Lubricating oil tank, lubricating oil system and aero-engine
By designing a lubricant fuel tank with a one-way guide and a rotating suction pipe, the problem of insufficient lubricant supply during aircraft flight is solved, and continuous lubrication and cooling of engine bearings and gear systems is achieved.
Patent Information
- Application Number
- CN202422353389.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-26
- Publication Date
- 2025-06-13
- Estimated Expiration
- 2034-09-26
AI Technical Summary
The existing lubricant tank cannot continuously supply lubricant in the aircraft's reverse flight attitude, resulting in the engine bearings and gear systems not being sufficiently lubricated and cooled.
A lubricating oil tank is designed, including a housing, suction pipe and one-way guide. The housing has a fuel refueling port, an oil outlet, and a first oil container cavity and a second oil container cavity arranged separately. The one-way guide only allows the lubricant to flow from the second oil container cavity to the first oil container cavity. The oil suction pipe is rotatably arranged in the first oil container cavity, and the oil inlet is always located at the bottom to ensure that the oil is continuously supplied when flying backwards.
In the aircraft's reverse flight attitude, the lubricant fuel tank can continuously supply lubricant to meet the lubricating and cooling needs of various bearings and gear systems of the engine, and the structure is simple.
Smart Images
Figure CN222977876U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of aviation technology, and in particular to a lubricating oil tank, a lubricating oil system and an aviation engine. Background Art
[0002] The oil tank is an important component in the engine oil system. The main function of the oil system is to provide the system with oil at a certain temperature and pressure to lubricate and cool the engine's bearings, gear systems, etc. The oil system should have an oil storage device, namely the oil tank, to provide continuous replenishment for the engine oil consumption. Since the aircraft has an inverted flight attitude and flight time requirements during flight, the existing design of the oil tank cannot meet the requirements of continuously supplying oil to the oil system in the inverted flight attitude, and thus cannot meet the requirements of lubrication and cooling of the engine's bearings and gear systems.
[0003] Therefore, a lubricating oil tank is urgently needed to solve the above-mentioned technical problems. Utility Model Content
[0004] The utility model aims to provide a lubricating oil tank, which can normally flow out and return lubricating oil when the aircraft is flying forward or backward, so as to meet the lubrication and cooling of various bearings and gear systems of the engine, and has a simple structure.
[0005] To achieve this purpose, the utility model adopts the following technical solutions:
[0006] In a first aspect, a lubricating oil tank is provided, comprising:
[0007] The housing has a refueling port, an oil outlet, and a first oil storage chamber and a second oil storage chamber that are separated and arranged. The first oil storage chamber is connected with the second oil storage chamber through a one-way flow guide. The one-way flow guide is located in the first oil storage chamber and is fixed relative to the first oil storage chamber. The one-way flow guide only allows the lubricating oil to flow from the second oil storage chamber to the first oil storage chamber. The refueling port is connected with the second oil storage chamber, and the oil outlet is connected with the first oil storage chamber.
[0008] The oil suction pipe is rotatably arranged in the first oil containing cavity, and the oil inlet of the oil suction pipe is always located at the bottom of the first oil containing cavity due to gravity.
[0009] As a preferred technical solution of the above-mentioned lubricating oil tank, the shell further has an oil return port, and the oil return port is connected to the second oil containing chamber.
[0010] As a preferred technical solution of the above-mentioned lubricating oil tank, the oil return port is connected to an oil return pipeline, and the outlet of the oil return pipeline is communicated with the first oil storage chamber.
[0011] As a preferred technical solution of the above lubricating oil tank, a partition plate for separating the first oil storage cavity and the second oil storage cavity is arranged inside the outer shell.
[0012] As a preferred technical solution of the above lubricating oil tank, a sealing ring is arranged between the partition plate and the inner wall of the outer shell.
[0013] As a preferred technical solution of the above lubricating oil tank, the one-way flow guiding member includes an anti-overflow pipe, and the anti-overflow pipe is a rigid plastic pipe.
[0014] As a preferred technical solution of the above lubricating oil tank, a counterweight is arranged at the oil inlet end of the oil suction pipe.
[0015] As a preferred technical solution of the above lubricating oil tank, the lubricating oil tank further includes a fixed seat arranged at the oil outlet. The oil suction pipe is rotatably arranged on the fixed seat. The fixed seat has a through hole, and the oil outlet, the through hole and the outlet of the oil suction pipe are communicated.
