CN107128496A - One kind four sends out whirlpool oar aircraft fuel delivery system - Google Patents
One kind four sends out whirlpool oar aircraft fuel delivery system Download PDFInfo
- Publication number
- CN107128496A CN107128496A CN201710257605.2A CN201710257605A CN107128496A CN 107128496 A CN107128496 A CN 107128496A CN 201710257605 A CN201710257605 A CN 201710257605A CN 107128496 A CN107128496 A CN 107128496A
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- fuel pump
- delivery system
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- 239000000446 fuel Substances 0.000 title claims abstract description 229
- 239000002828 fuel tank Substances 0.000 claims abstract description 30
- 239000003921 oil Substances 0.000 claims description 280
- 239000000295 fuel oil Substances 0.000 claims description 74
- 238000002347 injection Methods 0.000 claims description 30
- 239000007924 injection Substances 0.000 claims description 30
- 210000004209 hair Anatomy 0.000 claims description 18
- 230000008878 coupling Effects 0.000 claims description 10
- 238000010168 coupling process Methods 0.000 claims description 10
- 238000005859 coupling reaction Methods 0.000 claims description 10
- 230000008450 motivation Effects 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 239000003208 petroleum Substances 0.000 claims 1
- 238000005303 weighing Methods 0.000 claims 1
- 230000035611 feeding Effects 0.000 description 77
- 235000015927 pasta Nutrition 0.000 description 7
- 239000007788 liquid Substances 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 239000012530 fluid Substances 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 239000000346 nonvolatile oil Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 239000010729 system oil Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
-
- 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
- B64D37/04—Arrangement thereof in or on aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Jet Pumps And Other Pumps (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
Whirlpool oar aircraft fuel delivery system, including oil transportation case D and oil feeding reservoirs A, the oil transportation case B and oil transportation case C that are disposed adjacent successively are sent out the invention provides one kind four, the side of close the wing tip of each fuel tank internal is outside, and the side away from wing tip is inner side；Oil feeding reservoirs A, oil transportation case B, it is respectively equipped with fuel pump A, fuel pump B, fuel pump C on the inside of oil transportation case C, fuel pump C and fuel pump B are connected by same pipeline road with oil feeding reservoirs A, and fuel pump A is connected with engine；Oil feeding reservoirs A, oil transportation case B, it is respectively equipped with jet pump A, jet pump B, jet pump C on the outside of oil transportation case C, jet pump C is connected with fuel pump B, and jet pump B and jet pump A are connected with fuel pump A；Both sides in oil transportation case D are equipped with fuel pump D and jet pump D, and fuel pump D is connected with all fuel pump C, and jet pump D is connected with the fuel pump C adjacent with fuselage respectively.
Description
Technical field
The present invention relates to engine oil transportation technical field, more particularly to one kind four sends out whirlpool oar aircraft fuel delivery system.
Background technology
Four traditional hair whirlpool oar class aircrafts generally set left and right two independent oil supply systems, and left oil supply system is according to one
Fixed oil consumption order, supplies two engines of left wing, right oil supply system is according to certain simultaneously by the fuel oil in each fuel tank of left wing
Oil consumption order, two engines of right flank are supplied by the fuel oil in each fuel tank of right flank simultaneously.
The prior art has following defect：
1st, when the oil pump in certain fuel tank breaks down, great amount of fuel oil will be retained in this group of fuel tank, to prevent both sides machine
The wing produces excessive heeling moment, is also not allowed to use with the fuel oil in the symmetrical wing opposite side fuel tank group of the fuel tank group,
Cause the unavailable amount of fuel increase of full machine, so as to influence the execution of aerial mission；
2nd, certain fuel tank is when Fuel Remained is less in Fuel injection system, if aspect (pitching, rolling) larger, fuel pump
It possibly can not be immersed in fuel oil, influence system fuel feeding.
The content of the invention
To overcome at least one defect that above-mentioned prior art is present, send out whirlpool oar aircraft the invention provides one kind four and supply
Oil system, the both sides wing of the whirlpool oar aircraft is symmetrically respectively provided with two engines, and the aircraft fuel delivery system includes hair
Motivation fuel delivery system, each engine is provided with a set of engine fuel delivery system；
The engine fuel delivery system includes oil feeding reservoirs A, the oil transportation that the direction along wing tip to wing root is disposed adjacent successively
Case B and oil transportation case C, the side of the close wing tip of three fuel tank internals is outside, and the side away from wing tip is inner side.
Oil feeding reservoirs A, oil transportation case B, the oil transportation case C inner side are respectively equipped with fuel pump A, fuel pump B, fuel pump C, fuel oil
Pump C and fuel pump B are connected by same pipeline road with oil feeding reservoirs A, and fuel pump A is connected by oil feed line with engine
It is logical；
Fuel oil is conveyed to oil feeding reservoirs A by wherein fuel pump C and fuel pump B, and fuel pump A is defeated by the fuel oil in oil feeding reservoirs A
Give engine.
Oil feeding reservoirs A, oil transportation case B, the oil transportation case C outside are respectively equipped with jet pump A, jet pump B, jet pump C, injection
Pump C is connected with fuel pump B by pipeline road, and jet pump B and jet pump A are connected with fuel pump A by pipeline road；
Wherein jet pump be it is a kind of by the use of with certain pressure liquid as hydraulic fluid come injection or suction have compared with
The device of low-pressure or no pressure liquid；
Jet pump C is used for after oil transportation case C fuel consumption is complete, by the excess oil in oil transportation case C under fuel pump B drive
Injection is in oil transportation case B；
Jet pump B is used for after oil transportation case B fuel consumption is complete, by the excess oil in oil transportation case B under fuel pump A drive
Injection is in oil feeding reservoirs A；
Jet pump A is used to the fuel oil in the oil feeding reservoirs A outside being transported to the inner side, preferentially consumes the outside
Fuel oil, it is ensured that the oil feeding reservoirs A inner side is full always oily.
The both sides that the aircraft fuel delivery system is also included in the oil transportation case D being arranged in fuselage, oil transportation case D are equipped with combustion
Oil pump D and jet pump D, fuel pump D are connected by pipeline road with all fuel pump C, and jet pump D passes through pipeline road point
It is not connected with the fuel pump C adjacent with fuselage；
Four engines respectively have corresponding four fuel pump C of oil transportation case C, fuel pump D and this to be connected, and are used for
Give the corresponding oil feeding reservoirs A fuel feeding of four oil transportation case C simultaneously；
Jet pump D is used for after oil transportation case D fuel consumption is complete, under the two fuel pump C adjacent with fuselage drive
By in the excess oil difference injection in oil transportation case D to two oil transportation case C adjacent with fuselage.
It is preferred that, the oil feed line between engine and oil feeding reservoirs A corresponding with the engine balances valve provided with oil mass,
Switch is communicated between the oil feed line of two neighboring engine, oil mass balances valve and is located at connection in fuel feed flow direction
The upstream of switch；
In oil feed line, fuel oil first passes through oil mass balance valve, then by coupling cock, oil mass balance valve is used to control
The corresponding oil feeding reservoirs A of system oil transportation flow, it is controllable when the difference of the Fuel Oil Remaining of two neighboring engine exceedes setting value
Oil mass balance valve corresponding to the few engine of Fuel Oil Remaining processed, to carry out current limliting to oil transportation flow, while this is two neighboring
Coupling cock between the oil feed line of engine is opened, and increases the oil feeding reservoirs A of the engine more than Fuel Oil Remaining fuel consumption,
Realize the oil mass balance of two engines；
For four hair whirlpool oar aircrafts, four engines respectively have an oil mass that is corresponding and controlling its fuel supply flow rate to balance
A coupling cock is designed with valve, the oil feed line of two engines of every connection, four engines are altogether provided with three companies
Open up pass；
It is similar between oil mass equilibrium principle and adjacent engine between the wing of both sides, when left and right wing Fuel Oil Remaining
Difference when exceeding setting value, the oil mass balance valve of two engines of the few side wing of Fuel Oil Remaining is can control, with to defeated
Oily flow carries out current limliting, while all three coupling cocks are opened, makes the fuel consumption increase of the side wing more than Fuel Oil Remaining, real
The oil mass balance of existing left and right wing.
It is preferred that, check valve is provided between engine and oil mass balance valve, check valve is used to ensure oil transportation direction
Correctly, prevent that each fuel tank from going here and there mutually oil.
It is preferred that, float valve is provided with oil feeding reservoirs A, fuel pump D, fuel pump C and fuel pump B pass through with float valve
Same oil pipeline is connected, and the opening and closing of oil pipeline outlet passes through float valve control；
Fuel oil in oil transportation case D, oil transportation case C and oil transportation case B is pressurized by fuel pump D, fuel pump C and fuel pump B respectively
Oil feeding reservoirs A is flowed into by same pipeline road afterwards, when pasta is less than setting value in oil feeding reservoirs A, float valve is in pipeline fuel oil
Opened under pressure and itself suffered gravity, fuel oil is flowed into oil feeding reservoirs A by the pipeline road, when oil feeding reservoirs A pasta is higher than
During setting value, float valve closes valve under float buoyancy, closes the pipeline road, then three oil transportation casees can not be given
Oil feeding reservoirs A oil transportations.
It is preferred that, it is sequentially provided with pressure along fuel oil flow direction at each fuel pump outlet in the aircraft fuel delivery system
Signalling means and check valve, check valve are used to ensure that oil transportation is in the right direction, prevent that each fuel tank from going here and there mutually oil, pressure signal device is used
In the outlet pressure for detecting each fuel pump, when the fuel oil of fuel tank where it has consumed, fuel pump outlet insufficient pressure, pressure signal
Device is signaled to display and the control system of aircraft, is controlled automatically with showing each fuel pump working condition and participating in fuel delivery system
System.
It is preferred that, between jet pump B and fuel pump A be provided with injection electromagnetic switch, injection electromagnetic switch control jet pump B and
The break-make of oil circuit between fuel pump A；Because fuel pump A is being worked always, therefore jet pump B can be driven to extract oil transportation case B always
Interior fuel oil, in order that oil transportation case B oil consumptions after oil transportation case C and oil transportation case D, therefore controls by injection electromagnetic switch to draw
Pump B start and stop are penetrated, only injection electromagnetic switch can be just opened after oil transportation case D and oil transportation case C fuel oil have consumed, start consumption defeated
Fuel tank B fuel oil.
It is preferred that, the pipeline road porch of each engine is equipped with fule shut-off valve, when engine because failure is on fire
When, fule shut-off valve is closed, and prevents the intensity of a fire from passing in fuel tank to cause aircraft bigger harm along oil feed line.
It is preferred that, the quantity of the fuel pump A in each oil feeding reservoirs A is two, and two fuel pump A are used to meet fuel delivery
Amount, moreover it is possible to which increase fuel pump A is immersed in the probability in fuel oil when Fuel Remained is less in oil feeding reservoirs A, increase fuel oil uses effect
Rate.
The hair whirlpool oar aircraft fuel delivery system of one kind four that the present invention is provided, has the advantages that：
1st, the confession transportation oil of separate unit engine is supplied using single oil feeding reservoirs, and oil feeding reservoirs is kept full oil condition, it is ensured that
Aircraft fuel feeding under big posture is reliable；
2nd, when the fuel pump of certain fuel tank breaks down, can by jet pump by the fuel oil in the fuel tank using falling, will not
Accumulate a large amount of unavailable fuel oils；
3rd, realize that homonymy wing intersects fuel feeding, while realizing that both sides wing intersects fuel feeding so that each fuel delivery system is synchronous
Oil consumption, to ensure the overall oil mass balance of aircraft and gravity balance.
Brief description of the drawings
Fig. 1 is the structural representation of four hair whirlpool oar aircraft fuel delivery systems；
Fig. 2 is the structural representation of engine fuel delivery system；
Fig. 3 is the fuel tank distribution map of four hair whirlpool oar aircraft fuel delivery systems.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply meaning
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention guarantor
Protect the limitation of scope.
The hair whirlpool oar aircraft fuel delivery system of one kind four provided below in conjunction with the accompanying drawings the present invention is illustrated.
As shown in figure 1, sending out whirlpool oar aircraft fuel delivery system, the both sides wing pair of whirlpool oar aircraft the invention provides one kind four
It is respectively provided with two engines with claiming, aircraft fuel delivery system includes the engine fuel delivery system being arranged in wing and is arranged on
Oil transportation case D14 in fuselage, each engine 1 is provided with a set of engine fuel delivery system, that is, has four sets of engine feedings
Oil system, oil transportation case D14 is provided with one.
As shown in figure 3, both sides wing is respectively provided with two engines, it is engine 1 at wing root by taking starboard wing as an example,
Be the ＇ of engine 1 at the wing tip, the engine fuel delivery system supporting with engine 1 include oil feeding reservoirs A11, oil transportation case B12 and
Oil transportation case C13, includes oil feeding reservoirs A11 ＇, oil transportation case B12 ＇ and oil transportation case with engine the fuel delivery system supporting ＇ of engine 1
C13 ＇, the side for defining the close wing tip of each fuel tank internal is outside, and the side away from wing tip is inner side.
The structure of the engine fuel delivery system of engine 1 is as follows：
As shown in figure 1, oil feeding reservoirs A11, oil transportation case B12, the oil transportation case C13 inner side are respectively equipped with fuel pump A31, combustion
Oil pump B32, fuel pump C33, fuel pump C33 and fuel pump B32 are connected by same pipeline road with oil feeding reservoirs A11, combustion
Oil pump A31 is connected by oil feed line with engine 1, wherein, fuel oil is conveyed to confession by fuel pump C33 and fuel pump B32
Fuel oil in oil feeding reservoirs A11 is conveyed to the number of the fuel pump A31 in engine 1, oil feeding reservoirs A11 by fuel tank A11, fuel pump A31
Measure as two, two fuel pump A31 are used to meet fuel supply volume, moreover it is possible to increase when Fuel Remained is less in oil feeding reservoirs A11
Fuel pump A31 is immersed in the probability in fuel oil, increases fuel oil service efficiency.
As shown in figure 1, oil feeding reservoirs A11, oil transportation case B12, the oil transportation case C13 outside are respectively equipped with jet pump A21, drawn
Pump B22, jet pump C23 are penetrated, jet pump C23 is connected with fuel pump B32 by pipeline road, jet pump B22 and jet pump A21
It is connected with fuel pump A31 by pipeline road；
Wherein jet pump be it is a kind of by the use of with certain pressure liquid as hydraulic fluid come injection or suction have compared with
The device of low-pressure or no pressure liquid；
After oil transportation case C13 fuel consumption is complete, jet pump C23 is under fuel pump B32 drive by oil transportation case C13
Excess oil injection is in oil transportation case B12；
After oil transportation case B12 fuel consumption is complete, jet pump B22 is under fuel pump A31 drive by oil transportation case B12
Excess oil injection is in oil feeding reservoirs A11；
Jet pump A21 is used to the fuel oil in the oil feeding reservoirs A11 outside being transported to the inner side, preferentially consumes described outer
The fuel oil of side, it is ensured that the oil feeding reservoirs A11 inner side is full always oily.
As shown in figure 1, being provided with injection electromagnetic switch 8 between jet pump B22 and fuel pump A31, injection electromagnetic switch 8 is controlled
The break-make of oil circuit between jet pump B22 and fuel pump A31；Because fuel pump A31 is working always, therefore can drive injection always
Pump B22 extracts the fuel oil in oil transportation case B12, in order that oil transportation case B12 oil consumptions after oil transportation case C13 and oil transportation case D14, therefore
Jet pump B22 start and stop are controlled by injection electromagnetic switch 8, only after oil transportation case D14 and oil transportation case C13 fuel oil have consumed
Injection electromagnetic switch 8 can be just opened, starts to consume oil transportation case B12 fuel oil.
As shown in figure 1, oil feeding reservoirs A11 in be provided with float valve 5, fuel pump D34, fuel pump C33 and fuel pump B32 with
Float valve 5 is connected by same oil pipeline, and the opening and closing of oil pipeline outlet is controlled by float valve 5；
Fuel oil in oil transportation case D14, oil transportation case C13 and oil transportation case B12 passes through fuel pump D34, fuel pump C33 and combustion respectively
Oil feeding reservoirs A11 is flowed into by same pipeline road after oil pump B32 superchargings, when pasta is less than setting value in oil feeding reservoirs A11, float
Valve 5 is opened under pipeline fuel pressure and itself suffered gravity, fuel oil is flowed into oil feeding reservoirs A11 by the pipeline road, when
When oil feeding reservoirs A11 pasta is higher than setting value, float valve 5 closes valve under float buoyancy, closes the pipeline road,
Then three oil transportation casees can not give oil feeding reservoirs A11 oil transportations.
As shown in figure 1, at each fuel pump outlet in the engine fuel delivery system of engine 1 along fuel oil flow direction according to
Secondary to be provided with pressure signal device 6 and check valve 7, check valve 7 is used to ensure that oil transportation is in the right direction, prevents each fuel tank from going here and there mutually
Oil, pressure signal device 6 is used for the outlet pressure for detecting each fuel pump, when the fuel oil of fuel tank where it has consumed, fuel pump outlet
Insufficient pressure, pressure signal device 6 is signaled to display and the control system of aircraft, to show each fuel pump working condition and join
Automatically controlled with fuel delivery system.
As shown in figure 1, the pipeline road porch of engine 1 is equipped with fule shut-off valve 9, when engine 1 because failure rises
When fiery, fule shut-off valve 9 is closed, and prevents the intensity of a fire from passing in fuel tank to cause aircraft bigger harm along oil feed line.
The structure of the ＇ of engine 1 engine fuel delivery system is as follows：
As shown in Fig. 2 oil feeding reservoirs A11 ＇, oil transportation case B12 ＇, the oil transportation case C13 ＇ inner side are respectively equipped with fuel pump
A31 ＇, fuel pump B32 ＇, fuel pump C33 ＇, fuel pump C33 ＇ and fuel pump B32 ＇ pass through same pipeline road and oil feeding reservoirs
A11 ＇ are connected, and fuel pump A31 ＇ are connected by oil feed line with the ＇ of engine 1, wherein, fuel pump C33 ＇ and fuel pump
Fuel oil is conveyed to oil feeding reservoirs A11 ＇, fuel pump A31 ＇ and the fuel oil in oil feeding reservoirs A11 ＇ is conveyed into the ＇ of engine 1, fuel feeding by B32 ＇
The quantity of fuel pump A31 ＇ in case A11 ＇ is two, and two fuel pump A31 ＇ are used to meet fuel supply volume, moreover it is possible in fuel feeding
Increase fuel pump A31 ＇ are immersed in the probability in fuel oil when Fuel Remained is less in case A11 ＇, increase fuel oil service efficiency.
As shown in Fig. 2 oil feeding reservoirs A11 ＇, oil transportation case B12 ＇, the oil transportation case C13 ＇ outside are respectively equipped with jet pump
A21 ＇, jet pump B22 ＇, jet pump C23 ＇, jet pump C23 ＇ and fuel pump B32 ＇ are connected by pipeline road, jet pump
B22 ＇ and jet pump A21 ＇ are connected with fuel pump A31 ＇ by pipeline road；
Wherein jet pump be it is a kind of by the use of with certain pressure liquid as hydraulic fluid come injection or suction have compared with
The device of low-pressure or no pressure liquid；
After oil transportation case C13 ＇ fuel consumption is complete, jet pump C23 ＇ are under fuel pump B32 ＇ drive by oil transportation case C13 ＇
Interior excess oil injection is in oil transportation case B12 ＇；
After oil transportation case B12 ＇ fuel consumption is complete, jet pump B22 ＇ are under fuel pump A31 ＇ drive by oil transportation case B12 ＇
Interior excess oil injection is in oil feeding reservoirs A11 ＇；
Jet pump A21 ＇ are used to the fuel oil in the oil feeding reservoirs A11 ＇ outside being transported to the inner side, and preferential consumption is described
The fuel oil in outside, it is ensured that the oil feeding reservoirs A11 ＇ inner side is full always oily.
As shown in Fig. 2 being provided with the ＇ of injection electromagnetic switch 8, the ＇ of injection electromagnetic switch 8 between jet pump B22 ＇ and fuel pump A31 ＇
The break-make of oil circuit between control jet pump B22 ＇ and fuel pump A31 ＇；Because fuel pump A31 ＇ are working always, therefore can be always
Jet pump B22 ＇ are driven to extract the fuel oil in oil transportation case B12 ＇, in order that oil transportation case B12 ＇ are in oil transportation case C13 ＇ and oil transportation case D14
Oil consumption afterwards, therefore jet pump B22 ＇ start and stop are controlled by the ＇ of injection electromagnetic switch 8, only as oil transportation case D14 and oil transportation case
C13 ＇ fuel oil can just open the ＇ of injection electromagnetic switch 8 after having consumed, and start to consume oil transportation case B12 ＇ fuel oil.
As shown in Figures 1 and 2, provided with float valve 5 ＇, fuel pump D34, fuel pump C33 ＇ and fuel oil in oil feeding reservoirs A11 ＇
Pump B32 ＇ are connected with the ＇ of float valve 5 by same oil pipeline, and the opening and closing of oil pipeline outlet passes through float valve
5 ＇ are controlled；
Fuel oil in oil transportation case D14, oil transportation case C13 ＇ and oil transportation case B12 ＇ passes through fuel pump D34, fuel pump C33 ＇ respectively
Oil feeding reservoirs A11 ＇ are flowed into by same pipeline road after being pressurized with fuel pump B32 ＇, when pasta is less than setting value in oil feeding reservoirs A11 ＇
When, the ＇ of float valve 5 is opened under pipeline fuel pressure and itself suffered gravity, fuel oil is flowed into fuel feeding by the pipeline road
Case A11 ＇, when oil feeding reservoirs A11 ＇ pasta is higher than setting value, the ＇ of float valve 5 closes valve under float buoyancy, closes
The pipeline road, then three oil transportation casees can not give oil feeding reservoirs A11 ＇ oil transportations.
As shown in Fig. 2 being flowed at each fuel pump outlet in the ＇ of engine 1 engine fuel delivery system along fuel oil
The ＇ of pressure signal device 6 and the ＇ of check valve 7 are sequentially provided with, the ＇ of check valve 7 is used to ensure that oil transportation is in the right direction, prevents that each fuel tank is mutual
Mutually string is oily, and the ＇ of pressure signal device 6 is used for the outlet pressure for detecting each fuel pump, when the fuel oil of fuel tank where it has consumed, fuel pump
Outlet pressure is not enough, and the ＇ of pressure signal device 6 is signaled to display and the control system of aircraft, to show each fuel oil pump work shape
State simultaneously participates in fuel delivery system and automatically controlled.
As shown in Fig. 2 the ＇ of engine 1 pipeline road porch is equipped with the ＇ of fule shut-off valve 9, as the ＇ of engine 1 because failure
When on fire, the ＇ of fule shut-off valve 9 is closed, and prevents the intensity of a fire from passing in fuel tank to cause aircraft bigger harm along oil feed line.
As shown in Figures 1 and 2, the both sides in oil transportation case D14 are equipped with fuel pump D34 and jet pump D24, using starboard wing as
Example, fuel pump D34 is connected by pipeline road with fuel pump C33 and fuel pump C33 ＇, and jet pump D24 passes through pipeline road
It is connected with fuel pump C33；
Four engines respectively have corresponding four fuel pump C33 of oil transportation case C13, fuel pump D34 and this to be connected
It is logical, for giving the corresponding oil feeding reservoirs A11 fuel feeding of four oil transportation case C13 simultaneously；
Jet pump D24 is used for after oil transportation case D14 fuel consumption is complete, by oil transportation case D14 under fuel pump C33 drive
Interior excess oil distinguishes injection in oil transportation case C13 and oil transportation case C13 ＇.
As shown in Figures 1 and 2, the oil feed line between engine 1 and oil feeding reservoirs A11 balances valve 41, hair provided with oil mass
Oil feed line between the ＇ of motivation 1 and oil feeding reservoirs A11 ＇ balances the ＇ of valve 41, engine 1 and the ＇ of engine 1 fuel feed pump provided with oil mass
Switch 42 is communicated between road, oil mass balance valve 41 and oil mass balance valve 41 ＇ are located in fuel feed flow direction to be connected
The upstream of pass 42 is opened up, check valve 7 is provided between engine 1 and oil mass balance valve 41, the ＇ of engine 1 and oil mass balance are lived
The ＇ of check valve 7 is provided between 41 ＇ of door, check valve 7 and the ＇ of check valve 7 are used to ensure that oil transportation is in the right direction, prevent each oil
Case goes here and there mutually oil；
Below by specific embodiment, the present invention is described in further detail.
Specific embodiment：
The four hair whirlpool oar aircraft fuel delivery systems that the present invention is provided include four engines 1, and each engine 1 is equipped with a set of
Engine fuel delivery system, now by taking two engines of right side wing as an example, wherein being engine 1 at wing root, close to the wing
Point place is the ＇ of engine 1, due to identical on engine 1 and the respective confession transportation oils of the ＇ of engine 1, therefore by taking engine 1 as an example,
The ＇ of engine 1 embodiment is repeated no more.
When the full oil of all fuel tanks of aircraft and normal feeding oil, as shown in Figure 1：
Fuel pump A31 gives the fuel feeding of engine 1, and jet pump A21 will be drawn on the inside of fuel tank on the outside of fuel from fuel tank, work as fuel feeding
Fuel oil in case A11 is persistently consumed, and pasta is decreased until that float valve 5 is opened, and now starts fuel pump by automatic or manual
Fuel oil in oil transportation case D14 is conveyed to oil feeding reservoirs A11 by D34, fuel pump D34；
When fuel consumption is complete in oil transportation case D14 and float valve 5 is opened, then fuel pump C33 is started by automatic or manual,
Fuel oil in oil transportation case C13 is conveyed to oil feeding reservoirs A11 by fuel pump C33, while driving jet pump D24 by oil transportation case D14
Excess oil is drawn into oil transportation case C13；
When fuel consumption is complete in oil transportation case C13 and float valve 5 is opened, then fuel pump B32 is started by automatic or manual,
Fuel oil in oil transportation case B12 is conveyed to oil feeding reservoirs A11 by fuel pump B32, while driving jet pump C23 by oil transportation case C13
Excess oil is drawn into oil transportation case B12, while opening injection electromagnetic switch 8, then fuel pump A31 drives jet pump B22 by oil transportation case
Excess oil in B12 is drawn into oil feeding reservoirs A11；
When fuel consumption is complete in oil transportation case B12, then the fuel oil in oil feeding reservoirs A11, i.e., preferred oil consumption order are finally consumed
For：Oil transportation case D14->Each oil transportation case C->Each oil transportation case B->Each oil feeding reservoirs A.
When the difference of engine 1 and the ＇ of engine 1 Fuel Oil Remaining exceedes setting value, it is assumed that the Fuel Oil Remaining of engine 1
It is few, as shown in Figures 1 and 2：
Oil mass balance valve 41 is controlled, to carry out current limliting to oil feeding reservoirs A11 oil transportation flow, while engine 1 and starting
Coupling cock 42 between the ＇ of machine 1 is opened, and is increased oil feeding reservoirs A11 ＇ fuel consumption, is realized engine 1 and the ＇ of engine 1 oil mass
Balance；
For four hair whirlpool oar aircrafts, four engines 1 respectively have an oil mass that is corresponding and controlling its fuel supply flow rate to put down
Weigh valve 41, is designed with a coupling cock 42 on the oil feed line of two engines 1 of every connection, four engines 1 are set altogether
There are three coupling cocks 42；
It is similar between oil mass equilibrium principle and adjacent engine 1 between the wing of both sides, when left and right wing Fuel Oil Remaining
Difference when exceeding setting value, can control the oil mass balance valve 41 and the oil mass balance ＇ of valve 41 of the few side wing of Fuel Oil Remaining,
To carry out current limliting to oil transportation flow, while all three coupling cocks 42 are opened, make the fuel oil of the side wing more than Fuel Oil Remaining
The few side wing of Fuel Oil Remaining can be conveyed to by coupling cock 42, increases the fuel consumption of the side wing more than Fuel Oil Remaining,
Realize the oil mass balance of left and right wing.
When certain fuel pump is damaged, as fuel pump C33 break down can not in use, if start fuel pump B32, fuel pump
B32 can drive jet pump C23, using falling, to be not in because fuel pump is damaged and causes correspondence by the fuel oil in oil transportation case C13
The situation that fuel oil in fuel tank can not be used.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (8)
1. one kind four sends out whirlpool oar aircraft fuel delivery system, the both sides wing of the whirlpool oar aircraft is symmetrically respectively provided with two and started
Machine, it is characterised in that the aircraft fuel delivery system includes engine fuel delivery system, and each engine (1) is provided with a set of
The engine fuel delivery system；
The engine fuel delivery system includes oil feeding reservoirs A (11), the oil transportation that the direction along wing tip to wing root is disposed adjacent successively
Case B (12) and oil transportation case C (13), the side of the close wing tip of each fuel tank internal is outside, and the side away from wing tip is inner side；
Oil feeding reservoirs A (11), oil transportation case B (12), oil transportation case C (13) inner side are respectively equipped with fuel pump A (31), fuel pump B
(32), fuel pump C (33), fuel pump C (33) and fuel pump B (32) are connected by same pipeline road with oil feeding reservoirs A (11)
Logical, fuel pump A (31) is connected by oil feed line with engine (1)；
Oil feeding reservoirs A (11), oil transportation case B (12), oil transportation case C (13) outside are respectively equipped with jet pump A (21), jet pump B
(22), jet pump C (23), jet pump C (23) is connected with fuel pump B (32) by pipeline road, jet pump B (22) and injection
Pump A (21) is connected with fuel pump A (31) by pipeline road；
The both sides that the aircraft fuel delivery system is also included in the oil transportation case D (14) being arranged in fuselage, oil transportation case D (14) are all provided with
There are fuel pump D (34) and jet pump D (24), fuel pump D (34) is connected by pipeline road with all fuel pump C (33),
Jet pump D (24) is connected with the fuel pump C (33) adjacent with fuselage respectively by pipeline road.
2. it is according to claim 1 four hair whirlpool oar aircraft fuel delivery system, it is characterised in that engine (1) and with the hair
Oil feed line between the corresponding oil feeding reservoirs A (11) of motivation (1) is provided with oil mass balance valve (41), two neighboring engine (1)
Oil feed line between be communicated with switch (42), oil mass balance valve (41) fuel feed flow direction on be located at coupling cock
(42) upstream.
3. four hairs whirlpool oar aircraft fuel delivery system according to claim 2, it is characterised in that engine (1) and oil mass are flat
Check valve (7) is provided between weighing apparatus valve (41).
4. four hairs whirlpool oar aircraft fuel delivery system according to claim 1, it is characterised in that be provided with oil feeding reservoirs A (11)
Float valve (5), fuel pump D (34), fuel pump C (33) and fuel pump B (32) pass through same petroleum pipeline with float valve (5)
Road is connected, and the opening and closing of oil pipeline outlet is controlled by float valve (5).
5. four hairs whirlpool oar aircraft fuel delivery system according to claim 1, it is characterised in that the aircraft fuel delivery system
Pressure signal device (6) and check valve (7) are sequentially provided with interior each fuel pump outlet along fuel oil flow direction.
6. four hairs whirlpool oar aircraft fuel delivery system according to claim 1, it is characterised in that jet pump B (22) and fuel oil
Between pump A (31) be provided with injection electromagnetic switch (8), injection electromagnetic switch (8) control jet pump B (22) and fuel pump A (31) it
Between oil circuit break-make.
7. four hairs whirlpool oar aircraft fuel delivery system according to claim 1, it is characterised in that each engine (1) is defeated
Oil pipe line porch is equipped with fule shut-off valve (9).
8. four hairs whirlpool oar aircraft fuel delivery system according to claim 1, it is characterised in that in each oil feeding reservoirs A (11)
Fuel pump A (31) quantity is two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710257605.2A CN107128496B (en) | 2017-04-19 | 2017-04-19 | Four-engine turboprop aircraft oil supply and delivery system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710257605.2A CN107128496B (en) | 2017-04-19 | 2017-04-19 | Four-engine turboprop aircraft oil supply and delivery system |
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| CN107128496A true CN107128496A (en) | 2017-09-05 |
| CN107128496B CN107128496B (en) | 2021-07-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710257605.2A Active CN107128496B (en) | 2017-04-19 | 2017-04-19 | Four-engine turboprop aircraft oil supply and delivery system |
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| CN109404135A (en) * | 2018-12-07 | 2019-03-01 | 江西洪都航空工业集团有限责任公司 | A kind of oil-return type oil transportation control system |
| CN112644721A (en) * | 2020-12-23 | 2021-04-13 | 河北利翔航空科技有限公司 | Aircraft oil supply and delivery system and control method thereof |
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| CN112644721A (en) * | 2020-12-23 | 2021-04-13 | 河北利翔航空科技有限公司 | Aircraft oil supply and delivery system and control method thereof |
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| Publication number | Publication date |
|---|---|
| CN107128496B (en) | 2021-07-09 |
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