CN108361111A - A kind of gas oil separation structure - Google Patents
A kind of gas oil separation structure Download PDFInfo
- Publication number
- CN108361111A CN108361111A CN201810184750.7A CN201810184750A CN108361111A CN 108361111 A CN108361111 A CN 108361111A CN 201810184750 A CN201810184750 A CN 201810184750A CN 108361111 A CN108361111 A CN 108361111A
- Authority
- CN
- China
- Prior art keywords
- oil
- guide sleeve
- turbine wheel
- wheel shaft
- gas
- Prior art date
- 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.)
- Pending
Links
- 238000000926 separation method Methods 0.000 title claims abstract description 21
- 238000010276 construction Methods 0.000 claims abstract description 7
- 239000003921 oil Substances 0.000 description 47
- 239000010687 lubricating oil Substances 0.000 description 7
- 230000005540 biological transmission Effects 0.000 description 3
- 238000005461 lubrication Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
Abstract
The present invention relates to a kind of gas oil separation structures, including engine spindle, oil gas guide sleeve, engine spindle is hollow-core construction, it is formed by connecting by compressorshaft and turbine wheel shaft, equipped with the oil gas guide sleeve for extending radially through main shaft on the compressorshaft positioned at fore bearing chamber, oil gas guide sleeve is being provided with venthole positioned at main-shaft core position, turbine wheel shaft is radially provided with 2 the first uniformly distributed oil circuit holes, it is additionally provided with internal diameter on the inner wall near exhaust pipe in turbine wheel shaft and is more than the annular oil trap of inner wall surface, and is provided with the second oil circuit hole on oil trap.The present invention utilizes existing high-speed rotating engine spindle structure, does not need individual separating mechanism, while realizing Oil-gas Separation, can not only subtract low power consumption, the air of separation is burnt up through exhaust section, reduces the pollution to extraneous atmospheric environment.
Description
Technical field
The present invention relates to a kind of gas oil separation structures.
Background technology
Because of the rotation of the components such as bearing, gear and oil lubrication splash when aero-engine works, cause to exist in bearing bore
A large amount of mist of oils blend to form oil gas with bearing chamber air, and oil gas is unfavorable for lubrication and the cooling of system, it is therefore desirable to by oil gas
Discharge.If the oil gas in bearing bore, which is expelled directly out, will cause a large amount of consumption of lubricating oil, and pollute environment, therefore must will be in bearing bore
The lubricating oil contained in air is separated, to reduce lube use rate.Generally use centrifuge formula ventilator realizes oil gas at present
Separation, centrifuge formula ventilator are that the separation of liquid phase oil droplet in oil gas is carried out using centrifugal principle.Structure is mainly by rotor, shell
And the compositions such as bearing support, it is a complete attachment, is driven by special transmission mechanism.Rotor is to realize Oil-gas Separation
Core carries the impeller of 6~8 disc, and center is the central shaft of supporting rotor, and venthole is typically recessed on axis.It is mingled with sliding
After the oil gas of the small oil droplet of oil enters centrifuge formula ventilator, wheel rotation keeps air outwardly radial by one with the small oil droplet of lubricating oil
Power, i.e. centrifugal force.Since lubricating oil is different from the density of air, lubricating oil is thrown to inner walls by centrifugal force, by wall
Aperture flows back to casing inner cavity or bearing bore, and the gas after being detached is discharged from centre bore, to realize the function of Oil-gas Separation.It is existing
Some gas oil separation structures is complicated, need to design special transmission mechanism to drive, and the power of consumption of engine carries out when work
Oil-gas Separation reduces the output power of engine.
Invention content
The object of the present invention is to provide a kind of gas oil separation structures, while realizing Oil-gas Separation, need not be special
Transmission mechanism drives, simple in structure, and reduces the power consumption of engine.
The technical scheme is that the gas oil separation structure includes engine spindle, oil gas guide sleeve, mobilize owner
Axis is hollow-core construction, is formed by connecting by compressorshaft and turbine wheel shaft, is passed through equipped with radial on the compressorshaft positioned at fore bearing chamber
The oil gas guide sleeve of main shaft is worn, oil gas guide sleeve is being provided with venthole positioned at main-shaft core position, and turbine wheel shaft is radially provided with 2 uniformly
The first oil circuit hole, turbine wheel shaft be additionally provided on the inner wall near exhaust pipe internal diameter be more than inner wall surface annular oil-collecting
Slot, and the second oil circuit hole is provided on oil trap, the first oil circuit hole is mutually in 90 ° along engine spindle axis with the second oil circuit hole
The hollow-core construction at angle, the engine spindle extends to exhaust pipe.
In the use of the present invention, since fore bearing is to use pressure seal, the air pressure in bearing bore is more than ambient pressure, because
The oil gas in bearing bore enters compressor spindle axis under the action of bearing bore chamber pressure by oil gas guide sleeve before this.Into
The oil gas of spindle axis is rotated with main axis, and enters the turbine wheel shaft axle center being connected with compressor main shaft.Oil gas is rotating
Oil-gas Separation is carried out due to centrifugal force in the process, small lubricating oil oil droplet hits the condensed on inner walls in spindle axis into oil droplet.Oil
After pearl is expelled directly out from the first oil circuit hole or is collected on oil trap, it is discharged by the second oil circuit hole, the lubricating oil of discharge can be again
It utilizes, and the air separated is discharged into air after entering exhaust section burn-up by exhaust pipe along turbine wheel shaft.The present invention is using now
The high-speed rotating engine spindle structure having, does not need individual separating mechanism, while realizing Oil-gas Separation, not only may be used
To subtract low power consumption, the air of separation is burnt up through exhaust section, reduces the pollution to extraneous atmospheric environment.
Description of the drawings
Fig. 1 gas oil separation structure schematic diagrames of the present invention.
Specific implementation mode
As shown, gas oil separation structure includes engine spindle, oil gas guide sleeve 7, engine spindle is hollow-core construction, by
Compressorshaft 1 and turbine wheel shaft 2 are formed by connecting, equipped with the oil gas for extending radially through main shaft on the compressorshaft 1 positioned at fore bearing chamber
Guide sleeve 7, oil gas guide sleeve 7 are being provided with venthole positioned at main-shaft core position, and turbine wheel shaft 2 is radially provided with 2 the first uniformly distributed oil
Road hole 3 is additionally provided with the annular oil trap 4 that internal diameter is more than inner wall surface in turbine wheel shaft 2 on the inner wall near exhaust pipe 6, and
The second oil circuit hole 5 is provided on oil trap, the first oil circuit hole 3 is mutually in 90 ° along engine spindle axis with the second oil circuit hole 5
The hollow-core construction at angle, the engine spindle extends to exhaust pipe 6.
Claims (1)
1. a kind of gas oil separation structure, which is characterized in that the structure includes engine spindle, oil gas guide sleeve (7), engine
Main shaft is hollow-core construction, is formed by connecting by compressorshaft (1) and turbine wheel shaft (2), on the compressorshaft of fore bearing chamber (1)
Equipped with the oil gas guide sleeve (7) for extending radially through main shaft, oil gas guide sleeve (7) is being provided with venthole, turbine wheel shaft positioned at main-shaft core position
(2) be radially provided with two the first uniformly distributed oil circuit holes (3), also set on the inner wall of exhaust pipe (6) nearby in turbine wheel shaft (2)
There is internal diameter to be more than the annular oil trap (4) of inner wall surface, and is provided with the second oil circuit hole (5), the first oil circuit hole on oil trap
(3) with the second oil circuit hole (5) along engine spindle axis mutually at an angle of 90, the hollow-core construction of the engine spindle extends to
Exhaust pipe (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810184750.7A CN108361111A (en) | 2018-03-06 | 2018-03-06 | A kind of gas oil separation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810184750.7A CN108361111A (en) | 2018-03-06 | 2018-03-06 | A kind of gas oil separation structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108361111A true CN108361111A (en) | 2018-08-03 |
Family
ID=63003426
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810184750.7A Pending CN108361111A (en) | 2018-03-06 | 2018-03-06 | A kind of gas oil separation structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108361111A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115013157A (en) * | 2022-06-29 | 2022-09-06 | 中国航发湖南动力机械研究所 | Centrifugal ventilation structure of double-rotor aircraft engine gas turbine |
| CN117432782A (en) * | 2023-12-19 | 2024-01-23 | 中国核动力研究设计院 | Protective device for supercritical carbon dioxide power generation system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4755103A (en) * | 1986-02-21 | 1988-07-05 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Flow machine with feed arrangement for lubricants |
| US20050211093A1 (en) * | 2004-03-23 | 2005-09-29 | Pratt & Whitney Canada Corp. | Air/oil separation system and method |
| US20140144121A1 (en) * | 2012-11-28 | 2014-05-29 | Pratt & Whitney Canada Corp. | Gas turbine engine with bearing oil leak recuperation system |
| CN104989531A (en) * | 2015-06-23 | 2015-10-21 | 中国航空动力机械研究所 | Ventilation system for bearing cavities |
| CN105863847A (en) * | 2016-04-13 | 2016-08-17 | 中国科学院工程热物理研究所 | Bearing chamber axle center ventilating structure and gas turbine engine with same |
| CN106837553A (en) * | 2017-01-23 | 2017-06-13 | 中国科学院工程热物理研究所 | A kind of engine bearing chamber Oil-gas Separation and multiple bearing chamber axle center aeration structure |
| CN208073622U (en) * | 2018-03-06 | 2018-11-09 | 中国航发哈尔滨东安发动机有限公司 | A kind of gas oil separation structure |
-
2018
- 2018-03-06 CN CN201810184750.7A patent/CN108361111A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4755103A (en) * | 1986-02-21 | 1988-07-05 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Flow machine with feed arrangement for lubricants |
| US20050211093A1 (en) * | 2004-03-23 | 2005-09-29 | Pratt & Whitney Canada Corp. | Air/oil separation system and method |
| US20140144121A1 (en) * | 2012-11-28 | 2014-05-29 | Pratt & Whitney Canada Corp. | Gas turbine engine with bearing oil leak recuperation system |
| CN104989531A (en) * | 2015-06-23 | 2015-10-21 | 中国航空动力机械研究所 | Ventilation system for bearing cavities |
| CN105863847A (en) * | 2016-04-13 | 2016-08-17 | 中国科学院工程热物理研究所 | Bearing chamber axle center ventilating structure and gas turbine engine with same |
| CN106837553A (en) * | 2017-01-23 | 2017-06-13 | 中国科学院工程热物理研究所 | A kind of engine bearing chamber Oil-gas Separation and multiple bearing chamber axle center aeration structure |
| CN208073622U (en) * | 2018-03-06 | 2018-11-09 | 中国航发哈尔滨东安发动机有限公司 | A kind of gas oil separation structure |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115013157A (en) * | 2022-06-29 | 2022-09-06 | 中国航发湖南动力机械研究所 | Centrifugal ventilation structure of double-rotor aircraft engine gas turbine |
| CN117432782A (en) * | 2023-12-19 | 2024-01-23 | 中国核动力研究设计院 | Protective device for supercritical carbon dioxide power generation system |
| CN117432782B (en) * | 2023-12-19 | 2024-03-19 | 中国核动力研究设计院 | Protective device for supercritical carbon dioxide power generation system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2688790C (en) | Combined pumping and separating machine for the oil circuit of a turbojet | |
| US6893478B2 (en) | Air/oil separator | |
| CA2809985C (en) | Deoiler seal | |
| EP3865735B1 (en) | Near zero velocity lubrication system for a turbine engine | |
| CN105673825B (en) | Has the gear-box of Packed attachment blow vent | |
| US10253692B2 (en) | Aircraft engine having a device for separating oil | |
| CN208073622U (en) | A kind of gas oil separation structure | |
| RU2010151851A (en) | LUBRICATING ROTATING SHAFT | |
| CN110500159A (en) | Active gs-oil separator | |
| CN108087121B (en) | A kind of aero-engine eccentric contract | |
| CN108361111A (en) | A kind of gas oil separation structure | |
| JP2008232143A (en) | De-oiler system for aeroengine | |
| CN111330360B (en) | Air/oil mixture separation device | |
| KR840008474A (en) | Centrifugal Lube Pump for Exhaust Turbocharger | |
| RU2558719C1 (en) | Driving centrifugal breather with axial-flow impeller | |
| CN104889423B (en) | A kind of machine tool chief axis for preventing hard collision from impacting | |
| CN109072713A (en) | Turbojet including simplified bearing lubrication unit | |
| CN104141775B (en) | For deaerator and the aeroengine of power plant gear-box | |
| RU2551454C1 (en) | Gas turbine engine rotary breather | |
| CN106621578A (en) | Axial admission centrifugal ventilator | |
| CN103291415B (en) | Oil-gas Separation gear and there is the motor of this Oil-gas Separation gear | |
| CN210686085U (en) | Active oil-gas separator with rotating speed measuring device | |
| CN210660709U (en) | Fresh water pump for engine | |
| RU2724059C1 (en) | Centrifugal drive breather of gas turbine engine | |
| CN204591489U (en) | A kind of oil mist separator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |