CN111846257A - Aircraft fuel tank inerting system and fuel tank explosion-proof method - Google Patents
Aircraft fuel tank inerting system and fuel tank explosion-proof method Download PDFInfo
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- CN111846257A CN111846257A CN202010734806.9A CN202010734806A CN111846257A CN 111846257 A CN111846257 A CN 111846257A CN 202010734806 A CN202010734806 A CN 202010734806A CN 111846257 A CN111846257 A CN 111846257A
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- temperature sensor
- fuel tank
- tank
- heat exchanger
- pipeline
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- 239000002828 fuel tank Substances 0.000 title claims abstract description 54
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000010438 heat treatment Methods 0.000 claims abstract description 27
- 239000000446 fuel Substances 0.000 claims abstract description 20
- 239000000295 fuel oil Substances 0.000 claims abstract description 12
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 52
- 239000003921 oil Substances 0.000 claims description 18
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 16
- 239000001301 oxygen Substances 0.000 claims description 16
- 229910052760 oxygen Inorganic materials 0.000 claims description 16
- 239000007789 gas Substances 0.000 claims description 15
- 239000000523 sample Substances 0.000 claims description 14
- 239000004215 Carbon black (E152) Substances 0.000 claims description 11
- 229930195733 hydrocarbon Natural products 0.000 claims description 11
- 150000002430 hydrocarbons Chemical class 0.000 claims description 11
- 239000007791 liquid phase Substances 0.000 claims description 8
- 239000012071 phase Substances 0.000 claims description 5
- 238000002485 combustion reaction Methods 0.000 abstract description 3
- 238000003912 environmental pollution Methods 0.000 abstract description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 12
- 238000005516 engineering process Methods 0.000 description 9
- 239000012528 membrane Substances 0.000 description 8
- 238000004880 explosion Methods 0.000 description 7
- 229910052757 nitrogen Inorganic materials 0.000 description 6
- 238000000926 separation method Methods 0.000 description 5
- 239000011261 inert gas Substances 0.000 description 3
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000012510 hollow fiber Substances 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 230000035899 viability Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- RJCQBQGAPKAMLL-UHFFFAOYSA-N bromotrifluoromethane Chemical compound FC(F)(F)Br RJCQBQGAPKAMLL-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 239000012535 impurity 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
- -1 moisture Substances 0.000 description 1
- 239000002808 molecular sieve Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- URGAHOPLAPQHLN-UHFFFAOYSA-N sodium aluminosilicate Chemical compound [Na+].[Al+3].[O-][Si]([O-])=O.[O-][Si]([O-])=O URGAHOPLAPQHLN-UHFFFAOYSA-N 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
The invention discloses an aircraft fuel tank inerting system and a fuel tank explosion-proof method. The explosion-proof method of the fuel tank comprises the step of heating the fuel so that the fuel vapor concentration in the fuel tank is higher than a flammable threshold value. In addition, the temperature of the fuel oil in the fuel oil tank is higher, the preheating power of the fuel oil before entering an engine for combustion can be reduced, and the method has the advantages of short inerting time, no environmental pollution, simple and controllable system and the like.
Description
Technical Field
The invention relates to the technical field of aviation systems, in particular to an aircraft fuel tank inerting system and a fuel tank explosion-proof method.
Background
Aircraft fuel systems are one of the main causes of aircraft crashes due to fires or explosions. The fire and explosion protection capability of an aircraft fuel system is directly related to the viability and the vulnerability of the aircraft, and also related to the utilization rate, the cost and the personnel safety of the aircraft. If the fuel tank has explosion-proof capability, even if a fire disaster is caused by a medium bullet or other reasons, the aircraft cannot be damaged or killed, and the aircraft can be continuously used after being repaired, so that the utilization rate and the viability of the aircraft are correspondingly improved, and the vulnerability of the aircraft is reduced. The adoption of the explosion-proof technology of the fuel tank of the airplane can also increase the life-saving time, so that the airplane has enough time to return under the condition that the fuel tank fails. In addition, the aircraft can also be protected in emergency situations.
The fuel steam, oxygen and fire source are called as three factors of fire, and the fuel is very easy to ignite fire to cause catastrophic explosion due to special risks or failure states such as thunder, static spark, friction spark and the like in a fuel tank in the process of storage or transportation, thereby causing serious consequences. Research shows that the temperature of the mixed gas in the gas phase space of the upper part of the fuel tank and the mutual proportional relation of the fuel vapor concentration, the inert gas concentration and the oxygen concentration determine whether the fuel tank is exposed to a combustible state or not.
The common aircraft fuel tank inerting technology principle is that inert gases such as nitrogen and the like are filled in a fuel tank to enable the oxygen concentration in the fuel tank to be lower than a certain value, and a nonflammable environment is generated in the fuel tank, so that the fuel tank is prevented from exploding due to an ignition source, such as a liquid nitrogen inerting technology, a Halon 1301 inerting technology, a molecular sieve technology, a membrane separation technology and the like. The On-Board Inert Gas Generator System (OBIGGS) technology for preparing nitrogen-rich Gas by using hollow fiber membrane is the most economical and practical technology for suppressing the combustion and explosion of the airplane fuel tank at present. The OBIGGS is characterized in that bleed air from an engine or an environmental control system is subjected to temperature regulation, pressure regulation and removal of pollutants such as ozone, moisture, impurities and the like, then the bleed air is introduced into an air separation device formed by a hollow fiber membrane and separated into oxygen-rich gas and nitrogen-rich gas, the oxygen-rich gas is discharged out of the machine, and the nitrogen-rich gas is filled into a fuel tank for washing or flushing according to different flow modes.
However, the OBIGGS technology still has many problems, such as that the compensation loss of an airplane is large due to low efficiency of the separation membrane, the required pressure of the inlet of the separation membrane is high, the separation membrane cannot be used in many airplane models (such as a helicopter), the thin membrane wire and the permeation pore diameter are gradually blocked, the attenuation of the membrane performance is serious due to ozone in an air source, the fuel vapor leaks to pollute the environment when the fuel tank is filled with the nitrogen-rich gas, and the like.
The person skilled in the art therefore endeavors to develop an aircraft fuel tank inerting system and a fuel tank explosion protection method which have a wide range of applications, good durability, short inerting times and are environmentally friendly.
Disclosure of Invention
In view of the above-mentioned defects in the prior art, the technical problem to be solved by the present invention is to provide an aircraft fuel tank inerting system and a fuel tank explosion-proof method which have the advantages of wide application range, good durability, short inerting time and environmental friendliness.
In order to achieve the above object, the present invention provides an aircraft fuel tank inerting system comprising a heat exchanger placed inside the fuel tank, said heat exchanger being connected to a heating system.
Preferably, the heating system comprises a water pump and a water tank which are connected through pipelines, an outlet pipeline of the water tank is connected with the water pump, the water pump is connected with the heat exchanger through a pipeline, and the other end of the heat exchanger is connected to an inlet of the water tank through a pipeline; a heater is installed in the water tank.
Preferably, the heater and the water pump are both connected to a controller; a first temperature sensor and a first flow sensor are arranged on a pipeline between the water tank and the water pump; the liquid phase space of the water tank is connected with a third temperature sensor through a probe rod; a second temperature sensor is arranged on a pipeline between the heat exchanger and the inlet of the water tank;
the first temperature sensor, the first flow sensor, the third temperature sensor and the second temperature sensor are connected in parallel through cables and then connected with the controller.
Preferably, the heating system comprises an engine bleed air pipeline, the engine bleed air pipeline is connected with a fan through a pipeline, the downstream of the fan is connected with the heat exchanger, and an outlet pipeline of the heat exchanger is communicated to the outside of the machine.
Preferably, the fan is connected to the controller; a seventh temperature sensor and a second flow sensor are arranged on a pipeline between the fan and the heat exchanger; and the seventh temperature sensor and the second flow sensor are connected in parallel through a cable and then are connected with the controller.
Preferably, the upper gas phase space of the oil tank is connected with a hydrocarbon concentration sensor, an oxygen concentration sensor and a fourth temperature sensor through a probe rod, and the hydrocarbon concentration sensor, the oxygen concentration sensor and the fourth temperature sensor are connected with the controller after being connected in parallel through cables.
Preferably, the liquid phase space at the lower part of the oil tank is connected with a fifth temperature sensor and a sixth temperature sensor through a probe rod, and the fifth temperature sensor and the sixth temperature sensor are connected with the controller after being connected in parallel through cables.
An explosion-proof method for fuel tank includes heating fuel to make the vapor concentration of fuel in fuel tank higher than combustible threshold value.
Preferably, the fuel oil is heated by a heating system, and the heating system is connected with a heat exchanger arranged in the oil tank.
Preferably, the heating system is a water circulation heating system or a heating system connected to an engine bleed air duct of the aircraft.
The invention has the beneficial effects that: in addition, the temperature of the fuel oil in the fuel oil tank is higher, the preheating power of the fuel oil before entering an engine for combustion can be reduced, and the method has the advantages of short inerting time, no environmental pollution, simple and controllable system and the like.
Drawings
Fig. 1 is a schematic structural diagram of embodiment 1 of the present invention.
Fig. 2 is a schematic structural diagram of embodiment 2 of the present invention.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and examples, wherein the terms "upper", "lower", "left", "right", "inner", "outer", and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings, which is for convenience and simplicity of description, and does not indicate or imply that the referenced devices or components must be in a particular orientation, constructed and operated in a particular manner, and thus should not be construed as limiting the present invention. The terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Example 1
As shown in fig. 1, an aircraft fuel tank inerting system comprises a heat exchanger 6 placed inside a fuel tank 9, the heat exchanger 6 being connected to a heating system. In this embodiment, heating system includes water pump 5, water tank 1 of pipe connection, and 1 export pipe connection water pump 5 of water tank, 5 pipe connection heat exchangers 6 of water pump, 6 other end pipe connections of heat exchanger are to 1 entry of water tank, install heater 2 in the water tank 1.
The heater 2 and the water pump 5 are both connected to the controller 15, the first temperature sensor 3 and the first flow sensor 4 are installed on the pipeline between the water tank 1 and the water pump 5, the liquid phase space of the water tank 1 is connected with the third temperature sensor 8 through the probe rod, and the second temperature sensor 7 is installed on the pipeline between the heat exchanger 6 and the inlet of the water tank 1.
The upper gas phase space of the oil tank 9 is connected with a hydrocarbon concentration sensor 10, an oxygen concentration sensor 11 and a fourth temperature sensor 12 through a probe. The liquid phase space at the lower part of the oil tank 9 is connected with a fifth temperature sensor 13 and a sixth temperature sensor 14 through a probe rod. The accuracy that the liquid phase space of 9 lower parts of oil tank set up 2 temperature sensor multiplicable detections, simultaneously, detect different regions in the oil tank 9, improve explosion-proof security. In the present embodiment, the first temperature sensor 3, the first flow sensor 4, the third temperature sensor 8, the second temperature sensor 7, the hydrocarbon concentration sensor 10, the oxygen concentration sensor 11, the fourth temperature sensor 12, the fifth temperature sensor 13, and the sixth temperature sensor 14 are connected in parallel by cables and then connected to the controller 15.
When the aircraft fuel tank inerting system in the embodiment is used, the hydrocarbon concentration sensor 10, the oxygen concentration sensor 11 and the fourth temperature sensor 12 respectively detect the hydrocarbon concentration, the oxygen concentration and the temperature of mixed gas at the upper part of the fuel tank 9 through the probe rod, the fifth temperature sensor 13 and the sixth temperature sensor 14 respectively detect the temperature of fuel oil in the fuel tank 9 through the probe rod, when the temperature is within a combustible limit range, the water pump 5 starts to work, and when the temperature is outside the combustible limit range, the water pump 5 stops working. Specifically, when the water pump works, hot water pumped by the water pump in the water tank 1 sequentially flows through the first temperature sensor 3 and the first flow sensor 4, then enters the heat exchanger 6 to heat fuel in the oil tank 9, and then flows back to the water tank 1 through the second temperature sensor 7 to complete hot water circulation, and after the fuel in the oil tank 9 is heated, the concentration of fuel vapor in a gas phase space at the upper part of the oil tank 9 is increased and is outside a combustible limit, so that the purposes of inerting and explosion prevention are achieved.
In addition, the water in the water tank 1 is heated by the electric heater 2, the third temperature sensor 8 can detect the temperature of the liquid phase space at the lower part of the water tank 1 through the probe rod and transmit a signal to the controller 15, when the temperature is less than a set value, the controller 15 outputs a control signal to connect the electric heater 2, and the heating system starts to work; when the temperature is higher than the set value, the electric heater 2 does not work, and when the temperature is started, the electric heater is commanded to stop, so that the water in the water tank 1 can be started to heat the oil tank 9 at any time.
Example 2
As shown in fig. 2, the embodiment 2 has substantially the same structure as the embodiment 1, except that the heating system in this embodiment includes an engine bleed air duct, the engine bleed air duct is connected to a fan 16 through a duct, a heat exchanger 6 is connected downstream of the fan 16, and an outlet duct of the heat exchanger 6 is communicated to the outside of the machine. The fan 16 is connected to the controller 15, a seventh temperature sensor 17 and a second flow sensor 18 are mounted on a pipeline between the fan 16 and the heat exchanger 6, and the seventh temperature sensor 17, the second flow sensor 18, the hydrocarbon concentration sensor 10, the oxygen concentration sensor 11, the fourth temperature sensor 12, the fifth temperature sensor 13 and the sixth temperature sensor 14 are connected with the controller 15 after being connected in parallel through cables.
When the aircraft fuel tank inerting system in the embodiment is used, engine tail gas flows through the engine bleed air pipeline under the suction action of the fan 16, flows through the seventh temperature sensor 17 and the second flow sensor 18 in sequence, enters the heat exchanger 6 to heat fuel oil in the fuel tank 9, and the cooled waste gas is discharged out of the aircraft. The hydrocarbon concentration sensor 10, the oxygen concentration sensor 11 and the fourth temperature sensor 12 respectively detect the hydrocarbon concentration, the oxygen concentration and the temperature of the mixed gas at the upper part of the oil tank 9 through a probe rod, the fifth temperature sensor 13 and the sixth temperature sensor 14 respectively detect the temperature of fuel oil in the oil tank 9 through the probe rod, when the temperature is within a combustible limit range, the controller 15 controls the fan 16 to start working, and when the temperature is outside the combustible limit range, the fan 16 stops working.
An explosion-proof method for fuel tank includes heating fuel to make the vapor concentration of fuel in fuel tank higher than combustible threshold value. In particular, the fuel oil can be heated by a heating system which is connected with a heat exchanger 6 arranged in the oil tank. The heating system may be a water circulation heating system as in embodiment 1 of the invention or a heating system connected to the engine bleed air ducts of the aircraft as in embodiment 2.
The explosion-proof method of the fuel tank of the invention ensures that the concentration of fuel vapor is higher than a certain value, so that the fuel is outside the upper limit of the flammable limit, and the fuel is in an incombustible state, thereby achieving the aim of explosion prevention of the fuel tank.
The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (10)
1. An aircraft fuel tank inerting system, characterized by: the device comprises a heat exchanger (6) arranged in an oil tank (9), wherein the heat exchanger (6) is connected with a heating system.
2. An aircraft fuel tank inerting system as defined in claim 1, wherein: the heating system comprises a water pump (5) and a water tank (1) which are connected through pipelines, an outlet of the water tank (1) is connected with the water pump (5) through a pipeline, the water pump (5) is connected with the heat exchanger (6) through a pipeline, and the other end of the heat exchanger (6) is connected to an inlet of the water tank (1) through a pipeline; a heater (2) is installed in the water tank (1).
3. An aircraft fuel tank inerting system as defined in claim 2, wherein: the heater (2) and the water pump (5) are both connected to a controller (15); a first temperature sensor (3) and a first flow sensor (4) are arranged on a pipeline between the water tank (1) and the water pump (5); the liquid phase space of the water tank (1) is connected with a third temperature sensor (8) through a probe rod; a second temperature sensor (7) is arranged on a pipeline between the heat exchanger (6) and the inlet of the water tank (1);
the first temperature sensor (3), the first flow sensor (4), the third temperature sensor (8) and the second temperature sensor (7) are connected with the controller (15) in parallel through cables.
4. An aircraft fuel tank inerting system as defined in claim 1, wherein: the heating system comprises an engine bleed air pipeline, the engine bleed air pipeline is connected with a fan (16) through a pipeline, the downstream of the fan (16) is connected with the heat exchanger (6), and an outlet pipeline of the heat exchanger (6) is communicated to the outside of the machine.
5. An aircraft fuel tank inerting system as claimed in claim 4, wherein: the fan (16) is connected to a controller (15); a seventh temperature sensor (17) and a second flow sensor (18) are arranged on a pipeline between the fan (16) and the heat exchanger (6); the seventh temperature sensor (17) and the second flow sensor (18) are connected in parallel through a cable and then connected with the controller (15).
6. An aircraft fuel tank inerting system as defined in claim 1, wherein: the gas phase space on the upper part of the oil tank (9) is connected with a hydrocarbon concentration sensor (10), an oxygen concentration sensor (11) and a fourth temperature sensor (12) through a probe rod, and the hydrocarbon concentration sensor (10), the oxygen concentration sensor (11) and the fourth temperature sensor (12) are connected with a controller (15) after being connected in parallel through cables.
7. An aircraft fuel tank inerting system as defined in claim 1, wherein: the liquid phase space at the lower part of the oil tank (9) is connected with a fifth temperature sensor (13) and a sixth temperature sensor (14) through a probe rod, and the fifth temperature sensor (13) and the sixth temperature sensor (14) are connected with a controller (15) after being connected in parallel through cables.
8. An explosion-proof method for a fuel tank is characterized in that: comprises the step of heating the fuel so that the fuel vapor concentration in the fuel tank is higher than a flammable threshold.
9. A fuel tank explosion-proof method as set forth in claim 8, wherein: the fuel oil is heated by a heating system which is connected with a heat exchanger (6) arranged in the oil tank.
10. A fuel tank explosion-proof method as set forth in claim 9, wherein: the heating system is a water circulation heating system or a heating system connected with an engine bleed air pipeline of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734806.9A CN111846257B (en) | 2020-07-27 | 2020-07-27 | Aircraft fuel tank inerting system and fuel tank explosion-proof method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734806.9A CN111846257B (en) | 2020-07-27 | 2020-07-27 | Aircraft fuel tank inerting system and fuel tank explosion-proof method |
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| Publication Number | Publication Date |
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| CN111846257A true CN111846257A (en) | 2020-10-30 |
| CN111846257B CN111846257B (en) | 2022-03-11 |
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| CN114180079A (en) * | 2021-12-17 | 2022-03-15 | 南京航空航天大学 | Onboard fuel tank inerting method based on fuel oil comprehensive thermal management |
| CN114633886A (en) * | 2022-04-13 | 2022-06-17 | 重庆交通大学 | Liquid medicine sprays power glider with environmental protection performance |
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| CN114180079A (en) * | 2021-12-17 | 2022-03-15 | 南京航空航天大学 | Onboard fuel tank inerting method based on fuel oil comprehensive thermal management |
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| CN111846257B (en) | 2022-03-11 |
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