The invention relates to an aircraft propulsion system, which includes a turbojet and a heat exchanger system (200) which includes a main heat exchanger (202), a supply pipe (204) supplying hot air, a transfer pipe (222) transferring the hot air to an air management system, a main supply pipe (216) supplying cold air from the fan duct, an evacuation pipe (220) expelling the air to the outside, a sub heat exchanger (230) with a high pressure pipe (250) going through the sub heat exchanger (230), a sub supply pipe (232) supplying cold air and including a sub regulating valve (234), a sub evacuation pipe (236) expelling the air, a temperature sensor (223), and a control unit (224) which controls the system according to the temperature measured, wherein the sub regulating valve (234) comprises a door (240) articulated between a closed position and an open position, a return spring (242) which constraints the door (240) in the open position, and a realising system (244), controlled by the control unit (224), which is mobile between a blocking position and a realising position in which it releases the door (240) which is free to move to the open position.This embodiment allows a supplementary cold air flow if necessary.
AIRCRAFT PROPULSION SYSTEM INCLUDING A HEAT EXCHANGER SYSTEM
FLUGZEUGANTRIEBSSYSTEM MIT EINEM WÄRMETAUSCHERSYSTEM
SYSTÈME DE PROPULSION D'AÉRONEF COMPRENANT UN SYSTÈME D'ÉCHANGEUR THERMIQUE
2021-11-17
Patent
Electronic Resource
English
AIRCRAFT PROPULSION SYSTEM INCLUDING A HEAT EXCHANGER SYSTEM
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|AIRCRAFT PROPULSION SYSTEM INCLUDING A HEAT EXCHANGER SYSTEM
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|AIRCRAFT PROPULSION SYSTEM INCLUDING A HEAT EXCHANGER SYSTEM
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