An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure and a nozzle. The nacelle inlet structure extends circumferentially about an axial centerline. The nacelle inlet structure includes an inlet lip, a bulkhead and an internal cavity formed by and axially between the inlet lip and the bulkhead. The nozzle is configured to direct gas into the internal cavity axially towards the bulkhead.
THERMAL ANTI-ICING SYSTEM FOR AN AIRCRAFT PROPULSION SYSTEM
07.03.2024
Patent
Elektronische Ressource
Englisch
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