The invention relates to an aircraft propulsion system, which includes a turbojet and a heat exchanger system (200), which includes a heat exchanger (202) including, forward, a supply connection and an evacuation connection (254), and aft, a transfer connection (250) and at least one scoop connection (252a-b), a supply pipe (204) connected to the supply connection, and which bleeds hot air from the compression stages, a transfer pipe (222) connected to the transfer connection (250), and which transfers the hot air that has passed through the heat exchanger (202) to an air management system of the aircraft, for each scoop connection (252a-b), a scoop (216a-b) connected to the scoop connection (252a-b) and which bleeds cold air from a fan duct and an evacuation pipe (220), which includes an inlet (220a) connected to the evacuation connection (254) and an outlet (220b), which emerges on the outside, where the passage of the hot air through the heat exchanger (202) from the supply pipe (204) to the transfer pipe (222) takes place along a first transfer direction (60) and where the passage of the cold air through the heat exchanger (202) from each scoop (216a-b) to the inlet (220a) takes place along a second transfer direction parallel to the first transfer direction (60) but in the opposite direction.
AIRCRAFT PROPULSION SYSTEM INCLUDING A HEAT EXCHANGER SYSTEM
FLUGZEUGANTRIEBSSYSTEM MIT EINEM WÄRMETAUSCHERSYSTEM
SYSTÈME DE PROPULSION D'AVION COMPRENANT UN SYSTÈME D'ÉCHANGEUR THERMIQUE
2021-07-14
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F28D Wärmetauscher, soweit in keiner anderen Unterklasse vorgesehen, in denen die Wärmetauschmittel nicht in direkte Berührung miteinander kommen , HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT |
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