CN110498057B - Jet fuel oiling system of polar region ship helicopter - Google Patents
Jet fuel oiling system of polar region ship helicopter Download PDFInfo
- Publication number
- CN110498057B CN110498057B CN201910807435.XA CN201910807435A CN110498057B CN 110498057 B CN110498057 B CN 110498057B CN 201910807435 A CN201910807435 A CN 201910807435A CN 110498057 B CN110498057 B CN 110498057B
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- pipeline
- oil
- cabin
- aviation kerosene
- valve
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- 239000000446 fuel Substances 0.000 title claims abstract description 26
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 51
- 239000003350 kerosene Substances 0.000 claims abstract description 46
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 23
- 239000003921 oil Substances 0.000 claims description 37
- 238000010438 heat treatment Methods 0.000 claims description 11
- 230000003068 static effect Effects 0.000 claims description 9
- 238000001914 filtration Methods 0.000 claims description 5
- 239000000295 fuel oil Substances 0.000 claims description 4
- 239000007789 gas Substances 0.000 claims description 4
- 239000006249 magnetic particle Substances 0.000 claims description 4
- 239000003063 flame retardant Substances 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 230000009471 action Effects 0.000 claims description 2
- 230000005389 magnetism Effects 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 7
- 108010066057 cabin-1 Proteins 0.000 description 6
- 238000011835 investigation Methods 0.000 description 6
- 238000009423 ventilation Methods 0.000 description 6
- 229910001873 dinitrogen Inorganic materials 0.000 description 5
- 238000005485 electric heating Methods 0.000 description 4
- 239000002828 fuel tank Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 230000005611 electricity Effects 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000004793 Polystyrene Substances 0.000 description 1
- 239000004964 aerogel Substances 0.000 description 1
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 239000004794 expanded polystyrene Substances 0.000 description 1
- 230000009970 fire resistant effect Effects 0.000 description 1
- 229910052736 halogen Inorganic materials 0.000 description 1
- -1 halogen ion Chemical class 0.000 description 1
- 229920001903 high density polyethylene Polymers 0.000 description 1
- 239000004700 high-density polyethylene Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000011490 mineral wool Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 229920002223 polystyrene Polymers 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B17/00—Vessels parts, details, or accessories, not otherwise provided for
- B63B17/0027—Tanks for fuel or the like ; Accessories therefor, e.g. tank filler caps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/28—Liquid-handling installations specially adapted for fuelling stationary aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
The invention discloses a helicopter jet fuel oiling system for a polar region ship, which comprises the following components: a aviation kerosene tank; the fire-retarding and air-permeable cap is connected with the aviation kerosene cabin through a flange or a thread, and is arranged above the aviation kerosene cabin; the nitrogen filling inerting device is connected with the aviation kerosene cabin through a first valve and a first pipeline; the oil-submerged pump is connected with the aviation kerosene cabin through a second valve and a second pipeline; the oiling device is connected with the oil-submerged pump through a third valve and a third pipeline; the control device is connected with the nitrogen filling inerting device, the first valve, the oil-submerged pump, the second valve, the third valve and the oiling device. The aviation kerosene cabin is provided with a nitrogen filling inerting device, so that the oil storage capacity is large, and the safety of the oil cabin is high. The system equipment adopts a distributed arrangement design, is flexible to install and is suitable for complex ship structures.
Description
Technical Field
The invention relates to the technical field of refueling facilities, in particular to a jet fuel refueling system of a helicopter for a polar region ship.
Background
The polar science investigation is the embodiment of the comprehensive national force of a country and is highly valued by all countries of the world all the time; the polar science investigation ship is an important capability support for carrying out polar science investigation, a helicopter is usually arranged on the polar science investigation ship in order to expand polar science investigation capability and range, and a helicopter jet fuel oiling system is required to be arranged on the polar science investigation ship in order to enlarge the operation range and guarantee operation time of the helicopter.
Current integrated fueling facilities include mobile oil storage tanks, storage tank units, pump units, fueling devices. The movable oil storage tank and the oiling device are all integral equipment; the storage tank unit and the pump unit are fixed on the same base to form an integrated device; the storage tank unit is connected with the pump unit through a hose; the pump unit is connected with the oiling device through a hard pipe. The facility can be used for oil guarantee of the offshore helicopter, but has the problems of small fuel oil reserves, high integral installation requirement, single oiling operation, incapability of adapting to polar environment and the like, so that the facility cannot be used for oil guarantee of the polar ship helicopter.
Therefore, it is necessary to develop a polar ship helicopter jet fuel refueling system which has large oil storage capacity, high safety, flexible installation and adaptability to polar conditions.
Disclosure of Invention
Therefore, the embodiment of the invention provides a jet fuel refueling system of a polar region ship helicopter, which aims to solve the problems of small fuel oil reserves, high integral installation requirement, single refueling operation and incapability of adapting to polar region environments in polar region refueling facilities in the prior art.
The embodiment of the invention provides a jet fuel oiling system of a polar region ship helicopter, which comprises the following components:
a aviation kerosene tank;
The fire-retarding and air-permeable cap is connected with the aviation kerosene cabin through a flange or a thread, and is arranged above the aviation kerosene cabin;
the nitrogen filling inerting device is connected with the aviation kerosene cabin through a first valve and a first pipeline;
The oil-submerged pump is connected with the aviation kerosene cabin through a second valve and a second pipeline;
the oiling device is connected with the oil-submerged pump through a third valve and a third pipeline;
the control device is connected with the nitrogen filling inerting device, the first valve, the oil-submerged pump, the second valve, the third valve and the oiling device.
Optionally, the first pipe, the second pipe, and the third pipe are 316L double-walled pipes.
Optionally, the method further comprises: the heating module is paved outside the first pipeline, the second pipeline and the third pipeline;
And the heat insulation layer is covered outside the heating module.
Optionally, the fire-blocking and air-permeable cap is an electrically heated fire-blocking and air-permeable cap.
Optionally, the oiling device comprises: filter separator, flow sensor, pressure sensor, static eliminating pipe, oiling hose and reel.
Optionally, the method further comprises: and the magnetic starting device is connected with the oil-submerged pump.
Optionally, the method further comprises: the nitrogen filling inerting device is connected with the output ends of the nitrogen filling inerting device, the filtering separator, the flow sensor and the pressure sensor; the output serial port of the microprocessor is connected with the input end of the display screen.
Optionally, the aviation kerosene tank, the nitrogen filling inerting device and the oil submerged pump are arranged on the lower deck of the ship;
the oiling device is on the deck of the ship and around the deck of the helicopter;
The magnetic starting device and the oil-submerged pump are arranged in the same cabin;
The display screen and the oiling device are arranged in the same cabin.
Optionally, the method further comprises: one end of the oil return pipe is connected with an oil return pipe orifice of the oiling device, and the other end of the oil return pipe is connected with an oil return inlet of the aviation kerosene tank.
Optionally, the method further comprises:
The first interface of the three-way pipeline is connected with one end of the second pipeline, which is close to the aviation kerosene tank, the second interface of the three-way pipeline is connected with one end of the second pipeline, which is close to the oil submerged pump, and the third interface of the three-way pipeline is connected with the closed pipeline through a flange;
the soft magnetic disc is arranged at the joint of the three-way pipeline, which is close to the aviation kerosene tank; the soft magnetic disc is provided with a plurality of through holes; the outer diameter of the soft magnetic disc is equal to the inner diameter of the second pipeline;
The permanent magnet is arranged in the closed pipeline of the three-way pipeline;
three electromagnets are arranged around the outside of the second pipeline corresponding to the soft magnetic disc at 120 degrees.
The embodiment of the invention has the beneficial effects that:
1. the aviation kerosene cabin is provided with a nitrogen filling inerting device, so that the oil storage capacity is large, and the safety of the oil cabin is high. The system equipment adopts a distributed arrangement design, is flexible to install and is suitable for complex ship structures.
2. The oil pump can be controlled by local and remote start and stop, so that the safety and convenience of operation are ensured.
3. The aviation kerosene cabin adopts an electric heating ventilation cap, and the pipeline adopts a 316L double-wall pipe accompanied by a heating device, so that the system can be ensured to adapt to the polar working environment condition.
Drawings
The features and advantages of the present invention will be more clearly understood by reference to the accompanying drawings, which are illustrative and should not be construed as limiting the invention in any way, in which:
FIG. 1 illustrates a block diagram of a polar marine helicopter jet fuel fueling system in accordance with an embodiment of the present invention;
FIG. 2 illustrates a three-way pipeline configuration of a polar marine helicopter jet fuel fueling system in accordance with an embodiment of the present invention;
FIG. 3 illustrates another three-way pipeline configuration of a polar marine helicopter jet fuel fueling system in accordance with an embodiment of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
The embodiment of the invention provides a jet fuel oiling system of a polar region ship helicopter, which is shown in fig. 1 and comprises the following components: 1 of aviation kerosene tank, fire-retardant ventilation cap 2, nitrogen gas fills inerting device 3, oil-submerged pump 4, oiling device 5 and controlling means 6, wherein: the fire-retarding and air-permeable cap 2 is connected with the aviation kerosene cabin 1 through a flange or a thread, and the fire-retarding and air-permeable cap 2 is arranged above the aviation kerosene cabin 1; the nitrogen filling inerting device 3 is connected with the aviation kerosene tank 1 through a first valve and a first pipeline 101; the oil-submerged pump 4 is connected with the aviation kerosene tank 1 through a second valve and a second pipeline 102; the oiling device 5 is connected with the oil-submerged pump 4 through a third valve and a third pipeline 103; the control device 6 is connected with the nitrogen filling inerting device 3, the first valve, the oil-submerged pump, the second valve, the third valve and the oiling device.
In this embodiment, the aviation kerosene tank 1 is part of the tank structure, and no external oil storage tank is required.
The control device 6 is a computer or other terminals with processing capability, is connected with each valve in a wired or wireless way, controls the nitrogen filling inerting system to fill nitrogen into the aviation kerosene cabin, so that the oxygen content in the aviation kerosene cabin is maintained below 5%, and the safe inerting of the gas at the upper part of the aviation kerosene cabin is ensured; and the safety and convenience of the operation can be ensured through local or remote start-stop control. In this embodiment, only the conventional function of the control device 6 is adopted to realize the start-stop control of the equipment, and no special requirements are imposed on model parameters and the like of the control device 6, and in a specific implementation process, only the conventional control module in the prior art is adopted.
As an alternative embodiment, the first, second and third pipes are 316L double-walled pipes.
In the embodiment, the 316L double-wall pipe has good pitting corrosion resistance, and can be safely applied to halogen ion environments containing Cl and the like; and simultaneously, the hot cracking tendency during welding can be reduced.
As an alternative embodiment, further comprising: the heating module is paved outside the first pipeline, the second pipeline and the third pipeline; and the heat insulation layer is covered outside the heating module. The pipeline adopts a 316L double-wall pipe and is accompanied by a heating device, so that the system can be ensured to adapt to the polar working environment condition.
In the embodiment, the HDPE double-wall pipe is not broken in the environment of minus 60 ℃, the polar environment temperature is extremely low, and the heating module is arranged to keep the temperature of the double-wall pipe above minus 60 ℃ so that the double-wall pipe is not broken, and the use reliability is improved; the heat insulating layer is made of vacuum heat insulating plate, aerogel, foamed polyurethane, extruded polystyrene board, expanded polystyrene board, rock wool board or composite magnesium aluminum silicate heat insulating material, so as to improve heat insulating performance.
As an alternative embodiment, the firestop gas-permeable cap 2 is an electrically heated firestop gas-permeable cap.
In this embodiment, the electrically heated gas permeable cap is used to accommodate the cold environment of the polar region so that it can work normally. The electric heating fire-resistant ventilation cap maintains the pressure difference of the air pressure at the inner periphery and the outer periphery of the aviation kerosene cabin 1, maintains the inerting state of the inner part through the positive pressure in the aviation kerosene cabin 1, and simultaneously keeps the ventilation holes from being frozen through heating. The aviation kerosene cabin adopts an electric heating ventilation cap, so that the system can be ensured to adapt to the polar working environment condition.
As an alternative embodiment, the oiling device 5 includes: filter separator, flow sensor, pressure sensor, static eliminating pipe, oiling hose and reel.
In this embodiment, the filtering separator is used for purifying fuel, the flow sensor and the pressure sensor are used for measuring the flow and pressure of the fuel, the model parameters of the flow sensor and the pressure sensor are not particularly required, and the conventional functions and connection modes are adopted in the technical scheme; the static eliminating pipe is arranged on the outlet pipe of the filter to eliminate a large amount of static electricity accumulated due to the increase of the mutual friction area of oil liquid and the filter element of the filter, so as to avoid fire caused by static spark; the filler hose and reel are connected to the outlet of the filler device for connection to the helicopter's tank.
As an alternative embodiment, further comprising: and the magnetic starting device 7 is connected with the oil-submerged pump 4.
In the present embodiment, the operator performs start-stop control of the oil pump in the oil pump unit 4 by operating the magnetic start device.
As an alternative embodiment, further comprising: the nitrogen filling inerting device is connected with the output ends of the nitrogen filling inerting device, the filtering separator, the flow sensor and the pressure sensor; the output serial port of the microprocessor is connected with the input end of the display screen.
In this embodiment, the microprocessor is configured to collect status information parameters of the nitrogen gas filling inerting device, the filtering separator, the flow sensor and the pressure sensor, for example, collect a flow of nitrogen gas discharged from the nitrogen gas filling inerting device, calculate a nitrogen gas ratio in the discharged-fuel tank and the fueling device, and calculate an oxygen ratio; collecting filter differential pressure and fuel throughput information of the filter separator to determine whether the filter separator is operating properly; collecting the output of a flow sensor, and monitoring the fuel flow in the process of refueling in real time; the pressure sensor is arranged at the bottommost part of the oiling device and is used for detecting the pressure of a system in a pipeline, preventing the overpressure at the tail end of the pipeline and preventing the excessive differential pressure of fuel supplied to a helicopter fuel tank.
The display screen is used for displaying information parameters of each sensor in the nitrogen filling inerting system and the oiling device. In a specific embodiment, the display screen is a touch screen, or input devices such as a keyboard and a mouse are additionally configured, and an operator operates the magnetic starting device to start and stop the oil pump in the oil pumping unit 4 through the touch screen or the devices such as the keyboard and the mouse. After the aircraft flies in sky, static electricity can be accumulated, so that the static electricity is eliminated before oiling through the static eliminating pipe, and the ignition of fuel vapor caused by electric arc is avoided.
As an alternative embodiment, the aviation kerosene tank 1, the nitrogen filling inerting device 3 and the oil submerged pump are arranged on the lower deck of the ship; the oiling device 5 is on board the ship and around the helicopter deck; the magnetic starting device 7 and the oil-submerged pump 4 are arranged in the same cabin; the display screen is in the same cabin as the oiling device 5.
In this embodiment, the display screen and the fueling device are both disposed on the deck of the ship, so that the monitoring operation is facilitated while fueling.
As an alternative embodiment, further comprising: and one end of the oil return pipe 104 is connected with an oil return pipe opening of the oiling device 5, and the other end of the oil return pipe is connected with an oil return inlet of the aviation kerosene tank 1.
In this embodiment, a second oil pump is further provided in the middle of the oil return pipe, and after the helicopter finishes adding oil, the oil remaining in the oiling device 5 is guided back to the aviation kerosene tank 1. In a specific embodiment, since the refueling device is on the ship deck and the jet fuel tank is on the ship's lower deck, gravity can be relied upon to return the remaining fuel to the jet fuel tank.
As an alternative embodiment, as shown in fig. 2 and 3, the device further comprises a three-way pipeline, wherein a first interface of the three-way pipeline is connected with one end, close to the aviation kerosene cabin 1, of the second pipeline, a second interface of the three-way pipeline is connected with one end, close to the oil-submerged pump 4, of the second pipeline, and a third interface of the three-way pipeline is connected with the closed pipeline through a flange; the soft magnetic disc 201 is arranged at the interface of the three-way pipeline, which is close to the aviation kerosene cabin 1; the soft magnetic disc is provided with a plurality of through holes; the outer diameter of the soft magnetic disc is equal to the inner diameter of the second pipeline; permanent magnet 202, set up in the closed pipeline of the three-way pipe; three electromagnets 203 are disposed around the outside of the second pipe corresponding to the soft magnetic disk 201 at 120 °.
In this embodiment, the second pipe needs to be bent for connection due to the height difference between the aviation kerosene bunker and the oiling device. In a specific embodiment, the three-way pipe is a 45 ° connection. The electromagnet 203 is electrified to generate a magnetic field, so that the soft magnetic disc has magnetism and adsorbs magnetic particles in the fuel oil. The electromagnet 203 cuts off the power supply, and the magnetic particles fall into the closed pipeline under the action of gravity and are adsorbed by the permanent magnet 202.
In a specific embodiment, a valve is arranged at the third joint of the three-way pipeline, so that the three-way pipeline is convenient to detach and clean.
As an alternative embodiment, the first valve, the second valve and the third valve are electronic expansion valves.
In this embodiment, the electronic expansion valve includes a motor, a gear assembly, a valve stem assembly, and a valve seat assembly, wherein the valve seat assembly includes a valve seat and a valve seat insert disposed within the valve seat. The valve seat is provided with a valve port, a first interface connected with the inlet connecting pipe and a second interface connected with the outlet connecting pipe. The valve seat core divides the valve cavity of the valve seat into an inner cavity communicated with the valve port and an outer cavity surrounding the inner cavity, wherein the outer cavity is communicated with the inlet connecting pipe, the inner cavity is communicated with the outlet connecting pipe, and the peripheral wall of the valve seat core is provided with a circulation port capable of communicating the inner cavity and the outer cavity; thus, the opening and closing of the valve port controls the on-off of the inlet connecting pipe and the outlet connecting pipe, and the opening of the flow port controls the flow of the oil quantity.
According to the invention, the aviation kerosene tank is provided with the nitrogen filling inerting device, so that the oil storage capacity is large, the safety of the oil tank is high, meanwhile, the system equipment adopts a distributed arrangement design, the installation is flexible, and the system equipment is suitable for complex ship structures. The oil pump can be controlled by local and remote start and stop, so that the safety and convenience of operation are ensured. Moreover, the aviation kerosene cabin adopts an electric heating ventilation cap, and the pipeline adopts a 316L double-wall pipe accompanied by a heating device, so that the system can be ensured to adapt to the polar working environment condition.
Although embodiments of the present invention have been described in connection with the accompanying drawings, various modifications and variations may be made by those skilled in the art without departing from the spirit and scope of the invention, and such modifications and variations are within the scope of the invention as defined by the appended claims.
Claims (7)
1. A polar marine helicopter jet fuel fueling system comprising:
A aviation kerosene tank (1);
the fire-retarding breathable cap (2) is connected with the aviation kerosene cabin (1) through a flange or a thread, and the fire-retarding breathable cap (2) is arranged above the aviation kerosene cabin (1);
the nitrogen filling inerting device (3) is connected with the aviation kerosene cabin (1) through a first valve and a first pipeline;
The oil-submerged pump (4) is connected with the aviation kerosene cabin (1) through a second valve and a second pipeline;
The oiling device (5) is connected with the oil-submerged pump (4) through a third valve and a third pipeline;
the control device (6) is connected with the nitrogen filling inerting device (3), the first valve, the oil-submerged pump, the second valve, the third valve and the oiling device;
The heating module is paved outside the first pipeline, the second pipeline and the third pipeline;
A heat insulating layer covering the outside of the heating module;
The first interface of the three-way pipeline is connected with one end, close to the aviation kerosene cabin (1), of the second pipeline, the second interface of the three-way pipeline is connected with one end, close to the oil-submerged pump (4), of the second pipeline, and the third interface of the three-way pipeline is connected with the closed pipeline through a flange;
the soft magnetic disc is arranged at the interface of the three-way pipeline, which is close to the aviation kerosene cabin (1); the soft magnetic disc is provided with a plurality of through holes; the outer diameter of the soft magnetic disc is equal to the inner diameter of the second pipeline;
The permanent magnet is arranged in the closed pipeline of the three-way pipeline;
three electromagnets which are circumferentially arranged at 120 degrees outside the second pipeline corresponding to the soft magnetic disc;
Wherein the three-way pipeline is connected at 45 degrees; electrifying the electromagnet to generate a magnetic field, so that the soft magnetic disc has magnetism and is used for adsorbing magnetic particles in fuel oil; disconnecting the power supply connected with the electromagnet, and enabling the magnetic particles to fall into the closed pipeline under the action of gravity and then be adsorbed by the permanent magnet;
the aviation kerosene cabin (1), the nitrogen filling inerting device (3) and the oil-submerged pump are arranged on the lower deck of the ship;
-said refueling device (5) is on board and around the deck of the helicopter;
The magnetic starting device (7) and the oil-submerged pump (4) are arranged in the same cabin;
The display screen and the oiling device (5) are arranged in the same cabin.
2. The polar marine helicopter jet fuel refuelling system of claim 1, wherein the first, second, and third conduits are 316L double wall pipes.
3. The polar region marine helicopter jet fuel refuelling system according to claim 1, wherein said fire-retardant gas permeable cap (2) is an electrically heated fire-retardant gas permeable cap.
4. The polar region marine helicopter jet fuel refuelling system according to claim 1, characterized in that said refuelling device (5) comprises: filter separator, flow sensor, pressure sensor, static eliminating pipe, oiling hose and reel.
5. The polar marine helicopter jet fuel refuelling system of claim 4, further comprising: and the magnetic starting device (7) is connected with the oil-submerged pump (4).
6. The polar marine helicopter jet fuel refuelling system of claim 5, further comprising: the nitrogen filling inerting device comprises a display screen and a microprocessor, wherein a plurality of input serial ports of the microprocessor are connected with the output ends of the nitrogen filling inerting device (3), a filtering separator, a flow sensor and a pressure sensor; and the output serial port of the microprocessor is connected with the input end of the display screen.
7. The polar region marine helicopter jet fuel refuelling system of claim 1, further comprising: one end of the oil return pipe is connected with an oil return pipe orifice of the oiling device (5), and the other end of the oil return pipe is connected with an oil return inlet of the aviation kerosene cabin (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910807435.XA CN110498057B (en) | 2019-08-29 | 2019-08-29 | Jet fuel oiling system of polar region ship helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910807435.XA CN110498057B (en) | 2019-08-29 | 2019-08-29 | Jet fuel oiling system of polar region ship helicopter |
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| Publication Number | Publication Date |
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| CN110498057A CN110498057A (en) | 2019-11-26 |
| CN110498057B true CN110498057B (en) | 2024-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910807435.XA Active CN110498057B (en) | 2019-08-29 | 2019-08-29 | Jet fuel oiling system of polar region ship helicopter |
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| CN207955968U (en) * | 2018-02-02 | 2018-10-12 | 上海锆卓船舶设计有限公司 | A kind of sea ships and light boats fuel loading system and ocean platform |
| CN209096993U (en) * | 2018-10-31 | 2019-07-12 | 兴化市东方船舶设计有限公司 | A kind of fuel system of ship |
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| CN202807106U (en) * | 2012-09-12 | 2013-03-20 | 陕西鼓风机集团西安锅炉有限责任公司（西安特种汽车厂） | Fuel supply system of plane refueling vehicle |
| CN207809808U (en) * | 2018-02-02 | 2018-09-04 | 上海锆卓船舶设计有限公司 | A kind of helicopter oiling relief system and its ocean platform, ship |
| CN210364429U (en) * | 2019-08-29 | 2020-04-21 | 中国极地研究中心(中国极地研究所) | Helicopter jet fuel refueling system for polar region ship |
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