CN214171927U - Sealing device of aircraft engine lubricating oil tank - Google Patents
Sealing device of aircraft engine lubricating oil tank Download PDFInfo
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- CN214171927U CN214171927U CN202120163769.0U CN202120163769U CN214171927U CN 214171927 U CN214171927 U CN 214171927U CN 202120163769 U CN202120163769 U CN 202120163769U CN 214171927 U CN214171927 U CN 214171927U
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- lubricating oil
- oil tank
- shell
- connecting pipe
- cover plate
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Abstract
The utility model relates to the technical field of aero-engine lubricating oil tanks, in particular to a sealing device of an aero-engine lubricating oil tank, which comprises a shell, wherein the inner wall of the shell is provided with a rubber layer, the lubricating oil tank is arranged inside the shell, and the upper surface and the lower surface of the lubricating oil tank are both bonded with protective pads, the surface of the lubricating oil tank is protected by the shell to prevent the lubricating oil tank from directly contacting and colliding with external objects to generate damage, the rubber layer inside the shell enables the abrasion between the lubricating oil tank and the shell to be relieved, the protective pad wraps the corner of the lubricating oil tank to prevent lubricating oil from permeating after the corner of the lubricating oil tank is damaged by collision, connect the oil inlet of lubricating oil tank through the connecting pipe, and the connector position of connecting pipe seals through the sealing washer, places the sealing washer inside the shell, has alleviated the ageing speed of sealing washer, and then makes the phenomenon of the inside lubricating oil seepage of lubricating oil tank obtain control.
Description
Technical Field
The utility model relates to an aeroengine lubricating oil case technical field specifically is an aeroengine lubricating oil case's sealing device.
Background
The lubricating oil system has an important effect on the operation of an aircraft engine, the flight safety of the aircraft is directly influenced, after the lubricating oil tank is used for a long time, the sealing strip is aged, the sealing performance is reduced, the lubricating oil tank is enabled to have a leakage phenomenon, the consumption of the lubricating oil is increased, in addition, the probability of fuel oil leakage in the lubricating oil is increased due to the reduction of the sealing performance of the lubricating oil tank, the aircraft is easily enabled to have faults in the navigation process, and the normal navigation of the aircraft is not facilitated. In view of this, we propose a sealing device for the lubricating oil tank of an aircraft engine.
SUMMERY OF THE UTILITY MODEL
In order to make up for above not enough, the utility model provides an aeroengine lubricating oil tank's sealing device.
The technical scheme of the utility model is that:
the utility model provides an aeroengine lubricating oil tank's sealing device, includes the shell, the inner wall of shell is equipped with the rubber layer, the inside of shell is equipped with the lubricating oil tank, the upper and lower both sides surface of lubricating oil tank all bonds and has the protection pad, the left and right sides of lubricating oil tank all is equipped with the connecting rod, the connecting rod is kept away from the one end of lubricating oil tank with shell fixed connection, the upper surface of shell with the round hole has all been seted up on the rubber layer, the welding of round hole inner wall has the connecting pipe, the lower extreme of connecting pipe with the oil inlet of lubricating oil tank communicates with each other, the circumference outer wall department cover of connecting pipe is equipped with the sealing washer, the sealing washer is equipped with two, the standing groove has been seted up to the upper surface inside of shell, the inside apron that is equipped with of standing groove, the left side of apron is equipped with the spring.
As the preferred technical scheme, the corners of the protection pad are rounded.
Preferably, both ends of the spring are respectively welded with the cover plate and the inner wall of the placing groove.
As a preferable technical scheme, the upper side and the lower side of the placing groove are not communicated with the outside, and the placing groove corresponds to the center of the round hole.
As a preferable technical solution, the cover plate is located on the upper surface of the connection pipe, and both the length and the width of the cover plate are greater than the length of the diameter of the connection pipe.
