CN219638912U - Oil-gas separation device of aero-engine - Google Patents
Oil-gas separation device of aero-engine Download PDFInfo
- Publication number
- CN219638912U CN219638912U CN202320294371.XU CN202320294371U CN219638912U CN 219638912 U CN219638912 U CN 219638912U CN 202320294371 U CN202320294371 U CN 202320294371U CN 219638912 U CN219638912 U CN 219638912U
- Authority
- CN
- China
- Prior art keywords
- separator
- oil
- separator shell
- baffle
- gas separation
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Links
- 238000000926 separation method Methods 0.000 title claims abstract description 20
- 238000001816 cooling Methods 0.000 claims abstract description 20
- 239000002826 coolant Substances 0.000 claims abstract description 7
- 239000007788 liquid Substances 0.000 claims description 16
- 239000004020 conductor Substances 0.000 claims description 4
- 238000005260 corrosion Methods 0.000 claims description 4
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 claims description 3
- 239000010705 motor oil Substances 0.000 abstract description 19
- 230000017525 heat dissipation Effects 0.000 abstract description 8
- 239000003921 oil Substances 0.000 abstract description 8
- 238000010992 reflux Methods 0.000 abstract description 2
- 239000000110 cooling liquid Substances 0.000 description 5
- 230000000903 blocking effect Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Landscapes
- Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
Abstract
The utility model relates to the technical field of oil-gas separation devices, in particular to an oil-gas separation device of an aero-engine. The technical proposal comprises: including separator shell and protecgulum, protecgulum joint is provided with bottom baffle and upper baffle in the separator shell, leaves the clearance between bottom baffle both sides and the separator shell lateral wall, and a pair of upper baffle of bottom baffle top fixedly connected with, upper baffle position aligns with bottom baffle both sides clearance, and the coolant tank is installed to separator shell rear side upper end, and separator shell rear side below is provided with the cooling tank, installs the cooling tube between separator shell and the cooling tank. The circulating cooling structure is arranged in the separator shell, so that engine oil steam can be rapidly cooled to form oil drop reflux, and the cooling efficiency is improved by independent heat dissipation, so that the circulating cooling structure is suitable for oil-gas separation of large-scale equipment such as an aeroengine, and the normal use of the aeroengine is ensured.
Description
Technical Field
The utility model relates to the technical field of oil-gas separation devices, in particular to an oil-gas separation device of an aero-engine.
Background
The oil-gas separation device is a device for separating gas in liquid oil, wherein the oil-gas separation in an engine mainly separates incompletely combusted gas in an engine cylinder body from engine oil, and then the incompletely combusted gas is introduced into the engine cylinder body for re-combustion, so that the phenomenon that the engine oil enters the cylinder body and burns the engine oil can be effectively avoided.
However, when the traditional oil-gas separator works, the engine oil is mainly led into the separator shell as a whole, and is subjected to natural cooling and depressurization, so that the oil and gas are automatically separated, and the separated oil and gas are discharged from different discharging pipes.
Disclosure of Invention
The utility model aims to solve the problems in the background art and provides an aeroengine oil-gas separation device.
The technical scheme of the utility model is as follows: the utility model provides an aeroengine oil gas separation device, includes separator shell and protecgulum, protecgulum joint is in separator shell front side, be provided with bottom baffle and upper baffle in the separator shell, leave the clearance between bottom baffle both sides and the separator shell lateral wall, bottom baffle top fixedly connected with a pair of upper baffle, upper baffle position aligns with bottom baffle both sides clearance, the coolant tank is installed to separator shell rear side upper end, the annotate liquid hole has been seted up to coolant tank upper end, separator shell rear side below is provided with the cooling tank, install the cooling tube between separator shell and the cooling tank, the cooling tube both ends are located the coolant tank, the separator shell, lateral wall and the circulation pump is installed with the corresponding position of cooling tube.
Preferably, a pair of radiating holes are fixedly formed in the side wall of the radiating box, a fan is installed in each radiating hole, and a grid is installed on the outer side wall of the radiating box and at the position corresponding to each radiating hole.
Preferably, the air inlet pipe is arranged at the bottom of the separator shell, the position of the air inlet pipe is aligned with the center position of the bottom baffle, the exhaust pipe is arranged at the upper end of the separator shell, the liquid discharge pipe is arranged at the outer side of the bottom of the separator shell, and the inner wall of the bottom of the separator shell is inclined to one side of the liquid discharge pipe, so that bottom liquid can directly flow to the opening at the upper end of the liquid discharge pipe.
Preferably, the bottom of the bottom baffle is in a circular arc structure, and the width of the upper baffle is larger than the width of gaps at two sides of the bottom baffle.
Preferably, the size of the lower end of the separator housing is smaller than that of the upper end, and the upward flowing of the engine oil steam can achieve the purpose of reducing pressure due to the increase of the space, so that the engine oil steam can quickly form a liquid state.
Preferably, the radiating pipes are arranged in the separator shell and the radiating box in a serpentine manner, and are made of anti-corrosion heat-conducting materials, and some corrosive gas can be generated when gasoline burns, so that the radiating pipes made of the anti-corrosion heat-conducting materials are arranged in the separator shell and the radiating box.
Compared with the prior art, the utility model has the following beneficial technical effects: the novel circulation cooling structure is arranged in the separator shell, so that engine oil steam can be rapidly cooled, oil drop reflux is formed, cooling efficiency is improved through independent heat dissipation, the novel circulation cooling structure is suitable for oil-gas separation of large equipment such as an aeroengine, and normal use of the aeroengine is guaranteed.
Drawings
FIG. 1 is a schematic view of the internal structure of a separator housing according to the present utility model;
FIG. 2 is a schematic side view of the present utility model;
FIG. 3 is a schematic view of the internal structure of the heat dissipating box of the present utility model.
Reference numerals: 1. a separator housing; 11. an air inlet pipe; 12. a liquid discharge pipe; 13. a bottom baffle; 14. an upper baffle; 15. an exhaust pipe; 2. a front cover; 3. a cooling liquid tank; 31. a liquid injection hole; 4. a heat radiation box; 41. a heat radiation hole; 42. a blower; 43. a grille; 5. a heat radiating pipe; 6. and a circulation pump.
Detailed Description
The technical scheme of the utility model is further described below with reference to the attached drawings and specific embodiments.
Examples
As shown in fig. 1-3, the oil-gas separation device of the aeroengine provided by the utility model comprises a separator shell 1 and a front cover 2, wherein the front cover 2 is clamped on the front side of the separator shell 1, a bottom baffle 13 and an upper baffle 14 are arranged in the separator shell 1, gaps are reserved between two sides of the bottom baffle 13 and the side wall of the separator shell 1, a pair of upper baffles 14 are fixedly connected above the bottom baffle 13, the positions of the upper baffles 14 are aligned with the gaps on the two sides of the bottom baffle 13, a cooling liquid tank 3 is arranged at the upper end of the rear side of the separator shell 1, a liquid injection hole 31 is formed at the upper end of the cooling liquid tank 3, a heat dissipation tank 4 is arranged below the rear side of the separator shell 1, a heat dissipation pipe 5 is arranged between the separator shell 1 and the heat dissipation tank 4, two ends of the heat dissipation pipe 5 are positioned on the cooling liquid tank 3, and a circulating pump 6 is arranged on the side wall and at the position corresponding to the heat dissipation pipe 5.
A pair of radiating holes 41 are fixedly formed in the side wall of the radiating box 4, a fan 42 is arranged in the radiating holes 41, a grid 43 is arranged on the outer side wall of the radiating box 4 and corresponds to the radiating holes 41, an air inlet pipe 11 is arranged at the bottom of the separator housing 1, the position of the air inlet pipe is aligned with the center position of a bottom baffle 13, an exhaust pipe 15 is arranged at the upper end of the separator housing 1, a liquid discharge pipe 12 is arranged on the outer side of the bottom of the separator housing 1, the inner wall of the bottom of the separator housing 1 inclines towards the liquid discharge pipe 12, the bottom of the bottom baffle 13 is of an arc structure, the width of an upper baffle 14 is larger than the width of gaps on two sides of the bottom baffle 13, the lower end of the separator housing 1 is smaller than the upper end, radiating pipes 5 are arranged in the separator housing 1 and the radiating box 4 and are distributed in a serpentine mode, the radiating pipes 5 are made of anti-corrosion heat conducting materials, circulate in the radiating box 4 and absorb heat in the separator housing 1, and heat is discharged through the radiating holes 41 by the operation of the fan 42.
