CN106828948B - Fuel discharge design device for aircraft pressure refueling main pipe - Google Patents
Fuel discharge design device for aircraft pressure refueling main pipe Download PDFInfo
- Publication number
- CN106828948B CN106828948B CN201510896438.7A CN201510896438A CN106828948B CN 106828948 B CN106828948 B CN 106828948B CN 201510896438 A CN201510896438 A CN 201510896438A CN 106828948 B CN106828948 B CN 106828948B
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- Prior art keywords
- pressure
- main pipe
- fuel
- oil
- air inlet
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- 239000000446 fuel Substances 0.000 title claims abstract description 45
- 239000003921 oil Substances 0.000 claims abstract description 73
- 238000007599 discharging Methods 0.000 claims abstract description 15
- 239000000295 fuel oil Substances 0.000 claims abstract description 14
- 238000000034 method Methods 0.000 claims abstract description 14
- 239000002828 fuel tank Substances 0.000 claims description 26
- 239000000945 filler Substances 0.000 claims 5
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000002360 preparation method Methods 0.000 abstract description 3
- 238000004904 shortening Methods 0.000 abstract 1
- 238000005086 pumping Methods 0.000 description 10
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000010763 heavy fuel oil Substances 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention provides a device for discharging fuel of an aircraft pressure refueling main pipe, which comprises a pressure refueling connector, the pressure refueling main pipe, an air inlet valve and an oil discharge valve. An air inlet valve and an oil discharge valve are arranged on the pressure oiling main pipe, when pressure oiling is carried out, the pressure in the oiling main pipe enables the air inlet valve and the oil discharge valve to be in a closed state, fuel consumption in an oil tank is carried out in the flight process of an aircraft, the pressure of the oiling main pipe is reduced, the air inlet valve is opened for air inlet, and the oil discharge valve is opened for discharging fuel in the oiling main pipe. By adopting the invention, the aircraft can flow the residual oil in the pressure oiling main pipe into the oil tank along with the consumption of the fuel oil in the flight process, thereby increasing the available fuel oil of the aircraft, shortening the take-off preparation time of the aircraft and effectively preventing the possibility of damaging the oiling pipeline by adopting the technology of discharging the residual oil in the oiling main pipe by adopting the vacuum-proof valve.
Description
Technical Field
The invention belongs to the technical field of aviation, and relates to a fuel oil discharge device of a main pipe of an aircraft pressure refueling system.
Background
After the pressure refueling of domestic military aircraft and civil aircraft is finished, the fuel oil in the pressure refueling main pipe is pumped by adopting a refueling connector, and the pumping mode is that an anti-vacuum valve is arranged at the tail end of the refueling main pipe, and meanwhile, a pressure signal device is arranged behind the refueling connector, so that the pumping pressure is limited in the pumping process. The mode of removing the fuel oil of the pressure refueling main pipe is characterized in that on one hand, in the operation process, an operator forgets to pump the oil after the oil is added, so that the refueling main pipe always takes the oil for flying and landing, the weight of an aircraft is increased, and when the aircraft breaks down and lands in an emergency mode, potential safety hazards exist in the residual oil in the refueling main pipe; on one hand, during oil pumping, the vacuum valve must be ensured to work normally, the oil pumping pressure is controlled, and the oil pumping main pipe is prevented from being pumped into negative pressure in the oil pumping process to lead the main pipe to deform and damage; in one aspect, the pumping process increases pressure fueling time and aircraft takeoff preparation time.
Disclosure of Invention
The invention provides a main pipe fuel oil discharging device of an aircraft pressure oiling system, which is characterized in that after pressure oiling is completed, residual oil in an oiling main pipe flows into an oil tank along with the consumption of fuel oil in the aircraft flight process, so that the available fuel oil of the aircraft is increased, the oiling time is shortened, and the possibility that an oil adding pipeline is damaged by adopting a vacuum valve-preventing main pipe residual oil discharging technology is effectively prevented.