[0016] In a second aspect, a lubricating oil system is provided, including the lubricating oil tank according to any one of the above solutions.
[0017] In a third aspect, an aeroengine is provided, including the lubricating oil system described above.
[0018] The utility model has at least the following beneficial effects:
[0019] The lubricating oil tank includes an outer shell and an oil suction pipe. The outer shell has a fuel filling port, an oil outlet, and a first oil storage cavity and a second oil storage cavity which are separated. The first oil storage cavity and the second oil storage cavity are communicated through a one-way flow guiding member. The one-way flow guiding member is located in the first oil storage cavity and is fixed relative to the first oil storage cavity. The fuel filling port is communicated with the second oil storage cavity, and the oil outlet is communicated with the first oil storage cavity. The oil suction pipe is rotatably arranged in the first oil storage cavity, and the oil inlet of the oil suction pipe is always located at the bottom of the first oil storage cavity under the action of gravity. The first oil storage cavity and the second oil storage cavity are separated. When fuel is filled through the fuel filling port, the lubricating oil first fills the second oil storage cavity. When the lubricating oil in the second oil storage cavity reaches a certain amount, it will enter the first oil storage cavity through the one-way flow guiding member to fill the first oil storage cavity with lubricating oil. Since the oil suction pipe is rotatably arranged in the first oil storage cavity and the oil inlet of the oil suction pipe is always located at the bottom of the first oil storage cavity under the action of gravity, it is ensured that the lubricating oil system can be continuously supplied with lubricating oil when the aircraft is in an inverted attitude, so as to meet the lubrication and cooling of each bearing and gear system of the engine. In addition, the structures of the oil suction pipe, the first oil storage cavity and the second oil storage cavity are relatively simple. The one-way flow guiding member is fixedly arranged relative to the first oil storage cavity, that is, the position of the one-way flow guiding member does not change, so that it can be avoided that the lubricating oil flows back from the first oil storage cavity to the second oil storage cavity through the one-way flow guiding member when the aircraft is inverted. Description of the Drawings
[0020] To more clearly illustrate the technical solutions in the embodiments of the present utility model, the following will briefly introduce the drawings required for the description of the embodiments of the present utility model. Obviously, the drawings described below are only some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on the content of the embodiments of the present utility model and these drawings.
[0021] Figure 1 It is a cross-sectional view of the lubricating oil tank in the normal flight attitude of the aircraft provided by the embodiment of the present utility model;
[0022] Figure 2 It is a cross-sectional view of the lubricating oil tank in the inverted flight attitude of the aircraft provided by the embodiment of the present utility model.
[0023] In the figure:
[0024] 1. Outer shell; 11. First oil storage cavity; 12. Second oil storage cavity; 121. Fuel filling port; 2. Suction pipe; 3. Oil return pipeline; 4. Partition plate; 5. One-way flow guiding member; 6. Fixed seat. Specific embodiments
[0025] The following will further elaborate on the present utility model in conjunction with the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the present utility model, rather than limiting the present utility model. Additionally, it should be noted that for the sake of convenience of description, only the parts related to the present utility model rather than all the structures are shown in the drawings.
[0026] In the description of the present utility model, unless otherwise clearly defined and limited, the terms "connected", "connected to", and "fixed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
[0027] In the present utility model, unless otherwise clearly defined and limited, the first feature being "above" or "below" the second feature may include the direct contact between the first and second features, or may also include the situation where the first and second features are not in direct contact but in contact through additional features therebetween. Moreover, the first feature being "above", "over" and "on top of" the second feature includes the first feature being directly above and obliquely above the second feature, or merely indicating that the horizontal height of the first feature is higher than that of the second feature. The first feature being "below", "under" and "beneath" the second feature includes the first feature being directly below and obliquely below the second feature, or merely indicating that the horizontal height of the first feature is lower than that of the second feature.
[0028] In the description of the present embodiment, the orientation or positional relationships such as "above", "below", "right", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of description and simplifying the operation, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.
[0029] An embodiment of the present utility model provides an oil sump which can allow the oil to flow out and return to the sump normally when the aircraft is flying forward and backward, meet the lubrication and cooling of each bearing and gear system of the engine, and has a simple structure.
[0030] As Figure 1 and Figure 2 shown, the oil sump includes a housing 1 and an oil suction pipe 2. The housing 1 has a fuel filling port 121, an oil outlet, and a first oil storage cavity 11 and a second oil storage cavity 12 which are separated. The first oil storage cavity 11 is communicated with the second oil storage cavity 12 through a one-way flow guiding member 5. The one-way flow guiding member 5 is located in the first oil storage cavity 11 and is fixed relative to the first oil storage cavity 11. The one-way flow guiding member 5 only allows the oil to flow from the second oil storage cavity 12 to the first oil storage cavity 11. The fuel filling port 121 is communicated with the second oil storage cavity 12, and the oil outlet is communicated with the first oil storage cavity 11. The oil suction pipe 2 is rotatably arranged in the first oil storage cavity 11, and the oil inlet of the oil suction pipe 2 is always located at the bottom of the first oil storage cavity 11 under the action of gravity.
[0031] The first oil storage cavity 11 and the second oil storage cavity 12 are separated. When refueling through the fuel filling port 121, the lubricating oil first fills the second oil storage cavity 12. After a certain amount of lubricating oil in the second oil storage cavity 12 is reached, it will enter the first oil storage cavity 11 through the one-way flow guiding member 5 to fill the first oil storage cavity 11 with lubricating oil. Since the suction pipe 2 is rotatably arranged in the first oil storage cavity 11 and the oil inlet of the suction pipe 2 is always located at the bottom of the first oil storage cavity 11 due to gravity, it is ensured that the aircraft can continuously supply lubricating oil to the lubricating oil system in the inverted flight attitude to meet the lubrication and cooling of each bearing and gear system of the engine. In addition, the arrangement of the suction pipe 2, the first oil storage cavity 11 and the second oil storage cavity 12 has a relatively simple structure. The one-way flow guiding member 5 is fixedly arranged relative to the first oil storage cavity 11, that is, the position of the one-way flow guiding member 5 does not change, so as to prevent the lubricating oil from flowing back to the second oil storage cavity 12 through the one-way flow guiding member 5 when the aircraft is in an inverted flight. The one-way flow guiding member 5 only allows the lubricating oil to flow from the second oil storage cavity 12 to the first oil storage cavity 11, so as to ensure that the lubricating oil will not enter the second oil storage cavity 12 from the first oil storage cavity 11 when the aircraft is in an inverted flight, and ensure that there is sufficient lubricating oil volume to meet the need for lubricating oil volume in the inverted flight.
[0032] The housing 1 has an arc portion, a transition portion and an oil inlet portion, wherein the transition portion connects the arc portion and the oil inlet portion, the arc portion forms the first oil storage cavity 11, and the transition portion and the oil inlet portion form the second oil storage cavity 12. The housing 1 is an integrally formed structure, and the housing 1 has a side wall in a circular arc shape to adapt to the layout of other components of the aeroengine and avoid interference.
[0033] After the lubricating oil lubricates and cools each bearing and gear system, it needs to flow back into the first oil storage cavity 11 to prevent the heat absorbed by the lubricating oil from the components from not being taken away. Therefore, in some embodiments, the housing 1 also has an oil return port, and the oil return port is communicated with the second oil storage cavity 12. The oil return port receives the lubricating oil flowing back from each bearing and gear system. More specifically, an oil return pipe 3 is connected to the oil return port, and the outlet of the oil return pipe 3 is communicated with the first oil storage cavity 11. In this way, the lubricating oil flowing back from each bearing and gear system directly enters the first oil storage cavity 11 through the oil return pipe 3. Especially when the aircraft is in an inverted flight, the first oil storage cavity 11 is located above the second oil storage cavity 12, and the lubricating oil directly enters the first oil storage cavity 11 to provide lubricating oil for the first oil storage cavity 11 to meet the time requirement during the inverted flight of the aircraft. The shape of the oil return pipe is set according to the second oil storage cavity 12. As Figure 1 shown, the shape of the oil return pipe 3 is L-shaped, and no specific limitation is made in other embodiments.
[0034] In some embodiments, continue to refer to Figure 1 and Figure 2, a partition plate 4 is provided in the housing 1 to separate the first oil chamber 11 and the second oil chamber 12. The partition plate 4 can separate the first oil chamber 11 and the second oil chamber 12 to prevent the lubricating oil from being concentrated in the first oil chamber 11, thereby ensuring that the lubricating oil is concentrated in the first oil chamber 11 when the aircraft is flying inverted to lubricate and cool the bearing and gear system. The one-way guide 5 is provided on the partition plate 4. Exemplarily, the partition plate 4 is welded to the inner wall of the housing 1.
[0035] In order to prevent the lubricating oil from leaking from the partition plate 4 into the second oil storage chamber 12, a sealing ring is provided between the partition plate 4 and the inner wall of the housing 1. The provision of the sealing ring can improve the sealing performance between the first oil storage chamber 11 and the second oil storage chamber 12, so as to further ensure the amount of oil in the first oil storage chamber 11.
[0036] When the aircraft is flying inverted, the position of the one-way flow guide 5 relative to the first oil storage chamber 11 remains unchanged. For this purpose, the one-way flow guide 5 includes an anti-overflow pipe, such as Figure 2 As shown, the anti-overflow pipe is a hard plastic pipe. This ensures that the anti-overflow pipe is not deformed by gravity. In addition, the hard plastic pipe can also avoid being squeezed and deformed by other structures in the lubricating oil tank, ensuring smooth flow of lubricating oil. It should be noted that the oil return pipe and the oil suction pipe 2 are both hard plastic pipes.
[0037] In some other embodiments, the one-way flow guide 5 includes a one-way valve, which can be opened under a certain lubricating oil pressure to allow the lubricating oil to flow from the second oil storage chamber 12 into the first oil storage chamber 11 .
[0038] In some embodiments, in order to make the oil suction pipe 2 always be located at the bottom of the first oil storage chamber 11 under the action of gravity, a counterweight is provided at the oil inlet end of the oil suction pipe 2. The provision of the counterweight can increase the weight of the oil inlet end of the oil suction pipe 2, so that no matter whether the aircraft is in an inverted flight attitude or a forward flight attitude, the oil suction pipe 2 is located at the bottom of the first oil storage chamber 11 under the action of gravity, and the lubricating oil can be delivered to the bearing and gear system to achieve lubrication and cooling of the bearing and gear system.
[0039] In some embodiments, the lubricating oil tank further includes a fixing seat 6, which is disposed at the oil outlet, and the oil suction pipe 2 is rotatably disposed on the fixing seat 6, and the fixing seat 6 has a through hole, and the oil outlet, the through hole and the outlet of the oil suction pipe 2 are connected. The fixing seat 6 can provide support for the oil suction pipe 2, and the fixing seat 6 is arranged to ensure that the oil suction pipe 2 can rotate in the first oil storage chamber 11 while there is no oil leakage at the oil outlet, and the oil outlet, the through hole and the outlet of the oil suction pipe 2 are connected to ensure that the lubricating oil can flow out of the first oil storage chamber 11 smoothly.
[0040] The present utility model further provides an oil system, which includes the oil tank provided by the embodiment of the present utility model. Since the oil tank is included, the first oil storage cavity 11 and the second oil storage cavity 12 are separated. When refueling through the fuel filling port 121, the oil first fills the second oil storage cavity 12. After the oil in the second oil storage cavity 12 reaches a certain amount, it will enter the first oil storage cavity 11 through the one-way flow guiding member 5 to fill the first oil storage cavity 11 with oil. Since the oil suction pipe 2 is rotatably arranged in the first oil storage cavity 11, and the oil inlet of the oil suction pipe 2 is always located at the bottom of the first oil storage cavity 11 due to gravity, it is ensured that the oil system can continuously supply oil in the inverted flight attitude of the aircraft, meeting the lubrication and cooling of each bearing and gear system of the engine. In addition, the arrangement of the oil suction pipe 2, the first oil storage cavity 11 and the second oil storage cavity 12 is relatively simple. The one-way flow guiding member 5 is fixedly arranged relative to the first oil storage cavity 11, that is, the position of the one-way flow guiding member 5 does not change, so as to avoid the oil flowing back to the second oil storage cavity 12 through the one-way flow guiding member 5 when the aircraft is in an inverted flight attitude.
[0041] Since the above-mentioned oil tank is included, the oil system of the embodiment of the present utility model has all the advantages and beneficial effects of the above embodiment, which will not be elaborated here.
[0042] The present utility model further provides an aeroengine, which includes the oil system provided by the embodiment of the present utility model. Since the oil tank is included, the first oil storage cavity 11 and the second oil storage cavity 12 are separated. When refueling through the fuel filling port 121, the oil first fills the second oil storage cavity 12. After the oil in the second oil storage cavity 12 reaches a certain amount, it will enter the first oil storage cavity 11 through the one-way flow guiding member 5 to fill the first oil storage cavity 11 with oil. Since the oil suction pipe 2 is rotatably arranged in the first oil storage cavity 11, and the oil inlet of the oil suction pipe 2 is always located at the bottom of the first oil storage cavity 11 due to gravity, it is ensured that the oil system can continuously supply oil in the inverted flight attitude of the aircraft, meeting the lubrication and cooling of each bearing and gear system of the engine. In addition, the arrangement of the oil suction pipe 2, the first oil storage cavity 11 and the second oil storage cavity 12 is relatively simple. The one-way flow guiding member 5 is fixedly arranged relative to the first oil storage cavity 11, that is, the position of the one-way flow guiding member 5 does not change, so as to avoid the oil flowing back to the second oil storage cavity 12 through the one-way flow guiding member 5 when the aircraft is in an inverted flight attitude.
[0043] Since the above-mentioned oil system is included, the aeroengine of the embodiment of the present utility model has all the advantages and beneficial effects of the above embodiment, which will not be elaborated here.
[0044] In addition, the above are only the preferred embodiments of the present utility model and the technical principles applied. Those skilled in the art will understand that the present utility model is not limited to the specific embodiments described herein, and various obvious changes, re-adjustments and substitutions can be made by those skilled in the art without departing from the protection scope of the present utility model. Therefore, although the present utility model has been described in more detail through the above embodiments, the present utility model is not limited to the above embodiments only. Without departing from the concept of the present utility model, more other equivalent embodiments can be included, and the scope of the present utility model is determined by the scope of the appended claims.
Claims
1. A lubricating oil tank, characterized in that: include: The housing (1) comprises a refueling port (121), an oil outlet, and a first oil containing chamber (11) and a second oil containing chamber (12) which are separated from each other. The first oil containing chamber (11) and the second oil containing chamber (12) are connected via a one-way flow guide (5). The one-way flow guide (5) is located in the first oil containing chamber (11) and is fixed relative to the first oil containing chamber (11). The one-way flow guide (5) only allows lubricating oil to flow from the second oil containing chamber (12) to the first oil containing chamber (11). The refueling port (121) is connected to the second oil containing chamber (12), and the oil outlet is connected to the first oil containing chamber (11). The oil suction pipe (2) is rotatably arranged in the first oil containing chamber (11), and the oil inlet of the oil suction pipe (2) is always located at the bottom of the first oil containing chamber (11) due to gravity.
2. The lubricating oil tank according to claim 1, characterized in that: The housing (1) also has an oil return port, which is in communication with the second oil containing chamber (12).
3. The lubricating oil tank according to claim 2, characterized in that: The oil return port is connected to an oil return pipeline (3), and the outlet of the oil return pipeline (3) is in communication with the first oil containing chamber (11).
4. The lubricating oil tank according to claim 1, characterized in that: A partition plate (4) is arranged in the housing (1) to separate the first oil containing chamber (11) and the second oil containing chamber (12), and the one-way flow guide (5) is arranged on the partition plate (4).
5. The lubricating oil tank according to claim 4, characterized in that: A sealing ring is provided between the partition plate (4) and the inner wall of the outer shell (1).
6. The lubricating oil tank according to claim 1, characterized in that: The one-way flow guide (5) comprises an anti-overflow pipe, and the anti-overflow pipe is a hard plastic pipe.
7. The lubricating oil tank according to claim 1, characterized in that: A counterweight block is provided at the oil inlet end of the oil suction pipe (2).
8. The lubricating oil tank according to claim 1, characterized in that: The lubricating oil tank also includes a fixed seat (6), the fixed seat (6) is arranged at the oil outlet, the oil suction pipe (2) is rotatably arranged on the fixed seat (6), the fixed seat (6) has a through hole, and the oil outlet, the through hole and the outlet of the oil suction pipe (2) are connected.
9. A lubricating oil system, characterized in that: Comprising a lubricating oil tank as described in any one of claims 1-8.
10. An aircraft engine, characterized in that: Comprising the lubricating oil system as claimed in claim 9.