An aircraft fuel supply system under icing conditions with high water content, an aircraft and a method of fuel supply

Abstract

The application discloses an aircraft fuel supply system under high-water-content icing conditions, an aircraft and a fuel supply method, and relates to the technical field of aviation.The aircraft fuel supply system under high-water-content icing conditions can supply fuel to an engine through a cross fuel supply pipeline across a radiator and directly through a fuel filter when the radiator and the fuel filter are blocked by ice accumulation and send bypass and blockage alarm signals, thereby guaranteeing the working performance of the aircraft engine and safe operation of the aircraft, and the structure is simple, and no crew operation and attention are needed.The aircraft provided by the application solves the problem that the aircraft engine fuel supply pressure is insufficient due to blockage of the radiator and the fuel filter under high-water-content icing conditions, and guarantees normal operation of the aircraft engine.The fuel supply method provided by the application can effectively eliminate the hidden danger of insufficient aircraft engine fuel supply pressure under high-water-content icing conditions, and guarantees normal operation of the aircraft engine under high-water-content icing conditions.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and in particular to a fuel supply system, an aircraft, and a fuel supply method for aircraft fuel under conditions of high water content and icing. Background Technology

[0002] As domestic research and verification of aircraft fuel system performance under high water content icing conditions have progressed, it has been found that when aircraft fuel systems supply fuel to engines under prolonged high water content icing conditions at low temperatures (-2℃ to -18℃), ice easily accumulates at the fuel pump inlet, fuel lines, and on equipment such as radiators and fuel filters. If no measures are taken to raise the fuel temperature above 0℃ before the radiator or fuel filter, the ice accumulation on these components can clog the filter screens, causing a bypass. Even after bypassing, continued ice accumulation further increases the resistance of the radiator and fuel filter, leading to a decrease in system fuel supply pressure and flow, ultimately affecting engine performance and flight safety.

[0003] Existing technologies typically involve installing heating devices on fuel lines to heat the fuel and prevent it from freezing, or using multiple fuel lines to switch to other lines when the flow resistance of the fuel line with a filter becomes too high due to ice buildup. The method of installing heating / heat exchange devices on fuel lines presents several challenges. First, the heating device itself needs to have a sufficiently large heat exchange capacity, meaning it must be large and heavy; otherwise, the heat exchange time will be long, and the device may struggle to quickly raise the fuel temperature to a non-freezing state. Second, heating the fuel with a heat exchange device requires additional heat exchange return to the radiator and upstream piping, raising the question of whether the heat exchange capacity is sufficient to raise the temperature of the low-temperature fuel to a non-freezing state, while also increasing the weight of the heat exchange return line. The method of using multiple fuel lines requires a radiator, fuel filter, and various valves on each line, significantly increasing the system and aircraft weight. Given the limited space in the aircraft and engine, this method reduces the aircraft's space utilization.

[0004] Therefore, there is an urgent need to propose a solution to this problem. Summary of the Invention

[0005] The purpose of this invention is to provide a fuel supply system, aircraft, and fuel supply method for aircraft fuel under high water content and icing conditions, in order to solve the problems of existing aircraft fuel supply systems having complex and bulky structures, and being unable to quickly reduce fuel supply flow resistance to ensure normal operation of aircraft engines under high water content and icing conditions.

[0006] To achieve this objective, the present invention adopts the following technical solution:

[0007] A fuel supply system for aircraft fuel under conditions of high water content and icing includes a fuel supply pump, a main fuel supply line, an inter-flow inlet line, an inter-flow outlet line, a fuel supply check valve, a fuel shut-off valve, an inter-flow shut-off valve, an inter-flow check valve, a radiator, and a fuel filter.

[0008] During normal aircraft refueling, the fuel in the aircraft fuel tank is pressurized by the fuel supply pump and flows through the fuel supply check valve, then through the main fuel supply line to the fuel cut-off valve, then through the main fuel supply line to the radiator, then through the main fuel supply line to the fuel filter, and the fuel filter supplies fuel to the auxiliary fuel pump of the aircraft engine.

[0009] During aircraft cross-fuel supply, there are two types: active cross-fuel supply and passive cross-fuel supply. In active cross-fuel supply, a portion of the fuel flows through the cross-fuel inlet line to the cross-fuel shut-off valve, then through the cross-fuel supply line to supply fuel to other engines. Simultaneously, fuel passes through the cross-fuel check valve, then through the cross-fuel outlet line to the fuel filter to supply fuel to the auxiliary fuel pumps of the aircraft engines. Meanwhile, another portion of the fuel is pressurized by the fuel supply pump, flows through the fuel supply check valve, then through the main fuel supply line to the fuel shut-off valve, then through the main fuel supply line to the radiator, and finally through the main fuel supply line to the fuel filter.

[0010] When the aircraft is passively fueled by alternating fuel supply, a portion of the alternating fuel from the alternating fuel supply line passes through the alternating one-way valve, then through the alternating outlet line to the fuel filter, which supplies fuel to the auxiliary fuel pump of the aircraft engine; the other portion of the alternating fuel passes through the alternating shut-off valve, through the main fuel supply line to the fuel shut-off valve, then through the main fuel supply line to the radiator, then through the main fuel supply line to the fuel filter, which supplies fuel to the auxiliary fuel pump of the aircraft engine.

[0011] The radiator has a bypass alarm function, and the radiator can issue a bypass alarm signal when it enters the bypass state. The fuel filter has an oil filter blockage alarm function, and the fuel filter can issue an oil filter blockage alarm signal when it is blocked. The aircraft can open the cross-flow cut-off valve or keep the cross-flow cut-off valve in the open state when the radiator issues a bypass alarm signal and the fuel filter issues an oil filter blockage alarm signal.

[0012] In some embodiments, the fuel supply system further includes a fuel pump line, through which fuel from the aircraft fuel tank flows to the main fuel supply line and the cross-transmission inlet line after being pressurized by the fuel supply pump. The fuel pump line is provided with the fuel supply one-way valve.

[0013] In some embodiments, two fuel supply pumps are provided, and the two fuel supply pumps serve as hot backups for each other. One fuel supply pump supplies fuel from the aircraft fuel tank to the fuel pump line through a first branch line, and the other fuel supply pump supplies fuel from the aircraft fuel tank to the fuel pump line through a second branch line.

[0014] In some embodiments, the radiator has a bypass pressure signal sensor.

[0015] In some embodiments, the fuel filter has a clogging pressure signal sensor.

[0016] In some embodiments, the radiator has a bypass state, and a bypass alarm is issued when the radiator enters the bypass state. The flow resistance is the same in the bypass state and when the bypass alarm occurs.

[0017] In some embodiments, the fuel filter has a bypass state, and the flow resistance of the fuel filter when it reaches the fuel filter blockage alarm is less than the flow resistance of the fuel filter when it enters the bypass state.

[0018] An aircraft, including the aforementioned fuel supply system under conditions of high water content and icing of aircraft fuel.

[0019] A fuel supply method, employing the aforementioned fuel supply system for aircraft fuel under high water content icing conditions, the fuel supply method comprising the following steps:

[0020] S1. Real-time monitoring of the bypass alarm signal of the radiator and the oil filter blockage signal of the fuel filter;

[0021] S2. If the radiator issues a bypass alarm signal and the fuel filter issues an oil filter blockage alarm signal, open the cross-flow shut-off valve or keep the cross-flow shut-off valve in the open state.

[0022] In some embodiments, if the radiator issues a bypass alarm signal and the fuel filter does not issue a fuel filter blockage alarm signal, the aircraft alarm system issues a radiator bypass alarm signal. After the crew receives the bypass alarm signal, they notify the maintenance crew to inspect the radiator.

[0023] In some embodiments, if the radiator does not issue a bypass alarm signal, the fuel filter issues an oil filter blockage alarm signal, the aircraft alarm system issues an oil filter blockage signal, and the crew, upon receiving the oil filter blockage signal, notifies the maintenance crew to inspect the fuel filter.

[0024] The beneficial effects of this invention are:

[0025] The present invention proposes a fuel supply system for aircraft fuel under high water content and icing conditions. When ice accumulates in the fuel supply line radiator and fuel filter and a blockage alarm signal is issued, the cross-flow shut-off valve is opened, allowing a portion of the fuel to bypass the radiator and directly pass through the fuel filter. This directly increases the fuel pressure supplied to the engine, ensuring the operating performance of the aircraft engine and the safe operation of the aircraft. The system has a simple structure and requires no crew operation or attention.

[0026] The present invention proposes an aircraft that solves the problem of insufficient fuel supply pressure in aircraft engines caused by radiator and fuel filter blockage under high water content icing conditions, thus ensuring the normal operation of aircraft engines.

[0027] The fuel supply method proposed in this invention can effectively eliminate the hidden danger of insufficient fuel supply pressure in aircraft engines under high water content icing conditions, and ensure the normal operation of the aircraft engine under high water content icing conditions. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the content of the embodiments of the present invention and these drawings without creative effort.

[0029] Figure 1 This is a schematic diagram of the structure of a fuel supply system under high water content icing conditions in aircraft fuel during normal fuel supply, as proposed in an embodiment of the present invention.

[0030] Figure 2 This is a schematic diagram of the active cross-feeding structure of an aircraft fuel supply system under conditions of high water content and icing, as proposed in an embodiment of the present invention.

[0031] Figure 3 This is a schematic diagram of the passive alternating fuel supply system under conditions of high water content and icing of aircraft fuel, as proposed in an embodiment of the present invention.

[0032] In the picture:

[0033] 100. Aircraft fuel tank; 200. Auxiliary fuel pump; 300. Fuel supply pipeline;

[0034] 1. Fuel pump; 2. Main fuel supply line; 3. Cross-flow inlet line; 4. Cross-flow outlet line; 5. Fuel supply check valve; 6. Fuel shut-off valve; 7. Cross-flow shut-off valve; 8. Cross-flow check valve; 9. Radiator; 10. Fuel filter; 20. Pump line; 30. First branch line; 40. Second branch line. Detailed Implementation

[0035] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0036] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0037] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0038] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0039] On the one hand, this embodiment proposes a fuel supply system for aircraft fuel under high water content icing conditions, which solves the problem that the existing aircraft fuel supply system has a relatively complex and bulky structure, and it is difficult to quickly reduce the fuel supply flow resistance to ensure the normal operation of the aircraft engine under high water content icing conditions.

[0040] like Figures 1-3As shown, the fuel supply system for aircraft fuel under high water content icing conditions proposed in this embodiment includes a fuel supply pump 1, a main fuel supply line 2, an inter-flow inlet line 3, an inter-flow outlet line 4, a fuel supply check valve 5, a fuel cut-off valve 6, an inter-flow cut-off valve 7, an inter-flow check valve 8, a radiator 9, and a fuel filter 10. During normal fuel supply, the fuel in the aircraft fuel tank 100 is pressurized by the fuel supply pump 1 and flows through the fuel supply check valve 5, then through the main fuel supply line 2 to the fuel cut-off valve 6, then through the main fuel supply line 2 to the radiator 9, and then through the main fuel supply line 2 to the fuel filter 10. The fuel filter 10 supplies fuel to the auxiliary fuel pump 200 of the aircraft engine. During aircraft cross-fuel supply, there are two types: active cross-fuel supply and passive cross-fuel supply. During active cross-fuel supply, a portion of the fuel flows through the cross-fuel inlet line 3 to the cross-fuel shut-off valve 7, and then through the cross-fuel supply line 300 to supply fuel to other engines. At the same time, the fuel flows through the cross-fuel check valve 8, and then through the cross-fuel outlet line 4 to the fuel filter 10 to supply fuel to the auxiliary fuel pump 200 of the aircraft engine. Meanwhile, another portion of the fuel is pressurized by the fuel supply pump 1 and flows through the fuel supply check valve 5, then through the main fuel supply line 2 to the fuel shut-off valve 6, then through the main fuel supply line 2 to the radiator 9, and then through the main fuel supply line 2 to the fuel filter 10. When the aircraft is passively fueled by cross-fuel transfer, part of the cross-fuel transfer from the cross-fuel transfer line 300 passes through the cross-fuel transfer check valve 8, then through the cross-fuel transfer outlet line 4 to the fuel filter 10 to supply fuel to the auxiliary fuel pump 200 of the aircraft engine; the other part of the cross-fuel transfer passes through the cross-fuel transfer shut-off valve 7, through the main fuel supply line 2 to the fuel shut-off valve 6, then through the main fuel supply line 2 to the radiator 9, and then through the main fuel supply line 2 to the fuel filter 10. The fuel filter 10 supplies fuel to the auxiliary fuel pump 200 of the aircraft engine. The radiator 9 has a bypass state and bypass alarm function. The radiator 9 can issue a bypass alarm signal when it enters the bypass state. The fuel filter 10 has a fuel filter blockage alarm function. The fuel filter 10 can issue a fuel filter blockage alarm signal when the fuel filter is blocked. The aircraft can open the cross-fuel transfer shut-off valve 7 or keep the cross-fuel transfer shut-off valve 7 in the open state when the radiator 9 issues a bypass alarm signal and the fuel filter 10 issues a fuel filter blockage alarm signal.

[0041] Understandably, when the aircraft is in normal fuel supply, the fuel flows smoothly in the pipeline. At this time, the cross-flow cut-off valve 7 is closed, and the fuel is pumped by the fuel supply pump 1 to the main fuel supply line 2. A fuel supply check valve 5 is installed before the main fuel supply line 2 to prevent the fuel in the main fuel supply line 2 from flowing back to the aircraft fuel tank 100. The fuel in the main fuel supply line 2 passes through the fuel cut-off valve 6, radiator 9, fuel filter 10 and auxiliary fuel pump 200 in sequence, and then the auxiliary fuel pump 200 supplies fuel to the aircraft engine.

[0042] Cross-fueling of an aircraft refers to the process of supplying fuel to other engines or for the local engine to receive fuel from other fuel tanks when the fuel weights in different fuel tanks are inconsistent, in order to maintain the aircraft's balance. Supplying fuel to other engines is called active cross-fueling. During active cross-fueling, the aircraft fuel tank 100 simultaneously supplies fuel to both other engines and the local engine. Therefore, a portion of the fuel flows through the cross-fueling inlet line 3 to the cross-fueling shut-off valve 7, then through the cross-fueling supply line 300 to supply fuel to other engines. Simultaneously, the fuel passes through the cross-fueling check valve 8, then through the cross-fueling outlet line 4 to the fuel filter 10, supplying fuel to the aircraft engine's auxiliary fuel pump 200. Meanwhile, another portion of the fuel is pressurized by the fuel supply pump 1, flows through the fuel supply check valve 5, then through the main fuel supply line 2 to the fuel shut-off valve 6, then through the main fuel supply line 2 to the radiator 9, and finally through the main fuel supply line 2 to the fuel filter 10.

[0043] Receiving fuel from other fuel tanks is called passive cross-feeding. During passive cross-feeding, part of the cross-feeding fuel from the cross-feeding fuel line 300 passes through the cross-feeding one-way valve 8, then through the cross-feeding outlet line 4 to the fuel filter 10, which supplies fuel to the auxiliary fuel pump 200 of the aircraft engine. The other part of the cross-feeding fuel passes through the cross-feeding shut-off valve 7, through the main fuel line 2 to the fuel shut-off valve 6, then through the main fuel line 2 to the radiator 9, and then through the main fuel line 2 to the fuel filter 10, which supplies fuel to the auxiliary fuel pump 200 of the aircraft engine.

[0044] Both active and passive cross-feed refueling require the cross-feed shut-off valve 7 to be opened. During both active and passive cross-feed refueling, a portion of fuel bypasses the radiator 9 and flows directly to the fuel filter 10 via the cross-feed check valve 8. When the aircraft is flying at high altitude, the fuel in the fuel tank 100 enters a high-water-content, icing state. At this time, ice easily accumulates at the radiator 9 and fuel filter 10. This ice accumulation increases the flow resistance of the fuel passing through the radiator 9 and fuel filter 10, reducing the fuel pressure supplied to the engine and affecting engine performance and aircraft safety. Therefore, when the fuel flow resistance at the radiator 9 is high, causing it to enter a bypass state, and when the fuel flow resistance at the fuel filter 10 is high, causing the fuel filter 10 to issue a fuel filter blockage alarm signal, the cross-feed shut-off valve 7 is opened. This allows a portion of fuel to bypass the radiator 9 and flow directly to the fuel filter 10, directly increasing the fuel pressure supplied to the engine, ensuring the aircraft engine's operating performance and safe aircraft operation. The structure is simple and requires no crew operation or attention. It is worth noting that if the aircraft is in an active or passive cross-fuel supply state, the cross-fuel cut-off valve 7 is in the open state. Therefore, if the fuel in the aircraft fuel tank 100 is in a state of high water content and freezing, it is sufficient to keep the cross-fuel cut-off valve 7 in the open state.

[0045] In some optional embodiments, the fuel supply system further includes a fuel pump line 20. Fuel from the aircraft fuel tank 100, after being pressurized by the fuel supply pump 1, flows through the fuel pump line 20 to the main fuel supply line 2 and the cross-flow inlet line 3. A fuel supply one-way valve 5 is provided on the fuel pump line 20. The fuel pump line 20 connects the fuel pumped by the fuel supply pump 1 to the main fuel supply line 2 and the cross-flow inlet line 3. The fuel supply one-way valve 5 on the fuel pump line 20 simultaneously prevents fuel in the main fuel supply line 2 and the cross-flow inlet line 3 from flowing back into the aircraft fuel tank 100, thus improving the structural rationality of the fuel supply system.

[0046] In some optional embodiments, two fuel supply pumps 1 are provided, serving as hot backups for each other. One fuel supply pump 1 supplies fuel from the aircraft fuel tank 100 to the fuel pumping line 20 through a first branch line 30, while the other fuel supply pump 1 supplies fuel from the aircraft fuel tank 100 to the fuel pumping line 20 through a second branch line 40. This arrangement ensures that if one fuel supply pump 1 fails, the other fuel supply pump 1 can promptly pump fuel, guaranteeing uninterrupted fuel supply to the aircraft engine and improving the reliability of the fuel supply system and the flight safety of the aircraft.

[0047] In some optional embodiments, the radiator 9 has a bypass pressure signal sensor to monitor the fuel pressure of the radiator 9 and send an overpressure signal to the aircraft in a timely manner, thereby improving the structural rationality of the fuel supply system.

[0048] In some alternative embodiments, the fuel filter 10 has a blockage pressure signal sensor to monitor the fuel pressure of the fuel filter 10 and send an overpressure blockage signal to the aircraft in a timely manner, thereby improving the structural rationality of the fuel supply system.

[0049] In some optional embodiments, the radiator 9 has a bypass state, and a bypass alarm is issued when the radiator 9 enters the bypass state. The flow resistance is the same when the bypass state and the bypass alarm are in effect. This setting enables an immediate bypass alarm when the radiator 9 bypasses, improving the system's response speed and thus ensuring the speed of engine fuel supply pressure recovery. In some optional embodiments, the fuel filter 10 has a bypass state, and the flow resistance of the fuel filter 10 when it reaches the oil filter blockage alarm is less than the flow resistance when the fuel filter 10 enters the bypass state. Under different low temperatures under conditions of high water content and icing of fuel, the bypass alarms for the fuel filter 10 and the bypass state of the radiator 9 are not issued at the same time. However, as long as both alarms are issued simultaneously, the aircraft promptly opens the cross-flow cutoff valve 7, allowing a portion of fuel to flow directly to the fuel filter 10, thereby reducing the overall fuel circuit flow resistance in a timely manner. If ice accumulation worsens and the fuel flow resistance further increases, the fuel filter 10 can also enter the bypass state to ensure the stability of engine fuel supply.

[0050] It is worth noting that the bypass state refers to the bypass channel of the component being in an open state. When the oil pressure before and after the component is too high, the bypass channel is forced open, and part or most of the oil passes through the bypass channel. The radiator 9, fuel filter 10, and their bypass states are all existing technologies, and this embodiment does not impose too many restrictions on their specific structures and principles.

[0051] On the other hand, this embodiment proposes an aircraft including the above-mentioned fuel supply system under high water content icing conditions of aircraft fuel. By setting up a fuel supply system under high water content icing conditions of aircraft fuel, the problem of insufficient fuel supply pressure of aircraft engine caused by blockage of radiator 9 and fuel filter 10 under high water content icing conditions is solved, ensuring the normal operation of aircraft engine.

[0052] Furthermore, this embodiment also proposes a fuel supply method, employing the aforementioned fuel supply system for aircraft fuel under high water content icing conditions. The fuel supply method includes the following steps:

[0053] S1. Real-time monitoring of the bypass alarm signal of radiator 9 and the oil filter blockage signal of fuel filter 10;

[0054] S2. If the radiator 9 issues a bypass alarm signal and the fuel filter 10 issues an oil filter blockage alarm signal, open the cross-flow shut-off valve 7 or keep the cross-flow shut-off valve 7 in the open state.

[0055] Understandably, under conditions of high water content and icing in aircraft fuel, when ice accumulates at the radiator 9 and fuel filter 10, the fuel flow resistance increases. The radiator 9 issues a bypass warning signal, and the fuel filter 10 issues a fuel filter blockage warning signal. At this time, the cross-flow shut-off valve 7 is opened, or the cross-flow shut-off valve 7 is kept open (in active or passive cross-flow fuel supply), allowing a portion of the fuel to bypass the radiator 9 and flow directly to the fuel filter 10. This rapidly increases the fuel supply pressure of the auxiliary fuel pump 200, effectively eliminating the potential for insufficient fuel supply pressure in the aircraft engine under high water content and icing conditions, and ensuring the normal operation of the aircraft engine under these conditions.

[0056] In some optional embodiments, if the radiator 9 issues a bypass alarm signal but the fuel filter 10 does not issue a fuel filter blockage alarm signal, the aircraft alarm system issues a radiator bypass alarm signal. After the crew receives the bypass alarm signal, they notify the maintenance crew to inspect the radiator 9 to ensure the stability of the radiator 9 and improve the reliability and rationality of the fuel supply method.

[0057] In some optional embodiments, if the radiator 9 does not issue a bypass warning signal, the fuel filter 10 issues an oil filter blockage warning signal, the aircraft warning system issues an oil filter blockage signal, and after the crew receives the oil filter blockage signal, they notify the maintenance crew to inspect the fuel filter 10 to ensure the normal operation of the fuel filter 10 and improve flight safety.

[0058] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A fuel supply system for aircraft fuel under conditions of high water content and icing, characterized in that, It includes a fuel pump (1), a main fuel supply line (2), a cross-transmission inlet line (3), a cross-transmission outlet line (4), a fuel supply check valve (5), a fuel shut-off valve (6), a cross-transmission shut-off valve (7), a cross-transmission check valve (8), a radiator (9), and a fuel filter (10). During normal fuel supply, the fuel in the aircraft fuel tank (100) is pressurized by the fuel supply pump (1) and flows through the fuel supply check valve (5), then through the main fuel supply line (2) to the fuel cut-off valve (6), then through the main fuel supply line (2) to the radiator (9), and then through the main fuel supply line (2) to the fuel filter (10). The fuel filter (10) supplies fuel to the auxiliary fuel pump (200) of the aircraft engine. When the aircraft is in cross-fuel supply, it is divided into active cross-fuel supply and passive cross-fuel supply. When the aircraft is in active cross-fuel supply, a portion of the fuel goes through the cross-fuel inlet line (3) to the cross-fuel cut-off valve (7), and then through the cross-fuel supply line (300) to supply fuel to other engines. At the same time, the fuel goes through the cross-fuel check valve (8) and then through the cross-fuel outlet line (4) to the fuel filter (10) to supply fuel to the auxiliary fuel pump (200) of the aircraft engine. Meanwhile, another portion of the fuel is pressurized by the fuel supply pump (1) and flows through the fuel supply check valve (5), then through the main fuel supply line (2) to the fuel cut-off valve (6), then through the main fuel supply line (2) to the radiator (9), and then through the main fuel supply line (2) to the fuel filter (10). When the aircraft is passively fueled by cross-fuel transfer, part of the cross-fuel transfer fuel from the cross-fuel transfer line (300) passes through the cross-fuel transfer check valve (8), then through the cross-fuel transfer outlet line (4) to the fuel filter (10) to supply fuel to the auxiliary fuel pump (200) of the aircraft engine; the other part of the cross-fuel transfer fuel passes through the cross-fuel transfer shut-off valve (7), through the main fuel supply line (2) to the fuel shut-off valve (6), then through the main fuel supply line (2) to the radiator (9), and then through the main fuel supply line (2) to the fuel filter (10), which supplies fuel to the auxiliary fuel pump (200) of the aircraft engine; The radiator (9) has a bypass alarm function and can issue a bypass alarm signal when entering the bypass state. The fuel filter (10) has an oil filter blockage alarm function and can issue an oil filter blockage alarm signal when the oil filter is blocked. The aircraft can open the cross-flow cut-off valve (7) or keep the cross-flow cut-off valve (7) in the open state when the radiator (9) issues a bypass alarm signal and the fuel filter (10) issues an oil filter blockage alarm signal.

2. The fuel supply system for aircraft fuel under high water content icing conditions according to claim 1, characterized in that, The fuel supply system also includes a fuel pump line (20). The fuel in the aircraft fuel tank (100) is pressurized by the fuel supply pump (1) and flows through the fuel pump line (20) to the main fuel supply line (2) and the cross-transmission inlet line (3). The fuel pump line (20) is equipped with the fuel supply one-way valve (5).

3. The fuel supply system for aircraft fuel under high water content icing conditions according to claim 2, characterized in that, There are two fuel supply pumps (1), which serve as hot backups for each other. One fuel supply pump (1) supplies fuel from the aircraft fuel tank (100) to the fuel pump line (20) through the first branch line (30), and the other fuel supply pump (1) supplies fuel from the aircraft fuel tank (100) to the fuel pump line (20) through the second branch line (40).

4. The fuel supply system for aircraft fuel under high water content icing conditions according to claim 1, characterized in that, The radiator (9) has a bypass pressure signal sensor.

5. The fuel supply system for aircraft fuel under high water content icing conditions according to claim 1, characterized in that, The fuel filter (10) has a clogging pressure signal sensor.

6. The fuel supply system for aircraft fuel under high water content icing conditions according to claim 1, characterized in that, The radiator (9) has a bypass state. When the radiator (9) enters the bypass state, a bypass alarm is issued. The flow resistance is the same in the bypass state and when the bypass alarm is issued.

7. The fuel supply system for aircraft fuel under high water content icing conditions according to claim 1, characterized in that, The fuel filter (10) has a bypass state, and the flow resistance of the fuel filter (10) when it reaches the fuel filter blockage alarm is less than the flow resistance of the fuel filter (10) when it enters the bypass state.

8. An aircraft, characterized in that, Including the fuel supply system for aircraft fuel under high water content icing conditions as described in any one of claims 1-7.

9. A method for supplying oil, characterized in that, The fuel supply system for aircraft fuel under high water content icing conditions as described in any one of claims 1-7, the fuel supply method comprising the following steps: S1. Real-time monitoring of the bypass alarm signal of the radiator (9) and the oil filter blockage signal of the fuel filter (10); S2. If the radiator (9) issues a bypass alarm signal and the fuel filter (10) issues an oil filter blockage alarm signal, open the cross-flow shut-off valve (7) or keep the cross-flow shut-off valve (7) in the open state.

10. The oil supply method according to claim 9, characterized in that, If the radiator (9) issues a bypass alarm signal but the fuel filter (10) does not issue a fuel filter blockage alarm signal, the aircraft alarm system issues a radiator bypass alarm signal. After the crew receives the bypass alarm signal, they notify the maintenance crew to inspect the radiator (9).

11. The oil supply method according to claim 9, characterized in that, If the radiator (9) does not issue a bypass alarm signal, the fuel filter (10) issues an oil filter blockage alarm signal, the aircraft alarm system issues an oil filter blockage signal, and the crew, upon receiving the oil filter blockage signal, notifies the maintenance crew to inspect the fuel filter (10).

Images