CN107128496B - Four-engine turboprop aircraft oil supply and delivery system - Google Patents
Four-engine turboprop aircraft oil supply and delivery system Download PDFInfo
- Publication number
- CN107128496B CN107128496B CN201710257605.2A CN201710257605A CN107128496B CN 107128496 B CN107128496 B CN 107128496B CN 201710257605 A CN201710257605 A CN 201710257605A CN 107128496 B CN107128496 B CN 107128496B
- Authority
- CN
- China
- Prior art keywords
- oil
- fuel
- tank
- pump
- delivery
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000446 fuel Substances 0.000 claims abstract description 335
- 238000002347 injection Methods 0.000 claims abstract description 37
- 239000007924 injection Substances 0.000 claims abstract description 37
- 239000003921 oil Substances 0.000 claims description 282
- 239000000295 fuel oil Substances 0.000 claims description 24
- 239000010705 motor oil Substances 0.000 claims description 16
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 description 14
- 239000007788 liquid Substances 0.000 description 9
- 239000010763 heavy fuel oil Substances 0.000 description 7
- 230000005484 gravity Effects 0.000 description 4
- 230000002265 prevention Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000006378 damage Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
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)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention provides a four-engine turboprop aircraft oil supply and delivery system which comprises an oil delivery tank D, an oil supply tank A, an oil delivery tank B and an oil delivery tank C which are sequentially and adjacently arranged, wherein one side of the interior of each oil tank, which is close to a wing tip, is an outer side, and one side of the interior of each oil tank, which is far away from the wing tip, is an inner side; fuel pumps A, B and C are respectively arranged on the inner sides of the oil supply tank A, the oil delivery tank B and the oil delivery tank C, the fuel pumps C and B are communicated with the oil supply tank A through the same oil delivery pipeline, and the fuel pumps A are communicated with an engine; the outer sides of the oil supply tank A, the oil delivery tank B and the oil delivery tank C are respectively provided with an injection pump A, an injection pump B and an injection pump C, the injection pump C is communicated with the fuel pump B, and the injection pump B and the injection pump A are communicated with the fuel pump A; both sides in the fuel delivery tank D all are equipped with fuel pump D and ejector pump D, and fuel pump D is linked together with all fuel pumps C, and ejector pump D is linked together with the adjacent fuel pump C of fuselage respectively.
Description
Technical Field
The invention relates to the technical field of engine oil transportation, in particular to an oil supply and transportation system of a four-engine turboprop aircraft.
Background
The conventional four-engine turboprop aircraft is generally provided with a left oil supply system and a right oil supply system, wherein the left oil supply system supplies fuel oil in each oil tank of a left wing to two engines of the left wing simultaneously according to a certain oil consumption sequence, and the right oil supply system supplies fuel oil in each oil tank of a right wing to two engines of the right wing simultaneously according to a certain oil consumption sequence.
This prior art has the following drawbacks:
1. when an oil pump in a certain oil tank breaks down, a large amount of fuel oil can be reserved in the oil tank group, in order to prevent the wings on two sides from generating overlarge tilting moment, the fuel oil in the oil tank group on the other side of the wing symmetrical to the oil tank group is not allowed to be used, so that the unavailable fuel oil amount of the whole aircraft is increased, and the execution of a flight task is influenced;
2. when the residual fuel in the fuel supply process of a certain fuel tank is less, if the attitude (pitch and roll) of the airplane is larger, the fuel pump can not be immersed in the fuel, and the fuel supply of the system is influenced.
Disclosure of Invention
In order to overcome at least one defect in the prior art, the invention provides a four-engine turboprop aircraft oil supply and delivery system, wherein two engines are symmetrically arranged on wings on two sides of a turboprop aircraft respectively, the aircraft oil supply and delivery system comprises an engine oil supply and delivery system, and each engine is provided with one set of the engine oil supply and delivery system;
the engine oil supply and delivery system comprises an oil supply tank A, an oil delivery tank B and an oil delivery tank C which are sequentially and adjacently arranged along the direction from the wing tip to the wing root, wherein one side, close to the wing tip, of the interior of each oil tank is the outer side, and one side, far away from the wing tip, of each oil tank is the inner side.
The inner sides of the oil supply tank A, the oil delivery tank B and the oil delivery tank C are respectively provided with an oil fuel pump A, an oil fuel pump B and an oil fuel pump C, the oil fuel pump C and the oil fuel pump B are communicated with the oil supply tank A through the same oil delivery pipeline, and the oil fuel pump A is communicated with an engine through an oil supply pipeline;
the fuel pumps C and B deliver fuel to the fuel supply tank A, and the fuel pumps A deliver the fuel in the fuel supply tank A to the engine.
The outer sides of the oil supply tank A, the oil delivery tank B and the oil delivery tank C are respectively provided with an injection pump A, an injection pump B and an injection pump C, the injection pump C is communicated with the fuel pump B through an oil delivery pipeline, and the injection pump B and the injection pump A are communicated with the fuel pump A through the oil delivery pipeline;
the ejector pump is a device which uses liquid with certain pressure as working liquid to eject or pump liquid with lower pressure or no pressure;
the injection pump C is used for injecting residual oil in the oil delivery tank C into the oil delivery tank B under the driving of the oil fuel pump B after the fuel oil in the oil delivery tank C is consumed;
the injection pump B is used for injecting residual oil in the oil delivery tank B into the oil supply tank A under the driving of the fuel pump A after the fuel oil in the oil delivery tank B is consumed;
the ejector pump A is used for conveying the fuel on the outer side of the fuel supply tank A to the inner side, preferentially consumes the fuel on the outer side, and ensures that the inner side of the fuel supply tank A is full of the fuel all the time.
The aircraft oil supply and delivery system also comprises an oil delivery tank D arranged in the aircraft body, wherein both sides in the oil delivery tank D are provided with an oil fuel pump D and an ejector pump D, the oil fuel pump D is communicated with all the oil fuel pumps C through an oil delivery pipeline, and the ejector pump D is respectively communicated with the oil fuel pumps C adjacent to the aircraft body through the oil delivery pipeline;
the four engines are respectively provided with an oil delivery tank C corresponding to the four engines, and the fuel pumps D are communicated with the four fuel pumps C and used for simultaneously supplying oil to the oil supply tanks A corresponding to the four oil delivery tanks C;
the injection pump D is used for respectively injecting residual oil in the oil delivery tank D into the two oil delivery tanks C adjacent to the machine body under the driving of the two fuel pumps C adjacent to the machine body after the fuel oil in the oil delivery tanks D is consumed.
Preferably, an oil supply pipeline between the engine and the oil supply tank A corresponding to the engine is provided with an oil quantity balance valve, a communication switch is arranged between the oil supply pipelines of two adjacent engines, and the oil quantity balance valve is positioned at the upstream of the communication switch in the fuel supply flow direction;
in the oil supply pipeline, fuel oil firstly passes through an oil quantity balancing valve and then passes through a communicating switch, the oil quantity balancing valve is used for controlling the oil delivery flow of an oil supply tank A corresponding to the oil quantity balancing valve, when the difference of the residual oil quantities of two adjacent engines exceeds a set value, the oil quantity balancing valve corresponding to the engine with less residual oil quantity can be controlled to limit the oil delivery flow, and meanwhile, the communicating switch between the oil supply pipelines of the two adjacent engines is opened, so that the oil consumption of the oil supply tank A of the engine with more residual oil quantity is increased, and the oil quantity balance of the two engines is realized;
for a four-engine turboprop airplane, each of four engines is provided with an oil mass balance valve which corresponds to the engine and controls the oil supply flow of the engine, each oil supply pipeline connecting the two engines is provided with a communicating switch, and the four engines are provided with three communicating switches;
the principle of oil mass balance between the wings on the two sides is similar to that between the adjacent engines, when the difference between the residual oil mass of the left wing and the residual oil mass of the right wing exceeds a set value, the oil mass balance valves of the two engines on the wing with the small residual oil mass can be controlled to limit the flow of oil transportation, and meanwhile, all three communication switches are opened, so that the oil consumption of the wing on the wing with the large residual oil mass is increased, and the oil mass balance of the left wing and the right wing is realized.
Preferably, a check valve is arranged between the engine and the oil mass balance valve and used for ensuring correct oil transportation direction and preventing oil of each oil tank from being mixed mutually.
Preferably, a float valve is arranged in the oil supply tank A, the fuel pump D, the fuel pump C and the fuel pump B are communicated with the float valve through the same oil pipeline, and the opening and closing of an outlet of the oil pipeline are controlled by the float valve;
the fuel in the fuel delivery tank D, the fuel delivery tank C and the fuel delivery tank B respectively flows into the fuel delivery tank A through the same fuel delivery pipeline after being pressurized through the fuel pump D, the fuel pump C and the fuel pump B, when the oil level in the fuel delivery tank A is lower than a set value, the float valve is opened under the pressure of the fuel in the pipeline and the gravity borne by the float valve, so that the fuel flows into the fuel delivery tank A through the fuel delivery pipeline, when the oil level of the fuel delivery tank A is higher than the set value, the float valve closes the valve under the buoyancy action of the float, the fuel delivery pipeline is closed, and then the three fuel delivery tanks can not deliver the fuel to the fuel.
Preferably, each fuel pump outlet in the aircraft fuel supply and delivery system is sequentially provided with a pressure annunciator and a one-way valve along the fuel flow direction, the one-way valve is used for ensuring the correct fuel delivery direction and preventing the fuel tanks from being mixed with each other, the pressure annunciator is used for detecting the outlet pressure of each fuel pump, when the fuel of the fuel tank where the pressure annunciator is arranged is consumed, the outlet pressure of the fuel pump is insufficient, and the pressure annunciator sends a signal to the display and control system of the aircraft so as to display the working state of each fuel pump and participate in the automatic control of the fuel supply and delivery system.
Preferably, an injection electromagnetic switch is arranged between the injection pump B and the fuel pump A, and the injection electromagnetic switch controls the on-off of an oil path between the injection pump B and the fuel pump A; because the fuel pump A works all the time, the injection pump B is always driven to extract the fuel in the fuel delivery tank B, in order to ensure that the fuel delivery tank B consumes the fuel after the fuel delivery tank C and the fuel delivery tank D, the injection electromagnetic switch is used for controlling the start and stop of the injection pump B, and the injection electromagnetic switch is started only after the fuel of the fuel delivery tank D and the fuel delivery tank C is consumed, so that the fuel of the fuel delivery tank B is consumed.
Preferably, the fire prevention switch is all equipped with at the defeated oil pipe way entrance of every engine, and when the engine was on fire because of the trouble, the fire prevention switch closed, thereby prevents that the intensity of a fire from leading to the oil tank along the oil supply pipeline in and causing bigger harm to the aircraft.
Preferably, the number of the fuel pumps a in each fuel supply tank a is two, and the two fuel pumps a are used for meeting the fuel supply amount, and the probability that the fuel pumps a are immersed in fuel can be increased when the residual fuel in the fuel supply tanks a is less, so that the fuel use efficiency is increased.
The four-engine turboprop aircraft oil supply and delivery system provided by the invention has the following beneficial effects:
1. the oil supply and delivery mode that a single oil supply tank supplies oil to a single engine is adopted, and the oil supply tank is kept in a full oil state, so that the reliable oil supply of the airplane in a large posture is ensured;
2. when a fuel pump of a certain fuel tank fails, fuel in the fuel tank can be used through the ejector pump, and a large amount of unusable fuel cannot be accumulated;
3. the cross oil supply of the wings on the same side and the cross oil supply of the wings on the two sides are realized, so that the oil supply and delivery systems consume oil synchronously, and the oil mass balance and the gravity center balance of the whole airplane are ensured.
Drawings
FIG. 1 is a schematic structural diagram of an oil supply and delivery system of a four-engine turboprop aircraft;
FIG. 2 is a schematic diagram of an engine oil supply and delivery system;
FIG. 3 is a tank distribution diagram of a four-engine turboprop fuel supply and delivery system.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. 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 "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings, which are used for convenience in describing the invention and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the scope of the invention.
The oil supply and delivery system of the four-engine turboprop aircraft provided by the invention is explained below with reference to the attached drawings.
As shown in figure 1, the invention provides a four-engine turboprop aircraft oil supply and delivery system, wherein two engines are symmetrically arranged on wings on two sides of a turboprop aircraft respectively, the aircraft oil supply and delivery system comprises an engine oil supply and delivery system arranged in the wings and an oil delivery tank D14 arranged in a fuselage, each engine 1 is provided with one set of engine oil supply and delivery system, namely four sets of engine oil supply and delivery systems, and one oil delivery tank D14 is arranged.
As shown in fig. 3, two engines are respectively disposed on two side wings, taking a right wing as an example, the engine 1 is disposed near the wing root, and the engine 1 ' is disposed near the wing tip, the engine oil supply and delivery system matched with the engine 1 includes an oil supply tank a11, an oil delivery tank B12 and an oil delivery tank C13, the engine oil supply and delivery system matched with the engine 1 ' includes an oil supply tank a11 ', an oil delivery tank B12 ' and an oil delivery tank C13 ', and it is defined that one side of the inside of each oil tank near the wing tip is an outer side, and one side of the inside of each oil tank far from the wing tip is an inner side.
The engine oil supply and delivery system of the engine 1 is configured as follows:
as shown in fig. 1, fuel pumps a31, B32 and C33 are respectively arranged on the inner sides of the fuel supply tank a11, the fuel delivery tank B12 and the fuel delivery tank C13, the fuel pumps C33 and B32 are both communicated with the fuel supply tank a11 through the same fuel delivery pipeline, and the fuel pumps a31 are communicated with the engine 1 through fuel delivery pipelines, wherein the fuel pumps C33 and B32 deliver fuel to the fuel supply tank a11, the fuel pumps a31 deliver fuel in the fuel supply tank a11 to the engine 1, the number of the fuel pumps a31 in the fuel supply tank a11 is two, the two fuel pumps a31 are used for satisfying fuel supply, and when the remaining fuel in the fuel supply tank a11 is small, the probability that the fuel pump a31 is immersed in the fuel can be increased, and the fuel use efficiency can be increased.
As shown in fig. 1, the outer sides of the oil supply tank a11, the oil delivery tank B12 and the oil delivery tank C13 are respectively provided with an ejector pump a21, an ejector pump B22 and an ejector pump C23, the ejector pump C23 is communicated with the fuel pump B32 through an oil delivery pipeline, and the ejector pump B22 and the ejector pump a21 are both communicated with the fuel pump a31 through an oil delivery pipeline;
the ejector pump is a device which uses liquid with certain pressure as working liquid to eject or pump liquid with lower pressure or no pressure;
when the fuel of the fuel delivery tank C13 is consumed, the injection pump C23 is driven by the fuel pump B32 to inject the residual fuel in the fuel delivery tank C13 into the fuel delivery tank B12;
when the fuel in the fuel delivery tank B12 is consumed, the jet pump B22 is driven by the fuel pump A31 to guide the residual fuel in the fuel delivery tank B12 into the fuel supply tank A11;
the jet pump A21 is used for delivering the fuel at the outer side of the fuel supply tank A11 to the inner side, preferentially consuming the fuel at the outer side and ensuring that the inner side of the fuel supply tank A11 is full of fuel at all times.
As shown in fig. 1, an injection electromagnetic switch 8 is arranged between the injection pump B22 and the fuel pump a31, and the injection electromagnetic switch 8 controls the on-off of an oil path between the injection pump B22 and the fuel pump a 31; because the fuel pump A31 works all the time, the jet pump B22 is always driven to draw the fuel in the fuel delivery tank B12, in order to enable the fuel delivery tank B12 to consume the fuel after the fuel delivery tank C13 and the fuel delivery tank D14, the jet electromagnetic switch 8 is used for controlling the start and stop of the jet pump B22, and the jet electromagnetic switch 8 is started only after the fuel of the fuel delivery tank D14 and the fuel delivery tank C13 is consumed, so that the fuel of the fuel delivery tank B12 is consumed.
As shown in fig. 1, a float valve 5 is arranged in an oil supply tank a11, a fuel pump D34, a fuel pump C33 and a fuel pump B32 are communicated with the float valve 5 through the same oil pipeline, and the opening and closing of an outlet of the oil pipeline are controlled by the float valve 5;
the fuel in the fuel delivery tank D14, the fuel delivery tank C13 and the fuel delivery tank B12 respectively flows into the fuel delivery tank A11 through the same fuel delivery pipeline after being pressurized by the fuel pump D34, the fuel pump C33 and the fuel pump B32, when the fuel level in the fuel delivery tank A11 is lower than a set value, the float valve 5 is opened under the pressure of the pipeline fuel and the gravity borne by the float valve 5, so that the fuel flows into the fuel delivery tank A11 through the fuel delivery pipeline, when the fuel level of the fuel delivery tank A11 is higher than the set value, the float valve 5 closes the valve under the action of float buoyancy, the fuel delivery pipeline is closed, and all three fuel delivery tanks cannot deliver the fuel to the fuel delivery tank A11.
As shown in figure 1, a pressure annunciator 6 and a one-way valve 7 are sequentially arranged at the outlet of each fuel pump in an engine fuel supply and delivery system of an engine 1 along the fuel flow direction, the one-way valve 7 is used for ensuring the correct fuel delivery direction and preventing the fuel tanks from being mixed with each other, the pressure annunciator 6 is used for detecting the outlet pressure of each fuel pump, when the fuel in the fuel tank where the pressure annunciator 6 is insufficient, the pressure annunciator 6 sends a signal to a display and control system of an airplane to display the working state of each fuel pump and participate in the automatic control of the fuel supply and delivery system.
As shown in figure 1, fire prevention switch 9 is arranged at the inlet of an oil pipeline of engine 1, and when engine 1 is on fire due to faults, fire prevention switch 9 is closed to prevent fire from being transmitted into an oil tank along an oil supply pipeline, so that the aircraft is prevented from being damaged.
The engine oil supply and delivery system of the engine 1' is constructed as follows:
as shown in fig. 2, the inner sides of the oil supply tank a11 ', the oil delivery tank B12' and the oil delivery tank C13 'are respectively provided with an oil fuel pump a 31', an oil fuel pump B32 'and an oil fuel pump C33', the oil fuel pumps C33 'and B32' are all communicated with the oil supply tank a11 'through the same oil delivery pipeline, and the oil fuel pump a 31' is communicated with the engine 1 'through an oil supply pipeline, wherein the oil fuel pumps C33' and B32 'deliver oil to the oil supply tank a 11', the oil fuel pumps a31 'deliver oil from the oil supply tank a 11' to the engine 1 ', the number of the oil fuel pumps a 31' from the oil supply tank a11 'is two, and the two oil fuel pumps a 31' are used for meeting the fuel supply amount, and the probability of the oil fuel pumps a31 'in the fuel oil can be increased when the remaining oil in the oil supply tank a 11' is less, thereby increasing the fuel use efficiency.
As shown in fig. 2, the outer sides of the oil supply tank a11 ', the oil delivery tank B12 ' and the oil delivery tank C13 ' are respectively provided with an ejector pump a21 ', an ejector pump B22 ' and an ejector pump C23 ', the ejector pump C23 ' is communicated with the oil fuel pump B32 ' through an oil pipeline, and the ejector pump B22 ' and the ejector pump a21 ' are both communicated with the oil fuel pump a31 ' through an oil pipeline;
the ejector pump is a device which uses liquid with certain pressure as working liquid to eject or pump liquid with lower pressure or no pressure;
when the fuel oil in the fuel oil tank C13 ' is consumed, the injection pump C23 ' injects the residual oil in the fuel oil tank C13 ' into the fuel oil tank B12 ' under the drive of the fuel oil pump B32 ';
when the fuel oil in the fuel oil tank B12 ' is consumed, the jet pump B22 ' is driven by the fuel oil pump A31 ' to jet the residual oil in the fuel oil tank B12 ' into the fuel oil tank A11 ';
the jet pump a21 ' is used for delivering the fuel at the outer side of the fuel supply tank a11 ' to the inner side, and preferentially consumes the fuel at the outer side to ensure that the inner side of the fuel supply tank a11 ' is always full of fuel.
As shown in fig. 2, an injection electromagnetic switch 8 'is arranged between the injection pump B22' and the fuel pump a31 ', and the injection electromagnetic switch 8' controls the on-off of an oil path between the injection pump B22 'and the fuel pump a 31'; because the fuel pump A31 'works all the time, the jet pump B22' is always driven to draw the fuel in the fuel delivery tank B12 ', in order to ensure that the fuel delivery tank B12' consumes the fuel after the fuel delivery tank C13 'and the fuel delivery tank D14, the jet electromagnetic switch 8' is used for controlling the start and stop of the jet pump B22 ', and the jet electromagnetic switch 8' is started only after the fuel of the fuel delivery tank D14 and the fuel delivery tank C13 'is consumed, so that the fuel of the fuel delivery tank B12' is consumed.
As shown in fig. 1 and 2, a float valve 5 'is arranged in an oil supply tank a 11', a fuel pump D34, a fuel pump C33 'and a fuel pump B32' are communicated with the float valve 5 'through the same oil pipeline, and the opening and closing of the outlet of the oil pipeline is controlled by the float valve 5';
the fuel in the fuel delivery tank D14, the fuel delivery tank C13 ' and the fuel delivery tank B12 ' respectively flows into the fuel delivery tank A11 ' through the same fuel delivery pipeline after being pressurized through the fuel pump D34, the fuel pump C33 ' and the fuel pump B32 ', when the oil level in the fuel delivery tank A11 ' is lower than a set value, the float valve 5 ' is opened under the pressure of the fuel in the pipeline and the gravity borne by the float valve, so that the fuel flows into the fuel delivery tank A11 ' through the fuel delivery pipeline, when the oil level of the fuel delivery tank A11 ' is higher than the set value, the float valve 5 ' closes the float valve under the action of the buoyancy of the float, and the fuel delivery pipeline is closed, so that the three fuel delivery tanks cannot deliver the fuel to the fuel delivery tank A11 '.
As shown in figure 2, a pressure annunciator 6 ' and a check valve 7 ' are sequentially arranged at the outlet of each fuel pump in an engine fuel supply and delivery system of the engine 1 ' along the fuel flow direction, the check valve 7 ' is used for ensuring the correct fuel delivery direction and preventing the fuel tanks from being mixed with each other, the pressure annunciator 6 ' is used for detecting the outlet pressure of each fuel pump, when the fuel in the fuel tank where the pressure annunciator 6 ' is insufficient, the pressure annunciator 6 ' sends a signal to a display and control system of an airplane to display the working state of each fuel pump and participate in the automatic control of the fuel supply and delivery system.
As shown in fig. 2, the inlets of the oil pipelines of the engine 1 'are all provided with fire-proof switches 9', when the engine 1 'fires due to faults, the fire-proof switches 9' are closed, and the fire is prevented from being transmitted into the oil tank along the oil supply pipeline, so that the aircraft is prevented from being damaged.
As shown in fig. 1 and 2, two sides in the fuel delivery tank D14 are respectively provided with a fuel pump D34 and an ejector pump D24, taking a right wing as an example, the fuel pump D34 is communicated with a fuel pump C33 and a fuel pump C33' through a fuel delivery pipeline, and the ejector pump D24 is communicated with a fuel pump C33 through a fuel delivery pipeline;
each of the four engines is provided with an oil delivery tank C13 corresponding to the engine, and the fuel pump D34 is communicated with the four fuel pumps C33 and is used for simultaneously supplying oil to the oil supply tanks A11 corresponding to the four oil delivery tanks C13;
the jet pump D24 is used for jetting the residual oil in the oil delivery tank D14 into the oil delivery tank C13 and the oil delivery tank C13' respectively under the drive of the fuel pump C33 after the fuel oil in the oil delivery tank D14 is consumed.
As shown in fig. 1 and 2, an oil supply pipeline between an engine 1 and an oil supply tank a11 is provided with an oil quantity balance valve 41, an oil quantity balance valve 41 ' is provided on an oil supply pipeline between the engine 1 ' and the oil supply tank a11 ', a communication switch 42 is provided between the oil supply pipelines of the engine 1 and the engine 1 ', the oil quantity balance valve 41 and the oil quantity balance valve 41 ' are both located at the upstream of the communication switch 42 in the fuel oil supply flow direction, a check valve 7 is provided between the engine 1 and the oil quantity balance valve 41, a check valve 7 ' is provided between the engine 1 ' and the oil quantity balance valve 41 ', the check valve 7 and the check valve 7 ' are both used for ensuring the correct oil supply direction and preventing oil leakage of each oil tank;
the present invention is described in further detail below by way of specific examples.
The specific embodiment is as follows:
the four-engine turboprop aircraft oil supply and delivery system provided by the invention comprises four engines 1, each engine 1 is provided with a set of engine oil supply and delivery system, two engines on the right wing are taken as an example, wherein the engine 1 is arranged near the wing root, and the engine 1 ' is arranged near the wing tip, and the engine 1 ' are respectively identical in oil supply and delivery modes, so the engine 1 is taken as an example, and the implementation mode of the engine 1 ' is not repeated.
When all the oil tanks of the aircraft are full of oil and the aircraft is normally supplied with oil, as shown in fig. 1:
the fuel pump A31 supplies fuel to the engine 1, the ejector pump A21 sucks the fuel from the outer side of the fuel tank to the inner side of the fuel tank, when the fuel in the fuel tank A11 is continuously consumed, the fuel level descends until the float valve 5 is opened, and at the moment, the fuel pump D34 is automatically or manually started, and the fuel pump D34 conveys the fuel in the fuel conveying tank D14 to the fuel tank A11;
when the fuel in the fuel delivery tank D14 is consumed and the float valve 5 is opened, the fuel pump C33 is automatically or manually started, the fuel pump C33 delivers the fuel in the fuel delivery tank C13 to the fuel delivery tank A11, and simultaneously drives the jet pump D24 to suck the residual fuel in the fuel delivery tank D14 into the fuel delivery tank C13;
when the fuel in the fuel delivery tank C13 is consumed and the float valve 5 is opened, the fuel pump B32 is automatically or manually started, the fuel pump B32 delivers the fuel in the fuel delivery tank B12 to the fuel supply tank A11, the ejector pump C23 is driven to suck the residual fuel in the fuel delivery tank C13 into the fuel delivery tank B12, the ejector electromagnetic switch 8 is opened, and the fuel pump A31 drives the ejector pump B22 to suck the residual fuel in the fuel delivery tank B12 into the fuel supply tank A11;
when the fuel in the fuel delivery tank B12 is consumed, the fuel in the fuel supply tank a11 is consumed finally, that is, the preferred fuel consumption sequence is: an oil delivery tank D14- > each oil delivery tank C- > each oil delivery tank B- > each oil supply tank A.
When the difference between the remaining oil amounts of the engine 1 and the engine 1' exceeds a set value, assuming that the remaining oil amount of the engine 1 is small, as shown in fig. 1 and 2:
controlling the oil quantity balance valve 41 to limit the oil delivery flow of the oil supply tank A11, and simultaneously opening a communication switch 42 between the engine 1 and the engine 1 ', so that the oil consumption of the oil supply tank A11 ' is increased, and the oil quantity balance of the engine 1 and the engine 1 ' is realized;
for a four-engine turboprop airplane, each of the four engines 1 is provided with an oil mass balance valve 41 which corresponds to the engine and controls the oil supply flow of the engine, each oil supply pipeline connecting the two engines 1 is provided with a communicating switch 42, and the four engines 1 are provided with three communicating switches 42;
the principle of oil mass balance between the wings on the two sides is similar to that between the adjacent engines 1, when the difference between the residual oil mass of the left wing and the residual oil mass of the right wing exceeds a set value, the oil mass balance valve 41 and the oil mass balance valve 41' of the wing on the side with less residual oil mass can be controlled to limit the flow of the oil transportation, and simultaneously, all three communication switches 42 are opened, so that the fuel oil on the wing on the side with more residual oil mass can be transported to the wing on the side with less residual oil mass through the communication switches 42, the oil consumption of the wing on the side with more residual oil mass is increased, and the oil mass balance of.
When a certain fuel pump is damaged, if the fuel pump C33 fails and cannot be used, the fuel pump B32 is started, the fuel pump B32 can drive the ejector pump C23 to use the fuel in the fuel delivery tank C13, and the condition that the fuel in the corresponding fuel tank cannot be used due to damage of the fuel pump cannot occur.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (6)
1. A four-engine turboprop aircraft oil supply and delivery system is characterized in that two engines are symmetrically arranged on wings on two sides of a turboprop aircraft respectively, the aircraft oil supply and delivery system comprises an engine oil supply and delivery system, and each engine (1) is provided with one set of the engine oil supply and delivery system;
the engine oil supply and delivery system comprises an oil supply tank A (11), an oil delivery tank B (12) and an oil delivery tank C (13) which are sequentially and adjacently arranged along the direction from the wing tip to the wing root, wherein one side of the interior of each oil tank, which is close to the wing tip, is the outer side, and one side of the interior of each oil tank, which is far away from the wing tip, is the inner side;
the inner sides of the oil supply tank A (11), the oil delivery tank B (12) and the oil delivery tank C (13) are respectively provided with an oil fuel pump A (31), an oil fuel pump B (32) and an oil fuel pump C (33), the oil fuel pumps C (33) and B (32) are communicated with the oil supply tank A (11) through the same oil delivery pipeline, and the oil fuel pumps A (31) are communicated with the engine (1) through oil supply pipelines;
the outer sides of the oil supply tank A (11), the oil delivery tank B (12) and the oil delivery tank C (13) are respectively provided with an ejector pump A (21), an ejector pump B (22) and an ejector pump C (23), the ejector pump C (23) is communicated with the fuel pump B (32) through an oil pipeline, and the ejector pump B (22) and the ejector pump A (21) are communicated with the fuel pump A (31) through an oil pipeline;
the aircraft oil supply and delivery system further comprises an oil delivery tank D (14) arranged in the aircraft body, wherein both sides in the oil delivery tank D (14) are provided with an oil fuel pump D (34) and an ejector pump D (24), the oil fuel pump D (34) is communicated with all the oil fuel pumps C (33) through oil delivery pipelines, and the ejector pump D (24) is respectively communicated with the oil fuel pumps C (33) adjacent to the aircraft body through the oil delivery pipelines;
an oil supply pipeline between the engine (1) and an oil supply tank A (11) corresponding to the engine (1) is provided with an oil quantity balance valve (41), a communication switch (42) is arranged between the oil supply pipelines of two adjacent engines (1), and the oil quantity balance valve (41) is positioned at the upstream of the communication switch (42) in the fuel oil supply flow direction;
an injection electromagnetic switch (8) is arranged between the injection pump B (22) and the fuel pump A (31), and the injection electromagnetic switch (8) controls the on-off of an oil path between the injection pump B (22) and the fuel pump A (31).
2. The fuel supply and delivery system of a four-engine turboprop according to claim 1, characterized in that a check valve (7) is provided between the engine (1) and the fuel quantity balancing valve (41).
3. The aircraft fuel supply and delivery system of the four-engine turboprop according to claim 1, wherein a float valve (5) is arranged in the fuel supply tank A (11), the fuel pump D (34), the fuel pump C (33) and the fuel pump B (32) are communicated with the float valve (5) through the same fuel pipeline, and the opening and closing of the outlet of the fuel pipeline are controlled by the float valve (5).
4. The four-engine turboprop aircraft fuel supply and delivery system according to claim 1, wherein a pressure annunciator (6) and a check valve (7) are sequentially arranged at the outlet of each fuel pump in the aircraft fuel supply and delivery system along the fuel flow direction.
5. The fuel supply and delivery system of a four-engine turboprop aircraft according to claim 1, characterized in that a fire-protection switch (9) is provided at the inlet of the fuel delivery line of each engine (1).
6. The four-engine turboprop aircraft fuel supply and delivery system according to claim 1, wherein the number of fuel pumps a (31) in each fuel supply tank a (11) 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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107128496A CN107128496A (en) | 2017-09-05 |
| CN107128496B true CN107128496B (en) | 2021-07-09 |
Family
ID=59715919
Family Applications (1)
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107128496B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109404135B (en) * | 2018-12-07 | 2023-12-26 | 江西洪都航空工业集团有限责任公司 | Oil return type oil transportation control system |
| CN112644721B (en) * | 2020-12-23 | 2022-06-03 | 河北利翔航空科技有限公司 | Aircraft oil supply and delivery system and control method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4913380A (en) * | 1988-10-13 | 1990-04-03 | Omac, Inc. | Fuel system for Canard aircraft |
| CN201350974Y (en) * | 2008-12-23 | 2009-11-25 | 江西洪都航空工业集团有限责任公司 | Oil tank supercharged oil supply device |
| CN104648681A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | High-reliability fuel supplying and conveying system with gravity center adjusting capability |
| CN104648680A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Fuel tank layout of flying wing configuration type airplane |
| CN204750577U (en) * | 2015-05-15 | 2015-11-11 | 哈尔滨飞机工业集团有限责任公司 | Aircraft bellytank draws penetrates oil transportation device |
| CN105620772A (en) * | 2014-10-28 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Small airplane fuel supply system |
| CN105620771A (en) * | 2014-10-28 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Fuel supply and delivery system for double-engine turboprop airplane |
-
2017
- 2017-04-19 CN CN201710257605.2A patent/CN107128496B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4913380A (en) * | 1988-10-13 | 1990-04-03 | Omac, Inc. | Fuel system for Canard aircraft |
| CN201350974Y (en) * | 2008-12-23 | 2009-11-25 | 江西洪都航空工业集团有限责任公司 | Oil tank supercharged oil supply device |
| CN104648681A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | High-reliability fuel supplying and conveying system with gravity center adjusting capability |
| CN104648680A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Fuel tank layout of flying wing configuration type airplane |
| CN105620772A (en) * | 2014-10-28 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Small airplane fuel supply system |
| CN105620771A (en) * | 2014-10-28 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Fuel supply and delivery system for double-engine turboprop airplane |
| CN204750577U (en) * | 2015-05-15 | 2015-11-11 | 哈尔滨飞机工业集团有限责任公司 | Aircraft bellytank draws penetrates oil transportation device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107128496A (en) | 2017-09-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107128496B (en) | Four-engine turboprop aircraft oil supply and delivery system | |
| CN103057714A (en) | Auxiliary fuel system | |
| ES2219497T3 (en) | FUEL INERTIZATION SYSTEM. | |
| EP2086835B1 (en) | Water scavenging system | |
| GB1331735A (en) | Inerting systems for aircraft or other fuel tanks | |
| CN110639145B (en) | Methanol ship fire-fighting system and method | |
| KR20130121024A (en) | A fuel feed network for a rotorcraft engine, the network including means for priming a pump for sucking fuel from a feeder tank | |
| KR20170007446A (en) | Improved fuel injection architecture | |
| US9090356B2 (en) | System and method for reduced flammability of an aircraft fuel system | |
| JP6955956B2 (en) | Water supply device | |
| EP3165466B1 (en) | An aircraft fuel system | |
| US11858326B2 (en) | Fault-tolerant fuel isolation from engine firebay | |
| KR100775276B1 (en) | Refueling apparatus for aircraft with circualation line | |
| CN212074446U (en) | Large-scale unmanned aerial vehicle high reliability fuel oil system | |
| CN109404135B (en) | Oil return type oil transportation control system | |
| EP3636477B1 (en) | Pump device comprising a pump, a combustion engine for driving said pump and a fuel tank | |
| CN114435608B (en) | Embedded auxiliary oil tank system | |
| KR102396265B1 (en) | System for helicopter fuel supply with defueling function | |
| CN116331499A (en) | Unmanned aerial vehicle high reliability oil transportation system | |
| JP6035382B1 (en) | Automatic fuel supply system | |
| CN216950634U (en) | Double-oil-way oil supply pipeline of generator | |
| RU2403179C1 (en) | Method for balancing fuel reserve in aircraft wing tanks during ground operation (versions) | |
| CN110723253B (en) | Anti-backflow device and ship | |
| RU2323857C1 (en) | Plane fuel system | |
| RU2356800C1 (en) | Airplane fuel system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |