CN111038712A - Intermediate oil supply device of fuel oil system - Google Patents
Intermediate oil supply device of fuel oil system Download PDFInfo
- Publication number
- CN111038712A CN111038712A CN201911304366.7A CN201911304366A CN111038712A CN 111038712 A CN111038712 A CN 111038712A CN 201911304366 A CN201911304366 A CN 201911304366A CN 111038712 A CN111038712 A CN 111038712A
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- China
- Prior art keywords
- oil
- fuel
- box body
- tank
- supercharging
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- 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.)
- Pending
Links
- 239000003921 oil Substances 0.000 title claims abstract description 70
- 239000000295 fuel oil Substances 0.000 title claims abstract description 54
- 239000000446 fuel Substances 0.000 claims abstract description 48
- 230000000903 blocking effect Effects 0.000 claims description 6
- 230000036544 posture Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 7
- 239000007788 liquid Substances 0.000 description 6
- 238000000926 separation method Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 239000013049 sediment Substances 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 229910000975 Carbon steel Inorganic materials 0.000 description 1
- 239000010962 carbon steel Substances 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/14—Filling or emptying
- B64D37/20—Emptying systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention discloses an intermediate oil supply device of a fuel system, which relates to the technical field of aviation and comprises a box body, an anti-leakage device, an alarm device, an oil inlet, an oil outlet, a supercharging device, a fuel grid device, a settling tank, an oil drain valve and a box body mounting bracket, wherein the anti-leakage device is arranged on the box body; the middle oil supply device of the fuel oil system has the advantages of simple and reliable structure, high stability, adaptability to various flight conditions and flight postures, and capability of ensuring that the aircraft fuel oil system supplies oil to the turboprop engine more accurately and stably, thereby ensuring the normal and stable operation of the engine.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to an intermediate oil supply device of a fuel system.
Background
Aircraft fuel systems are also known as external fuel systems because the engine also has a system for delivering fuel to the combustion chamber, which is known as an internal fuel system. The heart of the airplane, the engine, relies on the heat generated by the combustion of fuel oil to do work and push the airplane to fly. Fuel is the energy source of the aircraft and the fuel system is the supply system for the aircraft energy source.
The fuel system mainly has the following functions: storing the fuel oil; fuel is safely and reliably delivered to the engine and APU under prescribed flight conditions; the position of the center of gravity is adjusted to keep the balance of the airplane and the stress of the wing structure.
There are two main types of engines used by general aviation aircraft: aviation piston engines and aviation turboprop engines. Because the aviation turboprop engine has great advantages compared with an aviation piston engine, the piston engine airplane is modified into the aviation turboprop engine on a large scale. However, the fuel system of the aviation piston engine is simple in structure and insufficient in stability, so that the requirements of the aviation turboprop engine on the fuel system are difficult to meet, the accurate and stable fuel supply to the turboprop engine cannot be guaranteed, and the requirements of an airplane on the fuel system in various flight states cannot be met, so that the fuel system of the aviation piston engine needs to be improved.
Disclosure of Invention
In order to solve the problems, the technical scheme adopted by the invention is as follows:
an intermediate oil supply device of a fuel system is characterized by comprising a box body, an oil inlet and an oil outlet which are arranged at one side of the box body, and a supercharging device and a fuel oil blocking device which are arranged inside the box body;
the oil inlet is communicated with the box body; the supercharging device is communicated with the oil outlet;
the supercharging device comprises a first supercharging device and a second supercharging device;
the first supercharging device and the second supercharging device are arranged in a vertically staggered mode.
Furthermore, the top of the box body is provided with a leakage-proof device;
one end of the leakage-proof device is communicated with the outside of the box body;
the other end of the leakage-proof device is communicated with the inside of the box body.
Further, the leakage-proof device is a floating switch, and the floating switch is communicated with the ventilation pipeline.
Further, the supercharging device is an electric fuel oil supercharging pump.
Furthermore, the number of the fuel oil gear separating devices is more than 2.
Furthermore, a first flow guide hole is formed in the middle of the fuel oil separation device, a second flow guide hole is formed in the edge of the fuel oil separation device, and the diameter of the first flow guide hole is larger than that of the second flow guide hole.
Furthermore, the box body structure also comprises an alarm system, wherein the alarm system comprises an alarm device arranged at the top of the box body, a controller connected with the alarm device and an alarm indicator lamp connected with the controller in a control mode.
Furthermore, the bottom of the box body is provided with a settling tank, the settling tank is provided with an oil drain valve, and the oil drain valve is arranged at the center of the settling tank.
Compared with the prior art, the invention has the following positive effects:
the invention relates to a middle refueling device of a fuel system.A supercharging device and a fuel oil baffle device are arranged in a box body, a first guide hole is arranged in the middle of the fuel oil baffle device, a second guide hole is arranged at the edge of the fuel oil baffle device, and the diameter of the first guide hole is larger than that of the second guide hole, so that the fuel oil passing performance is ensured, the violent flow of the fuel oil in the process of executing flight action can be reduced, the fuel oil quantity around the supercharging device is ensured, and the fuel oil is pressed out of an oil tank through the supercharging device; the supercharging device comprises a first supercharging device and a second supercharging device which are arranged in a vertically staggered manner, so that the airplane can be ensured to provide sufficient fuel pressure and flow for the engine in any posture;
the box body is provided with an anti-leakage device, one end of the anti-leakage device is communicated with the outside of the box body, and the other end of the anti-leakage device is communicated with the inside of the box body; when the aircraft flies at a negative speed, the anti-leakage device closes the ventilation pipeline, so that the box body is isolated from the atmosphere, and fuel oil cannot leak;
the box body is provided with an alarm device, when the oil level of the oil tank is too low, the alarm device transmits an alarm signal to the cab controller, and the controller controls the alarm indicator lamp to light up to remind a driver of the too low oil level;
be provided with the precipitation tank on the box, the precipitation tank is removable, when the fuel has the sediment in the oil tank, dismantlement that can be convenient gets off and wash the oil tank. An oil drain valve is also arranged on the settling tank, so that waste oil in an oil tank can be easily drained when fuel oil needs to be replaced;
the invention has the advantages of simple and reliable structure, high stability and adaptability to various flight conditions and flight attitudes, and can ensure that an aircraft fuel system can supply oil to a turboprop engine more accurately and stably, thereby ensuring the normal and stable operation of the engine.
Drawings
FIG. 1 is a schematic view of the present invention in an installed position;
FIG. 2 is a schematic structural view of the present invention;
FIG. 3 is a schematic diagram of the positions of an oil inlet and an oil outlet of the present invention;
FIG. 4 is a schematic view of the vent line and the leak prevention device of the present invention;
fig. 5 is a schematic diagram of the alarm device of the present invention.
In the figure, 1 aircraft frame, 2 tank, 3 installing supports, 4 vent line interfaces, 6 anti-leakage devices, 7 alarm devices, 8 fuel grid blocking devices, 9 fuel drain valves, 10 settling tanks, 11 first supercharging devices, 12 tank oil inlets, 13 tank oil outlets, 14 second supercharging devices, 600 controllers and 601 alarm indicator lamps.
Detailed Description
Example 1
As shown in fig. 1-3, the present invention provides a technical solution: the fuel oil separator comprises a box body 2, an oil inlet 12 and an oil outlet 13 which are arranged on one side of the box body, and a supercharging device and a fuel oil blocking device 8 which are arranged inside the box body 2;
the oil inlet 12 is communicated with the box body 2; the supercharging device is communicated with the oil outlet 13;
the supercharging devices comprise a first supercharging device 11 and a second supercharging device 14;
the first supercharging device 11 and the second supercharging device 14 are arranged in a vertically staggered manner.
The electric fuel oil booster pump has a pressure sensing function and can transmit a pressure signal in the oil pump to a control motor so as to control the start and stop of the oil pump; the first supercharging device 11 and the second supercharging device 14 are distributed in a vertically staggered manner, so that sufficient pressure and flow of an aircraft fuel system can be ensured in various flight states;
the number of the fuel oil baffle devices 8 is more than 2, and the fuel oil baffle devices are fixedly welded with the bottom or the top of the box body and are symmetrically distributed. The middle part of the fuel oil baffle device 8 is provided with a first flow guide hole, the edge of the fuel oil baffle device is provided with a second flow guide hole, the second flow guide holes are symmetrically distributed, and the diameter of the first flow guide hole is larger than that of the second flow guide hole, so that the irregular flow of fuel oil in the box body is slowed down.
Working process
As shown in fig. 1-3, when the aircraft is in a normal flight state, fuel oil flows into the interior of the tank 2 through the oil inlet 12 of the tank 2, at this time, the first supercharging device 11 starts to work, the second supercharging device 14 does not work temporarily, and the fuel oil flows out of the tank through the oil outlet 13 at a high speed flow rate and pressure through pressurization of the first supercharging device 11, flows to the engine, and meets normal working requirements of the engine. The middle of the fuel oil separation device 8 is provided with a first flow guide hole, the edge of the fuel oil separation device 8 is provided with a second flow guide hole, the diameter of the first flow guide hole is larger than that of the second flow guide hole, so that the passing performance of fuel oil is guaranteed, the violent flow of the fuel oil in the process of executing flight action can be reduced, the fuel oil quantity around the supercharging device is guaranteed, the fuel oil is pressed out of the fuel oil tank through the supercharging device, the violent collision of the fuel oil on the tank body is prevented, and the irregular flow of the fuel oil in the tank body is slowed down.
Example 2
As shown in fig. 1 to 4, the present invention provides a technical solution: the fuel oil separator comprises a box body 2, an oil inlet 12 and an oil outlet 13 which are arranged on one side of the box body, and a supercharging device and a fuel oil blocking device 8 which are arranged inside the box body 2;
the oil inlet 12 is communicated with the box body 2; the supercharging device is communicated with the oil outlet 13;
the supercharging devices comprise a first supercharging device 11 and a second supercharging device 14;
the first supercharging device 11 and the second supercharging device 14 are arranged in a vertically staggered manner.
The top of the box body 2 is provided with a leakage-proof device 6; one end of the leakage-proof device 6 is communicated with the outside of the box body; the other end of the leakage-proof device 6 is communicated with the inside of the box body.
Specifically, as shown in fig. 4, the anti-leakage device 6 is a GF5500-401 floating switch, has a liquid level self-control function, and when the aircraft is in a transient negative speed flight state, the oil tank is inclined downwards, the liquid level changes, and the outlet of the vent pipeline 4 is closed by an internal mechanism of the floating switch, so that the box body 2 is isolated from the atmosphere, and the fuel oil leakage is prevented.
Working process
As shown in fig. 1-4, when the aircraft is in a transient negative speed flight state, the aircraft is inclined downwards, the liquid level of the oil tank is inclined downwards, at the moment, the fuel oil enters the interior of the tank body through an oil inlet 12 of the tank body 2, the first supercharging device 11 cannot meet the supercharging working condition, and then the second supercharging device 14 works to ensure that the fuel oil can be continuously supercharged, so that the fuel oil flows out of the tank body through an oil outlet 13 at a flow rate and pressure suitable for the requirement of an engine. In the process, as shown in figure 4, the GF5500-401 floating switch of the leakage-proof device 6 moves according to the liquid level, the communication between the vent pipe 4 and the tank body is sealed, and the fuel in the oil inlet pipeline of the tank body 2 supplements the fuel consumption of the tank body through the siphon phenomenon, so that the pressure balance state in the tank body is maintained.
Example 3
As shown in fig. 1 to 5, the present invention provides a technical solution: the fuel oil separator comprises a box body 2, an oil inlet 12 and an oil outlet 13 which are arranged on one side of the box body, and a supercharging device and a fuel oil blocking device 8 which are arranged inside the box body 2;
the oil inlet 12 is communicated with the box body 2; the supercharging device is communicated with the oil outlet 13;
the supercharging devices comprise a first supercharging device 11 and a second supercharging device 14;
the first supercharging device 11 and the second supercharging device 14 are arranged in a vertically staggered manner.
The alarm system comprises an alarm device arranged at the top of the box body 2, a controller 600 connected with the alarm device 7 and an alarm indicator lamp 601 in control connection with the controller 600. The alarm device 7 is an electronic liquid level sensor and is connected with a cab controller 600, and the controller 600 controls an alarm indicator lamp 601 to be used for warning the pilot of low fuel quantity in the box body.
The fuel tank comprises a tank body and is characterized by further comprising a settling tank 10 and an oil drain valve 9, wherein the settling tank 10 and the oil drain valve 9 are arranged at the bottom of the tank body, the oil drain valve 9 is made of carbon steel, the nominal diameter of the settling tank is 10-100 mm, the settling tank 10 is arranged in the middle of the settling tank 10, the settling tank 10 is used for collecting fuel oil sediment of the tank body 2 and a part of fuel oil system, and the oil drain valve is used for draining oil and checking whether impurities exist in the fuel oil.
Working process
As shown in fig. 1-5, when the aircraft is in a normal flight state, fuel oil flows into the interior of the tank 2 through the oil inlet 12 of the tank 2, at this time, the first supercharging device 11 starts to work, the second supercharging device 14 does not work, and the fuel oil flows out of the tank through the oil outlet 13 through pressurization of the first supercharging device 11 at a high speed flow rate and pressure, flows to the engine, and meets normal working requirements of the engine. In the process, when the liquid level of the oil tank is too low, the alarm device 7 transmits a signal to the cab controller, and the controller 600 controls the alarm indicator lamp 601 to light up to warn the pilot of low oil quantity of fuel oil in the tank. When the fuel deposits too much, all fuel or fuel deposits in the tank can be discharged through the deposit oil drain valve 9, the detachable depositing tank 10 can collect the fuel deposits in the tank and part of the fuel system, and the inside of the tank can be cleaned and checked regularly.
Claims (8)
1. The intermediate oil supply device of the fuel system is characterized by comprising a box body (2), an oil inlet (12) and an oil outlet (13) which are arranged on one side of the box body (2), and a supercharging device and a fuel oil blocking device (8) which are arranged inside the box body (2);
the oil inlet (12) is communicated with the box body (2);
the pressure boosting device is communicated with the oil outlet (13);
the supercharging device comprises a first supercharging device (11) and a second supercharging device (14);
the first supercharging device (11) and the second supercharging device (14) are arranged in a vertically staggered mode.
2. An aircraft fuel system intermediate fuel supply as claimed in claim 1, characterised in that the tank (2) is provided at its top with a leak-proof device (6);
one end of the anti-leakage device (6) is communicated with the outside of the box body;
the other end of the anti-leakage device (6) is communicated with the inside of the box body.
3. An aircraft fuel system intermediate fuel supply as claimed in claim 2, characterized in that the leak-proof device (6) is a float switch.
4. An aircraft fuel system intermediate fuel supply as claimed in claim 1, wherein the pressurising means is selected from an electrically powered fuel booster pump.
5. An aircraft fuel system intermediate fuel supply as claimed in claim 1, characterised in that the number of fuel cut-off devices (8) is more than 2.
6. The aircraft fuel system intermediate oil supply device as claimed in claim 1, characterized in that a first flow guiding hole is arranged in the middle of the fuel baffle device (5), and a second flow guiding hole is arranged at the edge of the fuel baffle device (5).
7. The aircraft fuel system intermediate oil supply device as claimed in claim 1, characterized by further comprising an alarm system, wherein the alarm system comprises an alarm device (7) arranged at the top of the tank body (2), a controller (600) connected with the alarm device (7) and an alarm indicator lamp (601) connected with the controller (600).
8. An aircraft fuel system intermediate oil supply device according to claim 1, characterized in that a settling tank (10) is arranged at the bottom of the tank body (2), and an oil drain valve (9) is arranged on the settling tank (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911304366.7A CN111038712A (en) | 2019-12-17 | 2019-12-17 | Intermediate oil supply device of fuel oil system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911304366.7A CN111038712A (en) | 2019-12-17 | 2019-12-17 | Intermediate oil supply device of fuel oil system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111038712A true CN111038712A (en) | 2020-04-21 |
Family
ID=70237535
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911304366.7A Pending CN111038712A (en) | 2019-12-17 | 2019-12-17 | Intermediate oil supply device of fuel oil system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111038712A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB167209A (en) * | 1920-03-05 | 1921-08-05 | Vickers Ltd | Improvements in or relating to fuel supply systems for aircraft engines |
| CN204020551U (en) * | 2014-08-15 | 2014-12-17 | 徐工集团工程机械股份有限公司科技分公司 | Loader fuel tank device for preventing leakage |
| CN108639358A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of fuel combustion type aircraft flame-proof explosion-proof fuel tank |
| CN212047910U (en) * | 2019-12-17 | 2020-12-01 | 石家庄飞机工业有限责任公司 | Intermediate oil supply device of fuel oil system |
-
2019
- 2019-12-17 CN CN201911304366.7A patent/CN111038712A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB167209A (en) * | 1920-03-05 | 1921-08-05 | Vickers Ltd | Improvements in or relating to fuel supply systems for aircraft engines |
| CN204020551U (en) * | 2014-08-15 | 2014-12-17 | 徐工集团工程机械股份有限公司科技分公司 | Loader fuel tank device for preventing leakage |
| CN108639358A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of fuel combustion type aircraft flame-proof explosion-proof fuel tank |
| CN212047910U (en) * | 2019-12-17 | 2020-12-01 | 石家庄飞机工业有限责任公司 | Intermediate oil supply device of fuel oil system |
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