CN208931665U - A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system - Google Patents
A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system Download PDFInfo
- Publication number
- CN208931665U CN208931665U CN201821437987.3U CN201821437987U CN208931665U CN 208931665 U CN208931665 U CN 208931665U CN 201821437987 U CN201821437987 U CN 201821437987U CN 208931665 U CN208931665 U CN 208931665U
- Authority
- CN
- China
- Prior art keywords
- fuel
- gas
- outlet
- entrance
- compressor
- 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.)
- Expired - Fee Related
Links
Landscapes
- Fuel Cell (AREA)
Abstract
The utility model discloses a kind of fuel tanker inerting units using high pressure water separation regenerative air cycle cooling system, hydrogen, which is carried, with aircraft using engine bleed or cockpit bleed reacts the oxygen in consumed cabin air by hydrogen-oxygen fuel cell to generate inert gas for reducing fuel tank gas-phase space oxygen concentration, fuel cell reaction generates a large amount of vapor simultaneously, water separation is carried out to the inert gas that reaction generates using three-wheel boosting high pressure water separation regenerative air cycle cooling system system, collecting the water that separation generates can be used for aircraft daily water consumption, while the electric energy that fuel cell reaction generates is used for aviation power supply equipment.Tthe utility model system simple and stable can reduce energy consumption, reduce influence of the engine high pressure side bleed to engine performance, and can reduce the panelty of aircraft.
Description
Technical field
The utility model relates to fire-proof and explosion-proof technical field more particularly to a kind of fuel tanker inertings using high pressure water separation regenerative air cycle cooling system
Device.
Background technique
Fuel tanker gas-phase space oxygen concentration be higher than the flammable oxygen concentration of the limit, external incendiary source for example thunder and lightning, electrostatic,
In the presence of artillery fire strike etc., fuel vapor mixes with air object and combustion explosion easily occurs, and leads to fatal crass, causes greatly
Security of the lives and property hidden danger.The one frame TWA800 airliner on July 17th, 1996, Trans-World Airlines is international from New York Kennedy
Airport Paris Fei Zhu Charles de Gaulle Airport, which is taken off, explodes soon convenient for Long Island overhead, and 230 passenger and crews on machine is caused to suffer from
It is difficult.Investigation discovery accident is to cause short circuit to generate electric spark by electric wire broken on aircraft to enter fuel tank, causes Center Wing Tank
Explosion on fire.This time after accident, fuel tank gas-phase space combustibility is reduced, protection fuel tanker causes safely the wide of researcher
General concern.Three factors that fire occurs for fuel tank have incendiary source, combustible and combustion adjuvant.Since incendiary source is uncontrollable, fuel oil
Volatility cause gas-phase space to there is fuel vapor always, therefore preventing the important measures that fuel tanker fire occurs is to reduce
The presence of combustion adjuvant oxygen.Studies have shown that when fuel tanker gas-phase space oxygen concentration is lower than 12%(civil aircraft) and 9%(army
With aircraft) when the generation of fire can be effectively prevented.Federal Aviation management board (FAA) is by a large amount of theoretical and experimental studies
Show that fuel tank inerting technology is a kind of cost-effective method for reducing fuel tank gas-phase space oxygen concentration.
Fuel tank inerting technology refers to that (nitrogen gas concn can be high using inert gas such as nitrogen, carbon dioxide or nitrogen-rich gas
98%) etc. reach reduction gas-phase space up to the oxygen that fuel tank gas-phase space converts out gas-phase space is filled with to reduce oxygen concentration
Combustibility protects the purpose of fuel tank safety.The fuel tank inerting technology for developing comparative maturity at present is airborne nitrogen inerting technology processed, benefit
Nitrogen-rich gas is produced by hollow-fibre membrane with high-pressure engine bleed, inerting is carried out to fuel tank, the technology is in F-15, F-22, F-
35, the military secrets such as C-17 and Boeing 747, Airbus A320 etc. are widely used.But from current domestic and international application status
From the point of view of, the technology there are Middle hollow fiber membrane low efficiency, easily blocking, film inlet pressure is high, engine bleed amount is big the problems such as.
And with the development of airmanship, aircraft manufacturing develops towards larger capacity, safer direction, while aircraft electricity
To aviation power supply, more stringent requirements are proposed with water supply for the increase of sub- equipment and passenger.
Utility model content
Technical problem to be solved in the utility model is to provide one kind for defect involved in background technique and adopt
With the fuel tanker inerting unit of high pressure water separation regenerative air cycle cooling system, the panelty of the aircraft during fuel tank inerting is reduced, improves energy utilization
Rate guarantees the flight safety of aircraft.
The utility model uses following technical scheme to solve above-mentioned technical problem:
A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system, including hydrogen storage bottle, First Heat Exchanger, hydrogen-oxygen fuel electricity
Pond, the first compressor, the second heat exchanger, fan, separator, turbo-expander, water tank, check valve and fuel tank；
The hydrogen storage bottle is exported equipped with high pressure hydrogen；Hydrogen-oxygen fuel cell be equipped with anodic gas entrance, cathode gas inlet,
Power output port and offgas outlet；Separator is equipped with gas access, the gentle body outlet of liquid water out；Fuel tank is equipped with inertia
Gas access and gas vent；Water tank is equipped with entrance and exit；
The entrance of the First Heat Exchanger hot-side channel introduces the cathode gas of engine bleed, outlet and hydrogen-oxygen fuel cell
Body entrance is connected；
The high pressure hydrogen outlet of the anodic gas entrance of the hydrogen-oxygen fuel cell and hydrogen storage bottle is connected, power output port
It is connected with external aircraft electrical equipment；
The offgas outlet of the hydrogen-oxygen fuel cell, the first compressor, the hot-side channel of the second heat exchanger, separator
Gas access is sequentially connected；
The gas vent of the separator, turbo-expander, check valve, fuel tank inert gas entrance be sequentially connected；
The liquid water out of the separator is connected with the entrance of water tank, the outlet of water tank and external watering equipment
It is connected；
The shaft of the turbo-expander is coaxially connected with the shaft of first compressor, the shaft of fan respectively,
In, the turbo-expander supplies power to the first compressor for cooling down to the gas being discharged in separator
It works with fan, the first compressor of drive and fan；
The entrance of the second heat exchanger cold side channel connects ram-air, the outlet of the second heat exchanger cold side channel, fan,
The entrance of First Heat Exchanger cold side channel is connected；
The outlet of the First Heat Exchanger cold side channel, the gas vent of fuel tank connect atmosphere outside.
As a kind of further prioritization scheme of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system of the utility model, also wrap
Include the second compressor and the first motor；
The air inlet joint chair cabin bleed of second compressor, gas outlet and the First Heat Exchanger hot-side channel entrance
It is connected；
The shaft of first motor and the shaft of second compressor are coaxially connected, and are used to provide power to second
Compressor drives its work.
As a kind of further prioritization scheme of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system of the utility model, also wrap
Include the second motor, fuel oil injector and oil pump；
The shaft of second motor and the shaft of first compressor are coaxially connected, for further providing for power
To first compressor, drive its work；
The fuel oil injector is equipped with gas access, fuel filler and gas mixture outlet；The fuel tank is in its bottom
It is additionally provided with gas mixture entrance and fuel outlet；Oil pump is equipped with fuel filler and fuel outlet；
The fuel filler of the oil pump is connected with the fuel outlet of the fuel tank, and the fuel outlet of oil pump and the fuel oil draw
The fuel filler of emitter connects；
The gas access of the fuel oil injector is connected with the gas vent of the check valve, and the oil gas of fuel oil injector is mixed
Object outlet is closed to be connected with the gas mixture entrance of the fuel tank；
The inert gas entrance of the fuel tank is closed.
The invention also discloses it is a kind of based on this using high pressure water separation regenerative air cycle cooling system fuel tanker inerting unit working method,
Include following procedure:
Hydrogen in hydrogen storage bottle and the engine bleed after First Heat Exchanger cools down are reacted in hydrogen-oxygen fuel cell,
Consumption oxygen generates water simultaneously, reacts the electric energy input external power supply equipment of generation, and the tail gas of reaction is by the first compressor, the
Two heat exchangers and separator, the liquid water and dry inert gas isolated, wherein liquid water is stored by water tank
External watering equipment is supplied afterwards, and dry inert gas enters fuel tank gas-phase space by check valve after turbo-expander cools down
It is mixed to reduce fuel tank gas-phase space oxygen concentration.
The utility model compared with the prior art by using the above technical solution, has following technical effect that
The utility model using engine bleed or cockpit bleed by hydrogen-oxygen fuel cell reaction produce electricl energy with water with
The electricity consumption and water consumption increased day is provided.Vapor and rich nitrogen tail gas are generated by hydrogen-oxygen fuel cell real time reaction and utilize three
Wheel boosting high pressure water separation regenerative air cycle cooling system system carries out water separation progress liquid water storage and utilizes, and reduces the initial moisture storage capacity of aircraft, alleviates winged
Machine takes off gross mass, reduces aircraft panelty.The dry inert gas after high pressure water separation regenerative air cycle cooling system enters fuel tank reduction simultaneously
Gas-phase space oxygen concentration guarantees fuel tank safety.This system can reduce engine height from engine low-pressure side or cockpit bleed
Influence of the side bleed to engine performance is pressed, while providing electric energy for aircraft and water reduces aircraft panelty, improves energy
Measure utilization rate.
Detailed description of the invention
Fig. 1 is the system diagram of the fuel tanker inerting using high pressure water separation regenerative air cycle cooling system using engine bleed of embodiment 1；
Fig. 2 is the system diagram of the fuel tanker inerting using high pressure water separation regenerative air cycle cooling system using cockpit bleed of embodiment 2；
Fig. 3 is the system diagram that inerting is washed using the fuel tanker using high pressure water separation regenerative air cycle cooling system of cockpit bleed of embodiment 3.
In figure, 1, hydrogen storage bottle, 2, First Heat Exchanger, 3, hydrogen-oxygen fuel cell, 4, electrical equipment, the 5, first compressor, 6,
Second heat exchanger, 7, fan, 8, separator, 9, turbo-expander, 10, water tank, 11, check valve, 12, watering equipment, 13,
Fuel tank, the 101, second compressor, the 102, first motor, the 201, second motor, 202, fuel oil injector, 203, oil pump.
Specific embodiment
The technical solution of the utility model is described in further detail with reference to the accompanying drawing:
The utility model can be embodied in many different forms, and should not be assumed that be limited to the embodiments described herein.
On the contrary, it is thorough and complete to these embodiments are provided so that the disclosure, and this reality will be given full expression to those skilled in the art
With novel range.In the accompanying drawings, for the sake of clarity it is exaggerated component.
1), embodiment 1:
Fig. 1 is to utilize the system of the fuel tanker inerting using high pressure water separation regenerative air cycle cooling system of engine bleed, including hydrogen storage bottle 1, the
One heat exchanger 2, hydrogen-oxygen fuel cell 3, the first compressor 5, the second heat exchanger 6, fan 7, separator 8, turbo-expander 9,
Water tank 10, check valve 11 and fuel tank 13；Hydrogen storage bottle 1 is exported equipped with high pressure hydrogen；Hydrogen-oxygen fuel cell 3 enters equipped with anodic gas
Mouth, cathode gas inlet, power output port and offgas outlet；Separator 8 is equipped with gas access, the gentle body of liquid water out
Outlet；Fuel tank 13 is equipped with inert gas entrance and gas vent；Water tank 10 is equipped with entrance and exit.
The entrance of 2 hot-side channel of First Heat Exchanger introduces the cathode gas of engine bleed, outlet and hydrogen-oxygen fuel cell 3
Entrance is connected；The high pressure hydrogen outlet of the anodic gas entrance of hydrogen-oxygen fuel cell 3 and hydrogen storage bottle 1 is connected, power output port
It is connected with external aircraft electrical equipment 4；The hot side of the offgas outlet of hydrogen-oxygen fuel cell 3, the first compressor 5, the second heat exchanger 6
Channel, separator 8 gas access be sequentially connected；Gas vent, turbo-expander 9, check valve 11, the oil of separator 8
The inert gas entrance of case 13 is sequentially connected；The liquid water out of separator 8 is connected with the entrance of water tank 10, water tank 10
Outlet be connected with external watering equipment 12.
The shaft of turbo-expander 9 is coaxially connected with the shaft of the first compressor 5, the shaft of fan 7 respectively, wherein whirlpool
Wheel expanding machine 9 supplies power to the first compressor 5 and fan for cooling down to the gas being discharged in separator 8
7, the first compressor 5 and fan 7 is driven to work.
The entrance of second heat exchanger, 6 cold side channel connects ram-air, the outlet of 6 cold side channel of the second heat exchanger, fan 7,
The entrance of 2 cold side channel of First Heat Exchanger is connected；The outlet of 2 cold side channel of First Heat Exchanger, the gas vent of fuel tank 13 connect
Atmosphere outside.
The invention also discloses it is a kind of based on this using high pressure water separation regenerative air cycle cooling system fuel tanker inerting unit working method,
Detailed process is as follows:
1 li of hydrogen and the engine bleed after the cooling of First Heat Exchanger 2 are anti-in hydrogen-oxygen fuel cell 3 hydrogen storage bottle
It answers, consumption oxygen generates water simultaneously, reacts the electric energy input external power supply equipment 4 of generation, and the tail gas of reaction is calmed the anger by first
Machine 5, the second heat exchanger 6 and separator 8, the liquid water and dry inert gas isolated, wherein liquid water is by storage
Water tank 10 supplies external watering equipment 12 after storing, dry inert gas is after the cooling of turbo-expander 9 by check valve 11
It is mixed into 13 gas-phase space of fuel tank to reduce fuel tank gas-phase space oxygen concentration.
2), embodiment 2:
As shown in Fig. 2, on the basis of embodiment 1 further including the second compressor 101 and the first motor 102；Second pressure
The air inlet joint chair cabin bleed of mechanism of qi 101, gas outlet are connected with the entrance of 2 hot-side channel of First Heat Exchanger；First motor 102
Shaft and the shaft of the second compressor 101 be coaxially connected, be used to provide power to the second compressor, drive its work.
The present embodiment is difference from example 1 is that using the second compressor 101 and the first motor 102 to cockpit
Bleed is compressed to replace engine bleed, it is possible to reduce influence of the engine bleed to engine performance reduces aircraft generation
Repay loss.
3, embodiment 3
As shown in figure 3, further including the second motor 201, fuel oil injector 202 and oil pump on the basis of embodiment 2
203；The shaft of second motor 201 and the shaft of the first compressor 5 are coaxially connected, for further providing for power to the first pressure
Mechanism of qi 5 drives its work；Fuel oil injector 202 is equipped with gas access, fuel filler and gas mixture outlet；Fuel tank 13 exists
Its bottom is additionally provided with gas mixture entrance and fuel outlet；Oil pump 203 is equipped with fuel filler and fuel outlet；Oil pump 203
Fuel filler is connected with the fuel outlet of fuel tank 13, and the fuel outlet of oil pump 203 and the fuel filler of fuel oil injector 202 connect
It connects；The gas access of fuel oil injector 202 is connected with the gas vent of check valve 11, the gas mixture of fuel oil injector 202
Outlet is connected with the gas mixture entrance of fuel tank 13；The inert gas entrance of fuel tank 13 is closed.
The present embodiment and embodiment 1 and embodiment 2 are the difference is that give the first compressor using the second motor 201
Water separative efficiency can be improved in 5 energy supplies, while being washed using fuel oil injector 202 and oil pump 203 to fuel oil and can reduce fuel oil
Dissolved oxygen and gas-phase space oxygen concentration reduce influence of the fuel oil dissolved oxygen to gas-phase space oxygen concentration.
Those skilled in the art can understand that unless otherwise defined, all terms used herein (including skill
Art term and scientific term) there is meaning identical with the general understanding of those of ordinary skill in the utility model fields
Justice.It should also be understood that those terms such as defined in the general dictionary should be understood that with upper with the prior art
The consistent meaning of meaning hereinafter, and unless defined as here, will not with idealization or meaning too formal come
It explains.
Above-described specific embodiment, to the purpose of this utility model, technical scheme and beneficial effects carried out into
One step is described in detail, it should be understood that being not used to limit the foregoing is merely specific embodiment of the present utility model
The utility model processed, within the spirit and principle of the utility model, any modification, equivalent substitution, improvement and etc. done,
It should be included within the scope of protection of this utility model.
Claims (3)
1. a kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system, which is characterized in that including hydrogen storage bottle (1), First Heat Exchanger
(2), hydrogen-oxygen fuel cell (3), the first compressor (5), the second heat exchanger (6), fan (7), separator (8), turbine expansion
Machine (9), water tank (10), check valve (11) and fuel tank (13)；
The hydrogen storage bottle (1) exports equipped with high pressure hydrogen；Hydrogen-oxygen fuel cell (3) is equipped with anodic gas entrance, cathode gas enters
Mouth, power output port and offgas outlet；Separator (8) is equipped with gas access, the gentle body outlet of liquid water out；Fuel tank
(13) inert gas entrance and gas vent are equipped with；Water tank (10) is equipped with entrance and exit；
The entrance of First Heat Exchanger (2) hot-side channel introduces the cathode of engine bleed, outlet and hydrogen-oxygen fuel cell (3)
Gas access is connected；
The high pressure hydrogen outlet of the anodic gas entrance of the hydrogen-oxygen fuel cell (3) and hydrogen storage bottle (1) is connected, electric energy output end
Mouth and external aircraft electrical equipment (4) connect；
The offgas outlet of the hydrogen-oxygen fuel cell (3), the first compressor (5), the second heat exchanger (6) hot-side channel, moisture
Gas access from device (8) is sequentially connected；
The gas vent of the separator (8), turbo-expander (9), check valve (11), fuel tank (13) inert gas entrance
It is sequentially connected；
The liquid water out of the separator (8) is connected with the entrance of water tank (10), the outlet and outside of water tank (10)
Watering equipment (12) is connected；
The shaft of the turbo-expander (9) is coaxially solid with the shaft of first compressor (5), the shaft of fan (7) respectively
Even, wherein the turbo-expander (9) is used to cool down to the gas being discharged in separator (8), supplies power to simultaneously
First compressor (5) and fan (7) drive the first compressor (5) and fan (7) to work；
The entrance of second heat exchanger (6) cold side channel connects ram-air, the outlet of the second heat exchanger (6) cold side channel, wind
Fan (7), the entrance of First Heat Exchanger (2) cold side channel is connected；
The outlet of First Heat Exchanger (2) cold side channel, the gas vent of fuel tank (13) connect atmosphere outside.
2. using the fuel tanker inerting unit of high pressure water separation regenerative air cycle cooling system as described in claim 1, which is characterized in that further include the second pressure
Mechanism of qi (101) and the first motor (102)；
The air inlet joint chair cabin bleed of second compressor (101), gas outlet and the First Heat Exchanger (2) hot-side channel
Entrance is connected；
The shaft of first motor (102) and the shaft of second compressor (101) are coaxially connected, and are used to provide power
To the second compressor, drive its work.
3. using the fuel tanker inerting unit of high pressure water separation regenerative air cycle cooling system as claimed in claim 2, which is characterized in that further include the second electricity
Motivation (201), fuel oil injector (202) and oil pump (203)；
The shaft of second motor (201) and the shaft of first compressor (5) are coaxially connected, for further providing for
Power gives first compressor (5), drives its work；
The fuel oil injector (202) is equipped with gas access, fuel filler and gas mixture outlet；The fuel tank (13) is at it
Bottom is additionally provided with gas mixture entrance and fuel outlet；Oil pump (203) is equipped with fuel filler and fuel outlet；
The fuel filler of the oil pump (203) is connected with the fuel outlet of the fuel tank (13), the fuel outlet of oil pump (203) and
The fuel filler of the fuel oil injector (202) connects；
The gas access of the fuel oil injector (202) is connected with the gas vent of the check valve (11), fuel oil injector
(202) gas mixture outlet is connected with the gas mixture entrance of the fuel tank (13)；
The inert gas entrance of the fuel tank (13) is closed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821437987.3U CN208931665U (en) | 2018-09-03 | 2018-09-03 | A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821437987.3U CN208931665U (en) | 2018-09-03 | 2018-09-03 | A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208931665U true CN208931665U (en) | 2019-06-04 |
Family
ID=66719709
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821437987.3U Expired - Fee Related CN208931665U (en) | 2018-09-03 | 2018-09-03 | A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208931665U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018387A (en) * | 2018-09-03 | 2018-12-18 | 南京航空航天大学 | A kind of fuel tanker inerting unit and its method using high pressure water separation regenerative air cycle cooling system |
-
2018
- 2018-09-03 CN CN201821437987.3U patent/CN208931665U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018387A (en) * | 2018-09-03 | 2018-12-18 | 南京航空航天大学 | A kind of fuel tanker inerting unit and its method using high pressure water separation regenerative air cycle cooling system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109018387A (en) | A kind of fuel tanker inerting unit and its method using high pressure water separation regenerative air cycle cooling system | |
| CN106741984B (en) | A kind of system and its working method of catalytic reforming inerting aircraft fuel tank | |
| US9731834B2 (en) | Aircraft systems and methods with integrated tank inerting and power generation | |
| CA2913553C (en) | Nitrogen enriched air generation and fuel tank inerting system | |
| US8499567B2 (en) | Hybrid fuel tank inerting system | |
| Lapeña-Rey et al. | First fuel-cell manned aircraft | |
| US20220131165A1 (en) | Aircraft electrical power supply system and method of supplying electrical power in an aircraft | |
| EP2923948B1 (en) | Aircraft systems and methods with green fuel tanks | |
| ES2657541T3 (en) | Integrated recirculation fuel cell system | |
| US20160257419A1 (en) | Method and Device for Inerting a Fuel Tank | |
| CN107867404A (en) | The apparatus and method of fuel tank inerting | |
| CN107140229A (en) | One kind is tethered at unmanned plane energy supplyystem | |
| CN112572806B (en) | Loop control and nitrogen control coupling system comprehensively utilizing aircraft cabin pressure and working method | |
| CN208931665U (en) | A kind of fuel tanker inerting unit using high pressure water separation regenerative air cycle cooling system | |
| CN207956079U (en) | A kind of oxygen consumption type inerting fuel tank residual neat recovering system | |
| Kallo et al. | Fuel cell system development and testing for aircraft applications | |
| CN112960124A (en) | Ring control and airborne nitrogen generation coupling system and working method | |
| CN112960125A (en) | Aircraft cabin environmental control and onboard nitrogen generation coupling system | |
| CN204558589U (en) | Based on the aircraft generating system of fuel cell | |
| CN207965700U (en) | The device of waste-heat power generation in a kind of fuel-tank inert gas system using aircraft | |
| CN211196653U (en) | Dry ice type inert gas making cooling type oil tank inerting system | |
| CN208530861U (en) | A kind of fuel-tank inert gas device for combining plasma and photocatalysis technology | |
| CN110803404B (en) | Integrated nitrogen injection oxygen control fireproof intelligent device | |
| CN113090387A (en) | Nuclear energy aircraft engine and aircraft | |
| CN208036635U (en) | The device of fuel tank inerting |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190604 Termination date: 20210903 |