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Waste heat recovering device in aircraft fuel tank inerting system

A waste heat recovery device and fuel tank technology, applied in the field of aviation systems, can solve the problem of underutilization of energy, etc., and achieve the effects of high energy utilization, optimized performance, and short inerting time.

Pending Publication Date: 2018-09-04
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] However, the mixed gas after the reaction still contains a lot of heat. Generally, the heat is absorbed by the coolant and discharged, and the energy is not fully utilized.

Method used

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  • Waste heat recovering device in aircraft fuel tank inerting system
  • Waste heat recovering device in aircraft fuel tank inerting system
  • Waste heat recovering device in aircraft fuel tank inerting system

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Embodiment Construction

[0058] Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

[0059] This 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.

[0060] Such as figure 1 As shown, a waste heat recovery device in an aircraft fuel tank inerting system using absorption refrigeration.

[0061] The gas outlet of the oil tank 1 is connected to the first flame arrester 2 and the inlet of the fan 3 through pipelines; the outlet of the fan 3 and the outlet of the second electric regulating valve 19 are connected to the inlet of the cold side channel of the preheater 4 through pipelines; The outlet of the cold side channel of the heater...

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Abstract

The invention discloses a waste heat recovering device in an aircraft fuel tank inerting system and belongs to the technical field of aviation systems. According to the specific principle, mixed gas on the upper portion of an aircraft fuel tank is pumped out by a draught fan, subjected to temperature adjustment and pumped into a low-temperature plasma reactor, hydrocarbon in the mixed gas is motivated, dissociated and ionized by low-temperature plasmas, finally, harmless CO2 and H20 are generated, and nitrogen-rich gas obtained after drying flows back to an oil tank to be subjected to fuel oiltank inerting. However, the mixed gas generated after reaction still contains lots of heat, the waste heat recovering device utilizes heat in the gas after the reaction to drive an absorbing-type refrigerating technology or a spraying-type refrigerating technology, and the low-temperature gas is generated to cool a system controller. The waste heat recovering device has the advantages that the energy utilization rate is high, the inerting system performance is optimized, the inerting time is short, and the environment pollution is avoided.

Description

technical field [0001] The invention belongs to the technical field of aviation systems, in particular to a waste heat recovery device in an aircraft fuel tank inerting system. Background technique [0002] Engine fuel system fire or explosion is one of the main causes of aircraft crashes. The fire and explosion protection capability of the aircraft fuel system is directly related to the survivability and vulnerability of the aircraft, as well as the utilization rate, cost and personnel safety of the aircraft. If the fuel tank has explosion-proof capability, even if it is shot or other reasons cause a fire, it will not be destroyed, and the aircraft can continue to be used after being repaired, which increases the utilization rate and survivability of the aircraft accordingly, and reduces vulnerability. The adoption of aircraft fuel tank explosion-proof technology can also increase the life-saving time, so that the aircraft has enough time to return to the voyage in the ev...

Claims

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Application Information

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IPC IPC(8): B64D37/32B64D37/34
CPCB64D37/32B64D37/34
Inventor 彭孝天冯诗愚李超越谢辉辉刘卫华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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