A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a water separator configured to receive the compressed air from the compressor and remove moisture from the compressed air to dry the compressed air. Furthermore, the system includes a turbine configured to receive the dried air from the heat exchanger, with the dried air expanding as the dried air flows through the turbine. Moreover, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, the moisture removed from the compressed air by the water separator is routed to the defroster to melt the captured frozen particulate matter.
SYSTEM AND METHOD FOR COOLING AIRCRAFT COMPONENTS
2022-04-14
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Redundant aircraft cooling system for redundant aircraft components
Europäisches Patentamt | 2015
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