CN116654270A - Aircraft fuel tank inerting system and aircraft - Google Patents
Aircraft fuel tank inerting system and aircraft Download PDFInfo
- Publication number
- CN116654270A CN116654270A CN202310814485.7A CN202310814485A CN116654270A CN 116654270 A CN116654270 A CN 116654270A CN 202310814485 A CN202310814485 A CN 202310814485A CN 116654270 A CN116654270 A CN 116654270A
- Authority
- CN
- China
- Prior art keywords
- fuel tank
- inerting
- aircraft
- line
- wing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002828 fuel tank Substances 0.000 title claims abstract description 179
- 239000012530 fluid Substances 0.000 claims abstract description 57
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 16
- 239000007789 gas Substances 0.000 claims description 9
- 229910052757 nitrogen Inorganic materials 0.000 claims description 8
- 238000009423 ventilation Methods 0.000 abstract description 22
- 230000009286 beneficial effect Effects 0.000 abstract description 21
- 230000000694 effects Effects 0.000 abstract description 21
- 238000013461 design Methods 0.000 description 12
- 239000000446 fuel Substances 0.000 description 12
- 239000003921 oil Substances 0.000 description 8
- 238000012545 processing Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000001012 protector Effects 0.000 description 2
- 238000013022 venting Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000003305 oil spill Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention relates to an aircraft fuel tank inerting system and an aircraft. The aircraft fuel tank inerting system is used for an aircraft comprising a central wing fuel tank and outer wing main fuel tanks positioned on two sides, the aircraft also comprises a ventilation fuel tank positioned on the outer side of the outer wing main fuel tank and a ventilation pipeline used for communicating the central wing fuel tank or the outer wing main fuel tank to the ventilation fuel tank, and the aircraft fuel tank inerting system comprises an inerting fluid source, an inerting fluid pipeline, a pressure release pipeline and a pressure release device; wherein the inerting fluid line is for supplying inerting fluid from an inerting fluid source to the center wing fuel tank, the pressure relief line is for communicating the inerting fluid line to the vent line, and the pressure relief device is located in the pressure relief line and is for opening when the pressure differential is above a predetermined threshold to bypass the inerting fluid to the vent line. According to the technical scheme, the invention has the following beneficial technical effects: the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be eliminated, and the overpressure of the central wing fuel tank is avoided.
Description
Technical Field
The invention relates to an aircraft fuel tank inerting system and an aircraft comprising the same, and relates to the technical field of aircraft fuel system and inerting system design.
Background
In certain types of flight, the ventilation system of the central wing fuel tank is incompatible with the inerting system, after the ventilation system vent is immersed by fuel oil, the nitrogen-rich gas is not smoothly exhausted, the central wing fuel tank is pressurized, and the central wing fuel tank structure has the risk of overpressure damage. Meanwhile, the pressure is suppressed, so that a large amount of fuel in the fuel tank with the central wing overflows to the ventilation fuel tank through the ventilation pipeline, and further the fuel quantity of the fuel tank with the central wing is unexpectedly changed and deviates from the design expectation of a fuel system.
Some prior art models allow the overpressure fuel of the central wing to enter the outer wing fuel tank by installing an overpressure protector on the outer wing fuel tank, and if the outer wing fuel tank is overpressurized, the outer wing fuel will flow out of the engine through the outer wing overpressure protector to prevent the overpressure of the fuel tank. However, the scheme is mainly designed aiming at the ground oil spill, a pressure release valve is required to be installed at an opening of a lower wall plate structure of the wing, the processing difficulty of the wing structure is increased, and a large amount of fuel oil can be discharged through the pressure release valve once the oil tank is overpressurized.
Other models of the prior art provide an embodiment for preventing tank overpressure by adding a pressure sensor to the nitrogen-rich gas distribution line, and once the pressure sensor monitors that the line pressure exceeds a certain value, the inerting controller shuts off the inerting system to prevent tank overpressure. However, this solution increases the number of electrical devices of the system and the complexity of the control software by adding pressure sensors for overpressure monitoring.
Other models of the prior art provide an embodiment of nitrogen-rich gas distribution pipeline arrangement and overpressure protection of the oil tank, the scheme is suitable for an outer wing fuel tank of an all-tank inerting model, the nitrogen-rich gas distribution pipeline arrangement can avoid oil feeding of the distribution pipeline, wing inerting is achieved, and the overpressure protection design can enhance the safety of the oil tank. However, this solution is suitable for the addition of inerted outer-wing fuel tanks, the pressure relief valve of the nitrogen-rich gas distribution line being arranged in the venting tank, for the outer-wing fuel tank immediately adjacent to the venting tank, and not for the central-wing fuel tank.
Other models of the prior art focus on the design of a float valve, and under the condition of overpressure of a fuel tank, no matter whether a float is immersed by fuel or not, an effective opening can be formed at the position of a valve plate under the action of pressure difference, the opening can be ventilated and can overflow the fuel, and the float valve is suitable for being additionally provided with an inertized outer wing fuel tank and can prevent the overpressure of the outer wing fuel tank close to the ventilated fuel tank; however, for the central wing fuel tank far away from the ventilation fuel tank, because the central wing fuel tank is communicated with the ventilation fuel tank through a long pipeline, under the condition that the ventilation float valve in the central wing fuel tank is immersed by fuel, if inert gas in the central wing fuel tank is not smoothly discharged, the fuel tank is still pressurized, because the fuel overflows into the ventilation pipeline, the pressurizing amplitude of the fuel tank depends on the flowing resistance of the fuel in the ventilation pipeline, the flow resistance is closely related to the length, the diameter and the oil spilling rate of the ventilation pipeline, and the additional opening of the float valve only increases the oil spilling inlet, so that the pressurizing air source in the fuel tank is not eliminated, the pressurizing of the fuel tank caused by the oil spilling process of the ventilation pipeline is not changed, and the overpressure potential safety hazard of the central wing fuel tank with an inerting system cannot be eliminated.
Disclosure of Invention
It is an object of the present invention to provide an aircraft fuel tank inerting system that overcomes at least some of the disadvantages of the prior art and eliminates the center wing fuel tank overpressure safety hazard with an inerting system.
The above object of the invention is achieved by an aircraft fuel tank inerting system for an aircraft comprising a center wing fuel tank and outer wing main fuel tanks on both sides, the aircraft further comprising a vent fuel tank located outside the outer wing main fuel tanks and a vent line for communicating the center wing fuel tank or the outer wing main fuel tanks to the vent fuel tank, the aircraft fuel tank inerting system comprising an inerting fluid source, an inerting fluid line, a pressure relief line, and a pressure relief device;
wherein the inerting fluid line is for supplying inerting fluid from the inerting fluid source to the center wing fuel tank, the relief line is for communicating the inerting fluid line to the vent line, the relief device is located in the relief line and is for opening when a differential pressure across the relief device is above a predetermined threshold to bypass inerting fluid to the vent line.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be eliminated, and the overpressure of the central wing fuel tank is avoided.
Preferably, the pressure relief device is located entirely within the center wing fuel tank.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the wing wall structure is not required to be provided with an opening, and the processing difficulty of the structure is not increased.
Preferably, the vent line includes a center wing fuel tank vent line for communicating the center wing fuel tank to the vent fuel tank, and an outer wing main fuel tank vent line for communicating the outer wing main fuel tank to the vent fuel tank.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: by appropriate vent line design, either the center wing tank or the outer wing main tank can be effectively connected to the vent tank.
Preferably, the pressure relief line is used to communicate the inerting fluid line to the center wing tank vent line.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: by bypassing the inerting fluid to the center wing tank vent line, center wing tank overpressure is avoided.
Preferably, the pressure relief line is used to communicate the inerting fluid line to the main outer wing tank vent line.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: by bypassing the inerting fluid to the outer wing main tank vent line, center wing tank overpressure is avoided.
Preferably, the aircraft fuel tank inerting system further comprises a second pressure relief device mounted on the inerting fluid line and located outside the front spar of the center wing fuel tank fuselage outer section.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the second pressure release device with proper design can discharge the released inerting fluid to the atmosphere, so that the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be better eliminated, and the overpressure of the central wing fuel tank can be better avoided.
Preferably, the predetermined threshold is 4-6 PSI.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be better eliminated by properly designed pressure relief device differential pressure preset threshold value, and the overpressure of the central wing fuel tank can be better avoided.
Preferably, the inerting fluid is a nitrogen-rich gas.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the aircraft fuel tank inerting function can be better realized through proper inerting fluid.
Preferably, the pressure relief device is a pressure relief valve.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: through a proper pressure release device, the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be better eliminated, and the overpressure of the central wing fuel tank can be better avoided.
The above object of the invention is also achieved by an aircraft comprising an aircraft fuel tank inerting system as described in any of the above aspects.
According to the technical scheme, the aircraft provided by the invention has the following beneficial technical effects: the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be eliminated, and the overpressure of the central wing fuel tank is avoided.
Drawings
FIG. 1 is a schematic view of an aircraft fuel tank inerting system in accordance with an embodiment of the present invention.
FIG. 2 is a schematic view of an aircraft fuel tank inerting system in accordance with another embodiment of the present invention.
FIG. 3 is a schematic view of an aircraft fuel tank inerting system in accordance with another embodiment of the present invention.
List of reference numerals
1: center wing fuel tank;
2: an outer wing main fuel tank;
3: a ventilation oil tank;
4: a center wing fuel tank vent line;
5: an outer wing main fuel tank vent line;
6: a front beam;
7: a rear beam;
11: inerting the fluid line;
12: a pressure release pipeline;
13: a pressure release device;
14: and a second pressure release device.
Detailed Description
In the following, specific embodiments of the present invention will be described, and it should be noted that in the course of the detailed description of these embodiments, it is not possible in the present specification to describe all features of an actual embodiment in detail for the sake of brevity. It should be appreciated that in the actual implementation of any of the implementations, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that while such a development effort might be complex and lengthy, it would nevertheless be a routine undertaking of design, fabrication, or manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as having the benefit of this disclosure.
Unless defined otherwise, technical or scientific terms used in the claims and specification should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs. The terms "first," "second," and the like in the description and in the claims, are not used for any order, quantity, or importance, but are used for distinguishing between different elements. The terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprising" or "comprises", and the like, is intended to mean that elements or items that are immediately preceding the word "comprising" or "comprising", are included in the word "comprising" or "comprising", and equivalents thereof, without excluding other elements or items. The terms "connected" or "connected," and the like, are not limited to physical or mechanical connections, nor to direct or indirect connections.
In the following description, for the purposes of clarity of presentation of the structure and manner of operation of the present invention, the description will be made with the aid of directional terms, but such terms as "forward," "rearward," "left," "right," "outward," "inner," "outward," "inward," "upper," "lower," etc. are to be construed as convenience, and are not to be limiting.
FIG. 1 is a schematic view of an aircraft fuel tank inerting system in accordance with an embodiment of the present invention. FIG. 2 is a schematic view of an aircraft fuel tank inerting system in accordance with another embodiment of the present invention. FIG. 3 is a schematic view of an aircraft fuel tank inerting system in accordance with another embodiment of the present invention.
As shown in fig. 1-3, according to some embodiments of the present invention, an aircraft fuel tank inerting system for an aircraft comprising a center wing fuel tank 1 and outer wing main fuel tanks 2 located on both sides (i.e., on both sides of the center wing fuel tank 1), the aircraft further comprising a vent fuel tank 3 located outside the outer wing main fuel tanks 2, and a vent line for communicating the center wing fuel tank 1 or the outer wing main fuel tanks 2 to the vent fuel tank 3, the aircraft fuel tank inerting system comprising an inerting fluid source, an inerting fluid line 11, a pressure relief line 12, and a pressure relief device 13;
wherein the inerting fluid line 11 is used for supplying inerting fluid from an inerting fluid source to the center wing fuel tank 1 (thus, the inerting fluid line 11 may also be referred to as a "center wing fuel tank inerting fluid line"), the relief line 12 is used for communicating the inerting fluid line 11 to the vent line, the relief device 13 is located in the relief line 12 and is used for opening when the differential pressure across the relief device 13 is above a predetermined threshold value to bypass the inerting fluid to the vent line.
According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be eliminated, and the overpressure of the central wing fuel tank is avoided.
Specifically, when the ventilation of the central wing fuel tank is not smooth and the ventilation pipeline is overflowed, the medium flowing in the ventilation pipeline is changed from gas to liquid, the flow resistance is obviously increased, the pressure relief device is arranged between the inerting fluid pipeline of the central wing fuel tank and the ventilation pipeline, the pressure relief device is opened when the pressure difference is higher than a preset threshold value, the inerting fluid bypasses the ventilation pipeline, the pressure of the central wing fuel tank cannot be continuously increased, the overpressure of the central wing fuel tank can be prevented, and the damage to the structure of the fuel tank is prevented.
According to the invention, only the pressure release pipeline and the pressure release device are additionally arranged between the inerting fluid pipeline and the ventilation pipeline of the central wing fuel tank, namely, mechanical overpressure protection is adopted, and the mechanical overpressure protection does not need to increase electronic devices, does not change the architecture of a control system, and avoids increasing the number of electrical equipment of the inerting system and the complexity of control software; after inerting fluid is fed into the ventilation pipeline, a pressurizing source in the central wing fuel tank in a fuel overflow scene is eliminated, and the method is suitable for overpressure protection design of the central wing fuel tank; an aircraft inerting system design for preventing overpressure in fuel tanks is provided for laying out center wing fuel tanks with inerting systems in a domestic aircraft for three fuel tanks (i.e., including a center wing fuel tank and outer wing main fuel tanks on both sides), thereby improving aircraft safety.
In some embodiments, as shown in fig. 1-2, the pressure relief device 13 is located entirely within the center wing fuel tank 1. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the wing wall structure is not required to be provided with an opening, and the processing difficulty of the structure is not increased.
In some embodiments, as shown in fig. 1-3, the vent lines include a center wing fuel tank vent line 4 for communicating the center wing fuel tank 1 to the vent fuel tank 3, and an outer wing main fuel tank vent line 5 for communicating the outer wing main fuel tank 2 to the vent fuel tank 3. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: by appropriate vent line design, either the center wing tank or the outer wing main tank can be effectively connected to the vent tank.
In some embodiments, as shown in FIG. 1, a pressure relief line 12 is used to communicate the inerting fluid line 11 to the center wing tank vent line 4. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: by bypassing the inerting fluid to the center wing tank vent line, center wing tank overpressure is avoided.
In some embodiments, as shown in FIG. 2, a pressure relief line 12 is used to communicate the inerting fluid line 11 to the main outer wing tank vent line 5. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: by bypassing the inerting fluid to the outer wing main tank vent line, center wing tank overpressure is avoided.
In some embodiments, as shown in FIG. 3, the aircraft fuel tank inerting system further includes a second pressure relief device 14, the second pressure relief device 14 being mounted on the inerting fluid line 11 and located outside the front spar 6 of the outer fuselage section of the center wing fuel tank 1. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the second pressure release device with proper design can discharge the released inerting fluid to the atmosphere, so that the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be better eliminated, and the overpressure of the central wing fuel tank can be better avoided.
In some embodiments, as shown in fig. 1-2, the predetermined threshold value of the differential pressure across the pressure relief device 13 is 4-6 PSI. That is, when the pressure differential across the pressure relief device 13 (typically the pressure within the inerting fluid line 11 is higher than the pressure within the vent line, thereby creating a pressure differential) is above some predetermined threshold in the range of 4-6 PSI, the pressure relief device 13 opens to bypass the inerting fluid to the vent line. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be better eliminated by properly designed pressure relief device differential pressure preset threshold value, and the overpressure of the central wing fuel tank can be better avoided.
More preferably, the predetermined threshold value of the differential pressure across the pressure relief device 13 is 4.5 to 5.5PSI. More preferably, the predetermined threshold value of the differential pressure across the pressure relief device 13 is 5PSI.
In some embodiments, as shown in fig. 1-3, the inerting fluid is a nitrogen-rich gas. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: the aircraft fuel tank inerting function can be better realized through proper inerting fluid.
In some embodiments, as shown in fig. 1-2, the pressure relief device 13 is a pressure relief valve. According to the technical scheme, the aircraft fuel tank inerting system has the following beneficial technical effects: through a proper pressure release device, the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be better eliminated, and the overpressure out of the central wing fuel tank can be better avoided.
According to an embodiment of the invention, an aircraft comprises an aircraft fuel tank inerting system as in any of the above aspects. According to the technical scheme, the aircraft provided by the invention has the following beneficial technical effects: the overpressure potential safety hazard of the central wing fuel tank with the inerting system can be eliminated, and the overpressure of the central wing fuel tank is avoided.
While the invention has been described in terms of specific embodiments, those skilled in the art will recognize that the invention is not limited thereto, but that many modifications can be made by those skilled in the art without departing from the scope of the invention.
Claims (10)
1. An aircraft fuel tank inerting system for an aircraft comprising a center wing fuel tank and outer wing main fuel tanks on both sides, the aircraft further comprising a vent tank outboard of the outer wing main fuel tanks, and a vent line for communicating the center wing fuel tank or the outer wing main fuel tanks to the vent tank, characterized in that the aircraft fuel tank inerting system comprises an inerting fluid source, an inerting fluid line, a pressure relief line, and a pressure relief device;
wherein the inerting fluid line is for supplying inerting fluid from the inerting fluid source to the center wing fuel tank, the relief line is for communicating the inerting fluid line to the vent line, the relief device is located in the relief line and is for opening when a differential pressure across the relief device is above a predetermined threshold to bypass inerting fluid to the vent line.
2. An aircraft fuel tank inerting system according to claim 1, wherein the pressure relief device is located entirely within the center wing fuel tank.
3. An aircraft fuel tank inerting system according to claim 1, wherein the vent line comprises a center wing fuel tank vent line for communicating the center wing fuel tank to the vent fuel tank, and an outer wing main fuel tank vent line for communicating the outer wing main fuel tank to the vent fuel tank.
4. An aircraft fuel tank inerting system according to claim 3, wherein the pressure relief line is adapted to communicate the inerting fluid line to the center wing fuel tank vent line.
5. An aircraft fuel tank inerting system according to claim 3, wherein the pressure relief line is adapted to communicate the inerting fluid line to the main outer wing fuel tank vent line.
6. The aircraft fuel tank inerting system of claim 1, further comprising a second pressure relief device mounted on the inerting fluid line and located outside the front spar of the center wing fuel tank fuselage outer section.
7. An aircraft fuel tank inerting system according to claim 1, wherein the predetermined threshold is 4 to 6PSI.
8. An aircraft fuel tank inerting system according to claim 1, wherein the inerting fluid is a nitrogen-rich gas.
9. The aircraft fuel tank inerting system of claim 1, wherein the pressure relief device is a pressure relief valve.
10. An aircraft comprising an aircraft fuel tank inerting system as claimed in any of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310814485.7A CN116654270A (en) | 2023-07-04 | 2023-07-04 | Aircraft fuel tank inerting system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310814485.7A CN116654270A (en) | 2023-07-04 | 2023-07-04 | Aircraft fuel tank inerting system and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116654270A true CN116654270A (en) | 2023-08-29 |
Family
ID=87713874
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310814485.7A Pending CN116654270A (en) | 2023-07-04 | 2023-07-04 | Aircraft fuel tank inerting system and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116654270A (en) |
-
2023
- 2023-07-04 CN CN202310814485.7A patent/CN116654270A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7648103B2 (en) | Aircraft fuel tanks, systems and methods for increasing an aircraft's on-board fuel capacity | |
| EP3412577B1 (en) | Fuel system | |
| US5360034A (en) | Dual fuel tank system | |
| US8876055B2 (en) | Aircraft refuelling system | |
| EP1591359B1 (en) | Aircraft and fuel venting system therefor | |
| EP2045111B1 (en) | Fuel tank | |
| US8777165B2 (en) | Aircraft fuel system | |
| CN108473212B (en) | Catalytic inerting system for an aircraft with a plurality of fuel tanks | |
| EP2942226A1 (en) | Aircraft battery exhaust system | |
| CN103057714A (en) | Auxiliary fuel system | |
| EP1512433B1 (en) | Oxygen supply and distribution system for a passenger aircraft | |
| US9409651B2 (en) | Aircraft aerial refuelling system | |
| CS197306B2 (en) | Connection for filling the hollow system fitted with filling opening | |
| CN116654270A (en) | Aircraft fuel tank inerting system and aircraft | |
| US20110056974A1 (en) | Aircraft fuel tank system | |
| JP2014094663A (en) | Nitrogen-enriched gas supply system and aircraft | |
| EP2969767B1 (en) | Aircraft fuel tank inerting systems | |
| US20110056973A1 (en) | Vent pipe for an aircraft fuel system vent tank | |
| US2509978A (en) | Underwing refueling system | |
| GB2225817A (en) | Lubricating a turbojet engine | |
| EP0934449B1 (en) | Aircraft fuel transfer pump with auxiliary fuel line scavenge pump | |
| CN212074446U (en) | Large-scale unmanned aerial vehicle high reliability fuel oil system | |
| US9399395B2 (en) | Tank provided with an over-pressure valve | |
| US11118540B2 (en) | Vented tank systems and components | |
| DE102011122313A1 (en) | Coolant surge tank system, has surge tank with input terminal for connection with balancing circuit, where tank and container are separated from each other and independently positionable relative to each other |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |