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Cabin pressurizing oxygen supply system based on aerodynamic turbine driving

An aerodynamic and turbine technology, applied in the field of aviation systems, can solve the problems of structural pressure difference in the cockpit, large engine bleed air volume, loss of fuel compensation loss, etc., and achieve the effect of reducing requirements, reducing bleed air volume, and reducing compensatory loss

Pending Publication Date: 2020-04-07
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

For this reason, the cockpit structure is subjected to a huge pressure difference, which increases the strength requirements and weight of the cockpit structure, and brings about a large loss of engine bleed air volume and fuel compensation loss

Method used

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  • Cabin pressurizing oxygen supply system based on aerodynamic turbine driving

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Embodiment Construction

[0024] Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

[0025] 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.

[0026] Such as figure 1 As shown, the present invention discloses a cockpit pressurized oxygen supply system driven by an aerodynamic turbine, comprising a temperature sensor, a first electric control valve, a first heat exchanger, a water separator, a Venturi regulator, a pressure sensor , a first flow sensor, an aerodynamic turbine, a second electric control valve, a hollow fiber membrane separator, a centrifugal compressor, a second flow sensor, a second heat exchanger, a third flo...

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Abstract

The invention discloses a cabin pressurizing oxygen supply system based on aerodynamic turbine driving. The cabin pressurizing oxygen supply system comprises a temperature sensor, a first electric control valve, a first heat exchanger, a water separator, a Venturi pressure stabilizer, a pressure sensor, a first flow sensor, an aerodynamic turbine, a second electric control valve, a hollow fiber membrane separator, a centrifugal compressor, a second flow sensor, a second heat exchanger, a third flow sensor and a controller. According to the invention, the centrifugal compressor driven by the aerodynamic turbine is used for recycling the oxygen-enriched gas of the hollow fiber membrane separator. The oxygen content of the cabin is increased, the pressure height of the cabin is conveniently increased, and the requirement for the structural strength of the cabin is effectively reduced; the air entraining amount of an engine air compressor is reduced, and the compensation loss of an airplane is reduced; the system has no motor drive and is feasible to manufacture; the aerodynamic turbine has the advantages of being high in rotating speed, small in size and large in flow and meets the technical requirement for cabin pressurization and oxygen supply.

Description

technical field [0001] The invention relates to the technical field of aviation systems, in particular to a cabin pressurized oxygen supply system driven by an aerodynamic turbine. Background technique [0002] During the entire flight of the aircraft, the occupants will be affected by various environmental factors, among which hypoxia has the strongest impact on the physiological activities of the human body. When the aircraft is flying at high altitude, corresponding measures must be taken to ensure that the oxygen concentration level in the cockpit is not lower than the corresponding oxygen concentration level at an altitude of 2400 meters. maximum height. For this reason, the cockpit structure bears a huge pressure difference, which increases the strength requirements and weight of the cockpit structure, and brings about a large loss of engine bleed air volume and fuel compensation loss. [0003] Since the determination of the aircraft cockpit pressure system is closel...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D37/32B64D13/06
CPCB64D13/06B64D37/32B64D2013/0681
Inventor 喻成璋刘卫华张瑞华周鹏鹤
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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