CN219865183U - Lubricating system for aeroengine - Google Patents
Lubricating system for aeroengine Download PDFInfo
- Publication number
- CN219865183U CN219865183U CN202321764295.0U CN202321764295U CN219865183U CN 219865183 U CN219865183 U CN 219865183U CN 202321764295 U CN202321764295 U CN 202321764295U CN 219865183 U CN219865183 U CN 219865183U
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- CN
- China
- Prior art keywords
- oil
- heating
- control module
- module
- lubricating
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 230000001050 lubricating effect Effects 0.000 title claims abstract description 12
- 238000010438 heat treatment Methods 0.000 claims abstract description 63
- 235000014676 Phragmites communis Nutrition 0.000 claims abstract description 14
- 239000003921 oil Substances 0.000 claims description 67
- 239000010687 lubricating oil Substances 0.000 claims description 31
- 238000005461 lubrication Methods 0.000 claims description 9
- 238000001514 detection method Methods 0.000 claims description 6
- 239000003595 mist Substances 0.000 description 4
- 230000005484 gravity Effects 0.000 description 2
- 239000003637 basic solution Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Landscapes
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The utility model discloses a lubricating system for an aeroengine, which comprises an oil tank, an oil pump and a reed valve, wherein the oil tank is communicated with the oil pump through an oil pipe, the oil outlet end of the oil pump is communicated with the reed valve, and a heating part is arranged on the oil pipe between the oil tank and the oil pump. The lubricating system of the aero-engine solves the problem that the lubricating system of the aero-engine in the prior art can not ensure that the aero-engine still keeps working normally when the limit flying height is increased to 9 km.
Description
Technical Field
The utility model relates to an aeroengine, in particular to a lubrication system for the aeroengine.
Background
Existing aircraft engines include lubrication systems to lubricate various components of the aircraft engine to enable proper operation. The lubricating system of the existing aeroengine comprises an oil tank, an electronic oil pump, an oil nozzle and an auxiliary oil pipe, wherein the oil in the oil tank is sent into an engine air inlet channel through the oil nozzle by the electronic oil pump, then the oil is scattered into oil mist through the opening and closing actions of a high-frequency reed valve, and finally the oil mist is mixed with air from the air inlet channel to form an oil-gas mixture filled in a crankcase, so that all parts in the crankcase are lubricated.
In practical use, it was found that when the limit flying height of the aero-engine is increased to 9 km, the working performance of the aero-engine is drastically reduced, which easily causes a great flying risk.
Disclosure of Invention
The utility model aims to provide a lubricating system for an aeroengine, which solves the problem that the lubricating system of the aeroengine in the prior art can not ensure that the aeroengine still keeps working normally when the limit flying height is increased to 9 km.
In order to achieve the above object, the basic solution of the present utility model provides a lubrication system for an aeroengine, including a lubricating oil tank, an oil pump and a reed valve, wherein the lubricating oil tank is communicated with the oil pump through an oil pipe, and an oil outlet end of the oil pump is communicated with the reed valve, and the lubrication system is characterized in that: and a heating component is arranged on the oil pipe between the lubricating oil tank and the oil pump.
The beneficial effect of this basic scheme lies in: the heating component is utilized to heat the lubricating oil in the oil pipe between the lubricating oil tank and the oil pump, so that the fluidity of the lubricating oil is enhanced, the oil pump can pump enough lubricating oil to the reed valve to form oil mist, and further, the problem that the working performance is obviously reduced easily when the limit flying height of the aeroengine is increased to 9 km is avoided, and the flying risk is reduced.
Further, the heating component comprises a heating module, a temperature acquisition module and a heating control module, wherein the temperature acquisition module acquires an oil temperature detection value signal in an oil pipe and sends the oil temperature detection value signal to the heating control module, and when the heating control module compares that the oil temperature detection value is smaller than a preset minimum value of the oil temperature, the heating control module controls the heating module to heat; when the heating control module compares that the detected value of the lubricating oil temperature is larger than the preset maximum value of the lubricating oil temperature, the heating control module controls the heating module to stop heating. By adopting the arrangement, the automatic control of the heating lubricating oil is realized through the heating module, the temperature acquisition module and the heating control module without manual control, so that the use convenience of the lubricating system is improved.
Further, the oil tank is located above the oil pump. By adopting the arrangement, the lubricating oil in the lubricating oil tank can flow towards the oil pump automatically under the action of gravity, so that the structure is simplified, and the condition that the weight of the engine is obviously increased is avoided.
Drawings
FIG. 1 is a schematic view of an embodiment of a lubrication system for an aircraft engine according to the present utility model.
Detailed Description
The following is a further detailed description of the embodiments:
reference numerals in the drawings of the specification include: the device comprises a lubricating oil tank 1, a heating component 2, a heating module 21, a heating control module 22, a temperature acquisition module 23, an oil pump 3, a reed valve 4, a crankcase 5 and a crankshaft 6.
