CN115535268B - Aircraft fuel cooling system based on flight safety guarantee - Google Patents
Aircraft fuel cooling system based on flight safety guarantee Download PDFInfo
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- CN115535268B CN115535268B CN202211496562.0A CN202211496562A CN115535268B CN 115535268 B CN115535268 B CN 115535268B CN 202211496562 A CN202211496562 A CN 202211496562A CN 115535268 B CN115535268 B CN 115535268B
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- 239000000446 fuel Substances 0.000 title claims abstract description 83
- 238000001816 cooling Methods 0.000 title claims abstract description 42
- 238000002485 combustion reaction Methods 0.000 claims abstract description 62
- 239000007788 liquid Substances 0.000 claims abstract description 11
- 238000010992 reflux Methods 0.000 claims description 14
- 238000012544 monitoring process Methods 0.000 claims description 8
- 239000007921 spray Substances 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 6
- 239000002828 fuel tank Substances 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 2
- 239000003921 oil Substances 0.000 abstract description 147
- 239000000295 fuel oil Substances 0.000 abstract description 48
- 239000004449 solid propellant Substances 0.000 abstract description 15
- 239000003507 refrigerant Substances 0.000 abstract description 6
- 238000000034 method Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 9
- 239000007787 solid Substances 0.000 description 5
- 238000010521 absorption reaction Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 4
- 238000004891 communication Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 206010060904 Freezing phenomenon Diseases 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000009827 uniform distribution Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
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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
- B64D37/34—Conditioning fuel, e.g. heating
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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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an aircraft fuel cooling system based on flight safety guarantee, and relates to the technical field of flight safety guarantee. The fuel oil return system comprises an oil storage module, a fuel oil conveying module and a fuel oil return module, wherein an oil storage area comprises a preheating oil tank and a feeding oil tank, and a driving conveying box and a return pump are arranged in the preheating oil tank. According to the invention, the preheating pipe with the preheating cavity and the spiral pipe structure is additionally arranged in the turbojet engine, solid fuel oil is used as a refrigerant to cool the combustion cover and the drive scroll, and meanwhile, the solid fuel oil can be preheated by using the preheating of the combustion cover and the heat generated by the work of the drive scroll, so that the fuel oil in the oil tank is always kept in a liquid state, and the fuel oil is prevented from being frozen quickly; through setting up drive transport box, oil delivery axle and backwash pump, can discharge solid fuel from preheating the oil tank, flow back to the feed oil tank after preheating and cooling work, then pour into again and preheat inside the oil tank, realize liquid fuel dynamic balance, ensured the flight stability when the solution problem.
Description
Technical Field
The invention belongs to the technical field of flight safety guarantee, and particularly relates to an aircraft fuel cooling system based on flight safety guarantee.
Background
Aircraft are important vehicles in modern human society, which are able to transport passengers quickly to other seas at high speed, but as such, fuel reserves are also a significant problem during flight; in normal flight operation, fuel carried by the aircraft is usually sufficient and is stored in a solid state; however, when encountering extremely cold weather, the solid fuel oil is easier to freeze and cannot be used continuously, thereby causing flight accidents; in addition, the most common use of the existing aircraft is the turbojet engine, the cooling mode of the combustion chamber of the turbojet engine is usually air cooling, and although the cooling mode is finally used in the combustion-supporting process of the combustion chamber, the single function still causes a large amount of waste heat in the combustion chamber to be not utilized and wasted; therefore, after researching the structure of the existing airplane and the working principle of the turbojet engine, the two problems are combined, and the airplane fuel oil cooling system based on flight safety guarantee is designed to improve the existing airplane to a certain extent.
Disclosure of Invention
The invention aims to provide an aircraft fuel cooling system based on flight safety guarantee, and solves the problems that the existing solid fuel is easy to freeze when meeting extremely cold weather and the efficiency of a gas cooling engine is low.
