CN101891017A - Fuel-tank inert gas control device - Google Patents
Fuel-tank inert gas control device Download PDFInfo
- Publication number
- CN101891017A CN101891017A CN2010102342626A CN201010234262A CN101891017A CN 101891017 A CN101891017 A CN 101891017A CN 2010102342626 A CN2010102342626 A CN 2010102342626A CN 201010234262 A CN201010234262 A CN 201010234262A CN 101891017 A CN101891017 A CN 101891017A
- Authority
- CN
- China
- Prior art keywords
- fuel
- tank
- inert gas
- fuel tank
- control device
- 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.)
- Granted
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Safety Valves (AREA)
Abstract
The invention relates to a fuel-tank inert gas control device, which belongs to the field of aero-technology. The fuel-tank inert gas control device comprises a small flow limit hole, a small flow pipeline, a small check valve, a safety valve, a large check valve, a pressure reducer, a large flow limit hole, a large flow pipeline, and a block valve and the like, wherein in the two inert gas pipelines, one is used for controlling the normally-open feeding of the inert gas with low oxygen content and low flow under the action of the flow limit holes, and the other one is used for controlling the discontinuous feeding of the inert gas with high oxygen content and large flow according to the pressure demands of the fuel tank through the cooperation of the flow limit holes, the pressure reducer and the block valve. Through the cooperation among the flow limit holes and the pressure reducer and the like, the fuel-tank inert gas control device has the advantages of realizing the oxygen content and pressure controls of the inert gas in the fuel tank, and improving the working reliability. Meanwhile, the oxygen content control of the inert gas in the fuel tank has a larger margin and can reduce the requirements for oxygen content of the feed gas when the plane drops, so the fuel-tank inert gas control device can reduce the scale of the air separator, and reduce the cost and weight thereof.
Description
Technical field
The invention belongs to the aeronautical technology field, relate to a kind of fuel-tank inert gas control device.
Background technology
Fuel-tank inert gas is to improve the aircraft safety important technique measure, and fuel-tank inert gas control then is to guarantee that the fuel-tank inert gas performance reaches the gordian technique of security requirement.The external flow control valve that adopts, the oxygen concentration and the suction quantity of control fuel-tank inert gas gas.Because state of flight changes complicated, flow control valve is in the adjusting mode of operation for a long time, and this is just very high to the functional reliability requirement of flow control valve, and particularly the home products reliability is lower, is difficult to satisfy actual requirement.
Summary of the invention
The present invention seeks to: in order to solve the control of prior art fuel-tank inert gas to flow control valve requirement height, the problem that reliability is low the invention provides a kind of flow control valve that do not adopt, and has the fuel-tank inert gas control device of higher reliability.
Technical solution of the present invention is: a kind of fuel-tank inert gas control device, it comprises the low discharge metering hole, the low discharge pipeline, little check valve, fuel tank, big check valve, pressure reducer, the large flow pipe road, big flow metering hole, shutoff valve, wherein, divide two-way from the air eliminator outlet, link to each other with fuel tank with the large flow pipe road through the low discharge pipeline respectively, be provided with low discharge metering hole and little check valve on the low discharge pipeline between described air eliminator and the fuel tank in turn, large flow pipe road between described air eliminator and the fuel tank begins to be provided with in turn shutoff valve from air eliminator, big flow metering hole, pressure reducer, big check valve, wherein, the low discharge pipeline is the flute pore structure at the end of fuel tank, and the large flow pipe road is open horn opening at the end of fuel tank.
Described pressure reducer is for being the relative pressure reducer of benchmark with the bar pressure.
Described fuel tank is provided with safety valve.
Described low discharge pipeline is the flute pore structure at the end of fuel tank.
Described large flow pipe road is open horn opening at the end of fuel tank.
Described low discharge pipeline is air inlet open in usual, and the discontinuous air inlet need be carried out according to tank pressure in described large flow pipe road.
Low discharge metering hole on the described low discharge pipeline is used to satisfy fuel tank, and peaceful to fly the stage less to the inerting charge flow rate mushing, but the lower control requirement of oxygen concentration.
Shutoff valve on the described large flow pipe road, big flow metering hole, that pressure reducer is used to satisfy fuel tank is bigger to the inerting charge flow rate in the aircraft decline stage, but the higher control requirement of oxygen concentration.
The invention has the beneficial effects as follows: fuel-tank inert gas control device of the present invention requires different characteristics in each stage of aircraft flight to the inerting charge flow rate at fuel tank, fuel-tank inert gas is by the two-way air inlet, one road low discharge, continuous air inlet open in usual, the peaceful stage that flies uses for mushing, because this moment, charge flow rate was less, therefore the air inlet oxygen concentration is lower, and the control of fuel-tank inert gas oxygen concentration has bigger surplus capacity, thereby has alleviated the requirement of aircraft decline stage to the air inlet oxygen concentration; The big flow in another road, discontinuous air inlet, pressure reducer induction fuel tank pressure, when aircraft descends, fuel tank relative pressure step-down, pressure reducer is opened, the fuel tank plenum, when fuel tank pressure reached regulation, pressure reducer was closed, and fuel tank stops air inlet, because before aircraft descends, the fuel-tank inert gas oxygen concentration has big surplus capacity, so aircraft is when descending, and fuel-tank inert gas air inlet oxygen concentration can be higher relatively, corresponding flow is also bigger, as long as reach the requirement of fuel-tank inert gas oxygen concentration after the balance.Therefore fuel-tank inert gas control device of the present invention is simple in structure, can reduce the scale of air eliminator, cost-cutting, reduces weight, and regulates air inlet oxygen concentration and flow by metering hole, has higher safe reliability.
Description of drawings
Fig. 1 is principle of the invention figure.
Wherein 1: low discharge metering hole, 2: low discharge pipeline, 3: little check valve, 4: safety valve, 5: fuel tank, 6: big check valve, 7: pressure reducer, 8: large flow pipe road, 9: big flow metering hole, 10: shutoff valve, 11: air eliminator.
The specific embodiment
The present invention is further illustrated below by the specific embodiment:
See also Fig. 1.In the present embodiment, described fuel-tank inert gas control device comprises low discharge metering hole 1, low discharge pipeline 2, little check valve 3, safety valve 4, fuel tank 5, big check valve 6, pressure reducer 7, large flow pipe road 8, big flow metering hole 9, shutoff valve 10.Wherein, divide two-way, link to each other with fuel tank 5 with large flow pipe road 8 through low discharge pipeline 2 respectively from air eliminator 11 outlets.Be provided with low discharge metering hole 1 and little check valve 3 on the low discharge pipeline 2 between described air eliminator 11 and the fuel tank 5 in turn, wherein, described low discharge pipeline 2 is the flute pore structure at the end of fuel tank 5, promptly has row's flute hole exits, so that low discharge pipeline 2 is to fuel tank 5 even air feed.Large flow pipe road 8 between described air eliminator 11 and the fuel tank 5 is provided with shutoff valve 10, big flow metering hole 9, pressure reducer 7, big check valve 6 in turn from air eliminator 11 beginnings, wherein, large flow pipe road 8 is open horn opening at the end of fuel tank 5, thereby makes large flow pipe road 8 air feed fast.In addition, described pressure reducer 7 is relative pressure reducer, is benchmark with the bar pressure, the control pressure that comes out, thus guarantee that fuel tank is with respect to atmosphere superpressure not.Described fuel tank is provided with safety valve 4.In the present embodiment, the described low discharge peaceful required inerting gas flow of stage that flies of promptly mushing, big flow is a required inerting gas flow of aircraft decline stage.
Inerting gas of the present invention is from air eliminator 11.Give fuel tank 5 inertings by 8 two admission lines of low discharge pipeline 2 and large flow pipe road.Low discharge pipeline 2 is given fuel tank 5 continuous air inlets open in usual by low discharge metering hole 1 and little check valve 3, and the peaceful stage that flies uses for mushing.Because this moment, charge flow rate was less, so the air inlet oxygen concentration is lower, the control of fuel-tank inert gas oxygen concentration has bigger surplus capacity.
When aircraft is in the decline stage, give fuel tank 5 air feed by large flow pipe road 8 by shutoff valve 10, big flow metering hole 9, pressure reducer 7 and big check valve 6, the peaceful inerting oxygen concentration control that flies the stage has bigger surplus capacity owing to mush, thereby can be used for alleviating of the requirement of aircraft decline stage, to satisfy fuel tank 5 requirement to inerting in the aircraft decline stage to the air inlet oxygen concentration.
During actual the use, fuel-tank inert gas control device of the present invention is at first according to aircraft task envelope curve, calculate and test the peaceful fuel tank 5 inerting requirements such as phase fuel case 5 inerting charge flow rates, gas oxygen concentration, decline stage fuel tank 5 inerting charge flow rates, gas oxygen concentration that fly of determining respectively to climb by theory.
According to fuel tank 5 inerting charge flow rates, gas oxygen concentration requirement, calculate and test scale, low discharge metering hole 1 and the size of big flow metering hole 9 and the performance of pressure reducer 7 and safety valve 4 of determining air eliminator 11 respectively by theory then.
