CN212535863U - Aircraft engine lubricating oil tank - Google Patents
Aircraft engine lubricating oil tank Download PDFInfo
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- CN212535863U CN212535863U CN202020714614.7U CN202020714614U CN212535863U CN 212535863 U CN212535863 U CN 212535863U CN 202020714614 U CN202020714614 U CN 202020714614U CN 212535863 U CN212535863 U CN 212535863U
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Abstract
The utility model provides an aircraft engine lubricating oil tank, a baffle and an oil pipe are arranged in the lubricating oil tank, and the baffle divides the lubricating oil tank into an upper oil tank and a lower oil tank; an oil inlet pipe and an engine oil return pipe penetrate through the upper oil tank; an oil chamber is arranged in the lower oil tank and connected to the partition plate; an engine oil supply pipe penetrates through the lower oil tank and the oil chamber, and an opening through which oil flows between the oil supply chamber and the lower oil tank is formed between the oil chamber and the partition plate; an oil discharge pipe is arranged in the lower oil tank in a penetrating way; the one end and the baffle of oil pipe are connected, and the other end setting is just kept away from at the fuel feeding outdoor the baffle, oil pipe is used for the fuel feeding to flow into oil tank down from last oil tank. The utility model provides a lubricating oil tank structure guarantees that the aircraft still can normally supply oil under various gestures oil system.
Description
Technical Field
The utility model relates to an oil tank structure field especially relates to an aeroengine lubricating oil case.
Background
The lubricating oil tank of the engine has the functions of storing oil, dissipating heat of the lubricating oil, precipitating impurities in the lubricating oil and separating air in the lubricating oil, so that the circulating use of the lubricating oil of the engine is ensured. The existing simple lubricating oil tank structure is more applied to airplanes which do not make large maneuvering flight, such as civil aircrafts, and the like, and the oil supply requirements under the conditions of diving, overturning and the like cannot be met.
In order to solve the problems, a part of the lubricating oil tank is internally provided with a soft oil supply pipe, one end of the soft oil supply pipe is provided with a balance weight, and the position of the soft pipe can be changed along with the change of the flying posture under the action of gravity, so that an oil suction port of the oil supply soft pipe is always buried under the oil level. However, the hose type structure requires that the shape of the oil tank is regular and has a larger internal space, and the internal space layout of the existing aircraft is difficult to meet the requirements.
Meanwhile, the soft oil supply pipe is easily clamped by other components, the failure rate is high, and the hose is made of plastic or rubber and is easy to age, harden and become brittle. The reliability is poor, and the service life is short.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an aeroengine lubricating oil tank can alleviate the relatively poor, shorter problem of life of current oil tank reliability.
The utility model provides an aeroengine lubricating oil tank, be provided with baffle 1 and oil pipe 2 in the lubricating oil tank, baffle 1 divide the lubricating oil tank into two oil tanks about;
an oil inlet pipe 3 and an engine oil return pipe 4 penetrate through the upper oil tank;
an oil chamber 5 is arranged in the lower oil tank, and the oil chamber 5 is connected to the partition plate 1; an engine oil supply pipe 6 penetrates through the lower oil tank and the oil chamber 5, and an opening through which oil flows between the oil chamber 5 and the lower oil tank is formed between the oil chamber 5 and the partition plate 1; an oil drain pipe 7 is arranged in the lower oil tank in a penetrating way;
one end of the oil through pipe 2 is connected with the partition plate 1, the other end of the oil through pipe is arranged outside the oil chamber 5 and far away from the partition plate 1, and the oil through pipe 2 is used for supplying oil to flow into the lower oil tank from the upper oil tank.
Optionally, the partition board 1 is further provided with an air breather 8; the top of the upper oil tank is also provided with a ventilation interface 9.
Optionally, the ventilation device 8 is a tank ventilation pipe, and an outlet of the tank ventilation pipe is arranged towards the ventilation interface 9.
Alternatively, the capacity of the oil chamber 5 is determined according to the amount of oil required for the engine.
Optionally, the material of the partition board 1 is light alloy.
Optionally, the shape of the lubricating oil tank is determined according to the spatial layout of the aircraft engine.
The utility model provides a lubricating oil tank structure guarantees that the aircraft still can normally supply oil under various gestures oil system. The soft oil supply pipe is not adopted, so that the problems that the soft oil supply pipe is extremely easy to be clamped by other components, the failure rate is high, and the hose is easy to age, harden and become brittle due to the fact that the hose is made of plastic or rubber, the reliability is poor and the service life is short are solved.
Drawings
Fig. 1 is a schematic structural diagram of an aircraft engine lubricating oil tank provided by the present invention;
description of reference numerals:
1-a separator; 2-oil pipe; 3-oil inlet pipe;
4-an engine oil return pipe; 5-oil chamber; 6-engine oil supply pipe;
7, discharging an oil pipe; 8-a ventilation device; 9-vent interface.
