CN111530224A - Gas and oil mist separation equipment for emergency control system of airplane and use method - Google Patents
Gas and oil mist separation equipment for emergency control system of airplane and use method Download PDFInfo
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- CN111530224A CN111530224A CN202010412090.0A CN202010412090A CN111530224A CN 111530224 A CN111530224 A CN 111530224A CN 202010412090 A CN202010412090 A CN 202010412090A CN 111530224 A CN111530224 A CN 111530224A
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- 239000003595 mist Substances 0.000 title claims abstract description 48
- 238000000926 separation method Methods 0.000 title claims abstract description 27
- 238000000034 method Methods 0.000 title claims abstract description 12
- 239000007788 liquid Substances 0.000 claims abstract description 23
- 210000001503 joint Anatomy 0.000 claims abstract description 22
- 230000007246 mechanism Effects 0.000 claims abstract description 17
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 15
- 239000010959 steel Substances 0.000 claims abstract description 15
- 230000000694 effects Effects 0.000 claims abstract description 6
- 239000003921 oil Substances 0.000 claims description 79
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 37
- 239000007789 gas Substances 0.000 claims description 19
- 239000010720 hydraulic oil Substances 0.000 claims description 18
- 229910052757 nitrogen Inorganic materials 0.000 claims description 18
- 238000011084 recovery Methods 0.000 claims description 9
- 238000002955 isolation Methods 0.000 claims description 7
- 238000012544 monitoring process Methods 0.000 claims description 7
- 230000009467 reduction Effects 0.000 claims description 4
- 238000007599 discharging Methods 0.000 claims description 3
- 230000036541 health Effects 0.000 abstract description 5
- 230000006378 damage Effects 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 238000003915 air pollution Methods 0.000 abstract description 3
- 208000027418 Wounds and injury Diseases 0.000 abstract description 2
- 208000014674 injury Diseases 0.000 abstract description 2
- 238000004140 cleaning Methods 0.000 description 3
- 239000004744 fabric Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
Abstract
A gas and oil mist separation device of an aircraft emergency control system and a use method thereof belong to the technical field of mechanical hydraulic pressure. The clamping connecting rod mechanism and the locking pull rod in the separation equipment jointly form a fixed clamp of the separation equipment, and the clamping connecting rod mechanism is connected with the discharge port butt joint device through a universal rocker arm; the discharge port butt joint device is connected with the I-stage liquefying device through a connecting steel pipe, and a barometer, a liquid level indicator and an oil drain valve are arranged on the connecting steel pipe. The I-grade liquefaction core is arranged in the I-grade liquefaction device, and forms a gas and oil mist separation device together with the I-grade liquefaction device, 80% of oil mist is converted into liquid, and the residual gas and the oil mist are depressurized through a hose from a P1 port and then enter the II-grade liquefaction device for secondary liquefaction. The invention has compact mechanical structure, powerful functions of step-by-step oil-gas separation and liquefaction devices and extremely obvious separation effect, and can solve the problems of air pollution, injury to the health of staff and the like caused by difficulty in control of oil mist generated in the exhaust process of the emergency control system of the airplane.
Description
Technical Field
The invention belongs to the technical field of mechanical hydraulic pressure, and relates to a device which can liquefy oil mist carried in discharged nitrogen and effectively separate the liquefied oil mist from nitrogen when a system needs to discharge redundant nitrogen in an air pressure system to the outside of an airplane when the airplane is subjected to ground debugging of an emergency control system, so that the oil mist in the air is reduced, the harm to the body caused by the fact that workers inhale the oil mist into the body is prevented, and the pollution to the environment is reduced.
Background
The power source of the airplane control system mainly comprises a hydraulic system and a pneumatic system, and for some important systems, the system can be controlled not only by the hydraulic system, but also by the pneumatic system. However, when the pneumatic system is used as power, redundant nitrogen and partial hydraulic oil in a shared pipeline of the hydraulic system and the pneumatic system are required to pass through an exhaust port of the airplane and be exhausted out of the airplane body after the operation is finished, a large amount of hydraulic oil can be sprayed on structures and equipment around the exhaust port of the airplane, and a large amount of oil mist can be generated, so that an operator who is working can only wait for the oil mist to be dispersed to perform subsequent work. At present, in order to effectively separate and liquefy nitrogen and oil mist discharged from an air outlet of an airplane, a conventional method is to wind the air outlet of the airplane with a cleaning cloth, cover surrounding equipment with a protective device, then exhaust the air, and perform subsequent work after the surrounding oil mist is scattered; the other method is that a rubber pipe is connected to an exhaust port, and then redundant nitrogen and oil mist are exhausted to the outside of the factory building; although the two methods reduce the pollution of the oil mist to the health of an operator and the surrounding air environment from different angles, the problems are not thorough to process, firstly, nitrogen and the oil mist cannot be thoroughly separated in any mode, and meanwhile, the redundant oil mist can cause harm and pollution to the health of the operator and the surrounding air environment to different degrees; secondly, a large amount of cleaning cloth needs to be prepared in the first protection mode every time, and the cleaning cloth which is used up every time cannot be recycled, so that the resource waste is too large; and the second exhaust mode adopts hose connection, because the butt joint length of the exhaust port and the hose is very short, the hose pops away due to overlarge exhaust pressure sometimes, so that a protection device fails, most of nitrogen and oil mist are directly discharged to the periphery of the airplane without any protection device, large-area air pollution is caused, and surrounding equipment can be sprayed with hydraulic oil without increasing large workload.
In view of the reasons, the invention provides the gas and oil mist separation equipment for the emergency control system of the airplane, which has the advantages of novel structure and simple operation, not only can effectively separate the gas and the oil mist discharged outside the airplane body, but also can effectively complete the work without waiting for an operator after the exhaust is finished, and can ensure the personal health and the surrounding air quality.
Disclosure of Invention
The invention aims to provide a novel high-efficiency and low-pollution gas and oil mist separation device for an emergency control system of an airplane, which not only can greatly reduce the working strength of an operator and improve the working efficiency, but also has good flexibility and a wide application range.
The technical scheme adopted by the invention is as follows:
the utility model provides an emergent control system of aircraft is gaseous and oil mist splitter, includes clamping link mechanism 1, universal rocking arm 2, locking knob 3, discharge port interfacing apparatus 4, barometer 5, I level liquefaction core 6, locking pull rod 7, liquid level indicator 8, fuel outlet valve 9, connecting steel pipe 10, connecting bolt 11, I level liquefaction device 12, discharge hose 13, II level liquefaction device 14, weeping separation mesh board 15.
The clamping link mechanism 1 is of a triangular structure, a locking pull rod 7 is arranged on one side of the clamping link mechanism 1, and the clamping link mechanism 1 and the locking pull rod 7 jointly form a fixing clamp of the equipment and are used for fixing the equipment on a triangular structure frame around an airplane exhaust port.
One side of the clamping connecting rod mechanism 1 is connected with a universal rocker arm 2 through a connecting bolt 11, and the universal rocker arm 2 is connected with a discharge port butt joint device 4 through a locking knob 3; the universal rocker arm 2 is used for flexibly adjusting the discharge port butt joint device 4 in the longitudinal direction and the transverse direction, and finally, the exhaust holes of the airplane are accurately and tightly butted with the discharge port butt joint device 4; the locking knob 3 is used for fixing and locking the position of the exhaust hole of the airplane after the exhaust hole is butted with the exhaust port butting device 4.
The discharge port butt joint device 4 is connected with the I-stage liquefying device 12 through a connecting steel pipe 10, the connecting steel pipe 10 is provided with a barometer 5, and the barometer 5 is used for monitoring whether the air pressure discharged from the air discharge hole of the airplane meets a specified value and when the air discharge work is finished. The pipe diameter of the connecting steel pipe 10 is 2 times of that of the airplane exhaust port.
The I-stage liquefaction core 6 is arranged in the I-stage liquefaction device 12, the I-stage liquefaction core 6 and the I-stage liquefaction device 12 jointly form a gas and oil mist separation device, 80% of oil mist can be converted into liquid, and then the rest gas and oil mist are subjected to pressure reduction through a hose from a P1 port and enter the II-stage liquefaction device 14 for secondary liquefaction. The liquid level indicator 8 is used for monitoring the content of liquid oil in the I-stage liquefaction device 12, and when the content reaches an upper limit value, the oil is discharged into a hydraulic oil recovery container through an oil discharge valve 9; the oil drain valve 9 is closed when the equipment is in normal operation, and is used for draining the hydraulic oil in the I-stage liquefaction device 12.
The II-stage liquefying device 14 is connected with a P1 port of the I-stage liquefying device 12, the II-stage liquefying device 14 and the discharge hose 13 at the top of the II-stage liquefying device form a separating device for secondary gas and oil mist together, the oil mist is completely liquefied and separated from nitrogen, and finally redundant nitrogen is discharged to the outside of a factory building through the discharge hose 13.
The liquid leakage isolation mesh plate 15 is arranged in the I-stage liquefying device 12, and mainly eliminates the separated oil after liquefaction with nitrogen, thereby ensuring the separation effect.
A method of using an aircraft emergency operation system gas and oil mist separation device, comprising the steps of:
(1) when an airplane adopts a pneumatic system as a power source to operate a certain emergency function system, firstly loosening the locking pull rod 7, then installing the clamping connecting rod mechanism 1 on a triangular structure frame around an airplane exhaust hole, and then adjusting the locking pull rod 7 to pre-tighten;
(2) the locking knob 3 is unscrewed, the position of the discharge port butt joint device 4 is adjusted to enable the discharge port butt joint device to be accurately and tightly butted with an exhaust port of an airplane, and then the locking knob 3 and the locking pull rod 7 are unscrewed and screwed;
(3) checking whether the pointer of the barometer 5 is zero, opening the oil drain valves 9 of the first-stage liquefaction device 12 and the second-stage liquefaction device 14 to ensure that no redundant hydraulic oil exists in the two liquefaction devices, and then closing the oil drain valve 9;
(4) connecting the P1 ports of the I-stage liquefying device 12 and the II-stage liquefying device 14 by adopting hoses through quick-release connectors, and then leading the other end of the discharge hose 13 out of the plant;
(5) then the airplane carries out the exhaust work of emergency discharge, at the moment, the gage pressure of the barometer 5 can be seen to rapidly rise and then gradually drop to 0MP, the airplane exhaust work is proved to be finished, the liquid level indicator 8 is noticed to be observed, then the oil discharge valves 9 of the I-level liquefaction device 12 and the II-level liquefaction device 14 are opened in time, the oil in the airplane is discharged in the hydraulic oil recovery container, and the oil discharge valve 9 is closed;
(6) disconnecting a hose between the I-stage liquefaction device 12 and the II-stage liquefaction device 14, and discharging residual oil in the hose into a hydraulic oil recovery container;
(7) adjusting the locking knob 3 and the locking pull rod 7 to detach the equipment from the airplane completes the exhaust work of the emergency control system of the airplane.
The invention has the beneficial effects that:
(1) the air-oil separation and liquefaction device is compact in mechanical structure and powerful in function, and thoroughly solves the problems of air pollution, injury to the health of staff and the like caused by difficulty in control of oil mist generated in the exhaust process of the emergency control system of the airplane.
(2) The invention adopts the pressure indication of the barometer 5, can realize real-time monitoring whether the exhaust pressure of an exhaust system in the airplane meets a specified value or not, and whether back pressure is caused by pipeline blockage exists or not, ensures the stability of the whole exhaust liquefaction system, and can judge when the air pressure of a pipeline is exhausted according to the pressure indication visually;
(3) according to the invention, the I-stage liquefaction device 12 and the II-stage liquefaction device 14 are designed by adopting special structures, and the leakage isolation mesh plate 15 is additionally arranged at the lowest end of the devices, so that the separated oil cannot be discharged to the next link along with nitrogen gas, and the separation effect is extremely obvious;
(4) because the I-grade liquefaction core 6 is made of high-density steel wire mesh materials, the liquefaction effect can reach over 80 percent, and the I-grade liquefaction core can be cleaned by gasoline at any time according to the use standard, so that the cost is reduced, and the reuse utilization rate is high;
(5) the invention has the most important characteristics that the separation efficiency of the whole device on nitrogen and oil mist is extremely high, and the pollution degree on the peripheral air is extremely low, so that other work is not influenced in the exhaust process of an airplane, and the whole work efficiency is greatly improved;
drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of a secondary air and oil mist separation apparatus;
in the figure: 1 clamping link mechanism, 2 universal rocking arms, 3 locking knobs, 4 discharge port interfacing apparatus, 5 barometers, 6I grades of liquefaction cores, 7 locking pull rods, 8 liquid level indicator, 9 fuel outlet valve, 10 connecting steel pipes, 11 connecting bolts, 12I grades of liquefaction device, 13 discharge hose, 14 II grades of liquefaction device, 15 weeping isolation mesh board.
Detailed Description
The present invention is further illustrated by the following specific examples.
The invention relates to gas and oil mist separation equipment of an aircraft emergency control system, which mainly comprises a clamping connecting rod mechanism 1, a universal rocker arm 2, a locking knob 3, a discharge port butt joint device 4, a barometer 5, a I-stage liquefaction core 6, a locking pull rod 7, a liquid level indicator 8, an oil drain valve 9, a connecting steel pipe 10, a connecting bolt 11, an I-stage liquefaction device 12, a discharge hose 13, a II-stage liquefaction device 14 and a leakage isolation mesh plate 15, and the specific structure of the equipment is shown in figures 1 and 2.
The clamping connecting rod mechanism 1 and the locking pull rod 7 jointly form a fixing clamp of the equipment, and the fixing clamp is mainly used for fixing the equipment on a triangular structure frame around an airplane exhaust port; the universal rocker arm 2 is mainly used for flexibly adjusting the discharge port butt joint device 4 in the longitudinal direction and the transverse direction, and finally, the exhaust hole of the airplane is accurately and tightly butted with the discharge port butt joint device 4; the locking knob 3 is mainly used for fixing and locking the position of the exhaust hole of the airplane after the exhaust hole is butted with the exhaust port butting device 4; the barometer 5 is mainly used for monitoring whether the air pressure exhausted from the air exhaust hole of the airplane meets a specified value and when the air exhaust work is finished; the I-stage liquefaction core 6 and the I-stage liquefaction device 12 form a gas and oil mist separation device together, 80% of oil mist can be converted into liquid, and then the rest gas and oil mist are subjected to pressure reduction through a hose from a P1 port and then enter the II-stage liquefaction device 14 for secondary liquefaction; the liquid level indicator 8 is mainly used for monitoring the amount of liquid oil in the I-stage liquefaction device 12, and when the upper limit value is reached, the oil liquid can be discharged into a hydraulic oil recovery container through the oil discharge valve 9; the oil drain valve 9 is in a closed state when the equipment normally works, and is mainly used for draining hydraulic oil in the I-level liquefaction device 12; the connecting steel pipe 10 not only can realize the function of pressure reduction due to the fact that the pipe diameter of the connecting steel pipe is 2 times of that of an air outlet of an airplane, but also is a device for connecting the discharge port butt joint device 4 with the I-stage liquefying device 12; the connecting bolt 11 is mainly used for connecting the clamping connecting rod mechanism 1 and the universal rocker arm 2; the II-stage liquefying device 14 and the discharge hose 13 jointly form a secondary gas and oil mist separating device, so that oil mist is completely liquefied and separated from nitrogen, and finally redundant nitrogen is discharged to the outer side of a plant through the discharge hose 13; the liquid leakage isolation mesh plate 15 mainly eliminates the liquefied and separated oil with nitrogen, so as to ensure the separation effect.
A method of using an aircraft emergency operation system gas and oil mist separation device, comprising the steps of:
(1) when an airplane adopts a pneumatic system as a power source to operate a certain emergency function system, firstly loosening the locking pull rod 7, then installing the clamping connecting rod mechanism 1 on a triangular structure frame around an airplane exhaust hole, and then adjusting the locking pull rod 7 to pre-tighten;
(2) the locking knob 3 is unscrewed, the position of the discharge port butt joint device 4 is adjusted to enable the discharge port butt joint device to be accurately and tightly butted with an exhaust port of an airplane, and then the locking knob 3 and the locking pull rod 7 are unscrewed and screwed;
(3) checking whether the pointer of the barometer 5 is zero, opening the oil drain valves 9 of the first-stage liquefaction device 12 and the second-stage liquefaction device 14 to ensure that no redundant hydraulic oil exists in the two liquefaction devices, and then closing the oil drain valve 9;
(4) connecting the P1 ports of the I-stage liquefying device 12 and the II-stage liquefying device 14 by using hoses through quick-release connectors, and then leading the other end of the discharge hose 13 out of the plant;
(5) then, the airplane carries out emergent exhaust work, at the moment, the gage pressure of the barometer 5 can be seen to rapidly rise to P0MP, after a period of time, the gage pressure gradually falls to 0MP, at the moment, the airplane exhaust work is proved to be finished, attention is paid to observing the liquid level indicator 8, then the oil drain valves 9 of the I-stage liquefaction device 12 and the II-stage liquefaction device 14 are opened in time, so that the oil in the airplane is discharged in a hydraulic oil recovery container, and the oil drain valve 9 is closed;
(6) disconnecting a hose between the I-stage liquefaction device 12 and the II-stage liquefaction device 14, and discharging residual oil in the hose into a hydraulic oil recovery container;
(7) adjusting the locking knob 3 and the locking pull rod 7 to detach the equipment from the airplane completes the exhaust work of the emergency control system of the airplane.
The above-mentioned embodiments only express the embodiments of the present invention, but not should be understood as the limitation of the scope of the invention patent, it should be noted that, for those skilled in the art, many variations and modifications can be made without departing from the concept of the present invention, and these all fall into the protection scope of the present invention.
Claims (3)
1. The gas and oil mist separation equipment for the emergency control system of the airplane is characterized by comprising a clamping connecting rod mechanism (1), a universal rocker arm (2), a locking knob (3), a discharge port butt joint device (4), a barometer (5), a I-level liquefaction core (6), a locking pull rod (7), a liquid level indicator (8), an oil drain valve (9), a connecting steel pipe (10), a connecting bolt (11), an I-level liquefaction device (12), a discharge hose (13), a II-level liquefaction device (14) and a leakage isolation mesh plate (15);
the clamping connecting rod mechanism (1) is of a triangular structure, and forms a fixing clamp of the equipment together with the locking pull rod (7) for fixing the equipment on a triangular structure frame around an airplane exhaust port;
the clamping connecting rod mechanism (1) is connected with a universal rocker arm (2) through a connecting bolt (11), and the universal rocker arm (2) is connected with a discharge port butt joint device (4) through a locking knob (3); the universal rocker arm (2) is used for flexibly adjusting the discharge port butt joint device (4) in the longitudinal direction and the transverse direction, and finally, the exhaust hole of the airplane is accurately and tightly butted with the discharge port butt joint device (4); the locking knob (3) is used for fixing and locking the position of the exhaust hole of the airplane after the exhaust hole is butted with the discharge port butting device (4);
the discharge port butt joint device (4) is connected with the I-stage liquefying device (12) through a connecting steel pipe (10), a barometer (5) is arranged on the connecting steel pipe (10), and the barometer (5) is used for monitoring whether the air pressure discharged from the air discharge port of the airplane meets a specified value and when the air discharge work is finished;
the I-stage liquefaction core (6) is arranged in the I-stage liquefaction device (12), the I-stage liquefaction core (6) and the I-stage liquefaction device (12) jointly form a gas and oil mist separation device which is used for converting oil mist into liquid, and then the residual gas and oil mist are subjected to pressure reduction through a hose from a P1 port and then enter the II-stage liquefaction device (14) for secondary liquefaction; the liquid level indicator (8) is used for monitoring the content of liquid oil in the I-stage liquefying device (12), and when the content reaches an upper limit value, the oil is discharged into a hydraulic oil recovery container through an oil discharge valve (9); the oil drain valve (9) is in a closed state when the equipment normally works and is used for draining hydraulic oil in the I-level liquefaction device (12);
the second-stage liquefying device (14) is connected with a P1 port of the first-stage liquefying device (12), the second-stage liquefying device (14) and a discharge hose (13) at the top of the second-stage liquefying device jointly form a secondary gas and oil mist separating device, so that the oil mist is completely liquefied and separated from nitrogen, and finally, redundant nitrogen is discharged to the outer side of a factory building through the discharge hose (13);
the liquid leakage isolation mesh plate (15) is arranged in the I-level liquefying device (12), and mainly prevents the separated oil liquid after liquefaction from being discharged along with nitrogen, so that the separation effect is ensured.
2. An aircraft emergency control system gas and oil mist separation device according to claim 1, wherein the pipe diameter of the connecting steel pipe (10) is 2 times of the pipe diameter of an aircraft exhaust port.
3. A method of using an aircraft emergency operation system gas and oil mist separation device according to claim 1 or 2, comprising the steps of:
(1) when an airplane adopts a pneumatic system as a power source to operate a certain emergency function system, firstly loosening the locking pull rod (7), then installing the clamping connecting rod mechanism (1) on a triangular structure frame around an airplane exhaust hole, and then adjusting the locking pull rod (7) to pre-tighten;
(2) the locking knob (3) is unscrewed, the position of the discharge port butt joint device (4) is adjusted to enable the discharge port butt joint device to be accurately and tightly butted with an exhaust port of an airplane, and then the locking knob (3) and the locking pull rod (7) are unscrewed and screwed;
(3) checking whether a pointer of the barometer (5) is zero, opening oil drain valves (9) of a first-stage liquefaction device (12) and a second-stage liquefaction device (14) to ensure that no redundant hydraulic oil exists in the two liquefaction devices, and then closing the oil drain valves (9);
(4) the P1 ports of the I-level liquefying device (12) and the II-level liquefying device (14) are connected by a hose through a quick-release connector, and then the other end of the discharge hose (13) is led out to the outside of the plant;
(5) then the airplane carries out emergent exhaust work, at the moment, the gage pressure of the barometer (5) can be seen to rapidly rise and then gradually drop to 0MP, at the moment, the airplane exhaust work is proved to be finished, the liquid level indicator (8) is observed, then the oil drain valves (9) of the I-level liquefaction device (12) and the II-level liquefaction device (14) are opened in time, so that the oil in the airplane is discharged in the hydraulic oil recovery container, and the oil drain valve (9) is closed;
(6) disconnecting a hose between the I-stage liquefaction device (12) and the II-stage liquefaction device (14), and discharging residual oil in the hose into a hydraulic oil recovery container;
(7) adjusting the locking knob (3) and the locking pull rod (7) to detach the equipment from the airplane, namely finishing the air exhausting work of the emergency control system of the airplane.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010412090.0A CN111530224B (en) | 2020-05-15 | 2020-05-15 | Gas and oil mist separation device for aircraft emergency control system and use method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010412090.0A CN111530224B (en) | 2020-05-15 | 2020-05-15 | Gas and oil mist separation device for aircraft emergency control system and use method thereof |
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| CN111530224B CN111530224B (en) | 2024-04-16 |
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| JP2000024433A (en) * | 1998-05-07 | 2000-01-25 | Sumitomo Light Metal Ind Ltd | Oil mist collecting device |
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| CN108452627A (en) * | 2018-05-10 | 2018-08-28 | 常州市华立液压润滑设备有限公司 | A kind of oil gas separator |
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| CN110053889A (en) * | 2019-05-22 | 2019-07-26 | 四川飞达源通能源装备制造有限公司 | It is a kind of with datonation-inhibition and petroleum vapor recovery function aviation fuel storage system and the method for guaranteeing the quality |
| CN110433574A (en) * | 2019-08-02 | 2019-11-12 | 绵阳小巨人动力设备有限公司 | A kind of forced-ventilated fuel oil bubble stripper for Micro-Aviation Engine |
| CN212467601U (en) * | 2020-05-15 | 2021-02-05 | 沈阳飞机工业（集团）有限公司 | Gas and oil mist separation equipment for emergency control system of airplane |
-
2020
- 2020-05-15 CN CN202010412090.0A patent/CN111530224B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000024433A (en) * | 1998-05-07 | 2000-01-25 | Sumitomo Light Metal Ind Ltd | Oil mist collecting device |
| CN206778080U (en) * | 2017-04-12 | 2017-12-22 | 昆山凡尼谛克五金机械有限公司 | Oil fog processor |
| CN108452627A (en) * | 2018-05-10 | 2018-08-28 | 常州市华立液压润滑设备有限公司 | A kind of oil gas separator |
| CN110044233A (en) * | 2019-05-16 | 2019-07-23 | 沈阳飞机工业（集团）有限公司 | Contactless arm parts free travel checks measuring instrument and its application method |
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| CN111530224B (en) | 2024-04-16 |
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