An assembly (54) is provided for an aircraft propulsion system (20). This assembly (54) includes a nacelle inlet structure (34) and a nozzle (122). The nacelle inlet structure (34) extends circumferentially about an axial centerline (28). The nacelle inlet structure (34) includes an inlet lip (60), a bulkhead (64) and an internal cavity (90) formed by and axially between the inlet lip (60) and the bulkhead (64). The nozzle (122) is configured to direct gas into the internal cavity (90) axially towards the bulkhead (64).
THERMAL ANTI-ICING SYSTEM FOR AN AIRCRAFT PROPULSION SYSTEM
THERMISCHES ENTEISUNGSSYSTEM FÜR EIN FLUGZEUGANTRIEBSSYSTEM
SYSTÈME D'ANTIGIVRAGE THERMIQUE POUR SYSTÈME DE PROPULSION D'AÉRONEF
2024-03-06
Patent
Elektronische Ressource
Englisch
THERMAL ANTI-ICING SYSTEM FOR AN AIRCRAFT PROPULSION SYSTEM
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