Preferably, the cover plate is slidably connected to the placement groove.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model discloses a shell protects the surface of lubricating oil tank, prevent that the lubricating oil tank from direct and external object contact collision and producing the damage, the inside rubber layer of shell makes wearing and tearing between lubricating oil tank and the shell alleviated, wrap up the corner of lubricating oil tank through the protection pad, prevent the impaired back of turning collision of lubricating oil tank, make the lubricating oil infiltration, connect the oil inlet of lubricating oil tank through the connecting pipe, and the connector position of connecting pipe seals through the sealing washer, place the sealing washer inside the shell, the ageing speed of sealing washer has been alleviated, and then the phenomenon of the inside lubricating oil seepage of lubricating oil tank is controlled.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a sectional view of the whole structure of the present invention;
fig. 3 is a schematic view of a partial structure of the present invention.
In the figure:
a housing 1; a circular hole 11; a connecting pipe 111; a placement groove 12; a lubricating oil tank 2; a protection pad 21; a connecting rod 22; a rubber layer 3; a seal ring 4; a spring 5; and a cover plate 6.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Referring to fig. 1-3, the present invention provides a technical solution:
the utility model provides an aeroengine lubricating oil tank's sealing device, which comprises an outer shell 1, the inner wall of shell 1 is equipped with rubber layer 3, the inside of shell 1 is equipped with lubricating oil tank 2, the upper and lower both sides surface of lubricating oil tank 2 all bonds and has protection pad 21, the left and right sides of lubricating oil tank 2 all is equipped with connecting rod 22, connecting rod 22 keeps away from lubricating oil tank 2's one end and shell 1 fixed connection, round hole 11 has all been seted up on shell 1's upper surface and the rubber layer 3, the welding of the 11 inner walls of round hole has connecting pipe 111, the lower extreme of connecting pipe 111 communicates with each other with the oil inlet of lubricating oil tank 2, the circumference outer wall department cover of connecting pipe 111 is equipped with sealing washer 4, sealing washer 4 is equipped with two, standing groove 12 has been seted up to shell 1's upper surface inside, standing groove 12 is inside to be equipped with apron 6, the left side of apron 6 is equipped with spring 5.
It should be added that the inner wall of the sealing ring 4 is attached to the outer wall of the connecting pipe 111, the sealing ring 4 is fixedly connected to the connecting pipe 111, the sealing ring 4 on the lower end surface of the connecting pipe 111 is located on the inner wall of the upper surface of the lubricating oil tank 2, and the sealing ring 4 on the upper end surface of the connecting pipe 111 is located on the inner wall of the upper surface of the housing 1.
Preferably, the corners of the protection pad 21 are rounded, a sealing strip is bonded in the protection pad 21 and in the gap between the corners of the lubricant tank 2, and the width of the sealing strip is matched with the size of the gap between the protection pad 21 and the corners of the lubricant tank 2, so that the oil leakage phenomenon at the corners of the lubricant tank 2 is effectively prevented.
As a preference of the embodiment, both ends of the spring 5 are respectively welded with the cover plate 6 and the inner wall of the placing groove 12, so that the cover plate 6 can be pushed to one end of the placing groove 12 far away from the spring 5 by the resilience force of the spring 5 after the cover plate 6 moves inside the placing groove 12, thereby covering the upper surface of the connecting pipe 111.
As the optimization of this embodiment, the upper and lower both sides of the placing groove 12 are not communicated with the outside, and the placing groove 12 corresponds to the center position of the circular hole 11, so that the cover plate 6 is tightly clamped inside the placing groove 12, and the connecting pipe 111 is conveniently covered.
Preferably, the cover plate 6 is located on the upper surface of the connection pipe 111, the lower surface of the cover plate 6 contacts the upper surface of the connection pipe 111, and the length and width of the cover plate 6 are both greater than the length of the diameter of the connection pipe 111.
Preferably, the cover plate 6 is slidably connected to the placement groove 12, so that the cover plate 6 can move in the placement groove 12.
When the sealing device of the aero-engine lubricating oil tank of the utility model is used, the protective pads 21 on the upper and lower surfaces of the lubricating oil tank 2 can effectively prevent the corners outside the lubricating oil tank 2 from being damaged after being impacted, thereby generating an oil leakage phenomenon, the lubricating oil tank 2 is fixed by the connecting rod 22, the lubricating oil tank 2 is prevented from colliding with the shell 1 when moving in the airplane, the rubber layer 3 arranged on the inner wall of the shell 1 can reduce the abrasion caused by the friction with the lubricating oil tank 2, when the lubricating oil is required to be supplemented in the lubricating oil tank 2, the cover plate 6 is pushed to the left side, so that the cover plate 6 moves to the left inside the placing groove 12, the spring 5 is stressed and stretches to generate deformation, further, the connecting pipe 111 is exposed, the lubricating oil enters the lubricating oil tank 2 through the connecting pipe 111, after the lubricating oil is supplemented, the cover plate 6 loses the supporting force, the cover plate 6 is pushed to move inside the placing groove 12 through the resilience force of the spring 5, so that the cover plate 6 covers the upper surface of the connection pipe 111.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only preferred examples of the present invention, and is not intended to limit the present invention, and that the present invention can have various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall into the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. A sealing device for an aircraft engine fuel tank, comprising a housing (1), characterized in that: the inner wall of the shell (1) is provided with a rubber layer (3), a lubricating oil tank (2) is arranged inside the shell (1), protective pads (21) are bonded on the surfaces of the upper side and the lower side of the lubricating oil tank (2), connecting rods (22) are arranged on the left side and the right side of the lubricating oil tank (2), one end, far away from the lubricating oil tank (2), of each connecting rod (22) is fixedly connected with the shell (1), the upper surface of the shell (1) and the rubber layer (3) are respectively provided with a round hole (11), the inner wall of each round hole (11) is welded with a connecting pipe (111), the lower end of each connecting pipe (111) is communicated with an oil inlet of the corresponding lubricating oil tank (2), sealing rings (4) are sleeved on the outer wall of the circumference of each connecting pipe (111), two sealing rings (4) are arranged, a placing groove (12) is formed in the inner portion of the upper surface of the shell (1), a cover plate (6) is arranged in the placing groove (12), and a spring (5) is arranged on the left side of the cover plate (6).
2. A seal arrangement for an aircraft engine fuel tank as claimed in claim 1, wherein: the corners of the protective pad (21) are rounded.
3. A seal arrangement for an aircraft engine fuel tank as claimed in claim 1, wherein: and two ends of the spring (5) are respectively welded with the cover plate (6) and the inner wall of the placing groove (12).
4. A seal arrangement for an aircraft engine fuel tank as claimed in claim 1, wherein: the upper side and the lower side of the placing groove (12) are not communicated with the outside, and the placing groove (12) corresponds to the center of the round hole (11).
5. A seal arrangement for an aircraft engine fuel tank as claimed in claim 1, wherein: the cover plate (6) is positioned on the upper surface of the connecting pipe (111), and the length and the width of the cover plate (6) are both greater than the length of the diameter of the connecting pipe (111).
6. A seal arrangement for an aircraft engine fuel tank as claimed in claim 1, wherein: the cover plate (6) is connected with the placing groove (12) in a sliding mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120163769.0U CN214171927U (en) | 2021-01-21 | 2021-01-21 | Sealing device of aircraft engine lubricating oil tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120163769.0U CN214171927U (en) | 2021-01-21 | 2021-01-21 | Sealing device of aircraft engine lubricating oil tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214171927U true CN214171927U (en) | 2021-09-10 |
Family
ID=77593854
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120163769.0U Active CN214171927U (en) | 2021-01-21 | 2021-01-21 | Sealing device of aircraft engine lubricating oil tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214171927U (en) |
-
2021
- 2021-01-21 CN CN202120163769.0U patent/CN214171927U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Sealing device for aeroengine oil tank Effective date of registration: 20221130 Granted publication date: 20210910 Pledgee: Shandong Laizhou Rural Commercial Bank Co.,Ltd. Shentang Sub branch Pledgor: Shandong Zhongwei Power Technology Co.,Ltd. Registration number: Y2022980023726 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |