CN212467601U - Gas and oil mist separation equipment for emergency control system of airplane - Google Patents
Gas and oil mist separation equipment for emergency control system of airplane Download PDFInfo
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- CN212467601U CN212467601U CN202020810061.5U CN202020810061U CN212467601U CN 212467601 U CN212467601 U CN 212467601U CN 202020810061 U CN202020810061 U CN 202020810061U CN 212467601 U CN212467601 U CN 212467601U
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Abstract
An emergent control system gas and oil mist separation equipment of an airplane belongs 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 utility model discloses mechanical structure is inseparable, and oil-gas separation, liquefaction device powerful step by step, and the separation effect is extremely obvious, can solve air pollution, staff health that produced oil mist is difficult to control in the emergent control system exhaust process of aircraft and causes and receive a great deal of difficult point problems such as injury.
Description
Technical Field
The utility model belongs to the technical field of mechanical hydraulic pressure, it is when carrying out the ground debugging of certain emergent control system that the aircraft is related to, when the system need discharge unnecessary nitrogen gas in the air pressure system the aircraft outside, can liquefy through the oil mist that takes in the equipment with the nitrogen gas of discharging to make it with the effectual separation of nitrogen gas, thereby reduce the oil mist in the air, prevent that the staff from inhaleing the internal injury that causes the health and alleviate the pollution to the environment.
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 above all kinds of reasons, the utility model discloses a gaseous and oil mist splitter of this emergent control system of aircraft, this equipment structure is novel, and easy operation not only can will get rid of the external gaseous and the effectual separation of oil mist of aircraft, and after the exhaust is ended moreover, the operator need not to wait for, not only can high-efficiently accomplish work, but also can guarantee that individual health and peripheral air quality.
SUMMERY OF THE UTILITY MODEL
The utility model aims at being exactly the utility model a high-efficient, low novel emergent control system of aircraft gas and oil mist splitter that pollutes not only can alleviate operator's working strength, improve work efficiency by a wide margin, but also has fine flexibility, and its application scope is wide very much.
The utility model adopts the technical proposal that:
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 utility model has the advantages that:
(1) the utility model discloses a mechanical structure is inseparable, and oil-gas separation, liquefying plant powerful step by step have thoroughly solved the air pollution that produced oil mist is difficult to control in the emergent control system exhaust process of aircraft and causes, staff are healthy to receive a great deal of difficult point problems such as injury.
(2) The utility model adopts the pressure indication of the barometer 5, which can realize real-time monitoring whether the exhaust pressure of the exhaust system in the airplane meets the specified value, whether the pipeline is blocked to cause back pressure, ensure the stability of the whole exhaust liquefaction system, and judge when the air pressure of the pipeline is exhausted according to the pressure indication;
(3) the utility model adopts the special structural design of the I-stage liquefaction device 12 and the II-stage liquefaction device 14, and the liquid leakage isolation mesh plate 15 is additionally arranged at the lowest end of the devices, so that the separated oil can be strictly ensured not to be discharged to the next link along with nitrogen, 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 utility model has the most important characteristics that the separation efficiency of the whole device to nitrogen and oil mist is extremely fast, and the pollution degree to the surrounding air is extremely low, so that other work is not influenced in the process of exhausting the air of the airplane, and the whole working 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 will be further described with reference to the following specific embodiments.
The utility model provides a gaseous and oil mist splitter of emergent control system of aircraft, the utility model discloses a frock mainly comprises 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, 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 isolation mesh board 15, and concrete structure is as shown in figure 1, figure 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 represent the embodiments of the present invention, but can not be understood as the limitation of the scope of the present invention, and it should be noted that, for those skilled in the art, a plurality of variations and improvements can be made without departing from the concept of the present invention, and all of them belong to the protection scope of the present invention.
Claims (2)
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.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020810061.5U CN212467601U (en) | 2020-05-15 | 2020-05-15 | Gas and oil mist separation equipment for emergency control system of airplane |
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| CN202020810061.5U CN212467601U (en) | 2020-05-15 | 2020-05-15 | Gas and oil mist separation equipment for emergency control system of airplane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111530224A (en) * | 2020-05-15 | 2020-08-14 | 沈阳飞机工业（集团）有限公司 | Gas and oil mist separation equipment for emergency control system of airplane and use method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111530224A (en) * | 2020-05-15 | 2020-08-14 | 沈阳飞机工业（集团）有限公司 | Gas and oil mist separation equipment for emergency control system of airplane and use method |
| CN111530224B (en) * | 2020-05-15 | 2024-04-16 | 沈阳飞机工业（集团）有限公司 | Gas and oil mist separation device for aircraft emergency control system and use method thereof |
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