CN116119014B - Supercharged oil tank oil supply system for airplane - Google Patents
Supercharged oil tank oil supply system for airplane Download PDFInfo
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- CN116119014B CN116119014B CN202310279598.1A CN202310279598A CN116119014B CN 116119014 B CN116119014 B CN 116119014B CN 202310279598 A CN202310279598 A CN 202310279598A CN 116119014 B CN116119014 B CN 116119014B
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- tank
- valve
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- 239000003921 oil Substances 0.000 claims abstract description 399
- 239000000446 fuel Substances 0.000 claims abstract description 114
- 238000007906 compression Methods 0.000 claims abstract description 83
- 230000006835 compression Effects 0.000 claims abstract description 75
- 238000001914 filtration Methods 0.000 claims abstract description 32
- 238000011084 recovery Methods 0.000 claims abstract description 20
- 239000010779 crude oil Substances 0.000 claims abstract description 17
- 238000003825 pressing Methods 0.000 claims abstract description 7
- 238000005192 partition Methods 0.000 claims description 28
- 238000007789 sealing Methods 0.000 claims description 28
- 239000002828 fuel tank Substances 0.000 claims description 13
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 7
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000004891 communication Methods 0.000 description 5
- 239000012535 impurity Substances 0.000 description 5
- 239000007788 liquid Substances 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000010763 heavy fuel oil Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
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
- B64D37/10—Constructional adaptations thereof to facilitate fuel pressurisation
-
- 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
-
- 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
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M37/00—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
- F02M37/22—Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines, e.g. arrangements in the feeding system
- F02M37/32—Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines, e.g. arrangements in the feeding system characterised by filters or filter arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M37/00—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
- F02M37/22—Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines, e.g. arrangements in the feeding system
- F02M37/32—Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines, e.g. arrangements in the feeding system characterised by filters or filter arrangements
- F02M37/50—Filters arranged in or on fuel tanks
-
- 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
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Details Of Reciprocating Pumps (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The application relates to the technical field of aircraft oil supply system manufacturing, in particular to an aircraft supercharged oil tank oil supply system, which comprises a self-pressing oil tank, a multi-stage filtering and pressurizing conveying component communicated with the self-pressing oil tank and an oil recovery component communicated with the multi-stage filtering and pressurizing conveying component; the self-pressure type oil tank comprises a hard-mounted oil tank arranged in the wing, a soft-compression oil bag arranged in the hard-mounted oil tank, an air pressure plate for extruding the soft-compression oil bag and a pressurizing air pump for pushing the air pressure plate; the multistage filtering and pressurizing conveying assembly comprises a crude oil filter communicated with the soft compression oil bag, a primary oil booster pump communicated with the crude oil filter, a fine oil filter communicated with the primary oil booster pump and a secondary oil booster pump communicated with the fine oil filter, wherein the secondary oil booster pump is communicated with an oil inlet of the engine. The present application has the effect of facilitating continuous supply of engine fuel.
Description
Technical Field
The application relates to the technical field of aircraft oil supply system manufacturing, in particular to a supercharged oil tank oil supply system for an aircraft.
Background
With the vigorous development of Chinese economy and science and technology, flight activities are increasingly promoted, and particularly the possession of unmanned aerial vehicles and sport aircraft is increased year by year, so that more and more companies begin to engage in aircraft design, manufacturing and maintenance, and large unmanned aerial vehicles and sport aircraft often perform various flight maneuver exercises, and aircraft fuel tanks have larger jolts.
In the prior art, the design of an open two-point fuel system inlet of a traditional wing fuel tank is easy to suspend a fuel suction inlet, and impurities in aviation fuel cannot be deposited to the bottom of the fuel tank due to larger jolt of an aircraft, so that the impurities in the aviation fuel are easy to cause oil filtration blockage, the oil supply of an engine is discontinuous, and the engine is stopped.
With respect to the related art in the above, the inventors consider that: when any flight maneuver conforming to the flight specification is performed, the aircraft fuel supply system needs to store fuel and simultaneously continuously supply fuel to the aircraft engine.
Disclosure of Invention
In order to continuously supply fuel to an engine in various flight conditions in response to fuel supply demands of the engine, the present application provides a supercharged fuel tank fuel supply system for an aircraft.
The application provides a supercharged type oil tank oil supply system for aircraft adopts following technical scheme:
a supercharged oil tank oil supply system for an aircraft comprises a self-pressing oil tank and a multi-stage filtering and pressurizing conveying assembly communicated with the self-pressing oil tank;
the self-pressure type oil tank comprises a hard-mounted oil tank arranged in a wing, a soft-pressure oil bag arranged in the hard-mounted oil tank, an air pressure plate movably arranged in the hard-mounted oil tank and used for extruding the soft-pressure oil bag, and a supercharging air pump arranged on the hard-mounted oil tank and used for pushing the air pressure plate;
the multistage filtering pressurizing conveying assembly comprises a crude oil filter communicated with the soft compression oil bag, a primary oil booster pump communicated with the crude oil filter, a fine oil filter communicated with the primary oil booster pump and a secondary oil booster pump communicated with the fine oil filter, and the secondary oil booster pump is communicated with an oil inlet of an engine.
