An aircraft fuel vent system and an aircraft

Abstract

This application discloses an aircraft fuel venting system and an aircraft. The aircraft fuel venting system includes a fuel storage device and at least one venting pipe. The fuel storage device forms a fuel storage space and an expansion space. The venting pipe has a first part and a second part. The first end of the first part is located within the expansion space, and the second end of the first part is located outside the expansion space. The first part is arranged in a descending trend, with its position decreasing as it approaches its first end. Similarly, the second part is arranged in a descending trend, with its position decreasing as it moves away from the second end of the first part. Installing the venting pipe at its highest point prevents fuel from overflowing from the fuel storage device during normal operation. Simultaneously, during normal aircraft operation, the expansion space of the fuel storage device is always guided to balance with the external atmosphere, preventing damage to the fuel storage device due to pressure differences. The descending arrangement of both the first and second parts of the venting pipe prevents liquid accumulation in the pipe.

Description

Technical Field

[0001] This invention relates to the field of aircraft fuel tank venting technology, and more particularly to an aircraft fuel venting system and an aircraft. Background Technology

[0002] Aircraft fuel systems require non-fuel areas to be filled with inert gas or vented to prevent negative pressure from forming inside the fuel tank after fuel consumption, which could damage the fuel tank structure. Transport aircraft typically use inert gas to fill the fuel tank cavity, while general aviation aircraft usually connect the upper part of the fuel tank to the atmosphere to quickly equalize the pressure difference between the inside and outside of the fuel tank, protecting the fuel tank structure.

[0003] For general aviation aircraft, if the vent for connecting to the atmosphere were directly located on the structure above the fuel tank, although it would still function as a vent, it could allow moisture and impurities from parking and operation to enter the fuel tank and contaminate the fuel. Therefore, the vent is generally located on the lower side of the aircraft fuel tank. When the vent is located on the lower side of the aircraft fuel tank, a small amount of fuel or water vapor may overflow from the fuel tank through the vent. When the aircraft is operating at low temperatures, the vent may freeze, or it may be blocked by insect nests or mud, making it difficult for air to escape and affecting the safe venting function of the fuel tank. Summary of the Invention

[0004] In view of the above problems, the present invention overcomes at least one of them and proposes an aircraft fuel venting system and an aircraft.

[0005] The technical solution adopted in this invention is as follows:

[0006] This application provides an aircraft fuel venting system, which includes a fuel storage device and at least one venting line.

[0007] The fuel storage device is located inside the wing. The fuel storage device has an interconnected fuel storage space and an expansion space. The fuel storage space is used to store fuel, and the expansion space is located above the fuel storage space. The expansion space is used to provide space for the fuel to expand when heated.

[0008] The ventilation duct has a first part and a second part that are interconnected. The first end of the first part is located inside the expansion space, and the second end of the first part is located outside the expansion space. The first part is arranged in a downward trend, and the closer the first part is to the first end of the first part, the lower its position. The second part is arranged in a downward trend, and the farther the second part is from the second end of the first part, the lower its position.

[0009] The second part of the ventilation duct is located on the wing and is connected to the outside atmosphere of the wing.

[0010] By placing the first end of the first section of the venting line within the aircraft's expansion space, making the venting line the highest point, it is possible to prevent fuel from overflowing into the fuel storage device during normal operation. At the same time, during normal aircraft operation, the expansion space of the fuel storage device is always guided to be balanced with the external atmosphere, avoiding damage to the fuel storage device due to pressure differences between the inside and outside. Furthermore, by setting both the first and second sections of the venting line in a downward trend, it is possible to prevent liquid accumulation in the line.

[0011] Furthermore, the ventilation duct has an insulating section. When the wing is struck by lightning, the insulating section is used to prevent the current generated by the lightning from flowing from the wing to the fuel storage device, thus preventing the risk of damage to the fuel storage device.

[0012] The insulation section prevents the current generated when the aircraft is struck by lightning from flowing from the wings to the fuel storage unit, thereby avoiding the danger of lightning to the fuel storage unit and fuel vapor, and ensuring the safety of the aircraft when parked and throughout the entire operating profile.

[0013] In practical applications, the insulating section can be made of silicone.

[0014] Furthermore, the first end of the first part located within the expansion space is bent upward to form a bent portion. After the first end is bent, the horizontal plane where the first end port is located is higher than the horizontal plane where the first end port is located before the bend, and the horizontal plane where the first end port is located after the bend is not higher than the horizontal plane where the bent portion is located.

[0015] The bend is used to position the port at the highest point of the expansion space and to prevent liquid accumulation in the first part of the venting pipe within the expansion space.

[0016] In actual use, the wing is tilted relative to the horizontal plane, and the ventilation duct in the expansion space is also tilted relative to the horizontal plane. When the length of the ventilation duct in the expansion space is slightly longer and the aircraft is flying at an angle, the ventilation duct is more likely to be immersed in oil and the oil will enter the ventilation duct. At low temperatures, it will solidify into ice and obstruct ventilation. By bending the first end upward to form a bend, the possibility of oil entering the ventilation duct is reduced while ensuring that oil does not easily accumulate in the ventilation duct.

[0017] Furthermore, the aircraft fuel venting system also includes a through-frame connector, which is disposed on the side wall of the fuel storage device. The venting pipe passes through the through-frame connector and is installed on the fuel storage device, with the first end of the first part of the venting pipe placed within the expansion space.

[0018] Furthermore, the aircraft fuel venting system also includes a vent cover, which is fixed to the underside of the wing and has an air inlet, which is a V-shaped NACA inlet.

[0019] The ventilation duct is connected to the external atmosphere of the wing through the air inlet;

[0020] The tip of the V-shaped NACA nozzle points towards the front of the aircraft and aligns with the aircraft's flight direction.

[0021] Smaller air inlets make it difficult to implement active de-icing measures. The low-resistance air inlet design of the NACA inlet, combined with the venting duct arranged in a downward trend, allows for the high-speed ram airflow to clean away ice when it forms inside the venting duct, preventing icing and ventilation failure caused by the high-speed flight of the aircraft.

[0022] Furthermore, the vent cover also has a nozzle connected to the air inlet, which is used to connect to the vent pipe.

[0023] Furthermore, the wing includes an upper skin and a lower skin, which are fastened together to form a cavity, and the oil storage device is disposed within the cavity; the expansion space is disposed on the side near the upper skin.

[0024] The vent cover includes a first vent cover and a second vent cover, which are spaced apart and disposed on the lower skin of the aircraft.

[0025] The ventilation pipeline includes a first pipeline and a second pipeline, which are respectively connected to the first ventilation cover and the second ventilation cover.

[0026] Two ventilation lines are installed, each connected to the inside of the oil storage device. This serves as a backup ventilation system when the vent of one of the ventilation lines is blocked by insect nests or mud and cannot be cleared by airflow, thus enhancing the reliability of the system.

[0027] Furthermore, the wing also includes a first support beam, a second support beam, and a rib plate disposed between the first support beam and the second support beam. The support beam and the rib plate are disposed inside the cavity and divide the cavity into a first cavity and a second cavity. The first cavity is disposed on the side closer to the aircraft fuselage, and the fuel storage device is disposed in the first cavity.

[0028] The first vent cover and the second vent cover are disposed on the lower skin corresponding to the second cavity, with the second vent cover disposed on the side further away from the oil storage device.

[0029] The first vent cover and the second vent cover are spaced apart, with the second vent cover positioned further away from the oil storage device, so that the distance between the first vent cover and the second vent cover is as large as possible.

[0030] In actual use, the upper skin, lower skin, first support beam, second support beam, and ribs are sealed together to form the aforementioned oil storage device, which reduces the weight of the aircraft and makes it easier for the aircraft to fly.

[0031] Furthermore, the first portion of both the first and second pipelines located within the expansion space is made of rigid pipe material;

[0032] The first pipeline located outside the expansion space is made of insulated flexible tubing.

[0033] The second pipeline located outside the expansion space includes a first connecting pipe and a second connecting pipe connected to the first connecting pipe. The first connecting pipe is a rigid pipe, and the second connecting pipe is made of insulated flexible material. The second connecting pipe is used to connect to the second vent cover.

[0034] Furthermore, the aircraft fuel venting system also includes a mounting bracket, and the first pipe located outside the expansion space and the second pipe located outside the expansion space are respectively fixed to the upper or lower skin of the aircraft via the mounting bracket to prevent the pipes from bending and accumulating liquid.

[0035] This application also provides an aircraft including the aircraft fuel venting system described above.

[0036] The beneficial effects of this invention are:

[0037] (1) By setting the first end of the first part of the venting pipe in the expansion space of the aircraft, the venting pipe is installed at the highest point, which can prevent fuel from overflowing into the fuel storage device during normal operation. At the same time, the expansion space of the fuel storage device is always guided to be balanced with the outside atmosphere during normal operation of the aircraft, thus avoiding damage to the fuel storage device due to the pressure difference between the inside and outside. By setting the first part and the second part of the venting pipe in a downward trend, liquid accumulation in the pipe can be prevented.

[0038] (2) The insulation section prevents the current generated when the aircraft is struck by lightning from flowing from the wing to the fuel storage device, thereby avoiding the danger of lightning to the fuel storage device and fuel vapor, and ensuring the safety of the aircraft parking and the entire operating profile.

[0039] (3) By bending the first end upward to form a bend, the possibility of oil entering the venting pipe is reduced while ensuring that oil does not easily accumulate in the venting pipe.

[0040] (4) Two ventilation pipes are set up to be connected to the inside of the oil storage device. This is to provide a backup ventilation device when the ventilation port of one of the ventilation pipes is blocked by insect nests or mud and cannot be opened by airflow, thereby enhancing the reliability of the system.

[0041] (5) The NACA port is arranged in a V-shape with the small opening facing forward, so that the ram airflow can fully impact the inner groove of the NACA port and prevent the vent from freezing.

[0042] The aircraft fuel venting system based on the NACA port achieves pressure balance inside and outside the fuel storage unit at all times, preventing structural collapse of the fuel storage unit. It uses ram airflow to solve the de-icing problem of the vent, and the parallel backup venting pipeline system can prevent the vent from being blocked by foreign objects. The insulation of the venting pipeline avoids the impact of lightning strikes on the fuel vapor inside the fuel storage unit, ensuring the safety of the aircraft during parking and throughout the entire operating profile. Attached Figure Description

[0043] Figure 1 This is a schematic diagram of the axonal structure of the aircraft fuel venting system according to an embodiment of the present invention;

[0044] Figure 2 This is a top view schematic diagram of the aircraft fuel venting system according to an embodiment of the present invention;

[0045] Figure 3 This is a schematic cross-sectional view of the aircraft fuel venting system according to an embodiment of the present invention.

[0046] Figure 4 yes Figure 3 Enlarged structural diagram of A in the middle;

[0047] Figure 5 This is a schematic diagram of the axial structure of the vent cover according to an embodiment of the present invention.

[0048] The labels for the attached figures are as follows:

[0049] 100. Vent pipe; 110. First pipe; 120. Second pipe; 121. First connecting pipe; 122. Second connecting pipe; 130. First part; 140. Second part; 101. Insulating section; 102. Bending section; 200. Oil storage device; 210. Oil storage space; 220. Expansion space; 300. Through-frame joint; 400. Vent cover; 410. First vent cover; 420. Second vent cover; 401. Nozzle; 500. Wing; 510. Lower skin; 520. First support beam; 530. Second support beam; 540. Rib plate; 550. First cavity; 560. Second cavity; 600. Mounting seat. Detailed Implementation

[0050] The present invention will now be described in detail with reference to the accompanying drawings.

[0051] like Figures 1-4 As shown, this application provides an aircraft fuel venting system, which includes a fuel storage device 200 and two venting lines 100.

[0052] The oil storage device 200 is located inside the wing 500, and the oil storage device 200 has an interconnected oil storage space 210 and an expansion space 220. Figure 2 (Represented by dashed lines in the middle), the oil storage space 210 is used to store fuel oil, and the expansion space 220 is located above the oil storage space 210. The expansion space 220 is used to provide space for the fuel oil to expand when heated.

[0053] The ventilation duct 100 has a first part 130 and a second part 140 that are interconnected. The first end of the first part 130 is located inside the expansion space 220, and the second end of the first part 130 is located outside the expansion space 220. The first part 130 is arranged in a downward trend, and the closer the first end of the first part 130 is to the first part, the lower its position. The second part 140 is arranged in a downward trend, and the farther the second part 140 is from the second end of the first part 130, the lower its position.

[0054] The second part 140 of the ventilation duct 100 is located on the wing 500 and is connected to the external atmosphere of the wing.

[0055] By placing the first end of the first section 130 of the venting pipe 100 within the expansion space 220 of the aircraft, and installing the venting pipe 100 at its highest point, fuel overflow from the fuel storage device 200 during normal operation can be prevented. At the same time, during normal aircraft operation, the expansion space 220 of the fuel storage device 200 is always guided to be balanced with the external atmosphere, avoiding damage to the fuel storage device 200 due to pressure differences between the inside and outside. Furthermore, by setting the first section 130 and the second section 140 of the venting pipe 100 in a downward trend, liquid accumulation in the pipe can be prevented.

[0056] like Figure 1 As shown, in this embodiment, the ventilation duct 100 has an insulating section 101. When the wing 500 is struck by lightning, the insulating section 101 is used to prevent the current generated by the lightning from flowing from the wing 500 to the oil storage device 200, thereby preventing the risk of damage to the oil storage device 200.

[0057] The insulation section 101 prevents the current generated when the aircraft is struck by lightning from flowing from the wing 500 to the fuel storage device 200, thereby avoiding the danger of lightning to the fuel storage device 200 and fuel vapor, and ensuring the safety of the aircraft when parked and throughout the entire operating profile.

[0058] In actual use, the insulating section 101 can be made of silicone.

[0059] In this embodiment, the insulating section 101 is the second connecting pipe 122 of the first pipe 110 located outside the expansion space 220 and the second pipe 120 located outside the expansion space 220.

[0060] like Figure 2 and Figure 3As shown, in this embodiment, the first end of the first part 130 located in the expansion space 220 is bent upward to form a bent part 102. After the first end is bent, the horizontal plane where the first end port is located is higher than the horizontal plane where the first end port is located before bending, and the horizontal plane where the first end port is located after bending is at the same height as the horizontal plane where the bent part 102 is located.

[0061] The bend 102 is used to position the port of the first end at the highest point of the expansion space 220 and to prevent liquid accumulation inside the first part 130 of the vent 100 within the expansion space 220.

[0062] In this embodiment, the first end has a bending angle of 160° in the horizontal direction. In actual use, the bending angle is between 120° and 170°.

[0063] In actual use, the wing 500 is tilted relative to the horizontal plane, and the ventilation duct 100 located in the expansion space 220 is also tilted relative to the horizontal plane. When the length of the ventilation duct 100 located in the expansion space 220 is slightly longer and the aircraft is flying at an angle, the ventilation duct 100 is more likely to be immersed in oil and the oil will enter the ventilation duct 100. At low temperatures, it will solidify into ice and obstruct ventilation. By bending the first end upward to form a bend 102, the possibility of oil entering the ventilation duct 100 is reduced while ensuring that oil does not easily accumulate in the ventilation duct 100.

[0064] like Figure 1 As shown, in this embodiment, the aircraft fuel venting system also includes a through-frame connector 300, which is disposed on the side wall of the fuel storage device 200. The venting pipe 100 passes through the through-frame connector 300 and is installed on the fuel storage device 200, with the first end of the first part 130 of the venting pipe 100 placed in the expansion space 220.

[0065] In this embodiment, the aircraft fuel venting system also includes a vent cover 400, which is fixed to the underside of the wing 500. The vent cover 400 has an air inlet, which is a V-shaped NACA port.

[0066] The ventilation duct 100 is connected to the external atmosphere of the wing 500 through the air inlet;

[0067] The tip of the V-shaped NACA nozzle points towards the front of the aircraft and aligns with the aircraft's flight direction.

[0068] Smaller air inlets make it difficult to implement active de-icing measures. The low-resistance air inlet design of the NACA port, combined with the downward-sloping ventilation duct 100, allows for the removal of ice buildup in the duct 100 by high-speed ram airflow as the aircraft flies at high speed, preventing icing at the air inlet from causing ventilation failure.

[0069] like Figure 1 and Figure 5 As shown, in this embodiment, the vent cover 400 also has a nozzle 401 connected to the air inlet, and the nozzle 401 is used to connect to the vent pipe 100.

[0070] In this embodiment, rivets are also included, and the vent cover 400 is fixed to the lower skin 510 by the rivets.

[0071] In this embodiment, the NACA port of the vent cover 400 is positioned facing the outside of the wing 500, and the nozzle 401 is positioned inside the second cavity 560.

[0072] In this embodiment, the wing 500 includes an upper skin and a lower skin 510, which are fastened together to form a cavity, and the oil storage device 200 is disposed in the cavity; the expansion space 220 is disposed on the side near the upper skin.

[0073] The vent cover 400 includes a first vent cover 410 and a second vent cover 420, which are spaced apart on the lower skin 510 of the aircraft.

[0074] The two ventilation pipes 100 are a first pipe 110 and a second pipe 120, which are connected to a first vent cover 410 and a second vent cover 420, respectively.

[0075] Two ventilation pipes 100 are respectively connected to the inside of the oil storage device 200. This serves as a backup ventilation device when the ventilation port of one of the ventilation pipes 100 is blocked by insect nests or mud and cannot be cleared by airflow, thereby enhancing the reliability of the system.

[0076] like Figure 2 and Figure 3 As shown, in this embodiment, the wing 500 further includes a first support beam 520, a second support beam 530, and a rib 540 disposed between the first support beam 520 and the second support beam 530. The support beam and the rib 540 are disposed inside the cavity, dividing the cavity into a first cavity 550 and a second cavity 560. The first cavity 550 is disposed on the side close to the aircraft fuselage, and the fuel storage device 200 is disposed in the first cavity 550.

[0077] The first vent cover 410 and the second vent cover 420 are disposed on the lower skin 510 corresponding to the second cavity 560, with the second vent cover 420 disposed on the side further away from the oil storage device 200.

[0078] The first vent cover 410 and the second vent cover 420 are spaced apart, with the second vent cover 420 located further away from the oil storage device 200, so that the distance between the first vent cover 410 and the second vent cover 420 is as large as possible.

[0079] In actual use, the upper skin, lower skin 510, first support beam 520, second support beam 530 and rib 540 are sealed together to form the above-mentioned oil storage device 200, so as to reduce the weight of the aircraft and make the aircraft flight more convenient.

[0080] like Figures 1-4 As shown, in this embodiment, the first portion 130 of the first pipe 110 and the second pipe 120 located in the expansion space 220 are both made of rigid pipe material.

[0081] The first pipe 110 located outside the expansion space 220 is made of insulated flexible hose;

[0082] The second pipe 120 located outside the expansion space 220 includes a first connecting pipe 121 and a second connecting pipe 122 connected to the first connecting pipe 121. The first connecting pipe 121 is a rigid pipe, and the second connecting pipe 122 is made of insulated flexible material. The second connecting pipe 122 is used to connect to the second vent cover 420.

[0083] like Figure 4 As shown, in this embodiment, the aircraft fuel venting system also includes a mounting bracket 600. The first pipe 110 located outside the expansion space 220 and the second pipe 120 located outside the expansion space 220 are respectively fixed to the upper skin or lower skin 510 of the aircraft through the mounting bracket 600 to prevent the pipes from bending and causing liquid accumulation.

[0084] In this embodiment, clamps are also included. The two ends of the first pipe 110 located outside the expansion space 220 are respectively connected and fixed to the nozzles 401 of the through-frame connector 300 and the first vent cover 410 by clamps. The two ends of the second connecting pipe 122 located outside the expansion space 220 are respectively connected and fixed to the nozzles 401 of the first connecting pipe 121 and the second vent cover 420 by clamps.

[0085] This application also provides an aircraft including the aircraft fuel venting system described above.

[0086] The above description is merely a preferred embodiment of the present invention and does not limit the scope of patent protection of the present invention. Any equivalent structural transformations made based on the description and drawings of the present invention, whether directly or indirectly applied to other related technical fields, are similarly included within the scope of protection of the present invention.

Claims

1. An aircraft fuel venting system, characterized in that, The aircraft fuel venting system includes a fuel storage device and at least one venting line. The fuel storage device is located inside the wing. The fuel storage device has an interconnected fuel storage space and an expansion space. The fuel storage space is used to store fuel, and the expansion space is located above the fuel storage space. The expansion space is used to provide space for the fuel to expand when heated. The ventilation duct has a first part and a second part that are interconnected. The first end of the first part is located inside the expansion space, and the second end of the first part is located outside the expansion space. The first part is arranged in a downward trend, and the closer the first part is to the first end of the first part, the lower its position. The second part is arranged in a downward trend, and the farther the second part is from the second end of the first part, the lower its position. The second part of the ventilation duct is located on the wing and is connected to the outside atmosphere of the wing; The first end of the first part located in the expansion space is bent upward to form a bent portion. After the first end is bent, the horizontal plane where the first end port is located is higher than the horizontal plane where the first end port is located before the bend, and the horizontal plane where the first end port is located after the bend is not higher than the horizontal plane where the bent portion is located. The bending section is used to position the port of the first end at the highest point of the expansion space and to prevent liquid accumulation in the first part of the venting pipe within the expansion space. The aircraft fuel venting system also includes a vent cover, which is fixed to the underside of the wing and has an air inlet, which is a V-shaped NACA inlet. The ventilation duct is connected to the external atmosphere of the wing through the air inlet; The tip of the V-shaped NACA nozzle points towards the front of the aircraft and aligns with the aircraft's flight direction.

2. The aircraft fuel venting system as described in claim 1, characterized in that, The ventilation duct has an insulating section. When the wing is struck by lightning, the insulating section is used to prevent the current generated by the lightning from flowing from the wing to the fuel storage device, thus preventing the risk of damage to the fuel storage device.

3. The aircraft fuel venting system as described in claim 1, characterized in that, The aircraft fuel venting system also includes a through-frame connector, which is disposed on the side wall of the fuel storage device. The venting pipe passes through the through-frame connector and is installed on the fuel storage device, with the first end of the first part of the venting pipe placed in the expansion space.

4. The aircraft fuel venting system as described in claim 1, characterized in that, The vent cover also has a nozzle connected to the air inlet, which is used to connect to the vent pipe.

5. An aircraft fuel venting system as described in claim 1, characterized in that, The wing includes an upper skin and a lower skin, which are fastened together to form a cavity, and the oil storage device is disposed in the cavity; the expansion space is disposed on the side near the upper skin. The vent cover includes a first vent cover and a second vent cover, which are spaced apart and disposed on the lower skin of the aircraft. The ventilation pipeline includes a first pipeline and a second pipeline, which are respectively connected to the first ventilation cover and the second ventilation cover.

6. The aircraft fuel venting system as described in claim 5, characterized in that, The wing also includes a first support beam, a second support beam, and a rib plate disposed between the first support beam and the second support beam. The support beam and the rib plate are disposed inside the cavity and divide the cavity into a first cavity and a second cavity. The first cavity is disposed on the side closer to the aircraft fuselage, and the fuel storage device is disposed in the first cavity. The first vent cover and the second vent cover are disposed on the lower skin corresponding to the second cavity, with the second vent cover disposed on the side further away from the oil storage device.

7. An aircraft fuel venting system as described in claim 5, characterized in that, The first portion of both the first and second pipelines located within the expansion space are made of rigid pipe material; The first pipeline located outside the expansion space is made of insulated flexible tubing. The second pipeline located outside the expansion space includes a first connecting pipe and a second connecting pipe connected to the first connecting pipe. The first connecting pipe is a rigid pipe, and the second connecting pipe is made of insulated flexible material. The second connecting pipe is used to connect to the second vent cover. The aircraft fuel venting system also includes a mounting bracket, and a first pipe located outside the expansion space and a second pipe located outside the expansion space are respectively fixed to the upper or lower skin of the aircraft via the mounting bracket.

8. An aircraft fuel venting system as described in claim 5, characterized in that, The aircraft fuel venting system also includes a mounting bracket, and a first pipe located outside the expansion space and a second pipe located outside the expansion space are respectively fixed to the upper or lower skin of the aircraft via the mounting bracket.

9. An aircraft, characterized in that, The system includes an aircraft fuel venting system as described in any one of claims 1 to 8.

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