In order to solve the technical problems, the invention is realized by the following technical scheme:
the invention relates to an aircraft fuel cooling system based on flight safety guarantee, which comprises an oil storage module, an oil quantity monitoring module, a fuel conveying module, a power module and a fuel backflow module, wherein the oil storage module is arranged in wings, comprises two oil storage areas and is respectively arranged on the wings on two sides; the oil storage area comprises a preheating oil tank and a plurality of feeding oil tanks, wherein the preheating oil tank is communicated with the feeding oil tank, and the feeding oil tanks are mutually isolated; according to the structure of the oil tank arranged in the wing of the traditional airplane, the oil tanks on the wing on the same side are divided into a preheating oil tank and a feeding oil tank in the technical scheme, so that the functions of the oil tanks are refined, and the specific mode is that solid fuel oil is sent out from the preheating oil tank to participate in the preheating of the fuel oil and the cooling of an engine by utilizing the fuel oil, after the preheating and the cooling are finished, on one hand, the solid fuel oil directly participates in the combustion driving work, and on the other hand, the residual oil flows back into the feeding oil tank, so that the heat dissipation cooling and preheating work circulation of the fuel oil is realized; the power module is a turbojet engine and comprises a vortex cover and a driving vortex shaft, and the driving vortex shaft is rotationally clamped with the vortex cover; a preheating cavity is arranged in the vortex cover and is communicated with the oil storage area; the turbojet engine is a common aircraft engine in the prior art, and the preheating cavity is additionally arranged in the engine, so that fuel can be preheated, and a combustion chamber of the engine can be cooled in time by utilizing the heat absorption process of the fuel;
the peripheral side face of the driving scroll shaft is connected with a plurality of driving scrolls and a plurality of driven scrolls in a mortise-tenon manner, wherein the driving scrolls and the driven scrolls are respectively arranged at two opposite ends of the driving scroll shaft; the inner surface of the vortex cover is fixedly welded with a combustion cover, and the drive vortex shaft is in rotary fit with the combustion cover; the combustion cover is of a cylinder structure, and a combustion cavity is formed in the cylinder wall of the combustion cover; the preheating cavity is arranged between the combustion cover and the drive scroll shaft, the combustion cover is a conventional combustion chamber, the combustion chamber is relatively sealed by utilizing a cylindrical structure with a hollow cylindrical wall, so that heat generated by combustion is not easy to lose and is directly discharged to act on the drive scroll fan, the preheating cavity is arranged between the combustion cover and the drive scroll shaft, fuel oil can be directly acted on the combustion cover and the drive scroll shaft as a refrigerant, and the cooling efficiency and the fuel oil preheating efficiency are improved; a preheating pipe is arranged in the preheating cavity, is of a spiral pipe structure and is rotatably nested between the drive scroll and the combustion cover; by combining the structure, when fuel is injected into the spirally wound preheating pipe, the outer side absorbs the heat of the combustion cover, and the inner side absorbs the heat of the driving scroll, so that the preheating and cooling are realized efficiently; one end of the preheating pipe extends to the interior of the preheating oil tank and is a preheating end, and the other end of the preheating pipe extends to the interior of the feeding oil tank and is an oil supply return end; namely, the fuel oil is discharged from the preheating oil tank to participate in cooling and preheating work, and then flows back to the feeding oil tank for storage;
a communicating cavity is formed in the wall of the vortex cover, and a plurality of fuel spray pipes are welded and communicated between the communicating cavity and the combustion cavity; the communicating cavity and the fuel spray pipe are both arranged on one side of the oil supply return end of the preheating pipe of the vortex cover, and the communicating cavity is communicated with the preheating pipe; by combining the structure, after the fuel oil is cooled and preheated until the fuel oil flows back, one part of the fuel oil is injected into the fuel spray pipe through the communicating cavity to participate in combustion reaction, and the other part of the fuel oil flows back to be stored.
Furthermore, the fuel delivery module comprises a driving delivery box and a fuel delivery shaft, wherein a spiral keel is welded on the peripheral side surface of the fuel delivery shaft; the inner surface of the preheating oil tank is welded with a baffle, the oil conveying shaft is connected with the baffle through a rotating shaft, and the conveying box is driven to be bolted and fixed on the upper surface of the baffle.
Furthermore, a driven fluted disc is welded at the upper end of the oil conveying shaft and is arranged inside the driving conveying box; the lower end of the oil conveying shaft extends to the preheating end of the preheating pipe; a conveying motor is fixedly bolted on the inner surface of the driving conveying box, and one end of an output shaft of the conveying motor is welded with a driving gear; the driving gear is meshed with the driven fluted disc; by combining the structure, when the conveying motor is started, the driving gear drives the driven fluted disc and the oil conveying shaft to rotate, and the spiral keel of the oil conveying shaft conveys solid oil out through the preheating pipe by utilizing the spiral conveying structure to participate in preheating and cooling work.
Furthermore, a buffer area and an oil supply area are respectively arranged in the preheating oil tank through a baffle plate, wherein the buffer area is positioned above the oil supply area; the surface of the baffle is provided with a communicating opening, and the oil supply area and the buffer area are communicated with each other through the communicating opening; the buffer area is used for cooling and buffering the fuel oil after absorbing heat, and then the fuel oil flows into the fuel supply area through the communication port to participate in circulating preheating fuel oil supply.
Further, the oil mass monitoring module includes oil-carrying clamp plate and pressure sensor, wherein oil-carrying clamp plate and the slip block of feed oil tank internal surface, and pressure sensor sets up between the bottom surface of oil-carrying clamp plate and feed oil tank.
Further, the fuel return module comprises a return pump and a return pipe; the reflux pump is fixedly bolted with the inner surface of the preheating oil tank and is positioned in the buffer zone; the reflux pumps are electric liquid pumps, and the number of the reflux pumps is the same as that of the feeding oil tanks; the return pipe is arranged between the preheating oil tank and the feeding oil tank, one end of the return pipe extends to the interior of the return pump, and the other end of the return pipe extends to the lower part of the oil-carrying pressure plate.
Furthermore, the oil-carrying pressure plate is fixedly connected with a return pipe, and the return pipe is of a tile-shaped hose structure; the surface of the oil-carrying pressure plate is provided with a plurality of backflow holes, and the backflow holes are in inverted cone-shaped hole structures; a starting switch is arranged on one side surface of the backflow pipe, wherein the starting switch is of a light touch switch structure and is electrically connected with the backflow pump;
by integrating the structure, in the fuel oil backflow process, liquid fuel oil is firstly injected into a feed oil tank, and due to the fact that the initial flow rate is high, an oil carrying pressure plate presses down a pressure sensor under the action of fuel oil stamping and self gravity, and the oil quantity is measured in real time; when fuel in the preheating oil tank is continuously reduced, the backflow flow rate is reduced, the fuel carrying pressure plate floats upwards under the action of fuel buoyancy until the starting switch is touched, so that the backflow pump is started to pump the fuel in the fuel supply oil tank to the inside of the preheating oil tank and continuously participate in preheating and cooling work, in the process, the fuel is conveyed to the fuel supply oil tanks on two sides from the central preheating oil tank and then flows back to the central preheating oil tank again, and the fuel keeps dynamic uniform distribution.
Furthermore, a plurality of air inlets and a plurality of air outlets are respectively arranged at two opposite ends of the combustion cover, wherein the air inlets are opposite to the driven turbofan, and the air outlets are opposite to the driving turbofan.
It is added that in the structure, the oil-carrying pressure plate automatically floats upwards to be in a limit working state, and in a conventional working state, an oil quantity monitoring threshold value is arranged in a central processing unit of the airplane, and when the pressure measured by the pressure sensor exceeds the threshold value, the reflux pump can be started to reflux oil materials; in addition, the technical scheme still needs to ensure that the turbojet engine is in a working state before working, so a starting ignition device is also arranged between the feeding oil tank and the turbojet engine to ensure that the turbojet engine is smoothly started;
by combining the structure, the technical scheme mainly utilizes the solid fuel oil as the refrigerant to cool the combustion cover and the drive scroll of the turbojet engine, and simultaneously preheats the solid fuel oil by utilizing the heat generated by the preheating of the combustion cover and the work of the drive scroll, so that the quick-freezing phenomenon of the fuel oil in extremely cold weather can be effectively avoided, and the occurrence of flight accidents is reduced; in actual work, the specific workflow is as follows: in the initial state, the fuel is solid, the preheating oil tank and the feeding oil tank are in full load state, the fuel-carrying pressure plate and the return pipe are both placed at the top of the fuel, because the turbojet engine is in a starting state, the conveying motor is started simultaneously to convey the fuel to the preheating pipe to participate in preheating and cooling work, one part of the fuel after heat absorption participates in combustion reaction, the other part of the fuel returns to the feeding oil tank, and the return pump is also in a starting state at the moment and can pump the fuel returning from the top to the preheating oil tank; when the initial fuel in the fuel tank is exhausted, all the fuel in the fuel supply area is in liquid state, and the processes of cooling, preheating and refluxing in a circulating reciprocating mode can be realized.
The invention has the following beneficial effects:
according to the invention, the preheating pipe with the preheating cavity and the spiral pipe structure is additionally arranged in the turbojet engine, solid fuel oil is used as a refrigerant to cool the combustion cover and the drive scroll, and meanwhile, the solid fuel oil can be preheated by utilizing the preheating of the combustion cover and the heat generated by the work of the drive scroll, so that the fuel oil in the oil tank is always kept in a liquid state, and the phenomenon of quick freezing of the fuel oil is avoided; wherein carry box, oil delivery axle and backwash pump through setting up the drive, can discharge solid-state fuel from preheating the oil tank, flow back to the feed oil tank after preheating and cooling work, then pour into again and preheat inside the oil tank, realize liquid fuel dynamic balance, ensured the flight stability when solving the problem.
Of course, it is not necessary for any product in which the invention is practiced to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a device assembly structure diagram of an aircraft fuel cooling system based on flight safety guarantee according to the present invention;
FIG. 2 is a partial assembly structure diagram of an aircraft fuel cooling system based on flight safety assurance according to the present invention;
FIG. 3 is a front view of FIG. 2;
FIG. 4 isbase:Sub>A schematic view of the structure of section A-A in FIG. 3;
FIG. 5 is a partial view of portion C of FIG. 4;
FIG. 6 is a schematic view of the structure of section D-D in FIG. 4;
FIG. 7 is a partial display view of portion E of FIG. 6;
FIG. 8 is a partial view of portion F of FIG. 6;
FIG. 9 is a schematic view of the section B-B in FIG. 3;
FIG. 10 is a schematic view of the distribution inside the oil feeding zone.
In the drawings, the reference numbers indicate the following list of parts:
1. preheating an oil tank; 2. a feeding oil tank; 3. a turbojet engine; 4. a vortex cover; 5. a drive scroll; 6. a preheating chamber; 7. driving a turbofan; 8. a driven turbofan; 9. a combustion case; 10. a combustion chamber; 11. a preheating pipe; 12. communicating the cavity; 13. a fuel nozzle; 14. driving the transport box; 15. an oil delivery shaft; 16. a spiral keel; 17. a baffle plate; 18. a driven fluted disc; 19. a conveying motor; 20. a drive gear; 21. an oil-carrying pressure plate; 22. a reflux pump; 23. a return pipe; 24. a return orifice; 25. starting a switch; 26. an air inlet; 27. and (4) exhausting holes.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "middle", "outer", "inner", and the like, indicate an orientation or positional relationship, are used merely to facilitate the description of the invention and to simplify the description, and do not indicate or imply that the referenced components or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the invention.
Referring to fig. 1 to 10, the invention relates to an aircraft fuel cooling system based on flight safety guarantee, which comprises an oil storage module, an oil quantity monitoring module, a fuel delivery module, a power module and a fuel backflow module, wherein the oil storage module is arranged in wings, comprises two oil storage areas and is respectively arranged on two wings at two sides; the oil storage area comprises a preheating oil tank 1 and a plurality of feeding oil tanks 2, wherein the preheating oil tank 1 is communicated with the feeding oil tanks 2, and the feeding oil tanks 2 are mutually isolated; according to the structure of the oil tank arranged in the wing of the traditional airplane, a plurality of oil tanks on the wing on the same side are divided into a preheating oil tank 1 and a feeding oil tank 2 in the technical scheme, so that the functions of the oil tanks are refined, and the specific mode is that solid fuel oil is sent out from the preheating oil tank 1 to participate in the preheating of the fuel oil and the cooling of an engine by utilizing the fuel oil, after the preheating and the cooling are finished, on one hand, the solid fuel oil directly participates in the combustion driving work, and on the other hand, the residual oil flows back into the feeding oil tank 2, so that the heat dissipation cooling and the preheating work circulation of the fuel oil are realized; the power module is a turbojet engine 3 and comprises a vortex cover 4 and a drive vortex shaft 5, and the drive vortex shaft 5 is rotationally clamped with the vortex cover 4; a preheating cavity 6 is arranged in the vortex cover 4, and the preheating cavity 6 is communicated with an oil storage area; the turbojet engine 3 is a common aircraft engine in the prior art, and the preheating cavity 6 is additionally arranged in the engine in the technical scheme, so that fuel oil can be preheated, and a combustion chamber of the engine can be cooled in time by using the heat absorption process of the fuel oil;
a plurality of driving scroll fans 7 and a plurality of driven scroll fans 8 are connected to the peripheral side surfaces of the driving scroll shaft 5 in a mortise and tenon manner, wherein the driving scroll fans 7 and the driven scroll fans 8 are respectively arranged at two opposite ends of the driving scroll shaft 5; the inner surface of the vortex cover 4 is fixedly welded with a combustion cover 9, and the drive vortex shaft 5 is in rotary fit with the combustion cover 9; the combustion cover 9 is of a cylinder structure, and a combustion cavity 10 is formed in the cylinder wall of the combustion cover; the preheating cavity 6 is arranged between the combustion cover 9 and the drive scroll 5, wherein the combustion cover 9 is a conventional combustion chamber, the combustion chamber is relatively sealed by utilizing a cylindrical structure with a hollow cylindrical wall, so that heat generated by combustion is not easy to lose and is directly discharged to act on the drive turbofan 7, the preheating cavity 6 is arranged between the combustion cover 9 and the drive scroll 5, fuel oil can be directly acted on the combustion cover 9 and the drive scroll 5 as a refrigerant, and the cooling efficiency and the fuel oil preheating efficiency are improved; a preheating pipe 11 is arranged in the preheating cavity 6, wherein the preheating pipe 11 is of a spiral pipe structure and is rotatably nested between the drive scroll 5 and the combustion cover 9; with the structure, when fuel is injected into the spirally wound preheating pipe 11, the outer side absorbs the heat of the combustion cover 9, and the inner side absorbs the heat of the driving scroll 5, so that the preheating and cooling are realized efficiently; one end of the preheating pipe 11 extends to the inside of the preheating oil tank 1 to be a preheating end, and the other end extends to the inside of the feeding oil tank 2 to be an oil supply return end; namely, the fuel oil is discharged from the preheating oil tank 1 to participate in cooling and preheating work, and then flows back to the feeding oil tank 2 to be stored;
a communicating cavity 12 is arranged in the wall of the vortex cover 4, and a plurality of fuel spray pipes 13 are welded and communicated between the communicating cavity 12 and the combustion cavity 10; the communicating cavity channel 12 and the fuel spray pipe 13 are both arranged on one side of the oil supply return end of the preheating pipe 11 of the vortex cover 4, and the communicating cavity channel 12 is communicated with the preheating pipe 11; by combining the structure, after the fuel oil is cooled and preheated until the fuel oil flows back, one part of the fuel oil is injected into the fuel spray pipe 13 through the communicating cavity 12 to participate in combustion reaction, and the other part of the fuel oil flows back to be stored.
Preferably, the fuel delivery module comprises a driving delivery box 14 and a fuel delivery shaft 15, wherein a spiral keel 16 is welded on the peripheral side surface of the fuel delivery shaft 15; the inner surface of the preheating oil tank 1 is welded with a baffle 17, an oil conveying shaft 15 is rotatably coupled with the baffle 17, and a driving conveying box 14 is bolted and fixed on the upper surface of the baffle 17.
Preferably, a driven fluted disc 18 is welded at the upper end of the oil conveying shaft 15, and the driven fluted disc 18 is arranged inside the driving conveying box 14; the lower end of the oil delivery shaft 15 extends to the preheating end of the preheating pipe 11; a conveying motor 19 is fixedly bolted on the inner surface of the driving conveying box 14, and one end of an output shaft of the conveying motor 19 is welded with a driving gear 20; the driving gear 20 is meshed with the driven fluted disc 18; with the above structure, when the conveying motor 19 is started, the driving gear 20 drives the driven fluted disc 18 and the oil conveying shaft 15 to rotate, and the spiral keel 16 of the oil conveying shaft 15 conveys solid oil out through the preheating pipe 11 by using the spiral conveying structure to participate in preheating and cooling work.
Preferably, the interior of the preheating oil tank 1 is divided into a buffer area and an oil supply area by a baffle 17, wherein the buffer area is positioned above the oil supply area; the surface of the baffle 17 is provided with a communication port, and the oil supply area and the buffer area are communicated with each other through the communication port; the buffer area is used for cooling and buffering the fuel after absorbing heat, and then the fuel flows into the fuel supply area through the communication port to participate in circulating preheating fuel supply.
Preferably, the oil amount monitoring module includes an oil-carrying pressure plate 21 and a pressure sensor, wherein the oil-carrying pressure plate 21 is slidably engaged with the inner surface of the feeding oil tank 2, and the pressure sensor is disposed between the oil-carrying pressure plate 21 and the bottom surface of the feeding oil tank 2.
Preferably, the fuel return module comprises a return pump 22 and a return pipe 23; the reflux pump 22 is fixedly bolted with the inner surface of the preheating oil tank 1 and is positioned in the buffer zone; the return pump 22 is an electric liquid pump, and the number of the return pumps is the same as that of the feed oil tank 2; the return pipe 23 is disposed between the preheating oil tank 1 and the feeding oil tank 2, and has one end extending to the inside of the return pump 22 and the other end extending to the lower side of the oil-carrying pressure plate 21.
Preferably, the oil-carrying pressure plate 21 is fixedly connected with the return pipe 23, and the return pipe 23 is of a tile-shaped hose structure; the surface of the oil-carrying pressure plate 21 is provided with a plurality of return holes 24, and the return holes 24 are in an inverted conical hole structure; a starting switch 25 is arranged on one side surface of the return pipe 23, wherein the starting switch 25 is of a light-touch switch structure and is electrically connected with the return pump 22;
by integrating the structure, in the fuel oil backflow process, liquid fuel oil is firstly injected into the feeding fuel tank 2, and the fuel loading pressure plate 21 presses down the pressure sensor under the actions of fuel oil stamping and self gravity due to high initial flow rate, so that the fuel oil quantity is measured in real time; when the fuel in the preheating oil tank 1 is continuously reduced, the backflow flow rate is reduced, the fuel-carrying pressing plate 21 floats upwards under the action of fuel buoyancy until the starting switch 25 is touched, so that the backflow pump 22 is started, the fuel in the feeding oil tank 2 is pumped into the preheating oil tank 1 and continuously participates in preheating and cooling work, in the process, the fuel is conveyed to the feeding oil tanks 2 on two sides from the central preheating oil tank 1 and then flows back to the central preheating oil tank 1 again, and the fuel is kept in dynamic uniform distribution.
Preferably, the opposite ends of the combustion cover 9 are respectively provided with a plurality of air inlets 26 and a plurality of air outlets 27, wherein the air inlets 26 are opposite to the driven turbofan 8, and the air outlets 27 are opposite to the driving turbofan 7.
It is to be added that, in the above structure, the oil-carrying pressure plate 21 floats up automatically to the limit working state, and in the normal working state, an oil quantity monitoring threshold is set in the central processing unit of the aircraft, when the pressure measured by the pressure sensor exceeds the threshold, the reflux pump 22 can be started to reflux the oil material; in addition, the technical scheme still needs to ensure that the turbojet engine 3 is in a working state before working, so a starting ignition device is also arranged between the feeding oil tank 2 and the turbojet engine 3 to ensure that the turbojet engine 3 is smoothly started;
by combining the structure, the technical scheme mainly utilizes the solid fuel oil as a refrigerant to cool the combustion cover 9 and the drive scroll 5 of the turbojet engine 3, and simultaneously preheats the solid fuel oil by utilizing the preheating of the combustion cover 9 and the heat generated by the work of the drive scroll 5, so that the quick-freezing phenomenon of the fuel oil in extreme cold weather can be effectively avoided, and the occurrence of flight accidents is reduced; in actual work, the specific workflow is as follows: in an initial state, fuel oil is solid, the preheating oil tank 1 and the feeding oil tank 2 are in a full-load state, the fuel-carrying pressure plate 21 and the return pipe 23 are both placed at the uppermost part of the fuel oil, because the turbojet engine 3 is in a starting state, the conveying motor 19 is started at the same time to convey the fuel oil to the preheating pipe 11 to participate in preheating and cooling work, one part of the fuel oil after heat absorption participates in combustion reaction, the other part of the fuel oil flows back to the feeding oil tank 2, and the return pump 22 is also in a starting state at the moment and can pump the fuel oil flowing back from the upper part to the preheating oil tank 1; when the initial fuel in the feeding fuel tank 2 is exhausted, all the fuel in the fuel supply area is in a liquid state, and the processes of cooling, preheating and refluxing in a circulating reciprocating mode can be achieved.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (4)
1. The utility model provides an aircraft fuel cooling system based on flight safety guarantee, includes oil storage module, oil mass monitoring module, fuel delivery module, power module and fuel backward flow module, its characterized in that: the oil storage module is arranged in the wings, comprises two oil storage areas and is respectively arranged on the wings on two sides; the oil storage area comprises a preheating oil tank (1) and a plurality of feeding oil tanks (2), wherein the preheating oil tank (1) is communicated with the feeding oil tanks (2), and the feeding oil tanks (2) are mutually isolated; the power module is a turbojet engine (3) and comprises a vortex cover (4) and a drive vortex shaft (5), and the drive vortex shaft (5) is rotationally clamped with the vortex cover (4); a preheating cavity (6) is arranged in the vortex cover (4), and the preheating cavity (6) is communicated with the oil storage area;
the peripheral side face of the driving scroll shaft (5) is in mortise and tenon connection with a plurality of driving scrolls (7) and a plurality of driven scrolls (8), wherein the driving scrolls (7) and the driven scrolls (8) are respectively arranged at two opposite ends of the driving scroll shaft (5); the combustion cover (9) is fixedly welded on the inner surface of the vortex cover (4), and the driving vortex shaft (5) is in rotary fit with the combustion cover (9); the combustion cover (9) is of a cylinder structure, and a combustion cavity (10) is formed in the cylinder wall of the combustion cover; the preheating cavity (6) is arranged between the combustion cover (9) and the drive scroll (5); a preheating pipe (11) is arranged in the preheating cavity (6), wherein the preheating pipe (11) is of a spiral pipe structure and is rotatably nested between the drive scroll (5) and the combustion cover (9); one end of the preheating pipe (11) extends to be communicated with the interior of the preheating oil tank (1) and serves as a preheating end, and the other end of the preheating pipe extends to the interior of the feeding oil tank (2) and serves as an oil supply backflow end;
a communicating cavity (12) is formed in the wall of the vortex cover (4), and a plurality of fuel spray pipes (13) are welded and communicated between the communicating cavity (12) and the combustion cavity (10); the communicating cavity (12) and the fuel spray pipe (13) are both arranged on one side of the oil supply return end of the preheating pipe (11) of the vortex cover (4), and the communicating cavity (12) is communicated with the preheating pipe (11);
the oil quantity monitoring module comprises an oil-carrying pressure plate (21) and a pressure sensor, wherein the oil-carrying pressure plate (21) is clamped with the inner surface of the feeding oil tank (2) in a sliding manner, and the pressure sensor is arranged between the oil-carrying pressure plate (21) and the bottom surface of the feeding oil tank (2);
the fuel return module comprises a return pump (22) and a return pipe (23); the reflux pump (22) is fixedly bolted with the inner surface of the preheating oil tank (1) and is positioned in the buffer zone; the reflux pumps (22) are electric liquid pumps, and the number of the reflux pumps is the same as that of the feed oil tanks (2); the return pipe (23) is arranged between the preheating oil tank (1) and the feeding oil tank (2), one end of the return pipe extends to the inside of the return pump (22), and the other end of the return pipe extends to the lower part of the oil-carrying pressure plate (21);
the oil-carrying pressure plate (21) is fixedly connected with the return pipe (23), and the return pipe (23) is of a tile-shaped hose structure; the surface of the oil-carrying pressing plate (21) is provided with a plurality of backflow holes (24), and the backflow holes (24) are in an inverted conical hole structure;
a starting switch (25) is arranged on one side surface of the return pipe (23), wherein the starting switch (25) is of a light touch switch structure and is electrically connected with the return pump (22); the two opposite ends of the combustion cover (9) are respectively provided with a plurality of air inlets (26) and a plurality of air outlets (27), wherein the air inlets (26) are opposite to the driven turbofan (8), and the air outlets (27) are opposite to the driving turbofan (7).
2. The aircraft fuel cooling system based on flight safety guarantee according to claim 1, characterized in that the fuel delivery module comprises a driving delivery box (14) and a fuel delivery shaft (15), wherein a spiral keel (16) is welded on the peripheral side of the fuel delivery shaft (15); the inner surface of the preheating oil tank (1) is welded with a baffle (17), the oil conveying shaft (15) is in rotating shaft connection with the baffle (17), and the driving conveying box (14) is bolted and fixed on the upper surface of the baffle (17).
3. The aircraft fuel cooling system based on flight safety guarantee of claim 2, wherein a driven fluted disc (18) is welded at the upper end of the fuel delivery shaft (15), and the driven fluted disc (18) is arranged inside the driving delivery box (14); the lower end of the oil delivery shaft (15) extends to the preheating end of the preheating pipe (11); a conveying motor (19) is fixedly bolted to the inner surface of the driving conveying box (14), and one end of an output shaft of the conveying motor (19) is welded with a driving gear (20); the driving gear (20) is meshed with the driven fluted disc (18).
4. The aircraft fuel cooling system based on flight safety guarantee according to claim 3, wherein the interior of the preheating fuel tank (1) is provided with a buffer area and a fuel supply area respectively through a baffle (17), wherein the buffer area is positioned above the fuel supply area; the surface of the baffle (17) is provided with a communicating opening, and the oil supply area and the buffer area are communicated with each other through the communicating opening.
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| CN202211496562.0A CN115535268B (en) | 2022-11-28 | 2022-11-28 | Aircraft fuel cooling system based on flight safety guarantee |
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Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9221035D0 (en) * | 1991-10-17 | 1992-11-18 | Gec Aerospace Ltd | Aircraft fuel heating systems |
| JPH08200031A (en) * | 1995-01-25 | 1996-08-06 | Akemasa Otani | Engine oil circulation controller |
| JP2009047138A (en) * | 2007-08-22 | 2009-03-05 | Toyota Motor Corp | Internal combustion engine |
| CN202132114U (en) * | 2011-07-18 | 2012-02-01 | 中国人民解放军徐州空军学院 | Oil seal supply device of aircraft engine |
| CN103104309A (en) * | 2011-11-10 | 2013-05-15 | 福特环球技术公司 | A method for improving warm-up of an engine |
| CN203532109U (en) * | 2013-09-22 | 2014-04-09 | 河北钢铁集团矿业有限公司 | Fuel oil pre-heating device for strip mine dumper |
| WO2014105328A1 (en) * | 2012-12-28 | 2014-07-03 | General Electric Company | System for temperature and actuation control and method of controlling fluid temperatures in an aircraft |
| CN205677736U (en) * | 2016-05-17 | 2016-11-09 | 内蒙古包钢钢联股份有限公司 | A kind of diesel-type vehicle fuel pre-heating system |
| CN109515728A (en) * | 2018-11-08 | 2019-03-26 | 北京航空航天大学 | Aircraft heat management system and method with auxiliary hot oil case circuit |
| CN110080872A (en) * | 2019-05-30 | 2019-08-02 | 李明珠 | Engine new fuel oil cooling heat radiation system |
| CN112441242A (en) * | 2021-01-08 | 2021-03-05 | 金陵科技学院 | Fuel tank inerting system with coupled membrane nitrogen production and fuel cell and using method |
| CN113135296A (en) * | 2021-05-14 | 2021-07-20 | 金陵科技学院 | System for inhibiting fuel oil coking and working method thereof |
| CN113202678A (en) * | 2021-06-15 | 2021-08-03 | 北京理工大学 | Air inlet preheating system of diesel engine |
| CN114180079A (en) * | 2021-12-17 | 2022-03-15 | 南京航空航天大学 | Onboard fuel tank inerting method based on fuel oil comprehensive thermal management |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6021661B2 (en) * | 2013-01-30 | 2016-11-09 | 三菱重工業株式会社 | Fuel supply system, scramjet engine and method of operating the same |
| WO2014127146A1 (en) * | 2013-02-13 | 2014-08-21 | Mcalister Technologies, Llc | Systems and methods for improved engine cooling and energy generation |
| US9587546B2 (en) * | 2013-10-02 | 2017-03-07 | Ford Global Technologies, Llc | Methods and systems for hybrid vehicle waste heat recovery |
| CN107269432A (en) * | 2017-05-24 | 2017-10-20 | 张家港海纳德智能科技有限公司 | A kind of metering reflux for gasoline |
| CN108100273B (en) * | 2017-11-29 | 2021-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel cooling system |
| CN113716055B (en) * | 2021-08-17 | 2022-07-12 | 南京航空航天大学 | Fuel oil comprehensive heat management system and working method thereof |
-
2022
- 2022-11-28 CN CN202211496562.0A patent/CN115535268B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9221035D0 (en) * | 1991-10-17 | 1992-11-18 | Gec Aerospace Ltd | Aircraft fuel heating systems |
| JPH08200031A (en) * | 1995-01-25 | 1996-08-06 | Akemasa Otani | Engine oil circulation controller |
| JP2009047138A (en) * | 2007-08-22 | 2009-03-05 | Toyota Motor Corp | Internal combustion engine |
| CN202132114U (en) * | 2011-07-18 | 2012-02-01 | 中国人民解放军徐州空军学院 | Oil seal supply device of aircraft engine |
| CN103104309A (en) * | 2011-11-10 | 2013-05-15 | 福特环球技术公司 | A method for improving warm-up of an engine |
| WO2014105328A1 (en) * | 2012-12-28 | 2014-07-03 | General Electric Company | System for temperature and actuation control and method of controlling fluid temperatures in an aircraft |
| CN203532109U (en) * | 2013-09-22 | 2014-04-09 | 河北钢铁集团矿业有限公司 | Fuel oil pre-heating device for strip mine dumper |
| CN205677736U (en) * | 2016-05-17 | 2016-11-09 | 内蒙古包钢钢联股份有限公司 | A kind of diesel-type vehicle fuel pre-heating system |
| CN109515728A (en) * | 2018-11-08 | 2019-03-26 | 北京航空航天大学 | Aircraft heat management system and method with auxiliary hot oil case circuit |
| CN110080872A (en) * | 2019-05-30 | 2019-08-02 | 李明珠 | Engine new fuel oil cooling heat radiation system |
| CN112441242A (en) * | 2021-01-08 | 2021-03-05 | 金陵科技学院 | Fuel tank inerting system with coupled membrane nitrogen production and fuel cell and using method |
| CN113135296A (en) * | 2021-05-14 | 2021-07-20 | 金陵科技学院 | System for inhibiting fuel oil coking and working method thereof |
| CN113202678A (en) * | 2021-06-15 | 2021-08-03 | 北京理工大学 | Air inlet preheating system of diesel engine |
| CN114180079A (en) * | 2021-12-17 | 2022-03-15 | 南京航空航天大学 | Onboard fuel tank inerting method based on fuel oil comprehensive thermal management |
Non-Patent Citations (1)
| Title |
|---|
| 超声速飞行器热管理系统性能仿真及优化设计研究;唐玫;《优秀硕士学位论文全文数据库》;20180216;全文 * |
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