An aircraft pressure fuelling system manifold fuel drain comprising: the device comprises a pressure refueling connector, a fuel tank, a pressure refueling main pipe, an air inlet valve and an oil discharge valve; the pressure refueling connector of the pressure refueling system is arranged close to the fuel tank, the pressure refueling main pipe is arranged in the fuel tank, and the air inlet valve is arranged at the upper part of the pressure refueling main pipe and is used for air inlet when the pressure refueling main pipe discharges oil; the oil discharge valve is arranged at the bottom of the pressure oil filling main pipe and is used for discharging the fuel oil of the pressure oil filling main pipe; when the pressure is filled, the pressure in the filling main pipe enables the air inlet valve and the oil outlet valve to be in a closed state; in the flying process of the aircraft, fuel consumption in the fuel tank is reduced, the float of the air inlet valve descends along with the oil surface to enable the air inlet valve to be communicated with the oil-free space of the fuel tank, the air inlet valve is opened, the pressure of the fuel filling main pipe is reduced, and the fuel discharge valve is opened to discharge fuel in the fuel filling main pipe.
The pressure refueling connector is characterized in that the pressure refueling connector is arranged close to the fuel tank.
The pressure refueling main pipe is characterized in that the pressure refueling main pipe is arranged in a fuel tank, and an air inlet valve and an oil discharge valve are arranged on the pressure refueling main pipe.
The air inlet valve is characterized in that the air inlet valve is arranged at the upper part of the pressure oiling main pipe, and when pressure oiling is performed, the pressure of the pressure oiling main pipe exceeds a certain pressure, and the air inlet valve is closed; in the flight process of the aircraft, fuel consumption in the fuel tank is reduced, the float of the air inlet valve descends along with the fuel level to enable the air inlet valve to be communicated with the fuel-free space of the fuel tank, the air inlet valve is opened, and the pressure of the fuel filling main pipe is reduced.
The oil discharge valve is characterized in that the oil discharge valve is arranged at the bottom of the lowest part of the pressure oil filling main pipe, and when pressure oil is filled, the pressure of the pressure oil filling main pipe exceeds a certain pressure, and the oil discharge valve is closed; when the pressure of the main pipe falls to a certain pressure, the oil discharge valve is opened to discharge the fuel oil in the main pipe.
The invention provides a main pipe fuel oil discharging device of an aircraft pressure oiling system, which has the beneficial effects that: the pressure refueling does not need to discharge the fuel in the pressure refueling main pipe through operating the oil pumping, so that the refueling time is shortened; the fuel of the pressure refueling main pipe is discharged into the fuel tank along with the consumption of the fuel in the flight process, so that the available fuel of the aircraft is increased; the operator is prevented from forgetting to pump oil after the oil is added, so that potential safety hazards exist in residual oil in the oil filling main pipe; and the main pipe is prevented from being deformed and damaged when the oil is pumped due to the failure of the vacuum valve of the oil filling main pipe. The main pipe fuel oil discharging device of the aircraft pressure refueling system is simple, and the mechanical air inlet valve and the mechanical fuel oil discharging valve have higher reliability.
Drawings
FIG. 1 is a schematic diagram of a fuel drain assembly for an aircraft pressure fueling system manifold of the present invention.
Wherein the pressure refuel joint 1, the fuel tank 2, the pressure refuel header 3, the air inlet valve 4 and the oil discharge valve 5.
Detailed Description
The invention will be further described by way of a specific embodiment with reference to fig. 1:
referring to fig. 1, in this embodiment, the fuel discharging device of the main pipe of the aircraft pressure refueling system includes: a pressure refueling joint 1, a fuel tank 2, a pressure refueling main pipe 3, an air inlet valve 4 and a fuel discharge valve 5. The air inlet valve is arranged at the upper part of the highest position of the pressure refueling main pipe through a pipeline, and the oil discharge valve is arranged at the bottom of the lowest position of the pressure refueling main pipe.
When the pressure is filled, the fuel enters the air inlet valve 4 and the oil discharge valve 5 through the pressure filling manifold 3, the fuel pressure of the valve cavities of the air inlet valve 4 and the oil discharge valve 5 is increased, and when the fuel pressure exceeds a certain value, the fuel pressure is larger than the spring pressure of the valve bodies of the air inlet valve 4 and the oil discharge valve 5, and the valve cavities of the air inlet valve 4 and the oil discharge valve 5 are closed by the compression springs, so that the pressure is filled in the fuel tank through the filling control valve, and the fuel is added to the position where the fuel tank is full or needs to be filled.