An example is substantially as shown in figure 1: a lubrication system for an aeroengine comprises an oil tank 1, an oil pump 3 and a reed valve 4, wherein the oil tank 1 is communicated with the oil pump 3 through an oil pipe, and an oil outlet end of the oil pump 3 is communicated with the reed valve 4. In this embodiment, the oil tank 1 is located above the oil pump 3, and the heating member 2 is provided on the oil pipe between the oil tank 1 and the oil pump 3. In this embodiment, the heating component 2 includes a heating module 21, a temperature acquisition module 23 and a heating control module 22, where the temperature acquisition module 23 acquires a signal of a detected value of the oil temperature in the oil pipe and sends the signal to the heating control module 22, and when the heating control module 22 compares that the detected value of the oil temperature is less than a preset minimum value of the oil temperature, the heating control module 22 controls the heating module 21 to heat; when the heating control module 22 compares that the detected value of the lubricating oil temperature is greater than the preset maximum value of the lubricating oil temperature, the heating control module 22 controls the heating module 21 to stop heating. In this embodiment, the heating module 21 is preferably a resistance wire; the temperature acquisition module 23 is an existing temperature sensor. In this embodiment, the preset minimum value of the lubricating oil temperature is 0 ℃, and the preset maximum value of the lubricating oil temperature is 80 ℃; when the temperature acquisition module 23 detects that the temperature of the lubricating oil in the oil pipe is lower than 0 ℃, the heating control module 22 electrifies the heating module 21, so that the heating module 21 starts to heat the lubricating oil; when the temperature acquisition module 23 detects that the temperature of the lubricating oil in the oil pipe is higher than 80 ℃, the heating control module 22 controls the heating module 21 to be powered off, so that the heating module 21 stops heating the lubricating oil. In this embodiment, the power of the heating module 21 is 7W; the lubricating oil is used in the environment with the absolute pressure of 30KPa at the temperature of minus 50 ℃ and can flow by self weight.
The specific implementation process is as follows: the reed valve 4 is arranged on the crank case 5, the lubricating oil of the lubricating oil tank 1 flows towards the oil pump 3 under the action of gravity, and when the heating control module 22 of the heating component 2 detects that the temperature of the lubricating oil is lower than 0 ℃ through the temperature acquisition module 23, the heating control module 22 controls the heating module 21 to perform heating operation, so that the temperature of the lubricating oil is increased; when the heating control module 22 detects that the temperature of the lubricating oil is higher than 80 ℃ through the temperature acquisition module 23, the heating control module 22 controls the heating module 21 to stop heating. The lubricating oil enters the oil pump 3 through the heating part 2, is pumped out of the reed valve 4 from the oil pump 3, enters the crankcase 5, is dispersed into oil mist through the opening and closing of the reed valve 4 and the rotation action of the crankshaft 6, and lubricates each friction pair. After the aero-engine adopts the lubricating system, the limit flying height of the aero-engine is increased to 9000 meters, and the aero-engine can still normally run, so that the safety of an airplane is ensured.
The foregoing is merely exemplary embodiments of the present utility model, and specific structures and features that are well known in the art are not described in detail herein. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the structure of the present utility model, and these should also be considered as the scope of the present utility model, which does not affect the effect of the implementation of the present utility model and the utility of the patent.
Claims (3)
1. A lubrication system for aeroengine, includes lubricating tank, oil pump and reed valve, the lubricating tank passes through oil pipe and oil pump intercommunication, the play oil end and the reed valve intercommunication of oil pump, its characterized in that: and a heating component is arranged on the oil pipe between the lubricating oil tank and the oil pump.
2. A lubrication system for an aircraft engine according to claim 1, wherein: the heating component comprises a heating module, a temperature acquisition module and a heating control module, wherein the temperature acquisition module acquires an oil temperature detection value signal in an oil pipe and sends the oil temperature detection value signal to the heating control module, and when the heating control module compares that the oil temperature detection value is smaller than a preset minimum value of the oil temperature, the heating control module controls the heating module to heat; when the heating control module compares that the detected value of the lubricating oil temperature is larger than the preset maximum value of the lubricating oil temperature, the heating control module controls the heating module to stop heating.
3. A lubrication system for an aircraft engine according to claim 2, wherein: the oil tank is located above the oil pump.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321764295.0U CN219865183U (en) | 2023-07-06 | 2023-07-06 | Lubricating system for aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321764295.0U CN219865183U (en) | 2023-07-06 | 2023-07-06 | Lubricating system for aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219865183U true CN219865183U (en) | 2023-10-20 |
Family
ID=88323467
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321764295.0U Active CN219865183U (en) | 2023-07-06 | 2023-07-06 | Lubricating system for aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219865183U (en) |
-
2023
- 2023-07-06 CN CN202321764295.0U patent/CN219865183U/en active Active
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