CN111071465A - Low-temperature refrigeration nitrogen-making oil tank inerting system and working method thereof - Google Patents

Low-temperature refrigeration nitrogen-making oil tank inerting system and working method thereof Download PDF

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Publication number
CN111071465A
CN111071465A CN202010010268.9A CN202010010268A CN111071465A CN 111071465 A CN111071465 A CN 111071465A CN 202010010268 A CN202010010268 A CN 202010010268A CN 111071465 A CN111071465 A CN 111071465A
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China
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heat exchanger
nitrogen
oxygen
stop valve
rectifying tower
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CN202010010268.9A
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Chinese (zh)
Inventor
刘卫华
冯诗愚
李超越
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Priority to CN202010010268.9A priority Critical patent/CN111071465A/en
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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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J3/00—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification
    • F25J3/02—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream
    • F25J3/04—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream for air
    • F25J3/04521—Coupling of the air fractionation unit to an air gas-consuming unit, so-called integrated processes
    • F25J3/04527—Integration with an oxygen consuming unit, e.g. glass facility, waste incineration or oxygen based processes in general
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J3/00—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification
    • F25J3/02—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream
    • F25J3/04—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream for air
    • F25J3/04521—Coupling of the air fractionation unit to an air gas-consuming unit, so-called integrated processes
    • F25J3/04563—Integration with a nitrogen consuming unit, e.g. for purging, inerting, cooling or heating
    • 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
    • B64D2013/0681—Environmental Control Systems with oxygen control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J2205/00—Processes or apparatus using other separation and/or other processing means
    • F25J2205/84—Processes or apparatus using other separation and/or other processing means using filter
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J2210/00—Processes characterised by the type or other details of the feed stream
    • F25J2210/40—Air or oxygen enriched air, i.e. generally less than 30mol% of O2
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J2215/00—Processes characterised by the type or other details of the product stream
    • F25J2215/42—Nitrogen or special cases, e.g. multiple or low purity N2
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J2215/00—Processes characterised by the type or other details of the product stream
    • F25J2215/50—Oxygen or special cases, e.g. isotope-mixtures or low purity O2

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Thermal Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Separation By Low-Temperature Treatments (AREA)

Abstract

The invention discloses an inerting system of a low-temperature refrigeration nitrogen-making oil tank and a working method thereof, belonging to the technical field of fire prevention and explosion prevention. The working method of the invention is that bleed air from an aircraft engine is condensed into liquid air by an onboard refrigerating device after being filtered, heat exchanged and water removed, and the liquid air is separated in a rectifying tower to form nitrogen-rich liquid and oxygen-rich liquid. The nitrogen-rich liquid can be used for inerting an aircraft fuel tank through the decompression effect after being stored, so that the flammability of the fuel tank is reduced, and the flight safety of the aircraft is protected; the oxygen-enriched liquid can be used for supplying oxygen for the aircraft cabin after being decompressed. The oil tank inerting system can store nitrogen-rich gas, reduces the influence on engine bleed air, meets the aircraft oil tank inerting requirements under full-flight envelope and extreme conditions, and can be used for supplying oxygen when a cabin is depressurized to ensure flight safety.

Description

Low-temperature refrigeration nitrogen-making oil tank inerting system and working method thereof
Technical Field
The invention relates to the technical field of fire prevention and explosion prevention, in particular to an inerting system of a low-temperature refrigeration nitrogen-making oil tank and a working method thereof.
Background
When the oxygen concentration of the gas phase space of the aircraft fuel tank is greater than the lowest flammable limit oxygen concentration, the fuel tank is easy to burn and explode to cause the death of people due to the existence of an external ignition source. The fuel tank inerting technology is a method for reducing the combustibility of the fuel tank and reducing the occurrence of fire efficiently and economically, and the inert gas such as nitrogen or carbon dioxide is filled into a gas phase space of the fuel tank to replace oxygen in the fuel tank, so that the oxygen is lower than the minimum combustible limit oxygen concentration required by the combustion of the fuel oil, and the aim of inerting the fuel tank is fulfilled.
At present, the most widely applied and technically mature fuel tank inerting technology is mainly used for an organic-borne hollow fiber membrane nitrogen-making inerting system, and the hollow fiber membrane is used for separating high-pressure bleed air of an aircraft engine to form high-concentration nitrogen-rich gas for inerting the fuel tank. However, as the oil tank inerting technology is studied deeply, the hollow fiber membrane nitrogen inerting technology also exposes more and more problems, such as high required pressure, which cannot affect the performance of an engine; the membrane is easy to block and short in service life, so that the maintenance cost is increased; in addition, in the descending stage of the airplane, due to the fact that the external pressure is increased, a large amount of air enters the oil tank, the oxygen concentration is rapidly increased, and the inerting requirement of the hollow fiber membrane nitrogen preparation system cannot be met.
Disclosure of Invention
The invention aims to solve the technical problem of providing a low-temperature refrigeration nitrogen-making oil tank inerting system and a working method thereof.
The invention is realized by the following steps:
an inerting system of a low-temperature freezing nitrogen-making oil tank comprises an air filter, wherein an inlet of the air filter is connected with an aircraft engine bleed air, and an outlet of the air filter is sequentially connected with a first heat exchanger, a second heat exchanger, a third heat exchanger, a water separator and a fourth heat exchanger; the second heat exchanger is positioned below the inner part of the rectifying tower; the rear end of the fourth heat exchanger is sequentially connected with an evaporator and a first stop valve, and the first stop valve is connected to the rectifying tower. The invention utilizes the low temperature refrigeration of the rectifying tower to prepare nitrogen, utilizes the onboard refrigeration equipment to separate oxygen and nitrogen, utilizes the rectifying tower to separate oxygen-enriched liquid, stores the oxygen-enriched liquid in the oxygen-enriched liquid storage tank for cabin pressurization and oxygen supply, simultaneously separates and stores a large amount of nitrogen-enriched liquid in the nitrogen-enriched liquid storage tank, the nitrogen-enriched liquid can be used for inerting an aircraft oil tank through the decompression action after being stored, the flammability of the oil tank is reduced, the flight safety of the aircraft is protected, and the oxygen-enriched liquid can be used for oxygen supply of the aircraft cabin after being decompressed.
The rectifying tower is respectively provided with a nitrogen-rich liquid outlet and an oxygen-rich liquid outlet; an oxygen-enriched liquid outlet of the rectifying tower is sequentially connected with a second stop valve, an oxygen-enriched liquid storage tank, a third stop valve and an aircraft cabin; a nitrogen-rich liquid outlet of the rectifying tower is sequentially connected with a fourth stop valve, a nitrogen-rich liquid storage tank and a fifth stop valve; the outlet of the fifth stop valve is connected with the inlet of a hot side channel of the fourth heat exchanger; and the outlet of the hot side channel of the fourth heat exchanger is connected with an inert gas inlet of an aircraft fuel tank, and the upper end of the aircraft fuel tank is also provided with a vent communicated with the external environment.
Furthermore, two hot side channels of the first heat exchanger are respectively connected with the air filter and the second heat exchanger, and ram air is introduced into a cold side channel of the first heat exchanger and exhausted to the external environment.
Further, two hot side channels of the third heat exchanger are connected with the second heat exchanger and the water separator), and a cold side channel is introduced with ram air and exhausted to the external environment.
Furthermore, the two hot side channels of the evaporator are respectively connected with the fourth heat exchanger and the first stop valve.
Further, the evaporator is also connected with a refrigeration compressor, a condenser and a throttle valve, specifically, a cold side channel outlet of the evaporator is connected with an inlet of the refrigeration compressor, and a cold side channel inlet of the evaporator is connected with an outlet of the throttle valve; and a condenser is connected between the outlet of the refrigeration compressor and the inlet of the throttle valve. The low-temperature liquefaction is carried out through a refrigeration system consisting of a refrigeration compressor, an evaporator, a throttle valve and a condenser, the air is frozen into liquid, and the liquid enters a rectifying tower for rectification.
The invention also discloses a working method of the inerting system of the low-temperature refrigeration nitrogen-making oil tank, which is characterized by comprising the following steps:
the method comprises the following steps that bleed air of the aircraft engine is filtered and impurity-removed through an air filter, then is cooled through a first heat exchanger, then enters a second heat exchanger, the second heat exchanger is located below the inner part of a rectifying tower, enters the second heat exchanger and is cooled through heat exchange of a freezing liquid, then enters a third heat exchanger and is cooled through low-temperature ram air, water in the air is separated and removed after passing through a water separator, and then is continuously cooled through a fourth heat exchanger;
after entering the evaporator, a refrigeration system consisting of a refrigeration compressor, the evaporator, a throttle valve and a condenser is subjected to low-temperature liquefaction, air is frozen into liquid, and the liquid enters a rectifying tower for rectification;
nitrogen in the rectifying tower is firstly separated from liquid air to form nitrogen-rich gas, then the nitrogen-rich gas is condensed in the rectifying tower to form nitrogen-rich liquid, the nitrogen-rich liquid enters a nitrogen-rich liquid storage tank, and enters an aircraft oil tank gas phase space after passing through a fifth stop valve and a fourth heat exchanger hot side channel, and oxygen in the nitrogen-rich liquid is replaced and discharged to the external environment; meanwhile, the oxygen-enriched liquid of the rectifying tower is stored in the oxygen-enriched liquid storage tank through the second stop valve and enters the aircraft cabin through the third stop valve to supply oxygen.
Compared with the prior art, the invention adopting the technical scheme has the following technical effects:
the method comprises the steps of carrying out air entraining and temperature reduction for multiple times by utilizing a first heat exchanger, a second heat exchanger, a third heat exchanger and a fourth heat exchanger, then, entering a refrigeration system consisting of a refrigeration compressor, an evaporator, a throttle valve and a condenser for low-temperature liquefaction, freezing air into liquid, rectifying the liquid in a rectifying tower, and carrying out oil tank inerting by utilizing low-temperature refrigeration nitrogen preparation, namely, utilizing airborne refrigeration equipment for oxygen-nitrogen separation, utilizing the rectifying tower to separate oxygen-enriched liquid for cabin pressurization and oxygen supply, and simultaneously separating and storing a large amount of nitrogen-enriched liquid for oil tank inerting;
the invention utilizes the method of refrigeration nitrogen production to separate air and store nitrogen-rich gas for the inerting of the oil tank, and simultaneously stores oxygen-rich gas for the pressurization and oxygen supply of the cabin, thereby ensuring the inerting requirement of the oil tank of the airplane under the full flight envelope and extreme conditions, reducing the influence of engine bleed air on the performance of the airplane and ensuring the safety of the airplane.
Drawings
FIG. 1 is a schematic diagram of a system for inerting a refrigerated nitrogen-producing fuel tank in accordance with an embodiment of the present invention;
in the figure, 1, an air filter, 2, a first heat exchanger, 3, a second heat exchanger, 4, a third heat exchanger, 5, a water separator, 6, a fourth heat exchanger, 7, an evaporator, 8, a first stop valve, 9, a rectifying tower, 10, a second stop valve, 11, an oxygen-rich liquid storage tank, 12, a third stop valve, 13, an aircraft cabin, 101, a fifth stop valve, 102, a nitrogen-rich liquid storage tank, 103, a fourth stop valve, 201, an aircraft oil tank, 202, a throttle valve, 203, a condenser, 204 and a refrigeration compressor.
Detailed Description
The present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.
As shown in fig. 1, the inerting system for the low-temperature refrigeration nitrogen-making oil tank comprises an air filter 1, a first heat exchanger 2, a second heat exchanger 3, a third heat exchanger 4, a water separator 5, a fourth heat exchanger 6, an evaporator 7, a first stop valve 8, a rectifying tower 9, a second stop valve 10, an oxygen-enriched liquid storage tank 11, a third stop valve 12 and an aircraft cabin 13.
An inlet of the air filter 1 is connected with an aircraft engine bleed air, a hot side channel of the first heat exchanger 2 is connected with the air filter 1 and the second heat exchanger 3, and a cold side channel is introduced with ram air and exhausted to the external environment; the second heat exchanger 3 is arranged below the inner part of the rectifying tower 9; a hot side channel of the third heat exchanger 4 is connected with the second heat exchanger 3 and the water separator 5, and a cold side channel is introduced with ram air and is exhausted to the external environment; the hot side passage of the evaporator 7 is connected to the fourth heat exchanger 6 and the first shut-off valve 8. The outlet of the cold-side channel of the evaporator 7 is connected with the inlet of the refrigeration compressor 204, and the inlet of the cold-side channel of the evaporator 7 is connected with the outlet of the throttle valve 202; a condenser 203 is connected between the outlet of the refrigeration compressor 204 and the inlet of the throttle valve 202. The low-temperature liquefaction is carried out by a refrigeration system consisting of a refrigeration compressor 204, an evaporator 7, a throttle valve 202 and a condenser 203, and the air is frozen into liquid and enters a rectifying tower 9 for rectification.
The rectifying tower 9 is also provided with a nitrogen-rich liquid outlet and an oxygen-rich liquid outlet respectively; an oxygen-enriched liquid outlet of the rectifying tower 9 is sequentially connected with a second stop valve 10, an oxygen-enriched liquid storage tank 11, a third stop valve 12 and an aircraft cabin 13; a nitrogen-rich liquid outlet of the rectifying tower 9 is sequentially connected with a fourth stop valve 103, a nitrogen-rich liquid storage tank 102 and a fifth stop valve 101; the outlet of the fifth stop valve 101 is connected with the inlet of a hot side channel of the fourth heat exchanger 6; and the outlet of the hot side channel of the fourth heat exchanger 6 is connected with an inert gas inlet of an aircraft fuel tank 201, and the upper end of the aircraft fuel tank 201 is also provided with a vent communicated with the external environment.
The working method of the inerting system of the low-temperature refrigeration nitrogen-making oil tank comprises the following steps:
the method comprises the steps of filtering high-temperature high-pressure bleed air of an aircraft engine by an air filter 1 to remove impurities, cooling the bleed air by a first heat exchanger 2, transferring the bleed air into a second heat exchanger 3, cooling the bleed air by using a refrigerating liquid for heat exchange, transferring the bleed air into a third heat exchanger 4, cooling the bleed air by using low-temperature ram air, separating and removing the bleed air by a water separator 5, continuously cooling the bleed air by using a fourth heat exchanger 6, transferring the bleed air into a refrigerating system consisting of a refrigerating compressor 204, an evaporator 7, a throttle valve 202 and a condenser 203 for low-temperature liquefaction after transferring the bleed air into a liquid, transferring the air into a rectifying tower 9 for rectification, separating nitrogen from the liquid air to form nitrogen-rich gas, condensing the nitrogen-rich gas in the rectifying tower 9 to form nitrogen-rich liquid, transferring the nitrogen-rich liquid into a nitrogen-rich liquid storage tank 102, and transferring the, converting the oxygen therein and discharging to the external environment. Meanwhile, the oxygen-enriched liquid at the bottom of the rectifying tower 9 is stored in an oxygen-enriched liquid storage tank 11 through a second stop valve 10 and enters an aircraft cabin 13 through a third stop valve 12 for oxygen supply. The working method of the system can meet the requirements of aircraft oil tank inerting under full flight envelope and extreme conditions, reduces the influence on engine bleed air, ensures flight safety, and can provide a large amount of oxygen-enriched gas for pressurization and oxygen supply of an aircraft cabin.
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 (6)

1. The inerting system for the low-temperature freezing nitrogen-making oil tank is characterized by comprising an air filter (1), wherein an inlet of the air filter (1) is connected with bleed air of an aircraft engine, and an outlet of the air filter (1) is sequentially connected with a first heat exchanger (2), a second heat exchanger (3), a third heat exchanger (4), a water separator (5) and a fourth heat exchanger (6); the second heat exchanger (3) is positioned below the inner part of the rectifying tower (9); the rear end of the fourth heat exchanger (6) is sequentially connected with an evaporator (7) and a first stop valve (8), and the first stop valve (8) is connected with a rectifying tower (9);
the rectifying tower (9) is also provided with a nitrogen-rich liquid outlet and an oxygen-rich liquid outlet respectively;
an oxygen-enriched liquid outlet of the rectifying tower (9) is sequentially connected with a second stop valve (10), an oxygen-enriched liquid storage tank (11), a third stop valve (12) and an aircraft cabin (13);
a nitrogen-rich liquid outlet of the rectifying tower (9) is sequentially connected with a fourth stop valve (103), a nitrogen-rich liquid storage tank (102) and a fifth stop valve (101); the outlet of the fifth stop valve (101) is connected with the inlet of a hot side channel of the fourth heat exchanger (6); and the outlet of the hot side channel of the fourth heat exchanger (6) is connected with an inert gas inlet of an aircraft fuel tank (201), and the upper end of the aircraft fuel tank (201) is also provided with a vent communicated with the external environment.
2. The inerting system for the cryogenic nitrogen-making oil tank is characterized in that two hot side channels of the first heat exchanger (2) are respectively connected with the air filter (1) and the second heat exchanger (3), and a cold side channel of the first heat exchanger (2) is introduced with ram air and is exhausted to the external environment.
3. The inerting system for the cryogenic nitrogen-making oil tank according to claim 1, characterized in that two hot side channels of the third heat exchanger (4) are connected with the second heat exchanger (3) and the water separator (5), and a cold side channel is introduced with ram air and is discharged to the external environment.
4. The inerting system for the cryogenic nitrogen-making fuel tank as claimed in claim 1, wherein the two hot side channels of the evaporator (7) are respectively connected with the fourth heat exchanger (6) and the first stop valve (8).
5. The inerting system for the cryogenic refrigeration nitrogen-making oil tank is characterized in that the evaporator (7) is further connected with a refrigeration compressor (204), a condenser (203) and a throttle valve (202), specifically, a cold side channel outlet of the evaporator (7) is connected with an inlet of the refrigeration compressor (204), and a cold side channel inlet of the evaporator (7) is connected with an outlet of the throttle valve (202); a condenser (203) is connected between the outlet of the refrigeration compressor (204) and the inlet of the throttle valve (202).
6. The working method of the inerting system for the low-temperature refrigeration nitrogen-making oil tank is characterized by comprising the following steps of:
the method comprises the following steps that bleed air of the aircraft engine is filtered and impurity-removed through an air filter (1), then is cooled through a first heat exchanger (2), then enters a second heat exchanger (3), the second heat exchanger (3) is located below the inner part of a rectifying tower (9), enters the second heat exchanger (3) and is cooled through heat exchange of a refrigerating liquid, then enters a third heat exchanger (4) and is cooled through low-temperature ram air, water in the air is separated and removed after passing through a water separator (5), and then is continuously cooled through a fourth heat exchanger (6);
after entering the evaporator, a refrigeration system consisting of a refrigeration compressor (204), the evaporator (7), a throttle valve (202) and a condenser (203) is subjected to low-temperature liquefaction, air is frozen into liquid, and the liquid enters a rectifying tower (9) for rectification;
nitrogen in the rectifying tower (9) is firstly separated from liquid air to form nitrogen-rich gas, then the nitrogen-rich gas is condensed in the rectifying tower (9) to form nitrogen-rich liquid, the nitrogen-rich liquid enters a nitrogen-rich liquid storage tank (102), and enters a gas phase space of an aircraft oil tank (201) after passing through a fifth stop valve (101) and a hot side channel of a fourth heat exchanger (6), and oxygen in the nitrogen gas is replaced and discharged to the external environment; meanwhile, the oxygen-enriched liquid in the rectifying tower (9) is stored in an oxygen-enriched liquid storage tank (11) through a second stop valve (10) and enters an aircraft cabin (13) through a third stop valve (12) to be supplied with oxygen.
CN202010010268.9A 2020-01-06 2020-01-06 Low-temperature refrigeration nitrogen-making oil tank inerting system and working method thereof Pending CN111071465A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112918682A (en) * 2021-02-03 2021-06-08 南京航空航天大学 Four-wheel high-pressure water removal environment control system based on different cabin pressures and working method
CN112937874A (en) * 2021-02-04 2021-06-11 南京航空航天大学 Can realize that cabin disperses ring accuse of formula oxygen suppliment and machine carries nitrogen generation coupled system

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CN112937874B (en) * 2021-02-04 2022-03-04 南京航空航天大学 Can realize that cabin disperses ring accuse of formula oxygen suppliment and machine carries nitrogen generation coupled system

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Application publication date: 20200428