After the oiling is completed, the pressure of the pressure oiling main pipe 3, the pressure of the valve cavities of the air inlet valve and the pressure of the valve cavity of the oil outlet valve are reduced, and when the pressure is reduced to a certain value, the valve bodies of the air inlet valve 4 and the oil outlet valve 5 open the valve cavities of the air inlet valve 4 and the oil outlet valve 5 under the action of spring reset elasticity. If the refueling position is higher than the pressure refueling main pipe 3 and the air inlet valve 4, the pressure refueling main pipe 3 is full of fuel, a floater of the air inlet valve 4 floats upwards under the condition that the fuel tank is full of fuel, the pressure refueling main pipe 3 forms a closed cavity, and the fuel in the pressure refueling main pipe 3 cannot be discharged; if the fueling position is below the pressure fueling manifold 3 and the intake valve 4,
in the flight process, along with the consumption of fuel, the fuel height in the fuel tank 2 is reduced, the float of the air inlet valve 4 is opened along with the reduction of the oil level, the air inlet valve 4 is communicated with the oil-free space at the upper part of the fuel tank 2, when the oil level is lower than the oil discharge valve 5, the air inlet valve 4 is used for air inlet through the float valve, the oil discharge valve 5 is used for discharging oil, and the residual oil of the pressure oiling main pipe 3 is discharged.
In summary, the present invention performs the discharge of the residual fuel in the pressure tank header pipe by the pressure tank header pipe 3 installed in the fuel tank 2, on which the intake valve 4 and the discharge valve 5 are installed. The aircraft can flow into the oil tank along with the consumption of fuel in the flight process, so that the prior art is not used for pumping oil and discharging the residual oil of the pressure oiling main pipe, the aircraft take-off preparation time is shortened, the possibility that the oil feeding pipeline is damaged by adopting the technology for discharging the residual oil of the oiling main pipe by adopting the vacuum-proof valve is effectively prevented, and the available fuel of the aircraft is increased.
Claims (5)
1. An aircraft pressure fuelling system manifold fuel drain comprising: the device comprises a pressure refueling connector, a fuel tank, a pressure refueling main pipe, an air inlet valve and an oil discharge valve; the pressure refueling main pipe is arranged in the fuel tank, and the air inlet valve is arranged at the upper part of the pressure refueling main pipe and is used for air inlet when the pressure refueling main pipe discharges oil; the oil discharge valve is arranged at the bottom of the pressure oil filling main pipe and used for discharging the fuel oil of the pressure oil filling main pipe, the air inlet valve is arranged at the upper part of the highest position of the pressure oil filling main pipe through a pipeline, and the oil discharge valve is arranged at the bottom of the lowest position of the pressure oil filling main pipe; when the pressure is filled, the pressure in the filling main pipe enables the air inlet valve and the oil outlet valve to be in a closed state; in the flying process of the aircraft, fuel consumption in the fuel tank is reduced, the float of the air inlet valve descends along with the oil surface to enable the air inlet valve to be communicated with the oil-free space of the fuel tank, the air inlet valve is opened, the pressure of the fuel filling main pipe is reduced, and the fuel discharge valve is opened to discharge fuel in the fuel filling main pipe.
2. The pressure filler neck of claim 1, wherein the pressure filler neck is mounted adjacent to the fuel tank.
3. The pressure filler manifold of claim 1, wherein the pressure filler manifold is disposed within a fuel tank and wherein the inlet valve and the outlet valve are disposed on the pressure filler manifold.
4. The intake valve of claim 3, wherein the pressure fuelling manifold pressure exceeds a certain pressure and the intake valve closes; in the flight process of the aircraft, fuel consumption in the fuel tank is reduced, the float of the air inlet valve descends along with the fuel level to enable the air inlet valve to be communicated with the fuel-free space of the fuel tank, the air inlet valve is opened, and the pressure of the fuel filling main pipe is reduced.
5. A fuel outlet valve as claimed in claim 3, wherein, during pressure filling, the pressure filling manifold pressure
The oil discharge valve is closed when a certain pressure is exceeded; when the pressure of the main fueling pipe is reduced to a certain pressure, the fuel discharge valve is opened,
and discharging the fuel in the oiling main pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510896438.7A CN106828948B (en) | 2015-12-07 | 2015-12-07 | Fuel discharge design device for aircraft pressure refueling main pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510896438.7A CN106828948B (en) | 2015-12-07 | 2015-12-07 | Fuel discharge design device for aircraft pressure refueling main pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106828948A CN106828948A (en) | 2017-06-13 |
| CN106828948B true CN106828948B (en) | 2024-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510896438.7A Active CN106828948B (en) | 2015-12-07 | 2015-12-07 | Fuel discharge design device for aircraft pressure refueling main pipe |
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| CN (1) | CN106828948B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228479A (en) * | 2021-11-15 | 2022-03-25 | 岚图汽车科技有限公司 | Automobile fuel tank valve body arrangement method and structure |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE337716C (en) * | 1918-02-19 | 1921-06-07 | Dunlop Rubber Co | Bulletproof fuel tank for aircraft |
| GB573341A (en) * | 1942-08-21 | 1945-11-16 | Ernest Curle | Improvements in or relating to liquid storage tanks |
| RU94024243A (en) * | 1994-06-29 | 1997-04-10 | Е.А. Белолипецкий | Flying vehicle fuel system |
| RU2140380C1 (en) * | 1997-12-10 | 1999-10-27 | Акционерное общество открытого типа "ОКБ Сухого" | Aircraft compartment fuelling system |
| RU23068U1 (en) * | 2001-12-13 | 2002-05-20 | Федеральное государственное унитарное предприятие Государственное машиностроительное конструкторское бюро "Радуга" | FUEL SYSTEM OF THE AIRCRAFT WITH LARGE SHORT-TERM LONGITUDE OVERLOADS |
| CN102101434A (en) * | 2009-12-16 | 2011-06-22 | 上海通用汽车有限公司 | Automotive fuel tank |
| CN102700717A (en) * | 2012-06-08 | 2012-10-03 | 中国航空工业集团公司西安飞机设计研究所 | Method for distributing gravity oil filler cap of airplane |
| CN104943869A (en) * | 2015-06-23 | 2015-09-30 | 中国航空工业集团公司西安飞机设计研究所 | Ventilation tank residual fuel drainage system of reversed wing fuel system of large aircraft |
| CN105083586A (en) * | 2015-08-12 | 2015-11-25 | 中国航空工业集团公司西安飞机设计研究所 | Device for testing aerial refueling adapter equipment |
| CN105109700A (en) * | 2015-08-12 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | Residual-oil discharging system and oil discharging method of emergency oil discharging header pipe |
-
2015
- 2015-12-07 CN CN201510896438.7A patent/CN106828948B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE337716C (en) * | 1918-02-19 | 1921-06-07 | Dunlop Rubber Co | Bulletproof fuel tank for aircraft |
| GB573341A (en) * | 1942-08-21 | 1945-11-16 | Ernest Curle | Improvements in or relating to liquid storage tanks |
| RU94024243A (en) * | 1994-06-29 | 1997-04-10 | Е.А. Белолипецкий | Flying vehicle fuel system |
| RU2140380C1 (en) * | 1997-12-10 | 1999-10-27 | Акционерное общество открытого типа "ОКБ Сухого" | Aircraft compartment fuelling system |
| RU23068U1 (en) * | 2001-12-13 | 2002-05-20 | Федеральное государственное унитарное предприятие Государственное машиностроительное конструкторское бюро "Радуга" | FUEL SYSTEM OF THE AIRCRAFT WITH LARGE SHORT-TERM LONGITUDE OVERLOADS |
| CN102101434A (en) * | 2009-12-16 | 2011-06-22 | 上海通用汽车有限公司 | Automotive fuel tank |
| CN102700717A (en) * | 2012-06-08 | 2012-10-03 | 中国航空工业集团公司西安飞机设计研究所 | Method for distributing gravity oil filler cap of airplane |
| CN104943869A (en) * | 2015-06-23 | 2015-09-30 | 中国航空工业集团公司西安飞机设计研究所 | Ventilation tank residual fuel drainage system of reversed wing fuel system of large aircraft |
| CN105083586A (en) * | 2015-08-12 | 2015-11-25 | 中国航空工业集团公司西安飞机设计研究所 | Device for testing aerial refueling adapter equipment |
| CN105109700A (en) * | 2015-08-12 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | Residual-oil discharging system and oil discharging method of emergency oil discharging header pipe |
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|---|---|
| CN106828948A (en) | 2017-06-13 |
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Address after: 519000 1st floor, headquarters base office building, 1519 Yinwan Road, Wanchai, Xiangzhou District, Zhuhai City, Guangdong Province Applicant after: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: China aviation general aviation industrial base, Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
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