Configuration and working method of an energy recovery type fuel tank inerting system
A technology of energy recovery and fuel tanks, which is applied in the field of aviation systems, can solve the problems of large aircraft compensation loss and low efficiency of separation membranes, and achieve the effects of reducing flammability, improving separation efficiency, and increasing flow rate
Active Publication Date: 2021-04-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
However, judging from the application status at home and abroad, the airborne nitrogen inerting technology has the problem of low separation membrane efficiency and large aircraft compensatory losses.
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[0024] The present invention will be further described below in conjunction with embodiment. The following descriptions are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0025] Such as figure 1 As shown, a schematic configuration diagram of an energy recovery type fuel tank inerting system of the present invention includes engine bleed air; includes a first fan, a filter, a dryer, a heater, a humidity regulator, an ozone converter, a first control Valve, first electric pressure regulating valve, first manual pressure regulating valve, first pressure sensor, first temperature sensor, first flow sensor, humidity sensor, ozone concentration sensor, particle size detector, air separation module, second electric Pressure regulating valve, second manual pressure re...
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The invention discloses an energy recovery type fuel tank inerting system structure, and belongs to the technical field of aviation systems. Air is entrained from an engine, undergoes temperature adjustment, pressure adjustment and removal of pollutants such as ozone, moisture and impurities, then is introduced into an air separation device composed of a hollow fiber membrane and is separated intooxygen-enriched gas and nitrogen-enriched gas, the oxygen-enriched gas is sent to a cabin and is used for breathing of drivers and passengers, and the nitrogen-enriched gas is injected into a fuel tank according to different flow modes and is washed or flushed. The nitrogen-enriched gas flowing out of the hollow fiber membrane is firstly introduced into a turbo expander, part of energy is recovered, the temperature of the nitrogen-enriched gas is reduced, and the combustibility of the fuel tank is reduced; and additionally, the recovered energy is used for driving a fan to improve 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.
Description
technical field [0001] The invention belongs to the technical field of aviation systems, and relates to an explosion-proof system for an aircraft fuel tank, in particular to an energy recovery type fuel tank inerting system configuration. Background technique [0002] In the past 50 years, there have been 18 fuel tank explosion accidents of transport aircraft worldwide, killing a total of 542 people, which has become one of the main threats to civil aviation safety. In 1996, the combustible vapor of the TWA800 central wing fuel tank of Boeing 747 aircraft was ignited and caused an explosion, and all crew members were killed. This prompted the US Federal Aviation Administration to issue a series of amendments, advisory notices and airworthiness regulations, mandating that effective measures be taken to reduce ignition sources. and flammable vapor concentration to reduce the flammability of transport aircraft fuel tanks and increase the safety of fuel tanks. The Civil Aviatio...
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IPC IPC(8): B64D37/32B01D53/22B64D13/06
CPCB01D53/228B01D2053/221B64D13/06B64D37/32B64D2013/0651B64D2013/0662B64D2013/0681
Inventor 刘卫华冯诗愚彭孝天
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS