CN103982300A - Centrifugal separation device for aero-engine - Google Patents
Centrifugal separation device for aero-engine Download PDFInfo
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- CN103982300A CN103982300A CN201410225151.7A CN201410225151A CN103982300A CN 103982300 A CN103982300 A CN 103982300A CN 201410225151 A CN201410225151 A CN 201410225151A CN 103982300 A CN103982300 A CN 103982300A
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- housing
- porous metals
- centrifugal separator
- rotatingshaft
- seal ring
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- 238000000926 separation method Methods 0.000 title abstract description 20
- 229910052751 metal Inorganic materials 0.000 claims abstract description 83
- 239000002184 metal Substances 0.000 claims abstract description 83
- 150000002739 metals Chemical class 0.000 claims description 87
- 238000010943 off-gassing Methods 0.000 claims description 16
- 238000013022 venting Methods 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 13
- 230000015572 biosynthetic process Effects 0.000 claims description 6
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000012545 processing Methods 0.000 abstract description 2
- 239000010687 lubricating oil Substances 0.000 description 25
- 239000000203 mixture Substances 0.000 description 18
- 239000003921 oil Substances 0.000 description 17
- 230000000694 effects Effects 0.000 description 14
- 239000000463 material Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 239000000314 lubricant Substances 0.000 description 2
- 238000005461 lubrication Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 206010020651 Hyperkinesia Diseases 0.000 description 1
- 208000000269 Hyperkinesis Diseases 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- OJIJEKBXJYRIBZ-UHFFFAOYSA-N cadmium nickel Chemical compound [Ni].[Cd] OJIJEKBXJYRIBZ-UHFFFAOYSA-N 0.000 description 1
- 210000002421 cell wall Anatomy 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000001351 cycling effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910001120 nichrome Inorganic materials 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Landscapes
- Separating Particles In Gases By Inertia (AREA)
- Centrifugal Separators (AREA)
- Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
Abstract
The invention provides a centrifugal separation device for an aero-engine. The centrifugal separation device comprises a rotating shaft and a centrifugal separator sleeving the outer wall of the rotating shaft, wherein the centrifugal separator comprises a shell sleeving the rotating shaft and multiporous metal; the multiporous metal fills the shell; a plurality of oil return holes are formed in one end face of the shell along the circumferential direction. Compared with an amplitude-plate blade type centrifugal separation device, the centrifugal separation device disclosed by the invention is simple and compact in structure, convenient to assemble and disassemble, light in weight, low in processing and maintenance cost and high in oil-gas separation efficiency.
Description
Technical field
The present invention relates to aeroengine field, especially, relate to a kind of aeroengine centrifugal separator.
Background technique
Aero-Engine Lubrication System is the important component part of aviation turbo oar engine mechanical system, is responsible for supplying with aviation each part of turbo oar engine required lubricating oil, determining motor can be safely, work reliably.Along with modern aeroengine towards high temperature, at a high speed, high power to weight ratio development, the design of aeroengine lubrication system is had higher requirement.
Centrifugal separator is the important component part of oil system, and it is assemblied in accessory drive gearbox, mainly utilizes centrifugal field that the lubricant oil in transmission system is separated with hot gas.Lubricant oil after separating is reclaimed to cycling and reutilization, thereby ensure that transmission system can turn round for a long time under normal lubricating status.Once and centrifugal separator inefficiency or break down will cause oil system cisco unity malfunction, until whole power failure, consequence is extremely serious.At present, conventional is former blade type centrifugal separator.
Former blade type centrifugal separator gas and oil separation effect is low, and motor operation stability is low, and lube use rate is large, and the required lubricating oil amount of carrying of identical motor in cruising time is larger, and the volume of fuel tank also needs corresponding increase.Certainly will increase the weight of motor, thereby reduce the power to weight ratio of motor.
Summary of the invention
The object of the invention is to provide a kind of aeroengine centrifugal separator, large to solve prior art center plate blade type centrifugal separator lube use rate, is unsuitable for the technical problem that aeroengine is used.
For achieving the above object, according to the invention provides a kind of aeroengine centrifugal separator, comprise rotatingshaft and be sheathed on the centrifugal separator on rotatingshaft outer wall, centrifugal separator comprises the housing and the porous metals that are sheathed on rotatingshaft, and porous metals are filled in housing; On one end face of housing, along it, multiple spill ports are circumferentially set.
Further, centrifugal separator also comprises outgassing groove, and outgassing groove is arranged on the inwall of housing; Rotatingshaft inside arranges venting cavity, and sealing one end, venting cavity one end is communicated with atmosphere, and housing is connected with venting cavity by outgassing groove.
Further, housing comprises the first housing, the second housing, and one end of the first housing is uncovered, and another opposite end is sealing, and one end of the second housing is uncovered, and another opposite end is sealing; The uncovered outer wall of the first housing aligns affixed with the uncovered outer wall of the second housing, the first housing and the second housing are spliced to form housing; Spill port is arranged on the Closed End of the second housing.
Further, the center of the first housing axially forms the first mounting hole along it; The center of the second housing axially forms the second mounting hole along it; The extending end shape of the extending end of the first mounting hole and the second mounting hole surrounds outgassing groove.
Further, also comprise: the first seal ring and the second seal ring, the sidewall of the Closed End of the first housing is close to rotatingshaft and is extended axially formation seal ring along it, and the first seal ring is installed on seal ring inwall; The second seal ring is installed on the sidewall of the second housing and is close to rotatingshaft; The first seal ring and the second seal ring seal the first housing, the second housing and rotatingshaft.
Further, also comprise: driving gear, driving gear is shaped in one end of rotatingshaft, and driving gear extends axially formation mounting platform near one end of centrifugal separator along it, and centrifugal separator is sheathed to be installed on mounting platform.
Further, porous metals thickness is 42.4～22.4mm.
Further, porous metals thickness is 36.4～28.4mm.
Further, porous metals thickness is 32.4mm.
Further, the external diameter of porous metals is 87～87.5mm, and internal diameter is 46.5～47mm.
Further, spill port number is 20, and each spill port diameter is 93.55mm.
Further, porous metals comprise the first porous metals and the second porous metals; Housing comprises the first housing, the second housing, and one end of the first housing is uncovered, and another opposite end is sealing, and one end of the second housing is uncovered, and another opposite end is sealing; The uncovered outer wall of the first housing aligns affixed with the uncovered outer wall of the second housing, the first housing and the second housing are spliced to form housing; The first porous metals are positioned in the first housing, and the second porous metals are positioned in the second housing, and the first porous metals and the second porous metals are individually fixed in the first housing and the second housing by pin.
Further, the first porous metals and the second porous metals thickness equate.
The present invention has following beneficial effect:
Aeroengine provided by the invention is formed at the centrifugal separator on rotatingshaft with centrifugal separator by employing, make the gas mixture that enters centrifugal separator under the effect of centrifugal force, separate through porous metals, gas mixture is separated in porous metals, thereby improve lubricating oil recycling rate, reduce that motor is required carries lubricating oil amount, thereby reduced the gross weight of motor.Centrifugal separator provided by the invention is simple and compact for structure compared with former blade type centrifugal separator, mounting or dismounting are convenient, lightweight, processing maintenance cost is low, oil-gas separation efficiency is high.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is that the master of the preferred embodiment of the present invention looks cross-sectional schematic;
Fig. 2 is the schematic side view of the preferred embodiment of the present invention;
Fig. 3 is the metallographic schematic diagram of the preferred embodiment of the present invention.
Marginal data:
100, rotatingshaft; 110, driving gear; 120, venting cavity; 200, centrifugal separator; 210, the first housing; 211, the first mounting hole; 222, the second mounting hole; 215, seal ring; 220, the second housing; 221, spill port; 230, pin; 240, the first porous metals; 250, the second porous metals; 260, outgassing groove; 300, the first seal ring; 310, the second seal ring.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
The present invention is by using porous metals effect gas mixture parting material, thereby the lubricating oil in the gas mixture that engine interior is produced separates, and makes lubricating oil can again enter engine interior, the effect of performance lubricating oil.
Embodiment 1
Referring to Fig. 1, the invention provides a kind of aeroengine centrifugal separator, this device comprises rotatingshaft 100, is set in the centrifugal separator 200 on rotatingshaft 100 outer walls.The second end of rotatingshaft 100 arranges driving gear 110 near housing.By driving gear 110, rotatingshaft 100 is rotated.Rotatingshaft 100 rotates and drives centrifugal separator 200 to rotate, the inner centrifugal field that forms of centrifugal separator 200.
Referring to Fig. 1 and Fig. 2, centrifugal separator 200 comprises the first housing 210, the second housing 220, Oil-gas Separation material and pin 230.One end sealing of the first housing 210.One end of the first housing 210 is uncovered.The inside of the first housing 210 forms cavity.The center of the first housing 210 is axially arranged with the first mounting hole 211 along it.One end of the second housing 220 is uncovered.The opposite end of the second housing 220 is closed end.The inside of the second housing 220 forms cavity.The center of the second housing 220 is axially arranged with the second mounting hole 222 along it.
The open-mouth end of the open-mouth end of the first housing 210 and the second housing 220 joins.The open-mouth end outer wall alignment Joint of the first housing 210 and the second housing 220.The second mounting hole 222 aligns with the first mounting hole 211.The first side wall of the first mounting hole 211 is near the open-mouth end of the first housing 210 interval setting with it.The second sidewall of the second mounting hole 222 is near the open-mouth end of the second housing 220 interval setting with it.The middle part of the installation passage that the first side wall and the second sidewall surround at the first mounting hole 221 and the second mounting hole 222, as the cell wall of outgassing groove 260, surrounds outgassing groove 260.
The Closed End of the second housing 220 is provided with multiple spill ports 221.Spill port 221 is for to be circumferentially distributed on the second housing 220 along the second housing 220.Spill port 221 is shoulder hole.Can effectively prevent separate after lubricating oil again get back in centrifugal separator 200.
After the first housing 210 and the second housing 220 splicings, form circular housing.The first housing 210 and the second housing 220 are overall by affixed the outer wall splice ends of the first housing 210 and the second housing 220 formation by welding, as housing.Outgassing groove 260 is formed on the inwall of housing.Housing extends axially on the mounting platform of formation along it by the first mounting hole 211 and sheathed driving gear 110 rear ends that are installed on of the second mounting hole 222.Venting cavity 120 is set in the first end of rotatingshaft 100.Venting cavity 120 one end sealing the other ends are connected with atmosphere.Housing is sheathed on the rotatingshaft 100 outside venting cavity 120.On the sidewall of venting cavity 120, through hole is set.On the mounting platform of driving gear 110 rear ends, corresponding position arranges the second through hole.Venting cavity 120 in the second through hole connection rotatingshaft 100 and the outgassing groove 260 in inner walls.Enclosure interior is connected by outgassing groove 260 with atmosphere environment.
The inwall of the first housing 210 first end faces is close to rotatingshaft 100 and is extended to form vertically seal ring 215.The inwall of seal ring 215 is close to the first seal ring 300 is set.The inwall of the second housing 220 is circumferentially installed the second seal ring 310 along it.The first seal ring 300 and the second seal ring 310, by the internal face of housing and oil system sealing, can not enter in oil system the air that enters venting cavity 120 from outgassing groove 260 again.Prevent that not separated gas mixture from appearing oil system from housing and rotatingshaft 100 joints, cause lubricating oil to be revealed and loss reduction lubricating oil recovery utilization rate.
Enclosure interior is filled Oil-gas Separation material successively.Oil-gas Separation material is porous metals.Porous metals can be preferably the porous metals that nichrome is made for conventional porous metals, and the metallurgical microscope result figure of this material as shown in Figure 3.Referring to Fig. 3, owing to existing a large amount of apertures to be greater than the hole of 500 μ m in porous metals.And these holes are interlaced with each other, stacked, after hole, all can there is the edge of other holes.The gas mixture that enters these porous metals is outwards moved from centrifugal separator 200 center under the effect of centrifugal force.In hyperkinesia, oil droplet clashes into staggered wire in porous metals, and movement velocity declines, and gas continues to keep high-speed motion.Thereby make oil droplet separated from the gas.Porous metals have that specific surface area is large, hole structure is controlled and the performance such as good permeability.Lubricating oil can be stored in the spongy porosity of porous metals, under the effect of centrifugal force, promote oil-gas separation efficiency.These porous metals can make according to a conventional method, for example Liu Pei is raw, Huang Linguo is published in the fiber achievement method of mentioning in disclosed " 3.3. fibre metallurgy legal system is standby " in " Preparation methods for porous metal materials " of " functional material " 2002,33 (1) and prepares.Specifically also can be for making as disclosed preparation method in CN200810232586.9.The porous metals that employing nickel-cadmium is made are under the prerequisite that meets requirement of strength, and the gas mixture that can farthest will enter centrifugal separator 200 separates.
Porous metals comprise the first porous metals 240 and the second porous metals 250.The first porous metals 240 are identical with the second porous metals 250 structures.Be the block solid body of annulus.The first porous metals 240 and the second porous metals 250 are fixed in housing by the pin 230 that connects the first porous metals 240 and the second porous metals 250.The first porous metals 240 and the second porous metals 250 combine rear and housing formation Spielpassung.
Because housing is only connected with oil system by the spill port 221 being arranged on the second housing 220 Closed Ends, the gas mixture that enters housing can fully be acted in housing, until lubricating oil just flows back to housing from spill port 221 after assembling enough in porous metals again with porous metals.Gas mixture is fully separated.Spill port 221 arranges 20, and the aperture of each spill port 221 is 9.55mm.Adopt the spill port 221 of this size can make gas mixture enter enclosure interior and fully separate, can prevent that again gas mixture from just leaving housing without abundant separation.Improve the separating effect of gas mixture.
Lubricating oil after separation flows back in oil system and is again utilized from spill port 221 after assembling.Gas after simultaneously separating can enter in the venting cavity 120 in rotatingshaft 100 from the outgassing groove 260 forming between the first housing 210 and the second housing 220 inwalls.Thereby discharge oil system.Coordinate again the first seal ring 300 and the second seal ring 310 can further prevent that the gas mixture that carries a small amount of lubricating oil from entering in oil system again.By making venting cavity 120 and coordinating of centrifugal separator 200 aeroengine centrifugal separator play the effect of ventilation.
Separation effect and the gas mixture flow resistance therein of porous metals to gas mixture has relation.In the time that the thickness of the first porous metals 240 used and the second porous metals 250 is 16.2mm, it is optimum that the little and separation effect of flow resistance reaches.The external diameter of the first porous metals 240 used and the second porous metals 250 is 87.2mm, and internal diameter is 46.8mm.Adopt the first porous metals 240 and second porous metals 250 of this size reducing under the prerequisite of size of engine and weight, further strengthen the separation effect that enters the gas mixture in centrifugal separator 200.Through verification experimental verification, adopt the consumption of the centrifugal ventilator lubricating oil of radial plate type that oil gas centrifugal separator provided by the invention can be relatively conventional to decline 59%.Illustrate and adopt centrifugal separator provided by the invention can effectively improve oil-gas separation efficiency, thereby reduce lube use rate, reduce engine weight, improve motor stability in use and Security.
On the other hand, the weight of these porous metals be only same size aluminium 1/5.Thereby reduce the weight of motor.Can fully meet aeroengine in the situation of low weight.The simultaneously maximum gas mixture in escape engine in the case of the requirement that meets low weight, thus the required weight of carrying lubricating oil of motor reduced, thus further reduce the weight of motor.Make its especially with the needs of aeroengine.
Aeroengine provided by the invention has been carried out Performance Assessment test 300 hours with centrifugal separator in test room, uses on 5000kW level aviation turbo oar engine, and complete machine test run accumulative total 150 hours, average lube use rate is lower than 0.2L/ hour.Aeroengine provided by the invention with centrifugal separator with pass cylinder the centrifugal ventilator of former blade type compared with, simple and compact for structure, mounting or dismounting convenient, lightweight, process maintenance cost low, separation effect is high.
Embodiment 2
Be that with embodiment 1 difference housing is installed on the outer wall of driving gear 110.By fixing along circumferential three the uniform screws of rotatingshaft 100.Housing and rotatingshaft 100 are integrated.The consumption slippage of the board-like centrifugal ventilator lubricating oil of relative Amplitude is identical with embodiment 1.
Embodiment 3
Be with embodiment 1 difference: monoblock porous metals are only set, and the thickness of these porous metals is 32.4mm.The external diameter of mesoporous metal used is 87mm, and internal diameter is 47mm.The consumption slippage of the board-like centrifugal ventilator lubricating oil of relative Amplitude is identical with embodiment 1.
Embodiment 4
Be with embodiment 1 difference: the thickness of the first porous metals 240 is that the thickness of 10mm and the second porous metals 250 is 12.4mm.The external diameter of mesoporous metal used is 87.5mm, and internal diameter is 46.5mm.The consumption of the board-like centrifugal ventilator lubricating oil of relative Amplitude declines 39%.
Embodiment 5
Be with embodiment 1 difference: the thickness of the first porous metals 240 and the second porous metals 250 is 21.2mm.The consumption of the board-like centrifugal ventilator lubricating oil of relative Amplitude declines 49%.
Embodiment 6
Be with embodiment 1 difference: the thickness of the first porous metals 240 and the second porous metals 250 is 18.2mm.The consumption of the board-like centrifugal ventilator lubricating oil of relative Amplitude declines 55%.
Embodiment 7
Be with embodiment 1 difference: the thickness of the first porous metals 240 and the second porous metals 250 is 14.2mm.The consumption of the board-like centrifugal ventilator lubricating oil of relative Amplitude declines 54%.
Embodiment 8
Be with embodiment 1 difference: the thickness of the first porous metals 240 and the second porous metals 250 is 15.2mm.The consumption of the board-like centrifugal ventilator lubricating oil of relative Amplitude declines 57%.
Embodiment 9
Be with embodiment 1 difference: driving gear 110 is not set.The consumption of the board-like centrifugal ventilator lubricating oil of relative Amplitude declines 59%.
Embodiment 10
Be with embodiment 1 difference: do not set out air drain 260.The consumption of the board-like centrifugal ventilator lubricating oil of relative Amplitude declines 40%.
From embodiment 1～10, by adopting after centrifugal separator provided by the invention, can effectively improve aeroengine inside, in oil system, the separation effect of gas mixture, thus reduce the lube use rate in oil system, play and reduce costs, alleviate the effect of engine weight.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (13)
1. an aeroengine centrifugal separator, is characterized in that, comprise rotatingshaft (100) and be sheathed on the centrifugal separator (200) on described rotatingshaft (100) outer wall,
Described centrifugal separator (200) comprises the housing and the porous metals that are sheathed on described rotatingshaft (100), and described porous metals are filled in described housing;
On one end face of described housing, along it, multiple spill ports (221) are circumferentially set.
2. centrifugal separator according to claim 1, is characterized in that, described centrifugal separator (200) also comprises outgassing groove (260), and described outgassing groove (260) is arranged on the inwall of described housing;
Described rotatingshaft (100) inside arranges venting cavity (120), sealing one end, described venting cavity (120) one end is communicated with atmosphere, and described housing is connected with described venting cavity (120) by described outgassing groove (260).
3. centrifugal separator according to claim 1, is characterized in that, described housing comprises the first housing (210), the second housing (220),
One end of described the first housing (210) is uncovered, and another opposite end is sealing, and one end of described the second housing (220) is uncovered, and another opposite end is sealing;
The uncovered outer wall of described the first housing (210) aligns affixed with the uncovered outer wall of described the second housing (220), described the first housing (210) is spliced to form described housing with described the second housing (220);
Described spill port (221) is arranged on the Closed End of described the second housing (220).
4. centrifugal separator according to claim 3, is characterized in that,
The center of described the first housing (210) axially forms the first mounting hole (211) along it;
The center of described the second housing (220) axially forms the second mounting hole (222) along it;
The extending end of the extending end of described the first mounting hole (211) and described the second mounting hole (222) surrounds described outgassing groove (260).
5. centrifugal separator according to claim 3, it is characterized in that, also comprise: the first seal ring (300) and the second seal ring (310), the sidewall of the Closed End of described the first housing (210) is close to described rotatingshaft (100) and is extended axially and form seal ring (215) along it, and described the first seal ring (300) is installed on the inwall of described seal ring (215);
Described the second seal ring (310) is installed on the sidewall of described the second housing (220) and is close to described rotatingshaft (100);
Described the first seal ring (300) and the second seal ring (310) seal described the first housing (210), the second housing (220) and described rotatingshaft (100).
6. according to the centrifugal separator described in any one in claim 1～5, it is characterized in that, also comprise: driving gear (110), described driving gear (110) is shaped in one end of described rotatingshaft (100), described driving gear (110) extends axially formation mounting platform near one end of described centrifugal separator (200) along it, and described centrifugal separator (200) is sheathed to be installed on described mounting platform.
7. centrifugal separator according to claim 6, is characterized in that, described porous metals thickness is 42.4～22.4mm.
8. centrifugal separator according to claim 7, is characterized in that, described porous metals thickness is 36.4～28.4mm.
9. centrifugal separator according to claim 8, is characterized in that, described porous metals thickness is 32.4mm.
10. centrifugal separator according to claim 7, is characterized in that, the external diameter of described porous metals is 87～87.5mm, and internal diameter is 46.5～47mm.
11. centrifugal separators according to claim 10, is characterized in that, described spill port (221) number is 20, and each described spill port (221) diameter is 93.55mm.
12. centrifugal separators according to claim 7, is characterized in that, described porous metals comprise the first porous metals (240) and the second porous metals (250);
Described housing comprises the first housing (210), the second housing (220),
One end of described the first housing (210) is uncovered, and another opposite end is sealing, and one end of described the second housing (220) is uncovered, and another opposite end is sealing;
The uncovered outer wall of described the first housing (210) aligns affixed with the uncovered outer wall of described the second housing (220), described the first housing (210) is spliced to form described housing with described the second housing (220);
Described the first porous metals (240) are positioned in described the first housing (210), described the second porous metals (250) are positioned in described the second housing (220), and described the first porous metals (240) and described the second porous metals (250) are individually fixed in described the first housing (210) and described the second housing (220) by pin (230).
13. centrifugal separators according to claim 12, is characterized in that, described the first porous metals (240) and described the second porous metals (250) thickness equate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410225151.7A CN103982300B (en) | 2014-05-26 | 2014-05-26 | Aero-engine centrifugal separating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410225151.7A CN103982300B (en) | 2014-05-26 | 2014-05-26 | Aero-engine centrifugal separating device |
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| CN103982300A true CN103982300A (en) | 2014-08-13 |
| CN103982300B CN103982300B (en) | 2016-08-24 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106621578A (en) * | 2016-12-21 | 2017-05-10 | 中国燃气涡轮研究院 | Axial admission centrifugal ventilator |
| CN107762631A (en) * | 2016-08-19 | 2018-03-06 | 中国航发商用航空发动机有限责任公司 | Oil vent, ventilating system and gas-turbine unit |
| CN108204281A (en) * | 2016-12-20 | 2018-06-26 | 中国航发商用航空发动机有限责任公司 | Gs-oil separator, oil and gas separating system and aero-engine |
| CN114412643A (en) * | 2022-01-25 | 2022-04-29 | 中国航发贵阳发动机设计研究所 | Multi-stage oil return device integrating oil-gas separation function |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4714139A (en) * | 1985-10-02 | 1987-12-22 | Mtu Motoren-Und Turbinen Union Muenchen Gmbh | Lubricating system for gas turbine engines and pump for such a system |
| US6398833B1 (en) * | 2000-11-06 | 2002-06-04 | Pratt & Whitney Canada Corp. | Air/oil separator |
| US20050211093A1 (en) * | 2004-03-23 | 2005-09-29 | Pratt & Whitney Canada Corp. | Air/oil separation system and method |
| CN201021910Y (en) * | 2006-11-21 | 2008-02-13 | 哈尔滨哈飞汽车工业集团有限公司 | Gasoline hole device for gasoline pressure sensor of protruding table car engine |
| CN102872982A (en) * | 2012-10-08 | 2013-01-16 | 中国航空动力机械研究所 | Oil gas separation device |
-
2014
- 2014-05-26 CN CN201410225151.7A patent/CN103982300B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4714139A (en) * | 1985-10-02 | 1987-12-22 | Mtu Motoren-Und Turbinen Union Muenchen Gmbh | Lubricating system for gas turbine engines and pump for such a system |
| US6398833B1 (en) * | 2000-11-06 | 2002-06-04 | Pratt & Whitney Canada Corp. | Air/oil separator |
| US20050211093A1 (en) * | 2004-03-23 | 2005-09-29 | Pratt & Whitney Canada Corp. | Air/oil separation system and method |
| CN201021910Y (en) * | 2006-11-21 | 2008-02-13 | 哈尔滨哈飞汽车工业集团有限公司 | Gasoline hole device for gasoline pressure sensor of protruding table car engine |
| CN102872982A (en) * | 2012-10-08 | 2013-01-16 | 中国航空动力机械研究所 | Oil gas separation device |
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| CN107762631A (en) * | 2016-08-19 | 2018-03-06 | 中国航发商用航空发动机有限责任公司 | Oil vent, ventilating system and gas-turbine unit |
| CN108204281A (en) * | 2016-12-20 | 2018-06-26 | 中国航发商用航空发动机有限责任公司 | Gs-oil separator, oil and gas separating system and aero-engine |
| CN108204281B (en) * | 2016-12-20 | 2019-08-27 | 中国航发商用航空发动机有限责任公司 | Gs-oil separator, oil and gas separating system and aero-engine |
| CN106621578A (en) * | 2016-12-21 | 2017-05-10 | 中国燃气涡轮研究院 | Axial admission centrifugal ventilator |
| CN106621578B (en) * | 2016-12-21 | 2019-05-14 | 中国燃气涡轮研究院 | A kind of axial admission eccentric contract |
| CN114412643A (en) * | 2022-01-25 | 2022-04-29 | 中国航发贵阳发动机设计研究所 | Multi-stage oil return device integrating oil-gas separation function |
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