A fuel system with a sealed pressurization device, an aeroengine and an aircraft

Abstract

The present application relates to a kind of fuel system with sealed pressurizing device, aero-engine and aircraft, belong to aerospace technology field, solve the one of the problems that fuel system vent in prior art is directly communicated with atmosphere, aircraft high attitude flight, fuel quantity high position, fuel leakage is prone to occur, affect flight safety and aircraft emergency state cannot quickly drain oil.The sealed pressurizing device of the present application is set above the vent of oil tank, including shell, one end of shell has opening communicated with external atmosphere;And movable assembly, movable assembly is movably arranged in shell, and can be switched between first state and second state;Wherein, when movable assembly is in first state, close opening, to block the outflow of fuel in oil tank;When movable assembly is in second state, open opening, oil tank is communicated with external atmosphere.The present application realizes the blocking fuel skew, aircraft emergency state can quickly drain oil.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more particularly to a fuel system, aero-engine, and aircraft with a sealed pressurization device. Background Technology

[0002] However, during actual flight, due to mission requirements, aircraft often need to perform large-attitude flight maneuvers such as dives, climbs, and rolls. When the fuel level in the fuel tank is high, the vent of the traditional fuel system lacks an effective sealing and protection structure. As a result, fuel in the tank is prone to leaking out from the vent under the combined forces of inertia and gravity. This not only wastes fuel, but the leaked fuel may also come into contact with the aircraft's high-temperature components and electrical parts, causing fires, short circuits, and other safety accidents, seriously threatening the aircraft's flight safety. Summary of the Invention

[0003] Based on the above analysis, the present invention aims to provide a fuel system, aero-engine, and aircraft with a sealed pressurization device to solve one of the problems of existing fuel systems where the vent is directly connected to the atmosphere, making it easy for fuel to leak when the aircraft is flying in large attitudes or with high fuel levels, affecting flight safety and preventing the aircraft from quickly draining fuel in emergency situations.

[0004] One aspect of the present invention provides a fuel system having a sealing pressurization device, the sealing pressurization device being disposed above the vent of the fuel tank, comprising: A housing, one end of which has an opening communicating with the outside atmosphere; and An active component, which is movably disposed within the housing and is capable of switching between a first state and a second state; When the active component is in the first state, the opening is closed to prevent fuel from flowing out of the fuel tank; When the active component is in the second state, the opening is opened, and the fuel tank is connected to the outside atmosphere.

[0005] Furthermore, the movable component extends out from the other end of the housing and is connected to an external air source. The movable component switches between the first state and the second state under the drive of the external air source.

[0006] Furthermore, the active component includes: The fastener has two ends disposed on the side wall of the housing. A movable component, wherein the movable component is disposed within the housing and near one end of the opening; and A telescopic structure having a fixed end and a movable end, the fixed end being disposed on the fixed member and the movable end being disposed on the movable member.

[0007] Furthermore, two telescopic structures are provided.

[0008] Furthermore, the telescopic structure includes a first sleeve and a second sleeve.

[0009] Furthermore, the outer diameter of the first sleeve is smaller than the inner diameter of the second sleeve.

[0010] Furthermore, the bottom of the fuel tank is provided with a drain port, which is used to drain excess fuel from the fuel tank.

[0011] Furthermore, it also includes a fuel tank; the fuel tank includes an upper fuel tank and a lower fuel tank; the upper fuel tank and the lower fuel tank are connected by a vent pipe and a fuel pipe; The vent is located at the top of the upper oil tank; the vent pipe is connected to the vent.

[0012] A second aspect of the present invention provides an aircraft engine, including an engine body and the fuel system; The engine body includes a first engine and a second engine, and the fuel tank is provided with two fuel outlets, which are respectively connected to the first engine and the second engine. The external air source is the excess intake air discharged by the pressure relief valve of the first engine or the second engine.

[0013] A third aspect of the invention provides an aircraft including the aforementioned aircraft engine.

[0014] Furthermore, a spring is provided between the two telescopic structures, with one end of the spring fixed to the fixing member and the other end of the spring fixed to the movable member.

[0015] Furthermore, one end of the first sleeve extends out of the movable member, and the extended end of the first sleeve is configured as a closed end; the other end of the second sleeve extends into the second sleeve. The second sleeve is disposed on the fixing member, and the end of the second sleeve away from the first sleeve extends out of the housing and is connected to an external air source.

[0016] Furthermore, a gap is formed between the first sleeve and the second sleeve; When the external gas source is turned on, the closed end of the first sleeve blocks the opening, and the gas from the external gas source leaks into the housing through the gap.

[0017] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects: 1. This invention incorporates a sealing and pressurizing device at the vent. This device includes a housing and a movable component. When the aircraft is in high-attitude flight and the fuel level is high, the movable component switches to a first state, quickly sealing the opening between the housing and the atmosphere, blocking the connection between the fuel tank and the external atmosphere, preventing fuel from flowing out of the vent, and eliminating flight safety hazards caused by fuel leakage. When the aircraft is in normal flight, the movable component switches to a second state, opening the housing opening to maintain communication between the fuel tank and the external atmosphere. This allows the internal pressure of the fuel tank to dynamically balance as fuel is consumed and refueled, reducing the risk of deformation and damage to the fuel tank due to pressure differences. This invention has a simple and compact structure, suitable for the high-attitude and multi-condition flight characteristics of aircraft.

[0018] 2. The movable component of this invention adopts a combination of a double-sided sleeve telescopic structure and a spring, with a pre-reserved gap between the sleeves. The second sleeve is connected to an external air source. On one hand, the air source can quickly close the opening, preventing fuel from flowing out of the vent during large-attitude flight, thus eliminating safety hazards. After the air source is shut off, the spring automatically resets, restoring the fuel tank pressure balance. On the other hand, the sleeve gap allows for pressurization of leaking air, enabling gas to enter both fuel tanks. Combined with the solenoid valve at the fuel drain port, this achieves accelerated fuel release under the combined effects of air pressure and gravity, rapidly reducing aircraft weight and improving the safety of emergency landings.

[0019] 3. The air source in this invention directly uses the excess intake air discharged by the engine pressure relief valve, eliminating the need for dedicated air source pipelines, control components, and other supporting structures. This reduces the number of external components in the aircraft's fuel system and engine system, and improves energy utilization, thus saving energy and reducing emissions.

[0020] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0021] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts. Figure 1 This is one of the structural schematic diagrams of the fuel system in Example 1; Figure 2 This is the second schematic diagram of the fuel system in Example 1; Figure 3 This is a schematic diagram of the upper oil tank in Example 1; Figure 4 This is the third schematic diagram of the fuel system in Example 1; Figure 5 This is a partial structural diagram of the upper oil tank in Example 1; Figure 6 This is one of the structural schematic diagrams of the sealing and pressurizing device in Example 1; Figure 7 This is the second schematic diagram of the sealing and pressurizing device in Example 1; Figure 8 This is the third schematic diagram of the sealing and pressurizing device in Example 1; Figure 9 This is a schematic diagram of the dual-redundant oil supply structure in Example 2.

[0022] Figure label: 1-Sealing and pressurizing device; 11-Housing; 111-Opening; 12-Moving component; 121-Fixed component; 122-Moving component; 123-Telescopic structure; 1231-First sleeve; 1232-Second sleeve; 124-Positioning pin; 125-Spring; 13-External air source inlet pipe; 14-Atmosphere communication pipe; 2-Fuel tank; 21-Upper fuel tank; 211-First filler port; 212-First outlet; 213-Groove; 214-Straight pipe; 22-Lower fuel tank; 221-Second filler port; 222-Second outlet; 223-Air inlet; 23-Ventilation port; 24-Drain port; 241-Solenoid valve; 25-Ventilation pipe; 26-Fuel pipe; 3-Frame; 4-Fuel outlet line; 41-First fuel outlet line; 42-Second fuel outlet line; 5-Fuel pump; 6-Dual redundancy fuel supply structure; 61-Three-way valve; 62-Fuel outlet branch pipe. Detailed Implementation

[0023] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0024] Example 1 A specific embodiment of the present invention, such as Figure 1 As shown, a fuel system with a sealing pressurization device is disclosed. The sealing pressurization device 1 is disposed above the vent 23 of the fuel tank 2 and includes: The housing 11 has an opening 111 at one end that communicates with the outside atmosphere; and The active component 12 is movably disposed within the housing 11 and is capable of switching between a first state and a second state; When the active component 12 is in the first state, the opening 111 is closed to prevent fuel from flowing out of the fuel tank 2. When the active component 12 is in the second state, the opening 111 is opened, and the fuel tank 2 is connected to the outside atmosphere.

[0025] To address the issue of traditional fuel system vents being directly connected to the atmosphere, which can easily lead to fuel leakage and compromise flight safety during high-attack flight and when the fuel level is high, this embodiment, compared to existing technologies, features a different approach. In this embodiment, when the aircraft is in high-attack flight and the fuel level is high, the movable component 12 switches to a first state, quickly sealing the opening 111 of the shell 11 that connects to the atmosphere. This blocks the connection between the fuel tank 2 and the external atmosphere, preventing fuel from flowing out of the vent 23 and eliminating the flight safety hazard caused by fuel leakage. When the aircraft is in normal flight, the movable component 12 switches to a second state, opening the opening 111 of the shell 11, allowing the fuel tank 2 to remain connected to the external atmosphere. This ensures dynamic pressure balance within the fuel tank 2 as fuel is consumed and refueled, reducing the risk of deformation or damage to the fuel tank 2 due to pressure differences. This embodiment has a simple and compact structure, suitable for the high-attack and multi-condition flight characteristics of aircraft.

[0026] In one possible embodiment, the fuel system includes an integral fuel tank 2. A vent 23 is provided at the upper part of the fuel tank 2, and a drain port 24 is provided at the lower part for draining excess fuel from the fuel tank 2. A sealing and pressurizing device 1 is provided above the vent 23.

[0027] Furthermore, one end of the vent 23 is connected to the outside atmosphere, and the other end is connected to an external air source.

[0028] To address the issue of fuel potentially leaking from the vents when the aircraft is operating at large attitudes with a large fuel capacity, this embodiment includes a sealing and pressurizing device 1 above the vent 23.

[0029] For example, the sealing and pressurizing device 1 includes a housing 11, which includes sidewalls and a cover plate, and covers the vent 23. One end of the housing 11 has an opening 111 communicating with the outside atmosphere.

[0030] The sealing and pressurizing device 1 also includes a movable component 12, which is movably disposed within the housing 11 and can switch between a first state and a second state. When the movable component 12 is in the first state, the opening 111 is closed to prevent fuel from flowing out of the fuel tank 2; when the movable component 12 is in the second state, the opening 111 is opened, and the fuel tank 2 is connected to the outside atmosphere.

[0031] For example, such as Figure 6As shown, the movable component 12 in this embodiment includes a fixed member 121, a movable member 122, and a telescopic structure 123. The two ends of the fixed member 121 are disposed on the sidewalls of the housing 11, and the movable member 122 is disposed inside the housing 11 and near the opening 111. The telescopic structure 123 has a fixed end and a movable end. The fixed end is disposed on the fixed member 121, and the movable end is disposed on the movable member 122. The movable end can drive the movable member 122 to move, allowing the movable member 122 to switch between a first state and a second state, achieving precise driving of the movable member 122 and ensuring the reliability and response speed of state switching.

[0032] As one possible embodiment, such as Figure 7 As shown, the telescopic structure 123 in this embodiment includes a first sleeve 1231 and a second sleeve 1232. The first sleeve 1231 is fixed to the movable member 122, and the second sleeve 1232 is fixed to the fixed member 121. Preferably, two sets of the first sleeve 1231 and the second sleeve 1232 are provided, located on both sides of the fixed member 121 and the movable member 122, respectively. One end of the first sleeve 1231 extends into the second sleeve 1232, and the end of the second sleeve 1232 away from the first sleeve 1231 extends out of the housing 11 and is connected to an external air source through an external air source inlet pipe 13. The other end of the first sleeve 1231 extends out of the movable member 122. It should be noted that, as Figure 8 As shown, the protruding end of the first sleeve 1231 is a closed end.

[0033] When the external air source is turned on, the external air source is connected to the second sleeve 1232. The external air source enters the first sleeve 1231 through the second sleeve 1232 and pushes the closed end of the first sleeve 1231 toward the opening 111, thereby blocking the opening 111 and cutting off the communication channel between the fuel tank 2 and the outside atmosphere. This reduces the risk of fuel leakage from the opening 111 and improves the safety of the aircraft under large attitude or high fuel conditions.

[0034] Furthermore, a positioning post 124 is provided between the first sleeve 1231 and the second sleeve 1232 on both sides. One end of the positioning post 124 is fixed to the fixing member 121, and the other end passes through the through hole of the movable member 122 and can move in the through hole. A spring 125 is sleeved on the outside of the positioning post 124. One end of the spring 125 is fixed to the fixing member 121, and the other end is fixed to the movable member 122. The first sleeve 1231 can move forward under the push of an external air source. When the external air source is closed, the spring 125 pulls the movable member 122 and the first sleeve 1231 back, so that the closed end is away from the opening 111. The cooperation structure of the positioning post 124 and the spring 125 realizes the automatic reset of the movable member 122, improving the reliability of the system.

[0035] The bottom of the lower fuel tank 22 is equipped with a fuel drain port 24, which is used to drain excess fuel from the fuel tank 2. In the event of an emergency landing, carrying a large amount of fuel will increase the weight of the aircraft, so it is necessary to drain the excess fuel as soon as possible.

[0036] To address the issue of rapid fuel release during emergency landings, this embodiment employs a telescopic structure 123 where the outer diameter of the first sleeve 1231 is smaller than the inner diameter of the second sleeve 1232, creating a gap between them. When an external air source is activated, the closed end seals the opening 111, preventing the fuel tank 2 from communicating with the atmosphere. Gas leaks through the gap between the first and second sleeves 1231 and enters the upper fuel tank 21, then flows into the lower fuel tank 22 through the connecting pipe between the upper and lower fuel tanks. A portion of the gas enters the lower fuel tank 22 through the vent pipe 25 on one side of the casing 11. Fuel in the lower fuel tank 22, propelled by air pressure and gravity, accelerates downwards through the drain port 24. This achieves both sealing of the opening 111 and accelerated fuel release using air source pressure, improving fuel emission efficiency in emergency situations. Furthermore, the drain port 24 is equipped with a solenoid valve 241 to control its opening and closing.

[0037] In this embodiment, the sealing and pressurizing device 1 is integrated above the vent 23 of the upper fuel tank 21. It includes a housing 11 with an opening 111 and a switchable dual-state movable component 12. The movable component 12 adopts a combination of a double-sided sleeve telescopic structure and a spring 125, with a pre-reserved gap between the sleeves. The second sleeve 1232 is connected to an external air source. On the one hand, the air source can quickly close the opening 111, preventing fuel from flowing out of the vent 23 during large-attitude flight, thus eliminating safety hazards. After the air source is closed, the spring 125 automatically resets, restoring the air pressure balance of the fuel tank 2. On the other hand, the sleeve gap can achieve pressurization of air source leakage, allowing gas to enter the dual fuel tanks. In conjunction with the solenoid valve 241 of the fuel drain port 24, the fuel is accelerated to drain under the dual action of air pressure and gravity, rapidly reducing the aircraft weight and improving the safety of emergency landing.

[0038] As another possible implementation, such as Figure 1 and Figure 2 As shown, the fuel system includes an upper fuel tank 21 and a lower fuel tank 22, which are interconnected. The upper fuel tank 21 is located on the upper part of the frame 3, and the lower fuel tank 22 is located on the lower part of the frame 3, so as to make reasonable use of the aircraft frame space and achieve natural fuel delivery by gravity, thereby meeting the fuel supply needs of multiple engines.

[0039] like Figure 2As shown, the upper fuel tank 21 is provided with a first filler port 211 and a first outlet port 212 at the bottom; the lower fuel tank 22 is provided with a second filler port 221 at the top and a second outlet port 222 at the bottom. A fuel pipe 26 is provided between the first outlet port 212 and the second filler port 221. Fuel is added through the first filler port 211 and enters the lower fuel tank 22 through the fuel pipe 26. A level indicator is provided on one side of the first filler port 211 to display the fuel level in the upper fuel tank 21.

[0040] Furthermore, the upper fuel tank 21 and the lower fuel tank 22 are respectively equipped with fuel level sensors, which are used to detect the remaining fuel level in the upper fuel tank 21 and the lower fuel tank 22, so as to achieve accurate monitoring of the fuel level in the fuel tank.

[0041] like Figure 3 As shown, the lower part of the upper oil tank 21 is provided with a groove 213 for mounting the shaft. The lower two sides of the upper oil tank 21 are divided into a first part and a second part by the shaft. In order to avoid uneven fuel consumption between the first part and the second part, a straight oil pipe 214 is provided between the first part and the second part to solve the problem of uneven fuel consumption, so as to ensure smooth fuel flow and avoid local fuel shortage affecting fuel supply stability.

[0042] like Figure 4 As shown, the bottom of the lower fuel tank 22 is provided with two second fuel outlets 222, which are connected to the first engine and the second engine respectively. Furthermore, the lower fuel tank 22 is also provided with a drain port 24, which is used to drain fuel during engine maintenance or emergency landing of the aircraft, so as to reduce the weight of the aircraft and improve the safety of the emergency landing.

[0043] like Figure 5 As shown, the upper fuel tank 21 has a vent 23 on its top, and the lower fuel tank 22 has an air inlet 223 on its top. The vent 23 and the air inlet 223 are connected by a vent pipe 25. Furthermore, one end of the vent 23 is connected to the outside atmosphere, and the other end is connected to an external air source. A vent pipe 25 is provided on one side of the vent 23, connecting to the lower fuel tank 22.

[0044] Furthermore, it also includes a control unit, which is electrically connected to the control valve of the external air source and the solenoid valve 241 of the oil drain port 24, and is also electrically connected to the fuel level sensors of the upper fuel tank 21 and the lower fuel tank 22. The control unit can determine whether to open the external air source and whether to drain fuel based on the fuel level in the fuel tanks, taking into account the aircraft's attitude, and respond promptly.

[0045] Example 2 This embodiment discloses an aircraft engine, including an engine body and a fuel system with a sealed pressurization device as described in Embodiment 1.

[0046] The engine body includes a first engine and a second engine, and the two second oil outlets 222 of the lower oil tank 22 are respectively connected to the first engine and the second engine.

[0047] The turbocharger in the engine body compresses the intake air, which then enters the intercooler and is cooled before entering the engine body. A pressure relief valve is installed between the intercooler and the intake pipe to release excess intake air. This serves as the external air source for the second sleeve 1232 of the sealed pressurization device 1. In this embodiment, the air source directly uses the excess intake air released by the engine pressure relief valve, eliminating the need for dedicated air source piping, control components, and other supporting structures. This reduces the number of external components in the aircraft's fuel and engine systems, improves energy efficiency, and achieves energy conservation and emission reduction.

[0048] The lower fuel tank 22 is connected to the first engine via a first fuel outlet line 41, and to the second engine via a second fuel outlet line 42. A coarse air filter, a fuel pump 5, and a fine air filter are sequentially installed on the first fuel outlet line 41 and the second fuel outlet line 42, respectively. Fuel flows from the lower fuel tank 22 through the coarse air filter for coarse filtration, is pressurized by the fuel pump 5, and then flows through the fine air filter. In this embodiment, the fine air filter has a pressure regulating function, adjusting the fuel to the pressure required by the first and second engines. A portion of the fuel is returned to the upper fuel tank 21 or the lower fuel tank 22 via the return line, while the other portion is supplied to the first and second engines. Through this multi-stage filtration and pressure regulating structure, the cleanliness and pressure stability of the fuel supplied to the engines are improved, enhancing engine operational reliability.

[0049] When used in vehicles, the fuel pump is usually located inside the fuel tank, but when used in aircraft engines, it must be located outside the fuel tank.

[0050] To prevent the engine from shutting down due to fuel pump 5 failure, such as Figure 9 As shown, this embodiment features a dual-redundancy fuel supply structure 6. A three-way valve 61 and a branch pipe 62 are installed on the first fuel outlet line 41 leading from the lower fuel tank 22 to the first engine. The three-way valve 61 is positioned between the fuel pump 5 and the fine air filter. One end of the branch pipe 62 is connected to the three-way valve 61, and the other end is connected to the second fuel outlet line 42, located between the fuel pump 5 and the fine air filter in the second fuel outlet line 42. A start valve is installed on the three-way valve 61 to control the opening and closing of the pipeline. In the event of a first engine failure, fuel enters the first engine through the branch pipe 62, driven by the fuel pump 5 on the second fuel outlet line 42.

[0051] In this embodiment, when a single fuel pump or a single pipeline fails, the fuel supply path can be quickly switched through the three-way valve 61, and another fuel pump 5 can be used to supply fuel to both engines, completely avoiding engine shutdown caused by the failure of a single fuel pump 5, improving the reliability and fault tolerance of the aircraft engine fuel supply system, and meeting the high reliability requirements of the aviation field.

[0052] Compared with the prior art, the advantages of the aero-engine in this embodiment are the same as those of the fuel system with a sealed pressurization device in Embodiment 1, and will not be repeated here.

[0053] Example 3 This embodiment discloses an aircraft, including the aircraft engine of Embodiment 2.

[0054] The fuel system control unit is electrically connected to the aircraft's flight control system. When the flight control system detects large attitudes such as pitch or roll, and the fuel level sensor indicates a high fuel level, it activates the engine's pressure relief valve to seal the opening 111 of the housing 11 of the pressurization device 1. In the event of an emergency landing, the flight control system simultaneously signals the solenoid valve 241 of the fuel drain port 24 to release fuel in an emergency.

[0055] Compared with the prior art, the advantages of the aircraft in this embodiment are the same as those of the aero engine in embodiment 2, and will not be repeated here.

[0056] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A fuel system with a sealed pressurization device, characterized in that, The sealing and pressurizing device (1) is located above the vent (23) of the oil tank (2), and includes: A housing (11), one end of which has an opening (111) communicating with the outside atmosphere; and An active component (12) is movably disposed within the housing (11) and is capable of switching between a first state and a second state; When the active component (12) is in the first state, the opening (111) is closed to prevent fuel from flowing out of the fuel tank (2); when the active component (12) is in the second state, the opening (111) is opened and the fuel tank (2) is connected to the outside atmosphere. The movable component (12) extends out of the other end of the housing (11) and is connected to an external air source. The movable component (12) switches between the first state and the second state under the drive of the external air source. The movable component (12) includes: a fixing member (121) with both ends disposed on the side wall of the housing (11); a movable member (122) disposed inside the housing (11) and near one end of the opening (111); and a telescopic structure (123) having a fixed end and a movable end, the fixed end being disposed on the fixing member (121) and the movable end being disposed on the movable member (122).

2. The fuel system with a sealed pressurization device according to claim 1, characterized in that, Two telescopic structures (123) are provided.

3. The fuel system with a sealed pressurization device according to claim 1, characterized in that, The telescopic structure (123) includes a first sleeve (1231) and a second sleeve (1232).

4. The fuel system with a sealed pressurization device according to claim 3, characterized in that, The outer diameter of the first sleeve (1231) is smaller than the inner diameter of the second sleeve (1232).

5. The fuel system with a sealed pressurization device according to claim 3, characterized in that, The bottom of the fuel tank (2) is provided with a drain port (24), which is used to drain excess fuel in the fuel tank (2).

6. The fuel system with a sealed pressurization device according to claim 1, characterized in that, It also includes the fuel tank (2); The oil tank (2) includes an upper oil tank (21) and a lower oil tank (22); the upper oil tank (21) and the lower oil tank (22) are connected by a vent pipe (25) and an oil pipe (26); The vent (23) is located on the top of the upper oil tank (21); the vent pipe (25) is connected to the vent (23).

7. An aircraft engine, characterized in that, Includes the engine body and the fuel system as described in any one of claims 1-6; The engine body includes a first engine and a second engine, and the fuel tank (2) is provided with two fuel outlets, which are respectively connected to the first engine and the second engine; The external air source is the excess intake air discharged by the pressure relief valve of the first engine or the second engine.

8. An aircraft, characterized in that, Including the aircraft engine as described in claim 7.

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