An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the inner shroud.
Aircraft engine nacelle comprising a system of ice protection
09.05.2023
Patent
Elektronische Ressource
Englisch
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