention;
[0019] Figure 5 This is a schematic diagram of the structure of the stress installation ring in the utility model;
[0020] Figure 6This is a schematic diagram of the structure of the quick disassembly slot in the utility model;
[0021] Figure 7 This is a schematic structural diagram of the oil tank cover in the utility model;
[0022] Figure 8 This is a structural diagram of the oil tank cover of the utility model from another perspective;
[0023] Figure 9 This is a structural diagram of the side wall rubber ring installation groove in the utility model.
[0024] In the figure: 1. Side wall rubber ring installation groove; 2. Anti-oil leakage rubber ring installation groove; 3. First vent hole; 4. Quick disassembly groove; 5. Matching groove; 6. Installation positioning ring; 7. Stress installation ring; 8. Installation chamfer; 9. Second vent hole; 10. Internal support rib; 11. Intermediate casing; 12. Lubricating oil box body; 13. Engine rotor shaft through hole; 14. Engine inner channel; 15. Casing rubber ring installation groove; 16. Internal support member; 17. Inner channel guide; 18. Lubricating oil tank cover; 19. First sealing rubber ring; 20. Second sealing rubber ring; 21. Third sealing rubber ring. DETAILED DESCRIPTION
[0025] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.
[0026] See also Figures 1-9, a sealing structure of an aircraft engine oil tank, comprising an oil tank body 12 and an oil tank cover 18 adapted to one side of the oil tank body 12, a first vent hole 3 being fixedly connected to one side of the oil tank cover 18, a plurality of side wall rubber ring mounting grooves 1 being provided on the outer side of the oil tank cover 18, a second sealing rubber ring 20 being embedded in the side wall rubber ring mounting groove 1, a plurality of anti-oil leakage rubber ring mounting grooves 2 being provided on the outer side of the first vent hole 3, a first sealing rubber ring 19 being embedded in the anti-oil leakage rubber ring mounting groove 2, a concave quick-release groove 4 being provided on the side of the oil tank cover 18 away from the first vent hole 3, a stress mounting ring 7 being provided on the inner ring of the oil tank cover 18, the outer diameter of the oil tank cover 18 and the inner diameter of the connection position of the oil tank body 12 being an over-tolerance fit, and a side of the stress mounting ring 7 is provided A positioning ring 6 is installed, and several casing rubber ring mounting grooves 15 are provided on the outer diameter of the oil tank cover 18 and the inner wall of the oil tank body 12. A third sealing rubber ring 21 is embedded in the casing rubber ring mounting groove 15. A matching groove 5 is provided on the bottom inner side of the oil tank cover 18. An inclined mounting chamfer 8 is provided on the side of the oil tank cover 18. An intermediate casing 11 is provided on the outer side of the oil tank body 12. A second vent hole 9 is provided in the intermediate casing 11. Several internal support ribs 10 are provided on the inner wall of the intermediate casing 11 away from the oil tank cover 18. An engine rotor shaft through hole 13 for mounting the engine rotor shaft and an engine inner channel 14 for passing air are provided in the oil tank body 12. Several internal support members 16 are provided in the oil tank body 12, and several inner channel guides 17 are provided in the engine inner channel 14.
[0027] In this embodiment, the oil tank cover 18 is constructed of aluminum alloy and integrally cast. Two rubber rings are embedded in the sidewall rubber ring mounting groove 1 to prevent oil from leaking through the outer edge of the sidewall, while also increasing friction and ensuring a tight fit between the cover and the fuel tank. Two rubber rings are also embedded in the anti-leak rubber ring mounting groove 2 to prevent oil from leaking into the casing. To remove the oil tank cover 18, a removal ring (shaped to match the quick-release groove 4) is inserted into the groove and the cover 18 is pulled outward. During installation, the first vent hole 3 and the mounting locating ring 6 must be positioned in their corresponding mounting positions. The diameter of the mounting locating ring 6 is slightly smaller than the diameter of the mounting hole in the intermediate casing 11. Locking the mounting locating ring 6 into place facilitates subsequent installation and ensures proper installation of the oil tank body 12 sidewall. To ensure tightness during installation, the third sealing rubber ring 21 needs to be pressed against the side wall to prevent oil leakage. The elastic stress of the side wall of the oil tank body 12 is used for compression. The diameter of the side wall of the oil tank cover 18 is mismatched with the inner diameter of the oil tank body 12. During installation, the side wall undergoes elastic deformation, generating stress that compresses the second sealing rubber ring 20. Therefore, it is necessary to install a chamfer 8 to assist in installation to ensure that the side wall of the oil tank cover 18 can be accurately installed without damage during installation. The intermediate casing 11 is partially provided with a second vent hole 9. The second vent hole 9 is slightly larger than the first vent hole 3. After installation, the second vent hole 9 is sheathed on the outside of the first vent hole 3, and a sealing effect is achieved by squeezing the two first sealing rubber rings 19. Two internal support ribs 10 are designed inside the oil tank body 12 to increase the overall strength of the oil tank body 12 and prevent damage to the intermediate casing 11 due to external force or pressure from the oil tank body 12. The oil tank body 12 is the oil storage area of the oil tank, consisting of the enclosed space between the oil tank cover 18 and the intermediate casing 11. The engine rotor shaft through-hole 13 is the mounting hole for the engine rotor. The annular oil tank design ensures the correct installation of the engine rotor shaft and the smooth flow of air through the engine inner channel 14. The oil tank cover 18 has three sets of rubber sealing rings, namely the first sealing rubber ring 19, the second sealing rubber ring 20, and the third sealing rubber ring 21. Each set of two rubber rings can ensure that there is no oil leakage on the inside and outside of the oil tank and the pipeline through-hole. The three sets of rubber rings are respectively located in the side wall rubber ring installation groove 1, the anti-leakage rubber ring installation groove 2, and the casing rubber ring installation groove 15. The internal support member 16 is a supporting structure that ensures the overall strength of the oil tank and the intermediate casing 11. The inner channel guide 17 plays the role of supporting and internal piping, ensuring the installation position of the shaft and the structural strength of the intermediate casing 11. The first sealing rubber ring 19 , the second sealing rubber ring 20 and the third sealing rubber ring 21 are made of nitrile rubber (Buna-N), which is resistant to grease, hydraulic oil, lubricating oil and engine oil, as well as mild chemicals and water, ensuring that they will not be damaged by lubricating oil corrosion during use.
[0028] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art will be able to modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.
Claims
1. A sealing structure for an aircraft engine oil tank, comprising an oil tank body (12) and an oil tank cover (18) adapted to one side of the oil tank body (12), characterized in that: The oil tank cover (18) is fixedly connected to a first vent hole (3) on one side, and a plurality of side wall rubber ring mounting grooves (1) are provided on the outside of the oil tank cover (18), and a second sealing rubber ring (20) is embedded in the side wall rubber ring mounting groove (1). The first vent hole (3) is provided with a plurality of anti-leakage rubber ring mounting grooves (2), and a first sealing rubber ring (19) is embedded in the anti-leakage rubber ring mounting groove (2). The oil tank cover (18) is located on a side away from the first vent hole (3). An inwardly concave quick-release groove (4) is provided, the inner ring of the oil tank cover (18) is provided with a stress mounting ring (7), the inner diameter of the connection position between the outer side of the oil tank cover (18) and the oil tank body (12) is an over-tolerance fit, a mounting positioning ring (6) is provided on the side of the stress mounting ring (7), the outer diameter of the oil tank cover (18) and the inner wall of the oil tank body (12) are provided with a plurality of casing rubber ring mounting grooves (15), and a third sealing rubber ring (21) is embedded in the casing rubber ring mounting groove (15).
2. The sealing structure of an aircraft engine lubricating oil tank according to claim 1, characterized in that: A matching groove (5) is provided on the inner bottom of the oil tank cover (18), and an inclined mounting chamfer (8) is provided on the side of the oil tank cover (18).
3. The sealing structure of an aircraft engine lubricating oil tank according to claim 1, characterized in that: An intermediate casing (11) is provided on the outside of the oil box body (12), a second vent hole (9) is provided in the intermediate casing (11), and a plurality of internal support ribs (10) are provided on the inner wall of the intermediate casing (11) away from the oil box cover (18).
4. The sealing structure of an aircraft engine lubricating oil tank according to claim 1, characterized in that: The lubricating oil box (12) is provided with an engine rotor shaft through hole (13) for mounting the engine rotor shaft and an engine inner passage (14) for passing air.
5. The sealing structure of an aircraft engine lubricating oil tank according to claim 1, characterized in that: A plurality of internal support members (16) are provided in the lubricating oil box body (12).
6. The sealing structure of an aircraft engine lubricating oil tank according to claim 4, characterized in that: A plurality of inner channel guides (17) are provided in the inner channel (14) of the engine.