By adopting the technical scheme, the pressurizing air pump is operated, the air pressure in the hard-mounted oil tank is increased, the air pressure plate is moved, the soft compression oil bag is extruded, the pressure of aviation fuel in the soft compression oil bag is increased, the aviation fuel between the soft compression oil bag and the crude oil filter is always provided with a certain pressure, the aviation fuel is conveniently conveyed to the crude oil filter, the soft compression oil bag can be compressed after conveying the aviation fuel, the suspension of a fuel suction inlet is avoided, and meanwhile, the occurrence of larger oil wave when the rest fuel in the soft compression oil bag is conveyed to jolt on an airplane can be avoided; the primary oil booster pump can extract aviation fuel between the coarse oil filter and the primary oil booster pump, so that the coarse oil filter can be used for carrying out preliminary filtration on the aviation fuel, meanwhile, the aviation fuel between the coarse oil filter and the primary oil booster pump can be kept under pressure, the aviation fuel can be conveniently conveyed to the fine oil filter, the secondary oil booster pump can extract the aviation fuel between the fine oil filter and the secondary oil booster pump, the fine oil filter can be used for carrying out secondary filtration on the aviation fuel, meanwhile, the aviation fuel between the fine oil filter and the secondary oil booster pump can be kept under pressure, the aviation fuel can be conveniently conveyed to an engine, and the aviation fuel conveying process is more stable and efficient; in the double filtration consisting of the coarse oil filter and the fine oil filter, impurities in aviation fuel can be dispersedly intercepted in the coarse oil filter and the fine oil filter, the probability of blockage of the oil filter is reduced, and the fuel supply requirement of an engine can be met under various flight states, so that the fuel supply can be continuously carried out.
Optionally, a plurality of partition plates are arranged in the hard-mounted oil tank at intervals, the inner cavity of the hard-mounted oil tank is divided into a plurality of partition cavities by the plurality of partition plates, the partition cavities are divided into air pressure cavities and compression bag cavities by the air pressure plates, the pressurizing air pump is communicated with the air pressure cavities, and the partition plates are provided with vent pipes communicated with the adjacent air pressure cavities;
the soft compression oil bags are arranged in the compression bag cavities, and a control oil valve is arranged between the adjacent soft compression oil bags.
By adopting the technical scheme, the partition plate is arranged in the hard-mounted oil tank, the shape of the hard-mounted oil tank can be long and flat, so that the shape of the hard-mounted oil tank can be more attached to the wing, the partition plate improves the structural strength of the hard-mounted oil tank while the hard-mounted oil tank can provide protection for the soft compression oil bag, the hard-mounted oil tank can be used as a supporting structure of the wing, and the structural strength of the wing is improved; when the shape of the hard-mounted oil tank is irregular, the inner cavity of the hard-mounted oil tank can be divided into a plurality of regular spacing cavities by the spacing plates, the spacing cavities are conveniently and movably arranged in the spacing cavities, the spacing cavities are divided into an air pressure cavity and a compression bag cavity, the air pressure in the air pressure cavity is increased by the pressurizing air pump to drive the air pressure plate to move, the volumes of the air pressure cavity and the compression bag cavity also change along with the movement of the air pressure plate, air pressure can be transmitted into the adjacent air pressure cavity through the ventilation pipe, the soft compression oil bags are arranged in the compression bag cavity, the soft compression oil bags are communicated through the control oil valve, when a single soft compression oil bag leaks, the control oil valve is closed, the leakage of fuel oil can be reduced, and the safety is improved.
Optionally, each of the spacing cavities is provided with two air pressure plates, the control oil valve is arranged on the spacing plate, the central axis of the control oil valve is perpendicular to the gravity center vertical line of the hard-mounted oil tank, each spacing plate is provided with two air pipes, and the two air pipes are symmetrically arranged relative to the control oil valve.
Through adopting above-mentioned technical scheme, two atmospheric pressure boards can compress soft compression oil bag simultaneously, and the central axis perpendicular to of control oil valve is perpendicular to the barycenter plumb line of hard installation oil tank, and the influence that causes to the heart when reducing the soft compression oil bag of compression makes hard installation oil tank more steady, and two atmospheric pressure boards compress the back to soft compression oil bag simultaneously, can carry the atmospheric pressure to adjacent atmospheric pressure chamber through two breather pipes.
Optionally, the orifice of the vent pipe close to the booster air pump is a first orifice, the first orifice is arranged at a position where the partition plate is close to the control oil valve, the orifice of the vent pipe far away from the booster air pump is a second orifice, and the second orifice is arranged at a position where the partition plate is far away from the control oil valve.
Through adopting above-mentioned technical scheme, when the soft compression oil bag of atmospheric pressure board, the first mouth of pipe and the compression bag chamber intercommunication of breather pipe, the soft compression oil bag of atmospheric pressure board compression, the atmospheric pressure board removes to the direction that is close to the control oil valve, enables first mouth of pipe and atmospheric pressure chamber intercommunication, carries adjacent atmospheric pressure intracavity with the atmospheric pressure in the atmospheric pressure chamber through the second mouth of pipe, only need set up a booster pump and just can be in proper order to atmospheric pressure chamber gas injection pressurization.
Optionally, a sealing ring is arranged on the side surface of the air pressure plate, a sealing protrusion is arranged on the surface of the sealing ring away from the air pressure plate, a ball is movably arranged on the side surface of the air pressure plate, which is provided with the sealing ring, and the sealing ring is arranged at the position of the air pressure plate, which is close to the soft compression oil bag.
Through adopting above-mentioned technical scheme, sealing washer and sealed protruding play sealed effect, the atmospheric pressure of the atmospheric pressure intracavity of being convenient for drives the atmospheric pressure board and removes, is provided with the ball on the side of atmospheric pressure board, and the atmospheric pressure board of being convenient for slides in the interval intracavity, and ball and sealing washer are on the same side of atmospheric pressure board, can play the restriction effect to the atmospheric pressure board, avoid the atmospheric pressure board to take place to incline and deflect at the interval intracavity.
Optionally, an oil inlet valve communicated with the soft compression oil bag is arranged on the outer wall of the hard-mounted oil tank, and the soft compression oil bag communicated with the oil inlet valve is far away from the booster air pump;
the oil tank valve communicated with the soft compression oil bag is arranged on the outer wall of the hard-mounted oil tank, the oil tank valve is communicated with the crude oil filter, the oil drain valve communicated with the soft compression oil bag is arranged on the outer wall of the hard-mounted oil tank, and the soft compression oil bag communicated with the oil drain valve is close to the booster air pump.
Through adopting above-mentioned technical scheme, after the oil feed valve intercommunication adds oil pipe, can soft compression oil bag refuels, cooperation control valve can refuel whole soft compression oil bag, opens the oil tank valve, can carry the crude oil with the aviation fuel in the soft compression oil bag to strain, opens the oil drain valve, can be convenient for discharge the residual oil in the soft compression oil bag.
Optionally, a coarse filter cavity and a bypass filter cavity are formed in the coarse oil filter, a coarse filter element is arranged in the coarse filter cavity, a bypass filter element is arranged in the bypass filter cavity, a bypass pressure release valve is arranged between the coarse filter cavity and the bypass filter cavity, and the bypass pressure release valve is arranged at an oil inlet end of the coarse oil filter.
Through adopting above-mentioned technical scheme, after the aviation fuel got into the rough filtration chamber, the rough filter core was filtered aviation fuel, when the rough filter core jam was serious, the pressure of the aviation fuel that gets into the rough oil and strain can increase gradually, and when aviation fuel pressure reached certain degree, the bypass relief valve was opened, and aviation fuel can get into the bypass filtration chamber, filters aviation fuel through the bypass filter core, reduces the probability that the rough filter core jam led to the engine to stop.
Optionally, a fine filter cavity is formed in the fine oil filter, a fine filter element is arranged in the fine filter cavity, and a bypass valve is arranged between an oil inlet end and an oil outlet end of the fine oil filter.
Through adopting above-mentioned technical scheme, after the aviation fuel got into thin filter chamber, thin filter core was filtered aviation fuel, when thin filter core blocks up seriously, the aviation fuel's that gets into thin oil filter pressure can increase gradually, when aviation fuel pressure reaches certain degree, and the bypass valve is opened, and aviation fuel flows from the exit end of thin oil filter after passing through the bypass valve, reduces the probability that thin filter core blocks up and leads to the engine to stop.
Optionally, a first-stage one-way oil valve is arranged between the first-stage oil booster pump and the fine oil filter, and a second-stage one-way oil valve is arranged at the outlet end of the second-stage oil booster pump.
Through adopting above-mentioned technical scheme, one-level one-way oil valve can prevent aviation fuel and flow back to one-level oil booster pump, and second grade one-way oil valve can prevent aviation fuel and flow back to second grade oil booster pump, and the fuel feeding sequence of cooperation other valve steerable oil feeding system simultaneously.
Optionally, the device further comprises an oil recovery assembly, wherein the oil recovery assembly comprises a recovery oil pipe communicated with an oil outlet of the engine and an ejector pump communicated with the recovery oil pipe, the recovery oil pipe is communicated with a low-pressure liquid inlet of the ejector pump, the one-stage one-way oil valve is communicated with a high-pressure liquid inlet of the ejector pump, and an outlet of the ejector pump is communicated with the fine oil filter.