In this embodiment, first connect the external power source with the whole device, when engine oil steam enters into the inside of separator housing 1 through intake pipe 11, can receive the blocking of bottom baffle 13 at first, make the oil drop receive blocking, and drip to separator housing 1 bottom, wherein gas will be through the clearance upward movement of bottom baffle 13 both sides, the blocking of upper baffle 14 forms the oil drop again, drip to separator housing 1 bottom, finally the gaseous exhaust pipe 15 of unburnt in the engine oil steam is discharged, realize the purpose of oil-gas separation, in this process, because separator housing 1 lower extreme size is less than the upper end size, engine oil steam upward flow can be because the space increases, realize the purpose of depressurization, make the engine oil steam form liquid fast, simultaneously, can utilize the drive of circulating pump 6, make lubricating oil enter into separator housing 1 from cooling liquid tank 3, then get into the circulation flow in the radiator tank 4, absorb the heat in the separator housing 1, and utilize the work of fan 42, discharge heat through louvre 41, therefore realize the quick heat dissipation to separator housing 1, make the engine oil steam flow can be because of the size of upper end size is less than the upper end size, the purpose of reducing the engine oil drop is realized, the engine oil can be satisfied in the engine oil is fast, the engine oil can not drop is cooled down because the purpose of the engine oil is guaranteed to the high-gas separation is realized, the engine oil drop is not cooled down, the demand is avoided.
The above-described embodiments are merely a few preferred embodiments of the present utility model, and many alternative modifications and combinations of the above-described embodiments will be apparent to those skilled in the art based on the technical solutions of the present utility model and the related teachings of the above-described embodiments.
Claims (6)
1. The utility model provides an aeroengine oil gas separation device, includes separator shell (1) and protecgulum (2), protecgulum (2) joint is at separator shell (1) front side, its characterized in that: be provided with bottom baffle (13) and upper baffle (14) in separator shell (1), leave the clearance between bottom baffle (13) both sides and the separator shell (1) lateral wall, bottom baffle (13) top fixedly connected with a pair of upper baffle (14), upper baffle (14) position and bottom baffle (13) both sides clearance align, coolant tank (3) are installed to separator shell (1) rear side upper end, annotate liquid hole (31) have been seted up to coolant tank (3) upper end, separator shell (1) rear side below is provided with cooling tank (4), install cooling tube (5) between separator shell (1) and cooling tank (4), cooling tube (5) both ends are located coolant tank (3), separator shell (1), lateral wall and corresponding position with cooling tube (5) install circulating pump (6).
2. The oil-gas separation device of the aeroengine according to claim 1, wherein a pair of radiating holes (41) are fixedly formed in the side wall of the radiating box (4), a fan (42) is installed in the radiating holes (41), and a grid (43) is installed on the outer side wall of the radiating box (4) and at a position corresponding to the radiating holes (41).
3. The aeroengine oil-gas separation device according to claim 1, wherein an air inlet pipe (11) is arranged at the bottom of the separator housing (1) and aligned with the center of a bottom baffle (13), an exhaust pipe (15) is arranged at the upper end of the separator housing (1), a liquid discharge pipe (12) is arranged at the outer side of the bottom of the separator housing (1), and the inner wall of the bottom of the separator housing (1) is inclined to one side of the liquid discharge pipe (12).
4. The aeroengine oil-gas separation device according to claim 1, wherein the bottom of the bottom baffle (13) is of a circular arc structure, and the width of the upper baffle (14) is larger than the gap width of two sides of the bottom baffle (13).
5. An aeroengine oil and gas separator device according to claim 1, wherein the separator housing (1) has a lower end dimension smaller than an upper end dimension.
6. The oil-gas separation device of the aeroengine according to claim 1, wherein the radiating pipes (5) are arranged in the separator shell (1) and the radiating box (4) in a serpentine distribution, and the radiating pipes are made of anti-corrosion heat-conducting materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320294371.XU CN219638912U (en) | 2023-02-23 | 2023-02-23 | Oil-gas separation device of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320294371.XU CN219638912U (en) | 2023-02-23 | 2023-02-23 | Oil-gas separation device of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219638912U true CN219638912U (en) | 2023-09-05 |
Family
ID=87807688
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320294371.XU Active CN219638912U (en) | 2023-02-23 | 2023-02-23 | Oil-gas separation device of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219638912U (en) |
-
2023
- 2023-02-23 CN CN202320294371.XU patent/CN219638912U/en active Active
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| GR01 | Patent grant |