Detailed Description
Fig. 1 is the utility model provides an aeroengine lubricating oil tank's schematic structure diagram. Referring to fig. 1, a partition plate 1 and an oil pipe 2 are arranged in the oil tank provided by the utility model, and the oil tank is divided into an upper oil tank and a lower oil tank by the partition plate 1;
an oil inlet pipe 3 and an engine oil return pipe 4 penetrate through the upper oil tank;
an oil chamber 5 is arranged in the lower oil tank, and the oil chamber 5 is connected to the partition plate 1; an engine oil supply pipe 6 penetrates through the lower oil tank and the oil chamber 5, and an opening through which oil flows between the oil chamber 5 and the lower oil tank is formed between the oil chamber 5 and the partition plate 1; an oil drain pipe 7 is arranged in the lower oil tank in a penetrating way;
one end of the oil through pipe 2 is connected with the partition plate 1, the other end of the oil through pipe is arranged outside the oil chamber 5 and far away from the partition plate 1, and the oil through pipe 2 is used for supplying oil to flow into the lower oil tank from the upper oil tank.
Optionally, the partition board 1 is further provided with an air breather 8; the top of the upper oil tank is also provided with a ventilation interface 9.
Optionally, the ventilation device 8 is a tank ventilation pipe, and an outlet of the tank ventilation pipe is arranged towards the ventilation interface 9.
Alternatively, the capacity of the oil chamber 5 is determined according to the amount of oil required for the engine.
Optionally, the material of the partition board 1 is light alloy.
Optionally, the shape of the lubricating oil tank is determined according to the spatial layout of the aircraft engine.
The utility model provides an oil tank internal weld has the baffle, and the baffle divide into two oil tanks about the oil tank. An upper oil tank oil through pipe and a lower oil tank oil through pipe are welded below the partition plate, and a certain gap is reserved between the end part of the oil through pipe and the bottom of the oil tank. The oil pipe ensures the communication between the upper oil tank and the lower oil tank of the clapboard. A square oil chamber is arranged below the partition plate, and a certain interval is arranged between the outer wall of the oil chamber and the partition plate, so that oil and air can be conveniently introduced. The oil supply joint for the engine lubricating oil is arranged in the oil chamber, so that the oil supply joint can not expose the oil surface under any condition.
Claims (6)
1. The aircraft engine lubricating oil tank is characterized in that a partition plate and an oil through pipe are arranged in the lubricating oil tank, and the partition plate divides the lubricating oil tank into an upper oil tank and a lower oil tank;
an oil inlet pipe and an engine oil return pipe penetrate through the upper oil tank;
an oil chamber is arranged in the lower oil tank and connected to the partition plate; an engine oil supply pipe penetrates through the lower oil tank and the oil chamber, and an opening for supplying oil to flow between the oil chamber and the lower oil tank is arranged between the oil chamber and the partition plate; an oil discharge pipe is arranged in the lower oil tank in a penetrating way;
the one end and the baffle of oil pipe are connected, and the other end setting is just kept away from outside the grease chamber the baffle, oil pipe is used for the fuel feeding to flow into down the oil tank from last oil tank.
2. The aircraft engine fuel tank of claim 1 wherein said partition is further provided with a breather; and the top of the upper oil tank is also provided with a ventilation interface.
3. The aircraft engine fuel tank of claim 2 wherein the venting means is a tank vent pipe, the outlet of the tank vent pipe being disposed towards the vent interface.
4. The aircraft engine lubricating oil tank of claim 3, wherein the oil chamber capacity is determined according to the amount of lubricating oil required by the engine.
5. The aircraft engine lubricating oil tank of claim 4, wherein the partition plate is made of light alloy.
6. An aircraft engine lubricant tank according to claim 5, characterised in that the lubricant tank profile is determined in accordance with the spatial layout of the aircraft engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020714614.7U CN212535863U (en) | 2020-04-30 | 2020-04-30 | Aircraft engine lubricating oil tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020714614.7U CN212535863U (en) | 2020-04-30 | 2020-04-30 | Aircraft engine lubricating oil tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212535863U true CN212535863U (en) | 2021-02-12 |
Family
ID=74540650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020714614.7U Active CN212535863U (en) | 2020-04-30 | 2020-04-30 | Aircraft engine lubricating oil tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212535863U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113339140A (en) * | 2021-06-23 | 2021-09-03 | 中国航发沈阳发动机研究所 | Aircraft fuel tank |
-
2020
- 2020-04-30 CN CN202020714614.7U patent/CN212535863U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113339140A (en) * | 2021-06-23 | 2021-09-03 | 中国航发沈阳发动机研究所 | Aircraft fuel tank |
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