Through adopting above-mentioned technical scheme, the aviation fuel that the engine was retrieved carries the low pressure inlet of ejector pump through retrieving oil pipe, and the aviation fuel that has higher pressure gets into the ejector pump through high pressure inlet, through the effect of ejector pump, can extract the aviation fuel that retrieves in retrieving oil pipe, and the aviation fuel backward flow of being convenient for retrieve is carried in the fine oil filter from the export of ejector pump again.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the self-pressure type oil tank, the hard-mounting oil tank, the soft compression oil bag, the air pressure plate, the pressurizing air pump, the multi-stage filtering pressurizing conveying component, the crude oil filter, the primary oil booster pump, the fine oil filter and the secondary oil booster pump are arranged, the pressurizing air pump is operated, the air pressure in the hard-mounting oil tank is increased, the air pressure plate is moved, the soft compression oil bag is extruded, the pressure of aviation fuel in the soft compression oil bag is increased, the aviation fuel between the soft compression oil bag and the crude oil filter is always provided with a certain pressure, the aviation fuel is convenient to convey to the crude oil filter, the soft compression oil bag can be compressed after conveying the aviation fuel, and the phenomenon that the residual fuel in the soft compression oil bag is conveyed generates larger oil waves when an airplane bumps is avoided while the suspension of a fuel inlet is avoided; the primary oil booster pump can extract aviation fuel between the coarse oil filter and the primary oil booster pump, so that the coarse oil filter can be used for carrying out preliminary filtration on the aviation fuel, meanwhile, the aviation fuel between the coarse oil filter and the primary oil booster pump can be kept under pressure, the aviation fuel can be conveniently conveyed to the fine oil filter, the secondary oil booster pump can extract the aviation fuel between the fine oil filter and the secondary oil booster pump, the fine oil filter can be used for carrying out secondary filtration on the aviation fuel, meanwhile, the aviation fuel between the fine oil filter and the secondary oil booster pump can be kept under pressure, the aviation fuel can be conveniently conveyed to an engine, and the aviation fuel conveying process is more stable and efficient; in the double filtration consisting of the coarse oil filtration and the fine oil filtration, impurities in aviation fuel can be dispersedly intercepted in the coarse oil filtration and the fine oil filtration, the probability of blockage of the oil filtration is reduced, and the fuel supply requirement of an engine can be met under various flight states, and the fuel supply can be continuously carried out;
2. the sealing ring, the sealing bulge and the ball are arranged, so that the sealing ring and the sealing bulge play a sealing role, the air pressure in the air pressure cavity is convenient to drive the air pressure plate to move, the ball is arranged on the side surface of the air pressure plate, the air pressure plate is convenient to slide in the interval cavity, and the ball and the sealing ring are arranged on the same side surface of the air pressure plate, so that the air pressure plate can be limited, and the air pressure plate is prevented from inclining and deflecting in the interval cavity;
3. through setting up oil recovery subassembly, retrieving oil pipe and ejector pump, the aviation fuel that the engine was retrieved carries the low pressure inlet of ejector pump through retrieving oil pipe, and aviation fuel that has higher pressure gets into the ejector pump through high pressure inlet, through the effect of ejector pump, can extract the aviation fuel of retrieving in the oil pipe, the aviation fuel backward flow of being convenient for retrieving is carried in the fine oil filter from the export of ejector pump again.
Drawings
Fig. 1 is a schematic structural view of a supercharged fuel tank fuel supply system for an aircraft according to an embodiment of the present application.
Fig. 2 is an enlarged schematic view of the portion a in fig. 1.
Fig. 3 is a schematic cross-sectional view of a self-pressurizing fuel tank in an embodiment of the present application.
Fig. 4 is an enlarged schematic view of a portion B in fig. 3.
Fig. 5 is a schematic cross-sectional view of an oil filter in an embodiment of the present application.
Fig. 6 is an enlarged schematic view of a portion C in fig. 5.
Fig. 7 is an enlarged schematic view of the portion D in fig. 5.
Reference numerals illustrate: 01. an engine; 1. self-pressing oil tank; 11. a hard-mounted oil tank; 111. a partition plate; 12. soft compression oil bags; 13. an air pressure plate; 14. a booster air pump; 15. a compartment; 151. an air pressure chamber; 152. compressing the capsule; 16. an oil inlet valve; 17. an oil tank valve; 18. an oil drain valve; 2. a multi-stage filtration pressurized delivery assembly; 21. coarse oil filtration; 211. a coarse filtration chamber; 212. a bypass filter chamber; 213. a coarse filter element; 214. a bypass filter element; 215. a bypass relief valve; 22. a first-stage oil booster pump; 23. filtering fine oil; 231. a fine filter chamber; 232. a fine filter element; 233. a bypass shutter; 24. a secondary oil booster pump; 25. a first-stage one-way oil valve; 26. a second-stage one-way oil valve; 3. a vent pipe; 31. a first nozzle; 32. a second nozzle; 4. controlling an oil valve; 5. a seal ring; 51. a sealing protrusion; 6. a ball; 7. an oil recovery assembly; 71. recovering oil pipes; 72. and an ejector pump.
Detailed Description
The present application is described in further detail below in conjunction with figures 1-7.
The embodiment of the application discloses a supercharged oil tank oil supply system for an aircraft. Referring to fig. 1 and 2, a supercharged fuel tank fuel supply system for an aircraft comprises a self-pressure fuel tank 1 arranged in a wing, a multi-stage filtering and pressurizing conveying assembly 2 communicated with the self-pressure fuel tank 1, and an oil recovery assembly 7 communicated with the multi-stage filtering and pressurizing conveying assembly 2, wherein the multi-stage filtering and pressurizing conveying assembly 2 is communicated with an oil inlet of an engine, and the oil recovery assembly 7 is communicated with an oil outlet of the engine.
Referring to fig. 1 and 3, the self-pressure type oil tank 1 includes a hard-mounted oil tank 11 fixedly connected to a wing skeleton, a soft compression oil bag 12 provided in the hard-mounted oil tank 11, an air pressure plate 13 movably provided in the hard-mounted oil tank 11 for compressing the soft compression oil bag 12, and a booster air pump 14 fixedly connected to an outer wall of the hard-mounted oil tank 11 for driving the air pressure plate 13.
Referring to fig. 3 and 4, the shape of the hard-mounted oil tank 11 is set according to the space in the wing skeleton, the length direction of the hard-mounted oil tank 11 is parallel to the length direction of the wing, a partition plate 111 is fixedly connected in the hard-mounted oil tank 11 at intervals along the length direction, the partition plate 111 divides the internal space of the hard-mounted oil tank 11 into a plurality of partition spaces 15, the length direction of the partition spaces 15 is perpendicular to the length direction of the hard-mounted oil tank 11, the section shape of the length direction of the partition spaces 15 is always consistent, the hard-mounted oil tank 11 not only can provide protection for the soft-compression oil bag 12, but also can effectively improve the structural strength of the hard-mounted oil tank 11 after the partition plate 111 is arranged, the hard-mounted oil tank 11 can also be used as the wing structure to improve certain support, and the structural strength of the wing is improved.
The length direction of the spacing cavity 15 is perpendicular to the plate surface of the air pressure plate 13, the air pressure plate 13 divides the spacing cavity 15 into an air pressure cavity 151 and a compression bag cavity 152, the cross section shape of the spacing cavity 15 in the length direction is similar to the plate surface shape of the air pressure plate 13, in this embodiment, two air pressure plates 13 are movably arranged in one spacing cavity 15, and the two air pressure plates 13 are respectively arranged at two ends of the spacing cavity 15 in the length direction.
Referring to fig. 3 and 4, a sealing ring 5 is fixedly connected to a side surface of a gas pressure plate 13, a sealing protrusion 51 is arranged on the sealing ring 5, the sealing ring 5 is arranged on one side of the gas pressure plate 13 close to a soft compression oil bag 12, a gap between the gas pressure plate 13 and the inner wall of a spacing cavity 15 can be sealed through the sealing ring 5 and the sealing protrusion 51, a ball 6 is arranged on the side surface of the gas pressure plate 13, the gas pressure plate 13 can be arranged in the spacing cavity 15 in a sliding manner through the ball 6, and the ball 6, the sealing ring 5 and the sealing protrusion 51 cooperate to limit the gas pressure plate 13, so that the probability of tilting and deflecting the gas pressure plate 13 is reduced when the gas pressure plate 13 moves along the length direction of the spacing cavity 15.
The hard-mounted oil tank 11 is internally provided with a plurality of soft-compression oil bags 12, one soft-compression oil bag 12 is arranged in one compression bag cavity 152, the shape of the soft-compression oil bag 12 is set according to the shape of the compression bag cavity 152, a control oil valve 4 is arranged between adjacent soft-compression oil bags 12, the control oil valve 4 is fixedly connected to the middle part of a partition plate 111, the control oil valve 4 is opened to be communicated with the adjacent soft-compression oil bags 12, and the central axis of the control oil valve 4 is perpendicular to the vertical line of the gravity center of the hard-mounted oil tank 11.
Referring to fig. 3 and 4, the booster pump 14 is communicated with the air pressure chamber 151, and the booster pump 14 can perform air injection and pressurization on the air pressure chamber 151, so that the air pressure plate 13 moves towards the direction close to the soft compression oil bag 12, acting force is applied to the soft compression oil bag 12, the volume of the air pressure chamber 151 gradually increases along with the movement of the air pressure plate 13, and the volume of the compression bag chamber 152 gradually decreases along with the movement of the air pressure plate 13, so that aviation fuel in the soft compression oil bag 12 generates certain pressure.
The partition plates 111 are provided with vent pipes 3 communicated with adjacent air pressure cavities 151, each partition plate 111 is provided with two vent pipes 3, the two vent pipes 3 are symmetrically arranged about the control oil valve 4, each vent pipe 3 comprises a first pipe orifice 31 and a second pipe orifice 32, the first pipe orifice 31 is arranged on the surface, close to the booster air pump 14, of the partition plate 111, the second pipe orifice 32 is arranged on the surface, far away from the booster air pump 14, of the partition plate 111, and gas in the air pressure cavity 151 can be conveyed to the adjacent air pressure cavity 151 from the vent pipe 3.
Referring to fig. 3 and 4, in the present embodiment, two booster pumps 14 are provided on each of the hard-mounted oil tanks 11, the two booster pumps 14 are provided on both sides of the hard-mounted oil tank 11 near the air pressure plate 13, the two booster pumps 14 are provided on one end of the hard-mounted oil tank 11, the first nozzle 31 is provided at a position where the partition 111 is near the control oil valve 4, and the second nozzle 32 is provided at a position where the partition 111 is far from the control oil valve 4.
In another embodiment, a plurality of booster pumps 14 are arranged on each hard-mounted oil tank 11, one air pressure cavity 151 is communicated with one booster pump 14, and when the air pressure cavity 151 is maximized, the air pipe 3 can transmit air pressure generated by the booster pump 14 into the adjacent air pressure cavity 151, so that the corresponding air pressure plate 13 can apply acting force conveniently.
Referring to fig. 1 and 3, an oil inlet valve 16 communicated with a soft compression oil bag 12 is fixedly connected to the outer wall of a hard-mounted oil tank 11, the soft compression oil bag 12 communicated with the oil inlet valve 16 is far away from a booster air pump 14, an oil tank valve 17 communicated with the soft compression oil bag 12 is arranged on the outer wall of the hard-mounted oil tank 11, the oil tank valve 17 is communicated with the multistage filtering and pressurizing conveying assembly 2, the soft compression oil bag 12 communicated with the oil tank valve 17 is far away from the booster air pump 14, an oil drain valve 18 communicated with the soft compression oil bag 12 is arranged on the outer wall of the hard-mounted oil tank 11, and the soft compression oil bag 12 communicated with the oil drain valve 18 is close to the booster air pump 14.
Referring to fig. 1 and 5, the multistage filtering pressurized delivery assembly 2 includes a coarse oil filter 21 in communication with the oil tank valve 17, a primary oil booster pump 22 in communication with the coarse oil filter 21, a fine oil filter 23 in communication with the primary oil booster pump 22, and a secondary oil booster pump 24 in communication with the fine oil filter 23, the secondary oil booster pump 24 being in communication with an oil inlet of the engine.
The fuel tank valve 17 is opened to enable aviation fuel with certain pressure to be conveyed to the crude oil filter 21, the primary oil booster pump 22 is operated to pump, the crude oil filter 21 is in a negative pressure state, the crude oil filter 21 is convenient to filter the aviation fuel, the secondary oil booster pump 24 is operated to pump, the fine oil filter 23 is in a negative pressure state, and the fine oil filter 23 is convenient to filter the aviation fuel.
A primary one-way oil valve 25 is arranged between the primary oil booster pump 22 and the fine oil filter 23, a secondary one-way oil valve 26 is arranged between the secondary oil booster pump 24 and the engine, the primary one-way oil valve 25 can prevent the reverse flow of aviation fuel into the primary oil booster pump 22 when the primary oil booster pump 22 stops, and the secondary one-way oil valve 26 can prevent the reverse flow of aviation fuel into the secondary oil booster pump 24 when the secondary oil booster pump 24 stops.
Referring to fig. 5 and 6, a coarse filter chamber 211 and a bypass filter chamber 212 are formed in the coarse filter 21, a coarse filter element 213 is disposed in the coarse filter chamber 211, a bypass filter element 214 is disposed in the bypass filter chamber 212, a bypass relief valve 215 is disposed between the coarse filter chamber 211 and the bypass filter chamber 212, and the bypass relief valve 215 is disposed at an oil inlet end of the coarse filter 21.
After the aviation fuel enters the rough filter cavity 211, the rough filter core 213 filters the aviation fuel, when the rough filter core 213 is seriously blocked, the pressure of the aviation fuel entering the rough filter 21 can be gradually increased, when the pressure of the aviation fuel reaches a certain degree, the bypass pressure release valve 215 is opened, the aviation fuel can enter the bypass filter cavity 212, the aviation fuel is filtered through the bypass filter core 214, and the probability of stopping an engine caused by the blockage of the rough filter core 213 is reduced.
Referring to fig. 5 and 7, a fine filter cavity 231 is formed in the fine filter cavity 23, a fine filter element 232 is arranged in the fine filter cavity 231, a bypass valve 233 is arranged between an oil inlet end and an oil outlet end of the fine filter cavity 23, after aviation fuel enters the fine filter cavity 231, the fine filter element 232 filters the aviation fuel, when the fine filter element 232 is seriously blocked, the pressure of the aviation fuel entering the fine filter cavity 23 can be gradually increased, when the pressure of the aviation fuel reaches a certain degree, the bypass valve 233 is opened, the aviation fuel flows out from an outlet end of the fine filter cavity 23 after passing through the bypass valve 233, and the probability that the engine is stopped due to blockage of the fine filter element 232 is reduced.
Referring to fig. 1 and 5, the oil recovery assembly 7 includes a recovery oil pipe 71 communicating with an oil outlet of the engine and an ejector pump 72 communicating with the recovery oil pipe 71, the recovery oil pipe 71 communicating with a low pressure inlet of the ejector pump 72, the primary one-way oil valve 25 communicating with a high pressure inlet of the ejector pump 72, an outlet of the ejector pump 72 communicating with the fine oil filter 23.
The ejector pump 72 is in the prior art, and repeated description is omitted here, so that the high-pressure aviation fuel entering from the high-pressure liquid inlet of the ejector pump 72 can generate negative pressure at the low-pressure liquid inlet, the recovery oil pipe 71 is convenient to extract the aviation fuel flowing out from the oil outlet of the engine, and the efficiency of recovering the redundant aviation fuel of the engine is improved.
The implementation principle of the supercharged oil tank oil supply system for the aircraft is as follows: the pressurizing air pump 14 is operated to pump air into the air pressure cavity 151, the air pressure plate 13 moves towards the direction close to the soft compression oil bag 12, the soft compression oil bag 12 is squeezed, the pressure of aviation fuel in the soft compression oil bag 12 is increased, the oil tank valve 17 is opened to enable aviation fuel with a certain pressure to be conveyed to the coarse oil filter 21, the soft compression oil bag 12 conveys aviation fuel and then is compressed, the phenomenon that a fuel suction inlet is suspended is avoided, meanwhile, the fact that the residual fuel conveyed by the soft compression oil bag 12 generates larger oil waves when an airplane bumps is avoided, the first-stage oil booster pump 22 can extract aviation fuel, the outlet of the coarse oil filter 21 is in a negative pressure state, the aviation fuel is conveniently filtered by the coarse oil filter 21, the aviation fuel between the coarse oil booster pump 21 and the first-stage oil booster pump 22 is conveniently kept at a pressure, the aviation fuel is conveniently conveyed to the fine oil filter 23 after being pressurized by the first-stage oil booster pump 22, the aviation fuel is conveniently conveyed to the fine oil booster pump 23, the second-stage oil booster pump 24 can be conveniently filtered by the fine oil filter 23, the aviation fuel is conveniently conveyed to the fine oil booster pump 24, and the aviation fuel is conveniently and stably conveyed to the aviation engine after the fine oil booster pump 24 is pressurized; in the double filtration consisting of the coarse oil filter 21 and the fine oil filter 23, impurities in aviation fuel can be dispersedly intercepted in the coarse oil filter 21 and the fine oil filter 23, the probability of blocking the oil filter is reduced, and therefore, the fuel supply requirement of an engine can be met under various flight conditions, and the fuel supply can be continuously carried out.
The foregoing are all preferred embodiments of the present application, and are not intended to limit the scope of the present application in any way, therefore: all equivalent changes in structure, shape and principle of this application should be covered in the protection scope of this application.
Claims (9)
1. A supercharged fuel tank fuel supply system for an aircraft, characterized in that: the device comprises a self-pressing oil tank (1) and a multistage filtering, pressurizing and conveying assembly (2) communicated with the self-pressing oil tank (1);
the self-pressure type oil tank (1) comprises a hard-mounted oil tank (11) arranged in a wing, a soft-pressure oil bag (12) arranged in the hard-mounted oil tank (11), an air pressure plate (13) movably arranged in the hard-mounted oil tank (11) and used for extruding the soft-pressure oil bag (12), and a booster air pump (14) arranged on the hard-mounted oil tank (11) and used for pushing the air pressure plate (13);
the multistage filtering, pressurizing and conveying assembly (2) comprises a crude oil filter (21) communicated with the soft compression oil bag (12), a primary oil booster pump (22) communicated with the crude oil filter (21), a fine oil filter (23) communicated with the primary oil booster pump (22) and a secondary oil booster pump (24) communicated with the fine oil filter (23), wherein the secondary oil booster pump (24) is communicated with an oil inlet of an engine;
a plurality of partition plates (111) are arranged in the hard-mounted oil tank (11) at intervals, the inner cavity of the hard-mounted oil tank (11) is divided into a plurality of partition cavities (15) by the partition plates (111), the partition cavities (15) are divided into air pressure cavities (151) and compression bag cavities (152) by the air pressure plates (13), the air pressurizing pump (14) is communicated with the air pressure cavities (151), and vent pipes (3) communicated with adjacent air pressure cavities (151) are arranged on the partition plates (111);
the soft compression oil bags (12) are arranged in the compression bag cavities (152), and control oil valves (4) are arranged between adjacent soft compression oil bags (12).
2. A pressurized tank fuel supply system for aircraft according to claim 1, wherein: every set up two in the interval chamber (15) atmospheric pressure board (13), control oil valve (4) set up on division board (111), just the central axis of control oil valve (4) perpendicular to the focus perpendicular line of hard installation oil tank (11), every set up two on division board (111) breather pipe (3), two breather pipe (3) are about control oil valve (4) symmetry sets up.
3. A pressurized tank fuel supply system for aircraft according to claim 2, wherein: the mouth of pipe that breather pipe (3) is close to booster pump (14) is first mouth of pipe (31), first mouth of pipe (31) are seted up division board (111) are close to the position of control oil valve (4), breather pipe (3) are kept away from the mouth of pipe of booster pump (14) is second mouth of pipe (32), second mouth of pipe (32) are seted up division board (111) are kept away from the position of control oil valve (4).
4. A pressurized tank fuel supply system for aircraft according to claim 1, wherein: the sealing device is characterized in that a sealing ring (5) is arranged on the side face of the air pressure plate (13), a sealing protrusion (51) is arranged on the face, away from the air pressure plate (13), of the sealing ring (5), balls (6) are movably arranged on the side face, provided with the sealing ring (5), of the air pressure plate (13), and the sealing ring (5) is arranged at the position, close to the soft compression oil bag (12), of the air pressure plate (13).
5. The pressurized fuel tank fuel supply system for aircraft according to claim 4, wherein: an oil inlet valve (16) communicated with the soft compression oil bag (12) is arranged on the outer wall of the hard installation oil tank (11), and the soft compression oil bag (12) communicated with the oil inlet valve (16) is far away from the booster air pump (14);
the oil tank valve (17) communicated with the soft compression oil bag (12) is arranged on the outer wall of the hard-mounted oil tank (11), the oil tank valve (17) is communicated with the crude oil filter (21), the oil drain valve (18) communicated with the soft compression oil bag (12) is arranged on the outer wall of the hard-mounted oil tank (11), and the soft compression oil bag (12) communicated with the oil drain valve (18) is close to the booster air pump (14).
6. A pressurized tank fuel supply system for an aircraft according to claim 5, wherein: a coarse filter cavity (211) and a bypass filter cavity (212) are formed in the coarse oil filter (21), a coarse filter element (213) is arranged in the coarse filter cavity (211), a bypass filter element (214) is arranged in the bypass filter cavity (212), a bypass pressure relief valve (215) is arranged between the coarse filter cavity (211) and the bypass filter cavity (212), and the bypass pressure relief valve (215) is arranged at the oil inlet end of the coarse oil filter (21).
7. The pressurized fuel tank fuel supply system for aircraft according to claim 6, wherein: a fine filter cavity (231) is formed in the fine oil filter (23), a fine filter element (232) is arranged in the fine filter cavity (231), and a bypass valve (233) is arranged between an oil inlet end and an oil outlet end of the fine oil filter (23).
8. A pressurized tank fuel supply system for an aircraft according to claim 7, wherein: a primary one-way oil valve (25) is arranged between the primary oil booster pump (22) and the fine oil filter (23), and a secondary one-way oil valve (26) is arranged at the outlet end of the secondary oil booster pump (24).
9. A pressurized tank fuel supply system for aircraft according to claim 8, wherein: still include oil recovery subassembly (7), oil recovery subassembly (7) include with recovery oil pipe (71) of engine oil-out intercommunication and with injection pump (72) of recovery oil pipe (71) intercommunication, recovery oil pipe (71) with the low pressure inlet intercommunication of injection pump (72), one-level one-way oil valve (25) with the high pressure inlet intercommunication of injection pump (72), the export of injection pump (72) with fine oil filter (23) intercommunication.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310279598.1A CN116119014B (en) | 2023-03-21 | 2023-03-21 | Supercharged oil tank oil supply system for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310279598.1A CN116119014B (en) | 2023-03-21 | 2023-03-21 | Supercharged oil tank oil supply system for airplane |
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| Publication Number | Publication Date |
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| CN116119014A CN116119014A (en) | 2023-05-16 |
| CN116119014B true CN116119014B (en) | 2024-02-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202310279598.1A Active CN116119014B (en) | 2023-03-21 | 2023-03-21 | Supercharged oil tank oil supply system for airplane |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625297A (en) * | 2018-12-11 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of fuel system for Small General Aircraft |
| CN209719944U (en) * | 2019-02-27 | 2019-12-03 | 杭州牧星科技有限公司 | External pressurization oil supply system |
| CN110525668A (en) * | 2019-09-26 | 2019-12-03 | 上海啸风航空科技有限公司 | A kind of fuel bunker of novel belt axial limiting compression |
| CN112706931A (en) * | 2021-01-27 | 2021-04-27 | 西安九天航空科技有限公司 | Unmanned aerial vehicle fuel supply system and fuel supply and refueling control method |
| CN115266116A (en) * | 2022-06-28 | 2022-11-01 | 中国航发南方工业有限公司 | Aircraft engine fuel oil feeding system |
-
2023
- 2023-03-21 CN CN202310279598.1A patent/CN116119014B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625297A (en) * | 2018-12-11 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of fuel system for Small General Aircraft |
| CN209719944U (en) * | 2019-02-27 | 2019-12-03 | 杭州牧星科技有限公司 | External pressurization oil supply system |
| CN110525668A (en) * | 2019-09-26 | 2019-12-03 | 上海啸风航空科技有限公司 | A kind of fuel bunker of novel belt axial limiting compression |
| CN112706931A (en) * | 2021-01-27 | 2021-04-27 | 西安九天航空科技有限公司 | Unmanned aerial vehicle fuel supply system and fuel supply and refueling control method |
| CN115266116A (en) * | 2022-06-28 | 2022-11-01 | 中国航发南方工业有限公司 | Aircraft engine fuel oil feeding system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116119014A (en) | 2023-05-16 |
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