CN111071468A - Energy recovery type fuel tank inerting system configuration and working method thereof - Google Patents
Energy recovery type fuel tank inerting system configuration and working method thereof Download PDFInfo
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- CN111071468A CN111071468A CN202010010877.4A CN202010010877A CN111071468A CN 111071468 A CN111071468 A CN 111071468A CN 202010010877 A CN202010010877 A CN 202010010877A CN 111071468 A CN111071468 A CN 111071468A
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- 239000002828 fuel tank Substances 0.000 title claims abstract description 28
- 238000011084 recovery Methods 0.000 title claims abstract description 15
- 238000000034 method Methods 0.000 title claims description 9
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 70
- 239000007789 gas Substances 0.000 claims abstract description 70
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 55
- 239000001301 oxygen Substances 0.000 claims abstract description 55
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 55
- 238000000926 separation method Methods 0.000 claims abstract description 36
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 35
- 239000012528 membrane Substances 0.000 claims abstract description 17
- 239000012510 hollow fiber Substances 0.000 claims abstract description 9
- 230000001105 regulatory effect Effects 0.000 claims description 58
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 claims description 34
- 239000004215 Carbon black (E152) Substances 0.000 claims description 10
- 229930195733 hydrocarbon Natural products 0.000 claims description 10
- 150000002430 hydrocarbons Chemical class 0.000 claims description 10
- 230000033228 biological regulation Effects 0.000 claims description 9
- 230000009471 action Effects 0.000 claims description 6
- 239000000523 sample Substances 0.000 claims description 5
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000004880 explosion Methods 0.000 description 4
- 239000002245 particle Substances 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- 238000011010 flushing procedure Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- -1 moisture Substances 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 238000005406 washing Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000009429 distress Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
- B01D53/22—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols by diffusion
- B01D53/228—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols by diffusion characterised by specific membranes
-
- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D53/00—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols
- B01D53/22—Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases, aerosols by diffusion
- B01D2053/221—Devices
-
- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0651—Environmental Control Systems comprising filters, e.g. dust filters
-
- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0662—Environmental Control Systems with humidity control
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- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0681—Environmental Control Systems with oxygen control
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Separation Using Semi-Permeable Membranes (AREA)
Abstract
The invention discloses an energy recovery type fuel tank inerting system configuration, which belongs to the technical field of aviation systems. The nitrogen-rich gas flowing out of the hollow fiber membrane is firstly introduced into the turboexpander, part of energy is recycled, meanwhile, the temperature of the nitrogen-rich gas is reduced, the flammability of an oil tank is favorably reduced, in addition, the recycled energy is utilized to drive a fan to improve the flow rate of the oxygen-rich side, the internal and external pressure difference of the separation membrane is increased, and the separation efficiency is improved.
Description
Technical Field
The invention belongs to the technical field of aviation systems, relates to an explosion-proof system of an aircraft fuel tank, and particularly relates to an energy recovery type fuel tank inerting system configuration.
Background
In recent 50 years, 18 fuel tank explosion accidents of transport-type airplanes occur in the world, and 542 people are in distress, so that the major threat of civil aviation safety is achieved. In 1996, the combustible vapor in the TWA800 center wing fuel tank of the Boeing 747 aircraft is ignited to cause explosion, and the whole aircraft personnel is killed, so that the U.S. Federal aviation administration is prompted to issue a series of amendments, consultation notices and airworthiness regulations, and effective measures are forcibly required to be taken to reduce the ignition source and the concentration of the combustible vapor so as to reduce the flammability of the fuel tank of the transportation aircraft and increase the safety of the fuel tank. Similar aviation regulations are also established by civil aviation administration in China.
The federal aviation administration and the state department of transportation safety of the united states both consider the use of fuel tank inerting technology as a viable measure to reduce the risk of fuel tank explosions. At present, the airborne nitrogen inerting technology for preparing nitrogen-rich gas by using hollow fiber membrane is the most economic and practical aircraft fuel tank explosion suppression technology at present, and is applied to various types of airplanes of Boeing and air passengers and Chinese national models. The principle is that air from an engine is introduced into an air separation device formed by a hollow fiber membrane to be separated into oxygen-rich gas and nitrogen-rich gas after temperature regulation, pressure regulation and removal of pollutants such as ozone, moisture, impurities and the like, the oxygen-rich gas is sent to a cabin for being breathed by drivers and passengers, and the nitrogen-rich gas is filled into a fuel tank for washing or flushing according to different flow modes. However, in view of the current application situation at home and abroad, the airborne nitrogen inerting technology has the problem that the efficiency of a separation membrane is low, so that the compensation loss of the airplane is large.
Disclosure of Invention
The invention discloses an energy recovery type fuel tank inerting system configuration and a working method thereof, aiming at the problems in the prior art, the system configuration of the invention is characterized in that nitrogen-rich gas flowing out of a hollow fiber membrane is introduced into a turbine expander, part of energy is recovered, and the temperature of the nitrogen-rich gas is reduced, thus being beneficial to reducing the flammability of a fuel tank, in addition, the recovered energy is utilized to drive a fan to improve the flow rate of an oxygen-rich side, increase the pressure difference between the inside and the outside of a separation membrane and improve the separation efficiency.
The invention is realized by the following steps:
an energy recovery type fuel tank inerting system configuration comprises a first fan, wherein an inlet of the first fan is communicated with an engine for air entrainment, and an outlet of the first fan is sequentially connected with a filter, a dryer, a heater, a humidity regulator, an ozone converter and a first control valve; the outlet of the first control valve is respectively connected with a first electric pressure regulating valve and a first manual pressure regulating valve; the outlets of the first electric pressure regulating valve and the first manual pressure regulating valve are connected with one end of a first pressure sensor; the other end of the first pressure sensor is sequentially connected with a first temperature sensor, a first flow sensor, a humidity sensor, an ozone concentration sensor, a granularity detector and an air separation module; the air separation module comprises a gas inlet, a nitrogen-rich gas outlet and an oxygen-rich gas outlet;
the gas inlet of the air separation module is connected with the granularity detector; the nitrogen-rich gas outlet of the air separation module is respectively connected with a second electric pressure regulating valve and a second manual pressure regulating valve, the outlets of the second electric pressure regulating valve and the second manual pressure regulating valve are respectively connected with one end of a second flow sensor, the other end of the second flow sensor is sequentially connected with a first oxygen concentration sensor, a second temperature sensor, a second pressure sensor, a turbine expander, a third temperature sensor, a third pressure sensor, a first flame arrester and an oil tank, the first flame arrester is connected with the gas inlet of the oil tank, and the gas outlet of the oil tank is connected with the second flame arrester;
an oxygen-enriched gas outlet of the air separation module is sequentially connected with a third oxygen concentration sensor, a fifth temperature sensor, a fourth pressure sensor and a second fan, and the other end of the second fan is connected with a turbo expander; and the oxygen-enriched gas of the second fan is sent to the cabin for breathing.
Further, an oil tank in the system configuration is respectively provided with a hydrocarbon concentration sensor, a second oxygen concentration sensor and a fourth temperature sensor, and the hydrocarbon concentration sensor, the second oxygen concentration sensor and the fourth temperature sensor are respectively connected with the oil tank through probe rods.
Further, the system configuration is controlled by an automatic controller, and particularly, the automatic controller comprises a current input end and a current output end.
The current input end of the automatic controller is connected in parallel with a first pressure sensor, a first temperature sensor, a first flow sensor, a humidity sensor, an ozone concentration sensor, a granularity detector, a second flow sensor, a first oxygen concentration sensor, a second temperature sensor, a second pressure sensor, a third temperature sensor, a third pressure sensor, a hydrocarbon concentration sensor, a second oxygen concentration sensor, a fourth temperature sensor, a third oxygen concentration sensor, a fifth temperature sensor and a fourth pressure sensor through cables.
Furthermore, the current output end of the automatic controller is connected in parallel with the first fan, the heater, the humidity regulator, the ozone converter, the first control valve, the first electric pressure regulating valve and the second electric pressure regulating valve through cables.
The invention also discloses a working method of the energy recovery type fuel tank inerting system configuration, which is characterized by comprising the following steps:
when the oil tank is not in an inerting state, an onboard nitrogen inerting system for preparing nitrogen-rich gas by a hollow fiber membrane is started, and at the moment, a first fan, a heater, a humidity regulator, an ozone converter, a first control valve, a first electric pressure regulating valve and a second electric pressure regulating valve are opened;
engine bleed air enters a system under the suction action of a first fan, is filtered and dried in a filter and a dryer, is subjected to temperature and humidity adjustment in a heater and a humidity adjuster respectively, is removed in an ozone converter, flows through a first control valve, and is subjected to pressure adjustment in a first electric pressure adjusting valve or a first manual pressure adjusting valve;
the automatic control system comprises a first pressure sensor, a first temperature sensor, a first flow sensor, a humidity sensor, an ozone concentration sensor and a granularity detector, wherein the first pressure sensor, the first temperature sensor, the first flow sensor, the humidity sensor, the ozone concentration sensor and the granularity detector are used for respectively measuring a series of parameters of pressure, temperature, flow, humidity, ozone concentration and granularity of gas in front of a separation membrane and transmitting signals to an automatic controller, and the automatic controller is used for respectively outputting feedback signals to a heater, a humidity regulator, an ozone converter, a first control valve and a first electric pressure regulating valve;
the regulated gas enters an air separation module to generate nitrogen-rich gas and oxygen-rich gas; the nitrogen-rich gas is subjected to pressure regulation in a second electric pressure regulating valve or a second manual pressure regulating valve, and then flows through a second flow sensor, a first oxygen concentration sensor, a second temperature sensor and a second pressure sensor in sequence, and then enters a turbine expander for expansion, temperature reduction and pressure reduction, the turbine expander drives a second fan blade to rotate through a shaft during expansion, the nitrogen-rich gas subjected to temperature reduction and pressure reduction flows into an oil tank for flushing and inerting after flowing through a third temperature sensor, a third pressure sensor and a first flame arrester in sequence, and redundant gas in the oil tank flows through the second flame arrester and then is discharged out of the machine;
oxygen-enriched gas generated by the air separation module flows through the third oxygen concentration sensor, the fifth temperature sensor, the fourth pressure sensor and the second fan in sequence under the suction action of the second fan and then is sent to the cabin for the passengers to breathe.
The beneficial effects of the invention and the prior art are as follows:
the nitrogen-rich gas is firstly introduced into the turbine expander, so that the temperature of the nitrogen-rich gas is reduced, and the flammability of an oil tank is favorably reduced; the turbine expander drives the fan to accelerate the flow rate of the oxygen-enriched side, the internal and external pressure difference of the separation membrane is increased, and the separation efficiency is improved;
the working method of the system configuration of the invention comprises the following steps: the method comprises the steps of introducing air from an engine, adjusting temperature and pressure, removing pollutants such as ozone, moisture, impurities and the like, introducing the air into an air separation device formed by a hollow fiber membrane, separating the air into oxygen-rich gas and nitrogen-rich gas, sending the oxygen-rich gas to a cabin for the breathing of drivers and passengers, and filling the nitrogen-rich gas into a fuel tank for washing or flushing according to different flow modes. The nitrogen-rich gas flowing out of the hollow fiber membrane is firstly introduced into the turboexpander, part of energy is recycled, meanwhile, the temperature of the nitrogen-rich gas is reduced, the flammability of an oil tank is favorably reduced, in addition, the recycled energy is utilized to drive a fan to improve the flow rate of the oxygen-rich side, the internal and external pressure difference of the separation membrane is increased, and the separation efficiency is improved.
Drawings
FIG. 1 is a schematic view of an energy recovery fuel tank inerting system configuration of the present invention;
wherein 1-a first fan, 2-a filter, 3-a dryer, 4-a heater, 5-a humidifier, 6-an ozone converter, 7-a first control valve, 8-a first electric pressure regulating valve, 9-a first manual pressure regulating valve, 10-a first pressure sensor, 11-a first temperature sensor, 12-a first flow sensor, 13-a humidity sensor, 14-an ozone concentration sensor, 15-a particle size detector, 16-an air separation module, 17-a second electric pressure regulating valve, 18-a second manual pressure regulating valve, 19-a second flow sensor, 20-a first oxygen concentration sensor, 21-a second temperature sensor, 22-a second pressure sensor, 23-a turbo expander, 24-a third temperature sensor, 25-a third pressure sensor, 26-a first flame arrester, 27-an oil tank, 28-a second flame arrester, 29-a hydrocarbon concentration sensor, 30-a second oxygen concentration sensor, 31-a fourth temperature sensor, 32-a third oxygen concentration sensor, 33-a fifth temperature sensor, 34-a fourth pressure sensor, 35-a second fan and 36-an automatic controller.
Detailed Description
The present invention will be further described with reference to the following examples. The following description is only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Referring to FIG. 1, a schematic diagram of an energy recovery fuel tank inerting system configuration of the present invention includes engine bleed air; comprises a first fan, a filter, a dryer, a heater, a humidity regulator, an ozone converter, a first control valve, a first electric pressure regulating valve, a first manual pressure regulating valve, a first pressure sensor, a first temperature sensor, a first flow sensor, a humidity sensor, an ozone concentration sensor, a granularity detector, an air separation module, a second electric pressure regulating valve, a second manual pressure regulating valve, a second flow sensor, a first oxygen concentration sensor, a second temperature sensor, a second pressure sensor, a turbine expander, a third temperature sensor, a third pressure sensor, a first flame arrester, an oil tank, a second flame arrester, a hydrocarbon concentration sensor, a second oxygen concentration sensor, a fourth temperature sensor, a third oxygen concentration sensor, a fifth temperature sensor, a fourth pressure sensor, a second fan, a second temperature sensor, a third temperature sensor, a fourth pressure sensor, a second fan, a, An automatic controller.
The engine bleed air is connected with an inlet of the fan 1 through a pipeline; an outlet of the first fan 1 is sequentially connected with a filter 2, a dryer 3, a heater 4, a humidity regulator 5, an ozone converter 6 and one end of a first control valve 7 through pipelines; two ends of the first control valve 7 are simultaneously connected with one end of a first electric pressure regulating valve 8 and one end of a first manual pressure regulating valve 9 through pipelines; two ends of the first electric pressure regulating valve 8 and two ends of the first manual pressure regulating valve 9 are simultaneously connected with one end of a first pressure sensor 10 through pipelines; two ends of the first pressure sensor 10 are sequentially connected with a first temperature sensor 11, a first flow sensor 12, a humidity sensor 13, an ozone concentration sensor 14, a granularity detector 15 and an inlet of an air separation module 16 through pipelines; the air separation module comprises a gas inlet, a nitrogen-rich gas outlet and an oxygen-rich gas outlet.
The nitrogen-rich gas outlet of the air separation module 16 is simultaneously connected with one end of a second electric pressure regulating valve 17 and one end of a second manual pressure regulating valve 18 through pipelines; both ends of the second electric pressure regulating valve 17 and both ends of the second manual pressure regulating valve 18 are connected to one end of a second flow sensor 19 through pipes; two ends of the second flow sensor 19 are sequentially connected with a first oxygen concentration sensor 20, a second temperature sensor 21, a second pressure sensor 22, a turbine expander 23, a third temperature sensor 24, a third pressure sensor 25, a first flame arrester 26 and a gas inlet of an oil tank 27 through pipelines; the gas outlet of the oil tank 27 is connected with one end of a second flame arrester 28 through a pipeline; the second flame arrester 28 exhausts at its two ends.
A hydrocarbon concentration sensor 29 is connected to the oil tank 27 via a probe; the second oxygen concentration sensor 30 is connected with the oil tank 27 through a probe rod; the fourth temperature sensor 31 is connected with the oil tank 27 through a probe rod; an oxygen-enriched gas outlet of the air separation module 16 is sequentially connected with one end of a third oxygen concentration sensor 32, one end of a fifth temperature sensor 33, one end of a fourth pressure sensor 34 and one end of a second fan 35 through pipelines; oxygen-enriched gas at two ends of the second fan 35 is sent to the cabin for breathing; the turbo-expander 23 is connected to the second fan 35 via a shaft.
The system configuration of the present invention is controlled by an automatic controller 36. The automatic controller 36 includes a current input and a current output; a first pressure sensor 10, a first temperature sensor 11, a first flow sensor 12, a humidity sensor 13, an ozone concentration sensor 14, a particle size detector 15, a second flow sensor 19, a first oxygen concentration sensor 20, a second temperature sensor 21, a second pressure sensor 22, a third temperature sensor 24, a third pressure sensor 25, a hydrocarbon concentration sensor 29, a second oxygen concentration sensor 30, a fourth temperature sensor 31, a third oxygen concentration sensor 32, a fifth temperature sensor 33, and a fourth pressure sensor 34 are connected in parallel by cables and are connected with the current input end of the automatic controller 36; the current output end of the automatic controller 36 is respectively connected with the first fan 1, the heater 4, the humidity regulator 5, the ozone converter 6, the first control valve 7, the first electric pressure regulating valve 8 and the second electric pressure regulating valve 17 through cables.
The invention relates to an energy recovery type fuel tank inerting system configuration working process which comprises the following steps:
when the oil tank is not in an inerting state, an onboard nitrogen inerting system for preparing nitrogen-rich gas by a hollow fiber membrane is started, and at the moment, a first fan 1, a heater 4, a humidity regulator 5, an ozone converter 6, a first control valve 7, a first electric pressure regulating valve 8 and a second electric pressure regulating valve 17 are opened;
engine bleed air enters a system under the suction action of a first fan 1, is filtered and dried in a filter 2 and a dryer 3, is subjected to temperature and humidity adjustment in a heater 4 and a humidity adjuster 5 respectively, is removed in an ozone converter 6, flows through a first control valve 7, and is subjected to pressure adjustment in a first electric pressure adjusting valve 8 or a first manual pressure adjusting valve 9; the first pressure sensor 10, the first temperature sensor 11, the first flow sensor 12, the humidity sensor 13, the ozone concentration sensor 14 and the particle size detector 15 respectively measure parameters such as pressure, temperature, flow, humidity, ozone concentration and particle size of gas before the separation membrane and transmit signals to the automatic controller 36, and the automatic controller 36 respectively outputs feedback signals to the heater 4, the humidity regulator 5, the ozone converter 6, the first control valve 7 and the first electric pressure regulating valve 8;
the regulated gas enters an air separation module 16 to generate nitrogen-rich gas and oxygen-rich gas; the nitrogen-rich gas is subjected to pressure regulation in a second electric pressure regulating valve 17 or a second manual pressure regulating valve 18, and flows through a second flow sensor 19, a first oxygen concentration sensor 20, a second temperature sensor 21 and a second pressure sensor 22 in sequence, and then enters a turbine expander 23 to be expanded, cooled and depressurized, the turbine expander 23 drives a second fan 35 blade to rotate through a shaft when expanding, the nitrogen-rich gas after being cooled and depressurized flows into an oil tank to be flushed and inerted after flowing through a third temperature sensor 24, a third pressure sensor 25 and a first flame arrester 26 in sequence, and redundant gas in the oil tank flows through a second flame arrester 28 and then is discharged out of the machine;
the oxygen-enriched gas generated by the air separation module 16 flows through the third oxygen concentration sensor 32, the fifth temperature sensor 33, the fourth pressure sensor 34 and the second fan 35 in sequence under the suction action of the second fan 35, and then is sent to the cabin for the passengers to breathe.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only illustrative of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. An energy recovery type fuel tank inerting system configuration is characterized by comprising a first fan (1), wherein an inlet of the first fan (1) is communicated with an engine for air entraining, and an outlet of the first fan (1) is sequentially connected with a filter (2), a dryer (3), a heater (4), a humidity regulator (5), an ozone converter (6) and a first control valve (7); the outlet of the first control valve (7) is respectively connected with a first electric pressure regulating valve (8) and a first manual pressure regulating valve (9); the outlets of the first electric pressure regulating valve (8) and the first manual pressure regulating valve (9) are connected with one end of a first pressure sensor (10); the other end of the first pressure sensor (10) is sequentially connected with a first temperature sensor (11), a first flow sensor (12), a humidity sensor (13), an ozone concentration sensor (14), a granularity detector (15) and an air separation module (16); the air separation module (16) comprises a gas inlet, a nitrogen-rich gas outlet and an oxygen-rich gas outlet;
a gas inlet of the air separation module (16) is connected with the granularity detector (15);
a nitrogen-rich gas outlet of the air separation module (16) is respectively connected with a second electric pressure regulating valve (17) and a second manual pressure regulating valve (18), outlets of the second electric pressure regulating valve (17) and the second manual pressure regulating valve (18) are respectively connected with one end of a second flow sensor (19), the other end of the second flow sensor (19) is sequentially connected with a first oxygen concentration sensor (20), a second temperature sensor (21), a second pressure sensor (22), a turbine expander (23), a third temperature sensor (24), a third pressure sensor (25), a first flame arrester (26) and an oil tank (27), the first flame arrester (26) is connected with a gas inlet of the oil tank (27), and a gas outlet of the oil tank (27) is connected with a second flame arrester (28);
an oxygen-enriched gas outlet of the air separation module (16) is sequentially connected with a third oxygen concentration sensor (32), a fifth temperature sensor (33), a fourth pressure sensor (34) and a second fan (35), and the other end of the second fan (35) is connected with the turbo expander (23); the oxygen-enriched gas of the second fan (35) is sent to the cabin for breathing.
2. An energy recovery type fuel tank inerting system configuration according to claim 1, wherein a hydrocarbon concentration sensor (29), a second oxygen concentration sensor (30) and a fourth temperature sensor (31) are respectively arranged on a fuel tank (27) in the system configuration, and the hydrocarbon concentration sensor (29), the second oxygen concentration sensor (30) and the fourth temperature sensor (31) are respectively connected with the fuel tank (27) through probe rods.
3. An energy recovery fuel tank inerting system configuration as set forth in claim 2, wherein said system configuration is controlled by an automatic controller (36), and in particular, said automatic controller (36) comprises a current input and a current output;
the current input end of the automatic controller (36) is connected in parallel to the first pressure sensor (10), the first temperature sensor (11), the first flow sensor (12), the humidity sensor (13), the ozone concentration sensor (14), the granularity detector (15), the second flow sensor (19), the first oxygen concentration sensor (20), the second temperature sensor (21), the second pressure sensor (22), the third temperature sensor (24), the third pressure sensor (25), the hydrocarbon concentration sensor (29), the second oxygen concentration sensor (30), the fourth temperature sensor (31), the third oxygen concentration sensor (32), the fifth temperature sensor (33) and the fourth pressure sensor (34) through cables.
4. An energy recovery type fuel tank inerting system configuration according to claim 3, characterized in that the current output end of the automatic controller (36) is connected in parallel to the first fan (1), the heater (4), the humidity regulator (5), the ozone converter (6), the first control valve (7), the first electric pressure regulating valve (8) and the second electric pressure regulating valve (17) through cables.
5. The working method of the energy recovery type fuel tank inerting system configuration according to any one of claims 1 to 4, characterized in that the method comprises the following steps:
when the oil tank is not in an inerting state, an onboard nitrogen-making inerting system for preparing nitrogen-rich gas by using a hollow fiber membrane is started, and at the moment, a first fan (1), a heater (4), a humidity regulator (5), an ozone converter (6), a first control valve (7), a first electric pressure regulating valve (8) and a second electric pressure regulating valve (17) are opened;
engine bleed air enters a system under the suction action of a first fan (1), is filtered and dried in a filter (2) and a dryer (3), is subjected to temperature and humidity regulation in a heater (4) and a humidity regulator (5), is removed in an ozone converter (6), flows through a first control valve (7), and is subjected to pressure regulation in a first electric pressure regulating valve (8) or a first manual pressure regulating valve (9);
the device comprises a first pressure sensor (10), a first temperature sensor (11), a first flow sensor (12), a humidity sensor (13), an ozone concentration sensor (14) and a granularity detector (15), wherein a series of parameters of pressure, temperature, flow, humidity, ozone concentration and granularity of gas before a separation membrane are respectively measured and transmitted to an automatic controller (36), and the automatic controller (36) respectively outputs feedback signals to a heater (4), a humidity regulator (5), an ozone converter (6), a first control valve (7) and a first electric pressure regulating valve (8);
the regulated gas enters an air separation module (16) to generate nitrogen-rich gas and oxygen-rich gas; the nitrogen-rich gas is subjected to pressure regulation in a second electric pressure regulating valve (17) or a second manual pressure regulating valve (18), and enters a turbine expander (23) to be expanded, cooled and depressurized after sequentially flowing through a second flow sensor (19), a first oxygen concentration sensor (20), a second temperature sensor (21) and a second pressure sensor (22), the turbine expander (23) drives a second fan (35) blade to rotate through a shaft during expansion, the nitrogen-rich gas after being cooled and depressurized flows into an oil tank to be flushed and inerted after sequentially flowing through a third temperature sensor (24), a third pressure sensor (25) and a first flame arrester (26), and redundant gas in the oil tank flows through a second flame arrester 28 and is discharged outside the machine;
oxygen-enriched gas generated by the air separation module (16) flows through the third oxygen concentration sensor (32), the fifth temperature sensor (33), the fourth pressure sensor (34) and the second fan (35) in sequence under the suction action of the second fan (35) and then is sent to the cabin for the driver and passengers to breathe.
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