Temperature-controllable fuel tank inerting device based on catalytic combustion technology

A catalytic combustion and fuel tank technology, applied in the field of aviation systems, can solve the problems of uneven temperature of the catalytic reactor, difficult to control the outlet temperature, large preheating capacity, etc., and achieves simple structure, controllable temperature, and less preheating gas amount. Effect

Pending Publication Date: 2019-05-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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Problems solved by technology

[0005] However, the existing oxygen-consuming inerting system has the disadvantages of large preheat, uneven temperature of the catalytic reactor, and difficulty in controlling the outlet temperature.

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  • Temperature-controllable fuel tank inerting device based on catalytic combustion technology

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Embodiment Construction

[0020] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below in conjunction with specific embodiments.

[0021] Embodiments of the present invention provide a temperature-controllable fuel tank inerting device based on catalytic combustion technology, such as figure 1 As shown, it includes: oxygen concentration sensor 1, first flame arrester 3, output fan 4, first electric control valve 5, second electric control valve 6, third electric control valve 7, heater 8, first temperature sensor 9 , the second temperature sensor 10, the third temperature sensor 11, the reactor 12, the first catalytic bed 13, the second catalytic bed 14, the third catalytic bed 15, the controller 16, the input fan 17, the water separator 18, the fourth Electric control valve 19, check valve 20, second flame arrester 21.

[0022] The probe of the oxygen concentration sensor 1 ext...

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Abstract

The invention discloses a temperature-controllable fuel tank inerting device based on a catalytic combustion technology, and relates to the technical field of aviation systems. The temperature in a fuel tank and the temperature of a catalytic reaction outlet can be controlled, and a catalytic reaction is uniform. According to the principle of the device, a gas-phase space fuel steam and air mixture at the upper part of the fuel tank is divided into multiple parts which are introduced into a catalytic combustion reactor separately. The first part of the gas is preheated, and fuel steam is decomposed into oxygen and water vapor under the action of a catalyst and releases heat; gas in front of the other part of the gas continues to be subjected to a mixing reaction. Oxygen in air is consumedin the reaction process, and the reacted nitrogen-rich gas flows into the fuel tank for flushing and inerting. The device can be operated at normal temperature and normal pressure, the inerting efficiency is high, and only a part of the gas needs to be preheated, so that the requirement for a gas preheating device is low; the temperature of the reactor in the inerting process is uniform; the temperature of an outlet of the reactor is controllable.

Description

technical field [0001] The invention relates to the technical field of aviation systems, in particular to a temperature-controllable fuel tank inerting device based on catalytic combustion technology. Background technique [0002] The safety of modern aircraft has been widely concerned by the society, and fuel system combustion and explosion are one of the main causes of aircraft crashes. Statistics show that during the Vietnam War, the U.S. Air Force lost thousands of aircraft due to ground fire attacks, among which the proportion of aircraft crashes and fatalities due to the fire and explosion of aircraft fuel tanks was as high as 50%. According to the cabin safety research technical group (GSRTG) statistics of 3,726 civil aircraft accidents worldwide from 1966 to 2009, a total of 370 accidents were related to fuel tank combustion explosions. It can be seen that effective measures must be taken to prevent aircraft fuel tanks from detonating. [0003] The upper space of t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D37/32B64D37/34
Inventor 谢辉辉冯诗愚彭孝天朱天宇周利飚
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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