Calculate by theory and test determines that fuel tank 5 initial inertings reach the time of regulation requirement again, and determine the switch control logic of shutoff valve 10 according to this time, promptly when shutoff valve 10 is opened.
And when the initial inerting in fuel tank 5 ground reached the inerting oxygen concentration of regulation and pressure and requires, shutoff valve 10 was opened.Pressure reducer 7 induction fuel tanks 5 pressure, in the aircraft decline stage, fuel tank 5 relative pressure step-downs, pressure reducer 7 is opened, by the effect of big flow metering hole 9, from the big flow of air eliminator 11 but the higher inerting gas of oxygen concentration, through large flow pipe road 8, shutoff valve 10, big flow metering hole 9, pressure reducer 7 and big check valve 6, enter fuel tank 5, make fuel tank 5 reach the inerting oxygen concentration and the pressure requirement of regulation.When fuel tank 5 pressure reached regulation, pressure reducer 7 was closed, and fuel tank 5 stops air inlet.
During for fear of initial inerting, fuel tank 5 pressure are lower, and pressure reducer 7 is opened air inlet, on large flow pipe road 8 shutoff valve 10 are set.By the 2 initial inertings of low discharge pipeline during to the pressure stipulated, shutoff valve 10 is opened at fuel tank 5. Big check valve 6 and 3 of little check valves are to prevent fuel tank 5 IFO intermediate fuel oil and steam contamination air eliminator 11 thereof.When stage of mushing or system failure fuel tank 5 superpressures, safety valve 4 is opened exhaust, fuel tank 5 releases.
In sum, fuel-tank inert gas control device of the present invention is by the parallel gas feed inerting to fuel tank of low discharge pipeline and large flow pipe road, particularly pass through the low discharge metering hole 1 and the little check valve 3 of low discharge pipeline 2, give fuel tank 5 continuous air inlets open in usual, the peaceful stage that flies uses for mushing.Because this moment, charge flow rate was less, so the air inlet oxygen concentration is lower, the control of fuel-tank inert gas oxygen concentration has bigger surplus capacity.Utilize this surplus capacity to be reduced in of the control requirement of aircraft decline stage then to the inerting oxygen concentration.Like this, can reduce the scale of air eliminator, cost-cutting, reduce weight.Regulate air inlet oxygen concentration and flow by metering hole simultaneously, can improve system reliability.
Claims (8)
1. fuel-tank inert gas control device, it is characterized in that: comprise low discharge metering hole (1), low discharge pipeline (2), little check valve (3), fuel tank (5), big check valve (6), pressure reducer (7), large flow pipe road (8), big flow metering hole (9), shutoff valve (10) and air eliminator (11), wherein, air eliminator (11) is divided into two-way outlet, link to each other with fuel tank (5) with large flow pipe road (8) through low discharge pipeline (2) respectively, be provided with low discharge metering hole (1) and little check valve (3) on the low discharge pipeline (2) between described air eliminator (11) and the fuel tank (5) in turn, large flow pipe road (8) between described air eliminator (11) and the fuel tank (5) is provided with shutoff valve (10) in turn from air eliminator (11) beginning, big flow metering hole (9), pressure reducer (7), big check valve (6), wherein, the large flow pipe road is open horn opening at the end of fuel tank.
2. fuel-tank inert gas control device according to claim 1 is characterized in that: described pressure reducer (7) is for being the relative pressure reducer of benchmark with the bar pressure.
3. fuel-tank inert gas control device according to claim 2 is characterized in that: described fuel tank is provided with safety valve (4).
4. fuel-tank inert gas control device according to claim 3 is characterized in that: described low discharge pipeline is the flute pore structure at the end of fuel tank (5).
5. fuel-tank inert gas control device according to claim 4 is characterized in that: described large flow pipe road (2) is open horn opening at the end of fuel tank (5).
6. according to each described fuel-tank inert gas control device of claim 1 to 5, it is characterized in that: described low discharge pipeline (2) is air inlet open in usual, and the discontinuous air inlet need be carried out according to tank pressure in described large flow pipe road (8).
7. fuel-tank inert gas control device according to claim 6, it is characterized in that: the low discharge metering hole (1) on the described low discharge pipeline (2) is used to satisfy fuel tank, and peaceful to fly the stage less to the inerting charge flow rate mushing, but the lower control requirement of oxygen concentration.
8. fuel-tank inert gas control device according to claim 6, it is characterized in that: the shutoff valve (10) on the described large flow pipe road (8), big flow metering hole (9), that pressure reducer (7) is used to satisfy fuel tank is bigger to the inerting charge flow rate in the aircraft decline stage, but the higher control requirement of oxygen concentration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102342626A CN101891017B (en) | 2010-07-20 | 2010-07-20 | Fuel-tank inert gas control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102342626A CN101891017B (en) | 2010-07-20 | 2010-07-20 | Fuel-tank inert gas control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101891017A true CN101891017A (en) | 2010-11-24 |
| CN101891017B CN101891017B (en) | 2013-04-10 |
Family
ID=43100402
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010102342626A Active CN101891017B (en) | 2010-07-20 | 2010-07-20 | Fuel-tank inert gas control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101891017B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102175446A (en) * | 2011-02-24 | 2011-09-07 | 西北工业大学 | Detection device for safety valve assembly |
| CN104015929A (en) * | 2013-02-28 | 2014-09-03 | 空中客车营运有限公司 | Aircraft fuel tank arrangement |
| CN104520194A (en) * | 2012-08-24 | 2015-04-15 | 波音公司 | Aircraft fuel tank flammability reduction method and system |
| CN105151314A (en) * | 2015-08-25 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Operation method for fuel oil system |
| CN105404722A (en) * | 2015-10-30 | 2016-03-16 | 西北工业大学 | Method for analyzing influence of projectile impact on aircraft fuel tank inerting |
| US9567094B2 (en) | 2013-02-28 | 2017-02-14 | Airbus Operations Limited | Aircraft inerting system |
| US10000294B2 (en) | 2012-08-24 | 2018-06-19 | The Boeing Company | Aircraft fuel tank flammability reduction method and system |
| CN108190035A (en) * | 2017-12-15 | 2018-06-22 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of Inerting Aircraft Fuel Tanks device |
| CN109263845A (en) * | 2018-11-06 | 2019-01-25 | 南通中远海运川崎船舶工程有限公司 | The control main valve ventilation of room structure and method of ventilation of double fuel powered ship |
| CN109625298A (en) * | 2018-12-07 | 2019-04-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of oil gas isolating device and the aircraft with it |
| CN110697063A (en) * | 2019-11-05 | 2020-01-17 | 重庆交通大学 | Closed-loop aircraft fuel tank airborne inerting system |
| CN111038713A (en) * | 2019-12-23 | 2020-04-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Pressure regulating valve with constant pressure difference type parallel structure and regulating method |
| CN112298581A (en) * | 2020-10-30 | 2021-02-02 | 金陵科技学院 | Device and method for inerting oil tank of military unmanned aerial vehicle by using fuel oil backwashing |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1798687A (en) * | 2003-06-05 | 2006-07-05 | 液体空气乔治洛德方法利用和研究的具有监督和管理委员会的有限公司 | On-board system for generating and supplying oxygen and nitrogen |
| CN101708776A (en) * | 2009-12-04 | 2010-05-19 | 张星 | Inert system for civil airplane |
| EP2206646A2 (en) * | 2009-01-12 | 2010-07-14 | Hamilton Sundstrand Corporation | Dispatch critical fuel tank inerting system for aircraft |
| US20100176245A1 (en) * | 2009-01-14 | 2010-07-15 | Giorgio Isella | Cross ship architecture for dispatch critical fuel tank inerting system |
-
2010
- 2010-07-20 CN CN2010102342626A patent/CN101891017B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1798687A (en) * | 2003-06-05 | 2006-07-05 | 液体空气乔治洛德方法利用和研究的具有监督和管理委员会的有限公司 | On-board system for generating and supplying oxygen and nitrogen |
| EP2206646A2 (en) * | 2009-01-12 | 2010-07-14 | Hamilton Sundstrand Corporation | Dispatch critical fuel tank inerting system for aircraft |
| US20100176245A1 (en) * | 2009-01-14 | 2010-07-15 | Giorgio Isella | Cross ship architecture for dispatch critical fuel tank inerting system |
| CN101708776A (en) * | 2009-12-04 | 2010-05-19 | 张星 | Inert system for civil airplane |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102175446A (en) * | 2011-02-24 | 2011-09-07 | 西北工业大学 | Detection device for safety valve assembly |
| CN102175446B (en) * | 2011-02-24 | 2013-04-17 | 西北工业大学 | Detection device for safety valve assembly |
| CN104520194A (en) * | 2012-08-24 | 2015-04-15 | 波音公司 | Aircraft fuel tank flammability reduction method and system |
| CN104520194B (en) * | 2012-08-24 | 2016-01-13 | 波音公司 | Aircraft fuel tank comb. reduces method and system |
| US10000294B2 (en) | 2012-08-24 | 2018-06-19 | The Boeing Company | Aircraft fuel tank flammability reduction method and system |
| CN104015929A (en) * | 2013-02-28 | 2014-09-03 | 空中客车营运有限公司 | Aircraft fuel tank arrangement |
| US9567094B2 (en) | 2013-02-28 | 2017-02-14 | Airbus Operations Limited | Aircraft inerting system |
| US9969501B2 (en) | 2013-02-28 | 2018-05-15 | Airbus Operations Limited | Aircraft fuel tank arrangement |
| CN105151314A (en) * | 2015-08-25 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Operation method for fuel oil system |
| CN105151314B (en) * | 2015-08-25 | 2018-03-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of operating method of fuel system |
| CN105404722B (en) * | 2015-10-30 | 2018-06-05 | 西北工业大学 | A kind of method analyzed projectile impact and Inerting Aircraft Fuel Tanks are influenced |
| CN105404722A (en) * | 2015-10-30 | 2016-03-16 | 西北工业大学 | Method for analyzing influence of projectile impact on aircraft fuel tank inerting |
| CN108190035A (en) * | 2017-12-15 | 2018-06-22 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of Inerting Aircraft Fuel Tanks device |
| CN109263845A (en) * | 2018-11-06 | 2019-01-25 | 南通中远海运川崎船舶工程有限公司 | The control main valve ventilation of room structure and method of ventilation of double fuel powered ship |
| CN109625298A (en) * | 2018-12-07 | 2019-04-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of oil gas isolating device and the aircraft with it |
| CN110697063A (en) * | 2019-11-05 | 2020-01-17 | 重庆交通大学 | Closed-loop aircraft fuel tank airborne inerting system |
| CN110697063B (en) * | 2019-11-05 | 2020-12-11 | 重庆交通大学 | Closed-loop aircraft fuel tank airborne inerting system |
| CN111038713A (en) * | 2019-12-23 | 2020-04-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Pressure regulating valve with constant pressure difference type parallel structure and regulating method |
| CN111038713B (en) * | 2019-12-23 | 2023-06-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Pressure regulating valve with constant pressure difference type parallel structure and regulating method |
| CN112298581A (en) * | 2020-10-30 | 2021-02-02 | 金陵科技学院 | Device and method for inerting oil tank of military unmanned aerial vehicle by using fuel oil backwashing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101891017B (en) | 2013-04-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101891017B (en) | Fuel-tank inert gas control device | |
| CN105771115B (en) | The helicopter of addition water-based extinguishing agent goes out mountain fire method | |
| CN206386680U (en) | From the LNG fluid reservoir control pressure systems of supercharging | |
| CN112644721B (en) | Aircraft oil supply and delivery system and control method thereof | |
| NZ599862A (en) | Vapor recovery pump regulation of pressure to maintain air to liquid ratio | |
| CN201765910U (en) | Constant pressure oil supplement device | |
| CN106081132A (en) | Fuel power many rotor wing unmanned aerial vehicles fuel feeding scheme | |
| CN106402462A (en) | Composite waterproof hammer air valve group with rear adjustment type separate orifices | |
| CN202157370U (en) | Compensation tank type no negative pressure water supply device | |
| CN101761394B (en) | Negative overload resistant double-chamber oil supply device and method thereof | |
| CN201706199U (en) | Residual pulp pneumatic automatic conveying device | |
| CN103573753A (en) | Transient test loop of hydraulic valve | |
| CN205837214U (en) | A kind of fuel power many rotor wing unmanned aerial vehicles fuel feeding scheme | |
| CN102062242A (en) | Gas pressure regulator | |
| CN207989200U (en) | Linkage type major-minor fuel tank oil supply system | |
| CN204587753U (en) | A kind of nitrogen seal device for storage tank | |
| CN102791615A (en) | A system for reduction a system for reduction of emissions from volatile liquid cargo | |
| CN104843360A (en) | Nitrogen sealing device for storage tank and use method of nitrogen sealing device | |
| CN104648679A (en) | Oil sump tank layout structure of aviette | |
| CN208252908U (en) | A kind of pilot-operated type unloading overflow valve | |
| CN203052208U (en) | Conveying device from multiple storage tanks to multiple pumps | |
| CN206202279U (en) | A kind of pneumatic control device for locomotive emergency brake | |
| CN101852334B (en) | Pneumatic and automatic conveying device for residual slurry | |
| CN207072449U (en) | A kind of single head soda acid weighing filling machine | |
| CN201672243U (en) | Device of LNG filling station with automatic pressure reducing function |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |